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Apollo LM

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Apollo LM
Credit: © Mark Wade

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AKA: LEM;Lunar Excursion Module;Lunar Module. Status: Operational 1968. First Launch: 1968-01-22. Last Launch: 1972-12-07. Number: 10 . Thrust: 44.04 kN (9,901 lbf). Gross mass: 14,696 kg (32,399 lb). Unfuelled mass: 4,173 kg (9,199 lb). Specific impulse: 311 s. Height: 6.37 m (20.89 ft). Span: 9.07 m (29.75 ft).

Following the decision to use the lunar orbit rendezvous method to get to the moon, Grumman received the contract to develop the lunar module, which would take the first men to the surface to the moon. If funding had been available, modified lunar modules (dubbed LM Taxi, LM Shelter, and LM Truck) would have been used to set up the first lunar bases.

Unit Cost $: 50.000 million. Crew Size: 2. Habitable Volume: 6.65 m3. Spacecraft delta v: 4,700 m/s (15,400 ft/sec). Electric System: 50.00 kWh.

LM Langley Lighter American manned lunar lander. Study 1961. This early open-cab Langley design used cryogenic propellants. The cryogenic design was estimated to gross 3,284 kg - to be compared with the 15,000 kg / 2 man LM design that eventually was selected.

LM Langley Light American manned lunar lander. Study 1961. This early open-cab single-crew Langley lunar lander design used storable propellants, resulting in an all-up mass of 4,372 kg.

LM Langley Lightest American manned lunar lander. Study 1961. Extremely light-weight open-cab lunar module design considered in early Langley studies.

Apollo LLRV American manned lunar lander test vehicle. Bell Aerosystems initially built two manned lunar landing research vehicles (LLRV) for NASA to assess the handling characteristics of Apollo LM-type vehicles on earth.

Apollo LM Shelter American manned lunar habitat. Cancelled 1968. The LM Shelter was essentially an Apollo LM lunar module with ascent stage engine and fuel tanks removed and replaced with consumables and scientific equipment for 14 days extended lunar exploration.

Apollo LM Taxi American manned lunar lander. Cancelled 1968. The LM Taxi was essentially the basic Apollo LM modified for extended lunar surface stays.

Apollo LM Truck American lunar logistics spacecraft. Cancelled 1968. The LM Truck was an LM Descent stage adapted for unmanned delivery of payloads of up to 5,000 kg to the lunar surface in support of a lunar base using Apollo technology.

Apollo LM Lab American manned space station. Study 1965. Use of the Apollo LM as an earth-orbiting laboratory was proposed for Apollo Applications Program missions.

Apollo LASS S-IVB American lunar logistics spacecraft. Study 1966. The Douglas Company (DAC) proposed the "Lunar Application of a Spent S-IVB Stage (LASS)". The LASS concept required a landing gear on a S-IVB Stage.

Apollo LTA American technology satellite. 3 launches, 1967.11.09 (LTA-10R) to 1968.12.21 (LTA-B). Apollo Lunar module Test Articles were simple mass/structural models of the Lunar Module.

Apollo ELS American manned lunar habitat. Cancelled 1968. The capabilities of a lunar shelter not derived from Apollo hardware were surveyed in the Early Lunar Shelter Study (ELS), completed in February 1967 by AiResearch.

Apollo LASS American manned lunar habitat. Cancelled 1968. In the LASS (LM Adapter Surface Station) lunar shelter concept, the LM ascent stage was replaced by an SLA 'mini-base' and the position of the Apollo Service Module (SM) was reversed.

Apollo ALSEP American lunar lander. 7 launches, 1969.07.16 (EASEP) to 1972.12.07 (ALSEP). ALSEP (Apollo Lunar Surface Experiment Package) was the array of connected scientific instruments left behind on the lunar surface by each Apollo expedition.

Photo Gallery

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LM on Moon Credit: NASA

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LM Evolution LM Evolution. From left: July 1962, LOR decision, 220 inch Saturn IVB; November 1962, Grumman contract award, 260-inch S-IVB; 1963; 1967; as flown. Credit: © Mark Wade

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Apollo CSM / LM Apollo Command Service Module and Lunar Module Credit: © Mark Wade

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Apollo 10 Credit: Manufacturer Image

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Apollo Lunar Module Credit: © Mark Wade

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LM Ascent Stage Credit: NASA

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Apollo 16 1/6 G leap Apollo astronaut demonstrates low lunar gravity. Credit: NASA

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Apollo CSM and LM Credit: © Mark Wade

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Apolo LM Credit: © Mark Wade

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LM vs LK US Lunar Module compared to Soviet LK lunar lander Credit: © Mark Wade

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Lunar Module 3 view Credit: © Mark Wade

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• Research into rendezvous techniques - . Nation: USA. Program: Apollo. Spacecraft: Apollo LM, LM Mode Debate, LM Source Selection.

  NASA Administrator T. Keith Glennan requested $3 million for research into rendezvous techniques as part of the NASA budget for Fiscal Year 1960. In subsequent hearings, DeMarquis D. Wyatt, Assistant to the NASA Director of Space Flight Development, explained that these funds would be used to resolve certain key problems in making space rendezvous practical. Among these were the establishment of referencing methods for fixing the relative positions of two vehicles in space; the development of accurate, lightweight target-acquisition equipment to enable the supply craft to locate the space station; the development of very accurate guidance and control systems to permit precisely determined flight paths; and the development of sources of controlled power.

• Configurations for manned lunar landing by direct ascent - . Nation: USA. Program: Apollo. Spacecraft: Apollo LM, LM Mode Debate, LM Source Selection.

  Several possible configurations for a manned lunar landing by direct ascent being studied at the Lewis Research Center were described to the Research Steering Committee by Seymour C. Himmel. A six-stage launch vehicle would be required, the first three stages to boost the spacecraft to orbital speed, the fourth to attain escape speed, the fifth for lunar landing, and the sixth for lunar escape with a 10,000-pound return vehicle. One representative configuration had an overall height of 320 feet. H. H. Koelle of the Army Ballistic Missile Agency argued that orbital assembly or refueling in orbit (earth orbit rendezvous) was more flexible, more straightforward, and easier than the direct ascent approach. Bruce T. Lundin of the Lewis Research Center felt that refueling in orbit presented formidable problems since handling liquid hydrogen on the ground was still not satisfactory. Lewis was working on handling cryogenic fuels in space.

• Manned lunar landing and return (MALLAR) - . Nation: USA. Program: Apollo. Spacecraft: Apollo LM, LM Mode Debate, LM Source Selection.

  The Chance Vought Corporation completed a company-funded, independent, classified study on manned lunar landing and return (MALLAR), under the supervision of Thomas E. Dolan. Booster limitations indicated that earth orbit rendezvous would be necessary. A variety of lunar missions were described, including a two-man, 14-day lunar landing and return. This mission called for an entry vehicle of 6,600 pounds, a mission module of 9,000 pounds, and a lunar landing module of 27,000 pounds. It incorporated the idea of lunar orbit rendezvous though not specifically by name.

• Chance Vought study of the lunar orbit rendezvous method - . Nation: USA. Program: Apollo. Spacecraft: Apollo LM, Apollo Lunar Landing, LM Mode Debate, LM Source Selection. Thomas E. Dolan of the Chance Vought Corporation prepared a company-funded design study of the lunar orbit rendezvous method for accomplishing the lunar landing mission..

• Houbolt paper on rendezvous in space with minimum expenditure of fuel - . Nation: USA. Related Persons: Houbolt. Program: Apollo. Spacecraft: Apollo LM, LM Mode Debate, LM Source Selection.

  John C. Houbolt of the Langley Research Center presented a paper at the National Aeronautical Meeting of the Society of Automotive Engineers in New York City in which the problems of rendezvous in space with the minimum expenditure of fuel were considered. Additional Details: here....

• MIT Report on space guidance and control design - . Nation: USA. Program: Apollo. Spacecraft: Apollo LM, LM Guidance, LM Source Selection.

  A study report was issued by the MIT Instrumentation Laboratory on guidance and control design for a variety of space missions. This report, approved by C. Stark Draper, Director of the Laboratory, showed that a vehicle, manned or unmanned, could have significant onboard navigation and guidance capability.

• STG and Grumman discuss advanced spacecraft programs - . Nation: USA. Related Persons: Chamberlin, Faget, Gilruth. Program: Apollo. Spacecraft: Apollo LM, LM Source Selection.

  Robcrt R. Gilruth, Paul E. Purser, James A. Chamberlin, Maxime A. Faget, and H. Kurt Strass of STG met with a group from the Grumman Aircraft Engineering Corporation to discuss advanced spacecraft programs. Grumman had been working on guidance requirements for circumlunar flights under the sponsorship of the Navy and presented Strass with a report of this work.

• Formation of a working group on the manned lunar landing program - . Nation: USA. Related Persons: Low, George. Program: Apollo. Spacecraft: Apollo LM, LM Mode Debate, LM Source Selection.

  In a memorandum to Abe Silverstein, Director of NASA's Office of Space Flight Programs, George M. Low, Chief of Manned Space Flight, described the formation of a working group on the manned lunar landing program: "It has become increasingly apparent that a preliminary program for manned lunar landings should be formulated. This is necessary in order to provide a proper justification for Apollo, and to place Apollo schedules and technical plans on a firmer foundation.

  "In order to prepare such a program, I have formed a small working group, consisting of Eldon Hall, Oran Nicks, John Disher, and myself. This group will endeavor to establish ground rules for manned lunar landing missions; to determine reasonable spacecraft weights; to specify launch vehicle requirements; and to prepare an integrated development plan, including the spacecraft, lunar landing and takeoff system, and launch vehicles. This plan should include a time-phasing and funding picture, and should identify areas requiring early studies by field organizations."

• Lunar orbit method of accomplishing the lunar landing mission - . Nation: USA. Program: Apollo. Spacecraft: Apollo LM, LM Mode Debate, LM Source Selection. Representatives of the Langley Research Center briefed members of STG on the lunar orbit method of accomplishing the lunar landing mission..

• Seamans briefed on the lunar orbit rendezvous method - . Nation: USA. Related Persons: Seamans. Program: Apollo. Spacecraft: Apollo LM, LM Mode Debate, LM Source Selection.

  Associate Administrator of NASA Robert C. Seamans, Jr., and his staff were briefed by Langley Research Center personnel on the rendezvous method as it related to the national space program. Clinton E. Brown presented an analysis made by himself and Ralph W. Stone, Jr., describing the general operational concept of lunar orbit rendezvous for the manned lunar landing. The advantages of this plan in contrast with the earth orbit rendezvous method, especially in reducing launch vehicle requirements, were illustrated. Others discussing the rendezvous were John C. Houbolt, John D. Bird, and Max C. Kurbjun.

• Grumman began work on a lunar orbit rendezvous study - . Nation: USA. Program: Apollo. Spacecraft: Apollo LM, LM Mode Debate, LM Source Selection. The Grumman Aircraft Engineering Corporation began work on a company- funded lunar orbit rendezvous feasibility study..

• Manned lunar landing discussed with Space Exploration Program Council - . Nation: USA. Related Persons: Faget, von Braun. Program: Apollo. Spacecraft: Apollo LM, LM Mode Debate, LM Source Selection.

  During a meeting of the Space Exploration Program Council at NASA Headquarters, the subject of a manned lunar landing was discussed. Following presentations on earth orbit rendezvous (Wernher von Braun, Director of Marshall Space Flight Center), lunar orbit rendezvous (John C. Houbolt of Langley Research Center), and direct ascent (Melvyn Savage of NASA Headquarters), the Council decided that NASA should not follow any one of these specific approaches, but should proceed on a broad base to afford flexibility. Another outcome of the discussion was an agreement that NASA should have an orbital rendezvous program which could stand alone as well as being a part of the manned lunar program. A task group was named to define the elements of the program insofar as possible. Members of the group were George M. Low, Chairman, Eldon W. Hall, A. M. Mayo, Ernest O. Pearson, Jr., and Oran W. Nicks, all of NASA Headquarters; Maxime A. Faget of STG; and H. H. Koelle of Marshall Space Flight Center. This group became known as the Low Committee.

• Conference on lunar orbit rendezvous for the Apollo program - . Nation: USA. Related Persons: Maynard. Program: Apollo. Spacecraft: Apollo LM, LM Mode Debate, LM Source Selection.

  A conference was held at the Langley Research Center between representatives of STG and Langley to discuss the feasibility of incorporating a lunar orbit rendezvous phase into the Apollo program. Attending the meeting for STG were Robert L. O'Neal, Owen E. Maynard, and H. Kurt Strass, and for the Langley Research Center, John C. Houbolt, Clinton E. Brown, Manuel J. Queijo, and Ralph W. Stone, Jr. The presentation by Houbolt centered on a performance analysis which showed the weight saving to be gained by the lunar rendezvous technique as opposed to the direct ascent mode. According to the analysis, a saving in weight of from 20 to 40 percent could be realized with the lunar orbit rendezvous technique.

• Second meeting of the Low Committee - . Nation: USA. Related Persons: Low, George. Program: Apollo. Spacecraft: Apollo LM, LM Mode Debate, LM Source Selection.

  At the second meeting of the Manned Lunar Landing Task Group (Low Committee), a draft position paper was presented by George M. Low, Chairman. A series of reports on launch vehicle capabilities, spacecraft, and lunar program support were presented and considered for possible inclusion in the position paper.

• Low Committee first draft report - . Nation: USA. Program: Apollo. Spacecraft: Apollo LM, LM Mode Debate, LM Source Selection.

  The Manned Lunar Landing Task Group (Low Committee) submitted its first draft report to NASA Associate Administrator Robert C. Seamans, Jr. A section on detailed costs and schedules still was in preparation and a detailed itemized backup report was expected to be available in mid- February.

• NASA Inter-Center meeting on space rendezvous - . Nation: USA. Program: Apollo. Spacecraft: Apollo LM, LM Source Selection.

  A NASA inter-Center meeting on space rendezvous was held in Washington, D.C. Air Force and NASA programs were discussed and the status of current studies was presented by NASA Centers. Members of the Langley Research Center outlined the basic concepts of the lunar orbit rendezvous method of accomplishing the lunar landing mission.

• The midterm review of the Apollo feasibility studies was held at STG - . Nation: USA. Program: Apollo. Spacecraft: Apollo LM, LM Source Selection.

  The midterm review of the Apollo feasibility studies was held at STG. Oral status reports were made by officials of Convair Astronautics Division of the General Dynamics Corporation on March 1, The Martin Company on March 2, and the General Electric Company on March 3. The reports described the work accomplished, problems unsolved, and future plans. Representatives of all NASA Centers attended the meetings, including a majority of the members of the Apollo Technical Liaison Groups. Members of these Groups formed the nucleus of the mid-term review groups which met during the three-day period and compiled lists of comments on the presentations for later discussions with the contractors.

• Manned Lunar Landing via Rendezvous report - . Nation: USA. Program: Apollo. Spacecraft: Apollo LM, LM Mode Debate, LM Source Selection.

  A circular, "Manned Lunar Landing via Rendezvous," was prepared by John C. Houbolt from material supplied by himself, John D. Bird, Max C. Kurbjun, and Arthur W. Vogeley, who were members of the Langley Research Center space station subcommittee on rendezvous. Other members of the subcommittee at various times included W. Hewitt Phillips, John M. Eggleston, John A. Dodgen, and William D. Mace.

• Apollo MORAD, ARP, and MALLIR recommendations - . Nation: USA. Program: Apollo. Spacecraft: Apollo LM.

  Recommendations on immediate steps to be taken so that the three key projects - MORAD (Manned Orbital Rendezvous and Docking), ARP (Apollo Rendezvous Phases), and MALLIR (Manned Lunar Landing Involving Rendezvous) - could get under way were:

  • Approve the MORAD project and let a study contract to consider general aspects of the Scout rendezvous vehicle design, definite planning and schedules, and tie down cost estimates more exactly.
  • Delegate responsibility to STG to give accelerated consideration to rendezvous aspects of Apollo, tailoring developments to fit directly into the MALLIR project.
  • Let a study contract to establish preliminary design, scheduling, and cost figures for the three projects.

• Lundin Committee to assess Lunar landing mission - . Nation: USA. Related Persons: Seamans. Program: Apollo. Spacecraft: Apollo LM, LM Mode Debate, LM Source Selection.

  Robert C. Seamans, Jr., NASA's Associate Administrator, requested the Directors of the Office of Launch Vehicle Programs and the Office of Advanced Research Programs to bring together members of their staffs with other persons from NASA Headquarters to assess a wide variety of possible ways of accomplishing the lunar landing mission. This study was to supplement the one being done by the Ad Hoc Task Group for Manned Lunar Landing Study (Fleming Committee) but was to be separate from it. Additional Details: here....

• Lunar orbit rendezvous plan - . Nation: USA. Program: Apollo. Spacecraft: Apollo LM, LM Mode Debate, LM Source Selection. Basic concepts of the lunar orbit rendezvous plan were presented to the Lundin Committee by John C. Houbolt of Langley Research Center..

• Langley Research Center lunar landing paper - . Nation: USA. Related Persons: Faget. Program: Apollo. Spacecraft: Apollo LM, LM Mode Debate, LM Source Selection.

  Maxime A. Faget, Paul E. Purser, and Charles J. Donlan of STG met with Arthur W. Vogeley, Clinton E. Brown, and Laurence K. Loftin, Jr., of Langley Research Center on a "lunar landing" paper. Faget's outline was to be used, with part of the information to be worked up by Vogeley.

• Lunar orbit rendezvous briefing - . Nation: USA. Program: Apollo. Spacecraft: Apollo LM, LM Mode Debate, LM Source Selection. Members of Langley Research Center briefed the Heaton Committee on the lunar orbit rendezvous method of accomplishing the manned lunar landing mission..

• Langley simulated spacecraft flights in approaching the moon's surface - . Nation: USA. Program: Apollo. Spacecraft: Apollo LM, LM Simulator, LM Source Selection.

  Langley Research Center simulated spacecraft flights at speeds of 8,200 to 8,700 feet per second in approaching the moon's surface. With instruments preset to miss the moon's surface by 40 to 80 miles, pilots with control of thrust and torques about all three axes of the craft learned to establish orbits 10 to 90 miles above the surface, using a graph of vehicle rate of descent and circumferential velocity, an altimeter, and vehicle attitude and rate meters, as reported by Manuel J. Queijo and Donald R. Riley of Langley.

• Golovin Committee evaluates three rendezvous methods for manned lunar landing - . Nation: USA. Program: Apollo. Spacecraft: Apollo LM, LM ECS, LM Source Selection.

  The Large Launch Vehicle Planning Group (Golovin Committee) notified the Marshal! Space Flight Center (MSFC), Langley Research Center, and the Jet Propulsion Laboratory (JPL) that the Group was planning to undertake a comparative evaluation of three types of rendezvous operations and direct flight for manned lunar landing. Rendezvous methods were earth orbit, lunar orbit, and lunar surface. MSFC was requested to study earth orbit rendezvous, Langley to study lunar orbit rendezvous, and JPL to study lunar surface rendezvous. The NASA Office of Launch Vehicle Programs would provide similar information on direct ascent. Additional Details: here....

• Studies being done on rendezvous modes for accomplishing a manned lunar landing - . Nation: USA. Program: Apollo. Spacecraft: Apollo LM, LM Mode Debate, LM Source Selection.

  In a memorandum to the Large Launch Vehicle Planning Group (LLVPG) staff, Harvey Hall of NASA described the studies being done by the Centers on rendezvous modes for accomplishing a manned lunar landing. These studies had been requested from Langley Research Center, Marshall Space Flight Center, and the Jet Propulsion Laboratory on August 23. STG was preparing separate documentation on the lunar orbit rendezvous mode. An LLVPG team to undertake a comparative evaluation of rendezvous and direct ascent techniques had been set up. Members of the team included Hall and Norman Rafel of NASA and H. Braham and L. M. Weeks of Aerospace Corporation.

  The evaluation would consider:

  • Effect of total flight time on specifications and reliability of equipment and on personnel.
  • Effect of vehicle system reliability in each case, including the number of engine starts and restarts.
  • Dependence on data, data-rate, and distance from ground station for control of assembly and refueling operations
  • Launch and injection windows
  • Effect of differences in the total weight propelled to earth escape velocity
  • Relative merits of lunar gravity and of a lunar base in general versus an orbital station for rendezvous and assembly purposes.
  Reliability estimates on vehicles would be based on LLVPG data; estimates on equipment would rely on experience with similar types in known applications.

• Manned Lunar-Landing through use of Lunar-Orbit Rendezvous - . Nation: USA. Program: Apollo. Spacecraft: Apollo LM, LM Mode Debate, LM Source Selection.

  Under the direction of John C. Houbolt of Langley Research Center, a two-volume work entitled "Manned Lunar-Landing through use of Lunar-Orbit Rendezvous" was presented to the Golovin Committee (organized on July 20). The study had been prepared by Houbolt, John D. Bird, Arthur W. Vogeley, Ralph W. Stone, Jr., Manuel J. Queijo, William H. Michael, Jr., Max C. Kurbjun, Roy F. Brissenden, John A. Dodgen, William D. Mace, and others of Langley. The Golovin Committee had requested a mission plan using the lunar orbit rendezvous concept. Bird, Michael, and Robert H. Tolson appeared before the Committee in Washington to explain certain matters of trajectory and lunar stay time not covered in the document.

• Houbolt letter on lunar orbit rendezvous (LOR) plan - . Nation: USA. Related Persons: Seamans. Program: Apollo. Spacecraft: Apollo LM, LM Mode Debate, LM Source Selection.

  In a letter to NASA Associate Administrator Robert C. Seamans, Jr., John C. Houbolt of Langley Research Center presented the lunar orbit rendezvous (LOR) plan and outlined certain deficiencies in the national booster and manned rendezvous programs. This letter protested exclusion of the LOR plan from serious consideration by committees responsible for the definition of the national program for lunar exploration.

• Grumman study on lunar orbit rendezvous - . Nation: USA. Program: Apollo. Spacecraft: Apollo LM, LM Mode Debate, LM Source Selection.

  The Grumman Aircraft Engineering Corporation developed a detailed, company-funded study on the lunar orbit rendezvous technique: characteristics of the system (relative cost of direct ascent, earth orbit rendezvous, and lunar orbit rendezvous); developmental problems (communications, propulsion); and elements of the system (tracking facilities, etc.). Joseph M. Gavin was appointed in the spring to head the effort, and Robert E. Mullaney was designated program manager.

• Langley presentation of lunar orbit rendezvous - . Nation: USA. Program: Apollo. Spacecraft: Apollo LM, LM Mode Debate, LM Source Selection. John C. Houbolt of Langley Research Center and Charles W. Mathews of MSC made a presentation of lunar orbit rendezvous versus earth orbit rendezvous to the Manned Space Flight Management Council..

• Ad Hoc Lunar Landing Module Working Group - . Nation: USA. Program: Apollo. Spacecraft: Apollo LM, LM Source Selection.

  Robert R. Gilruth, MSC Director, in a letter to NASA Headquarters, described the Ad Hoc Lunar Landing Module Working Group which was to be under the direction of the Apollo Spacecraft Project Office. The Group would determine what constraints on the design of the lunar landing module were applicable to the effort of the Lewis Research Center. Gilruth asked that Eldon W. Hall represent NASA Headquarters in this Working Group. (At this time, the lunar landing module was conceived as being that part of the spacecraft which would actually land on the moon and which would contain the propulsion system necessary for launch from the lunar surface and injection into transearth trajectory. Pending a decision on the lunar mission mode, the actual configuration of the module was not yet clearly defined.)

• Chance Vought to study spacecraft rendezvous - . Nation: USA. Program: Apollo. Spacecraft: Apollo LM, LM Mode Debate, LM Source Selection.

  NASA Headquarters selected the Chance Vought Corporation of Ling-Temco-Vought, Inc., as a contractor to study spacecraft rendezvous. A primary part of the contract would be a flight simulation study exploring the capability of an astronaut to control an Apollo-type spacecraft.

• Chance Vought briefed on lunar orbit rendezvous - . Nation: USA. Program: Apollo. Spacecraft: Apollo LM, LM Mode Debate, LM Source Selection.

  Members of Langley Research Center briefed representatives of the Chance Vought Corporation of Ling- Temco-Vought, Inc., on the lunar orbit rendezvous method of accomplishing the lunar landing mission. The briefing was made in connection with the study contract on spacecraft rendezvous awarded by NASA Headquarters to Chance Vought on March 1.

• Preliminary Apollo program schedules - . Nation: USA. Program: Apollo. Spacecraft: Apollo LM.

  A small group within the MSC Apollo Spacecraft Project Office developed a preliminary program schedule for three approaches to the lunar landing mission: earth orbit rendezvous, direct ascent, and lunar orbit rendezvous. The exercise established a number of ground rules :

  • Establish realistic schedules that would "second guess" failures but provide for exploitation of early success.
  • Schedule circumlunar, lunar orbit, and lunar landing missions at the earliest realistic dates.
  • Complete the flight development of spacecraft modules and operational techniques, using the Saturn C-1 and C-1B launch vehicles, prior to the time at which a "man-rated" C-5 launch vehicle would become available.
  • Develop the spacecraft operational techniques in "buildup" missions that would progress generally from the simple to the complex.
  • Use the spacecraft crew at the earliest time and to the maximum extent, commensurate with safety considerations, in the development of the spacecraft and its subsystems.
  The exercise also provided a basis for proceeding with the development of definitive schedules and a program plan.

• Lunar orbit rendezvous technique - . Nation: USA. Program: Apollo. Spacecraft: Apollo LM, LM Mode Debate, LM Source Selection. Representatives of MSC made a formal presentation at Marshall Space Flight Center on the lunar orbit rendezvous technique for accomplishing the lunar mission..

• Rosen recommends Saturn C-5 design and lunar orbit rendezvous - . Nation: USA. Related Persons: Rosen, Milton. Program: Apollo. Spacecraft: Apollo LM, Apollo Lunar Landing, CSM Recovery, LM Mode Debate, LM Source Selection.

  Milton W. Rosen, NASA Office of Manned Space Flight Director of Launch Vehicles and Propulsion, recommended that the S-IVB stage be designed specifically as the third stage of the Saturn C-5 and that the C-5 be designed specifically for the manned lunar landing using the lunar orbit rendezvous technique. The S-IVB stage would inject the spacecraft into a parking orbit and would be restarted in space to place the lunar mission payload into a translunar trajectory. Rosen also recommended that the S- IVB stage be used as a flight test vehicle to exercise the command module (CM), service module (SM), and lunar excursion module (LEM) (previously referred to as the lunar excursion vehicle (LEV)) in earth orbit missions. The Saturn C-1 vehicle, in combination with the CM, SM, LEM, and S-IVB stage, would be used on the most realistic mission simulation possible. This combination would also permit the most nearly complete operational mating of the CM, SM, LEM, and S-IVB prior to actual mission flight.

• Indecision on the lunar mission mode causing delays in Apollo program - . Nation: USA. Program: Apollo. Spacecraft: Apollo LM, Apollo Lunar Landing, LM Mode Debate, LM Source Selection.

  MSC Associate Director Walter C. William reported to the Manned Space Flight Management Council that the lack of a decision on the lunar mission mode was causing delays in various areas of the Apollo spacecraft program, especially the requirements for the portions of the spacecraft being furnished by NAA.

• Advantages of lunar orbit rendezvous - . Nation: USA. Program: Apollo. Spacecraft: Apollo LM, LM Mode Debate, LM Source Selection.

  John C. Houbolt of Langley Research Center, writing in the April issue of Astronautics, outlined the advantages of lunar orbit rendezvous for a manned lunar landing as opposed to direct flight from earth or earth orbit rendezvous. Under this concept, an Apollo-type spacecraft would fly directly to the moon, go into lunar orbit, detach a small landing craft which would land on the moon and then return to the mother craft, which would then return to earth. The advantages would be the much smaller craft performing the difficult lunar landing and takeoff, the possibility of optimizing the smaller craft for this one function, the safe return of the mother craft in event of a landing accident, and even the possibility of using two of the small craft to provide a rescue capability.

• Presentation on the lunar orbit rendezvous technique - . Nation: USA. Related Persons: Holmes, Brainard. Program: Apollo. Spacecraft: Apollo LM, LM Mode Debate, LM Source Selection.

  A presentation on the lunar orbit rendezvous technique was made to D. Brainerd Holmes, Director, NASA Office of Manned Space Flight, by representatives of the Apollo Spacecraft Project Office. A similar presentation to NASA Associate Administrator Robert C. Seamans, Jr., followed on May 31.

• Preliminary Statement of Work for Apollo lunar excursion module - . Nation: USA. Program: Apollo. Spacecraft: Apollo LM, LM Source Selection. A preliminary Statement of Work for a proposed lunar excursion module was completed, although the mission mode had not yet been selected..

• Schedule for contract for development of Apollo lunar excursion module - . Nation: USA. Program: Apollo. Spacecraft: Apollo LM, LM Source Selection.

  A schedule for the letting of a contract for the development of a lunar excursion module was presented to the Manned Space Flight Management Council by MSC Director Robert R. Gilruth in anticipation of a possible decision to employ the lunar rendezvous technique in the lunar landing mission.

• Delta V requirements for the Apollo lunar landing mission were established - . Nation: USA. Program: Apollo. Spacecraft: Apollo LM, LM Guidance, LM Source Selection. The delta V (rate of incremental change in velocity) requirements for the lunar landing mission were established and coordinated with NAA by the Apollo Spacecraft Project Office..

• Report on a simulated lunar landing trainer - . Nation: USA. Program: Apollo. Spacecraft: Apollo LM, LM Source Selection. Charles W. Frick, MSC Apollo Project Office Manager, assigned MIT Instrumentation Laboratory to report on a simulated lunar landing trainer using guidance and navigation equipment and other displays as necessary or proposed..

• Invitation to bid for the Apollo lunar excursion module - . Nation: USA. Program: Apollo. Spacecraft: Apollo LM, Apollo Lunar Landing, LM Original Specification, LM Source Selection.

  MSC invited 11 firms to submit research and development proposals for the lunar excursion module (LEM) for the manned lunar landing mission. The firms were Lockheed Aircraft Corporation, The Boeing Airplane Company, Northrop Corporation, Ling-Temco-Vought, Inc., Grumman Aircraft Engineering Corporation, Douglas Aircraft Company, General Dynamics Corporation, Republic Aviation Corporation, Martin- Marietta Company, North American Aviation, Inc., and McDonnell Aircraft Corporation. Additional Details: here....

• Conclusions on the selection of a lunar mission mode based on studies conducted in 1961 and 1962 - . Nation: USA. Program: Apollo. Spacecraft: Apollo LM, LM Mode Debate, LM Source Selection.

  The Office of Systems under NASA's Office of Manned Space Flight summarized its conclusions on the selection of a lunar mission mode based on NASA and industry studies conducted in 1961 and 1962:

  • There were no significant technical problems which would preclude the acceptance of any of the modes, if sufficient time and money were available. (The modes considered were the C-5 direct ascent, C-5 earth orbit rendezvous (EOR), C-5 lunar orbit rendezvous (LOR), Nova direct ascent, and solid-fuel Nova direct ascent.)
  • The C-5 direct ascent technique was characterized by high development risk and the least flexibility for further development.
  • The C-5 EOR mode had the lowest probability of mission success and the greatest development complexity.
  • The Nova direct ascent method would require the development of larger launch vehicles than the C-5. However, it would be the least complex from an operational and subsystem standpoint and had greater crew safety and initial mission capabilities than did LOR.
  • The solid-fuel Nova direct flight mode would necessitate a launch vehicle development parallel to the C-5. Such a development could not be financed under current budget allotments.
  • Only the LOR and EOR modes would make full use of the development of the C-5 launch vehicle and the command and service modules. Based on technical considerations, the LOR mode was distinctly preferable.
  • The Directors of MSC and Marshall Space Flight Center had both expressed strong preference for the LOR mode.
  On the basis of these conclusions, the LOR mode was recommended as most suitable for the manned lunar landing mission. (The studies summarized in this document were used by the Manned Space Flight Management Council in their mission mode decision on June 22.)

• Preliminary design of the Apollo lunar landing radar - . Nation: USA. Program: Apollo. Spacecraft: Apollo LM, LM Guidance, LM Source Selection. NAA selected the lunar landing radar and completed the block diagram for the spacecraft rendezvous radar. Preliminary design was in progress on both types of radar..

• Eight companies to bid on Apollo lunar excursion module - . Nation: USA. Program: Apollo. Spacecraft: Apollo LM, LM Source Selection.

  Of the 11 companies invited to bid on the lunar excursion module on July 25, eight planned to respond. NAA had notified MSC that it would not bid on the contract. No information had been received from the McDonnell Aircraft Corporation and it was questionable whether the Northrop Corporation would respond.

• LEM added to Apollo CSM Statement of Work - . Nation: USA. Program: Apollo. Spacecraft: Apollo LM, LM Communications, LM ECS, LM Guidance, LM Hatch, LM Source Selection.

  The NAA spacecraft Statement of Work was revised to include the requirements for the lunar excursion module (LEM) as well as other modifications. The LEM requirements were identical with those given in the LEM Development Statement of Work of July 24.

  The command module (CM) would now be required to provide the crew with a one-day habitable environment and a survival environment for one week after touching down on land or water. In case of a landing at sea, the CM should be able to recover from any attitude and float upright with egress hatches free of water. Additional Details: here....

• Nine industry proposals for the Apollo lunar excursion module received - . Nation: USA. Program: Apollo. Spacecraft: Apollo LM, LM Source Selection.

  Nine industry proposals for the lunar excursion module were received from The Boeing Company, Douglas Aircraft Company, General Dynamics Corporation, Grumman Aircraft Engineering Corporation, Ling-Temco-Vought, Inc., Lockheed Aircraft Corporation, Martin-Marietta Corporation, Northrop Corporation, and Republic Aviation Corporation. NASA evaluation began the next day. Additional Details: here....

• Study of Apollo docking and crew transfer - . Nation: USA. Program: Apollo. Spacecraft: Apollo LM, CSM Hatch, LM Communications, LM ECS, LM Hatch, LM Source Selection.

  Apollo Spacecraft Project Office requested NAA to perform a study of command module-lunar excursion module (CM-LEM) docking and crew transfer operations and recommend a preferred mode, establish docking design criteria, and define the CM-LEM interface. Both translunar and lunar orbital docking maneuvers were to be considered. The docking concept finally selected would satisfy the requirements of minimum weight, design and functional simplicity, maximum docking reliability, minimum docking time, and maximum visibility.

  The mission constraints to be used for this study were :

  • The first docking maneuver would take place as soon after S-IVB burnout as possible and hard docking would be within 30 minutes after burnout.
  • The docking methods to be investigated would include but not be limited to free fly-around, tethered fly-around, and mechanical repositioning.
  • The S-IVB would be stabilized for four hours after injection.
  • There would be no CM airlock. Extravehicular access techniques through the LEM would be evaluated to determine the usefulness of a LEM airlock.
  • A crewman would not be stationed in the tunnel during docking unless it could be shown that his field of vision, maneuverability, and communication capability would substantially contribute to the ease and reliability of the docking maneuver.
  • An open-hatch, unpressurized CM docking approach would not be considered.
  • The relative merit of using the CM environmental control system to provide initial pressurization of the LEM instead of the LEM environmental control system would be investigated.

• Studies of Apollo unmanned logistic system - . Nation: USA. Program: Apollo. Spacecraft Bus: Apollo LM. Spacecraft: Apollo ULS.

  Two three-month studies of an unmanned logistic system to aid astronauts on a lunar landing mission would be negotiated with three companies, NASA announced. Under a $150,000 contract, Space Technology Laboratories, Inc., would look into the feasibility of developing a general-purpose spacecraft into which varieties of payloads could be fitted. Under two $75,000 contracts, Northrop Space laboratories and Grumman Aircraft Engineering Corporation would study the possible cargoes that such a spacecraft might carry. NASA Centers simultaneously would study lunar logistic: trajectories, launch vehicle adaptation, lunar landing touchdown dynamics, scheduling, and use of roving vehicles on the lunar surface.

• Contract with Armour Research Foundation for investigation of conditions on the lunar surface - . Nation: USA. Program: Apollo. Spacecraft: Apollo LM, LM Landing Gear, LM Source Selection.

  NASA contracted with the Armour Research Foundation for an investigation of conditions likely to be found on the lunar surface. Research would concentrate first on evaluating the effects of landing velocity, size of the landing area, and shape of the landing object with regard to properties of the lunar soils. Earlier studies by Armour had indicated that the lunar surface might be composed of very strong material. Amour reported its findings during the first week of November.

• Apollo lunar excursion module systems - . Nation: USA. Program: Apollo. Spacecraft: Apollo LM.

  The lunar excursion module was defined as consisting of 12 principal systems: guidance and navigation, stabilization and control, propulsion, reaction control, lunar touchdown, structure including landing and docking systems, crew, environmental control, electrical power, communications, instrumentation, and experimental instrumentation. A consideration of prime importance to practically all systems was the possibility of using components from Project Mercury or those under development for Project Gemini.

• Final manned lunar landing mode report - . Nation: USA. Related Persons: Kennedy, Wiesner. Program: Apollo. Spacecraft: Apollo LM, LM Mode Debate, LM Source Selection.

  Faced by opposition of mode selection by Jerome Wiesner, Kennedy's science adviser, NASA let contracts to McDonnell and STL for direct two-man flight modes. Both concluded that it was feasible but would require LH2/LOX stages for descent and ascent from lunar surface, which NASA/STG adamantly opposed. This was also the last stab - for the time being - at 'lunar Gemini'.

  The Office of Systems under NASA's Office of Manned Space Flight completed a manned lunar landing mode comparison embodying the most recent studies by contractors and NASA Centers. The report was the outgrowth of the decision announced by NASA on July 11 to continue studies on lunar landing modes while basing planning and procurement primarily on the lunar orbit rendezvous (LOR) technique. Additional Details: here....

• Lunar surface might not be covered with dust layers - . Nation: USA. Program: Apollo. Spacecraft: Apollo LM, LM ECS, LM Source Selection.

  The Amour Research Foundation reported to NASA that the surface of the moon might not be covered with layers of dust. The first Armour studies showed that dust particles become harder and denser in a higher vacuum environment such as that of the moon, but the studies had not proved that particles eventually become bonded together in a rocket substance as the vacuum increases.

• Selection of Grumman to build the Apollo lunar excursion module - . Nation: USA. Related Persons: Webb. Program: Apollo. Spacecraft: Apollo LM, Apollo Lunar Landing, LM Source Selection.

  NASA announced that the Grumman Aircraft Engineering Corporation had been selected to build the lunar excursion module of the three-man Apollo spacecraft under the direction of MSC. The contract, still to be negotiated, was expected to be worth about $350 million, with estimates as high as $1 billion by the time the project would be completed. Additional Details: here....

• Negotiations on the lunar excursion module (Apollo LEM) contract begin - . Nation: USA. Program: Apollo. Spacecraft: Apollo LM, LM Source Selection.

  About 100 Grumman Aircraft Engineering Corporation and MSC representatives began seven weeks of negotiations on the lunar excursion module (LEM) contract. After agreeing on the scope of work and on operating and coordination procedures, the two sides reached fiscal accord. Negotiations were completed on January 3, 1963. Eleven days later, NASA authorized Grumman to proceed with LEM development.

• Inflight practice at orbital maneuvering said to be essential for lunar missions - . Nation: USA. Program: Apollo. Spacecraft: Apollo LM, LM Guidance.

  At a news conference in Cleveland, Ohio, during the 10-day Space Science Fair there, NASA Deputy Administrator Hugh L. Dryden stated that inflight practice at orbital maneuvering was essential for lunar missions. He believed that landings would follow reconnaissance of the moon by circumlunar and near- lunar-surface flights.

• Study of Apollo CSM-LEM transposition and docking - . Nation: USA. Program: Apollo. Spacecraft: Apollo LM, CSM RCS, LM RCS, LM Weight.

  North American completed a study of CSM-LEM transposition and docking. During a lunar mission, after the spacecraft was fired into a trajectory toward the moon, the CSM would separate from the adapter section containing the LEM. It would then turn around, dock with the LEM, and pull the second vehicle free from the adapter. The contractor studied three methods of completing this maneuver: free fly-around, tethered fly- around, and mechanical repositioning. Of the three, the company recommended the free fly-around, based on NASA's criteria of minimum weight, simplicity of design, maximum docking reliability, minimum time of operation, and maximum visibility.

  Also investigated was crew transfer from the CM to the LEM, to determine the requirements for crew performance and, from this, to define human engineering needs. North American concluded that a separate LEM airlock was not needed but that the CSM oxygen supply system's capacity should be increased to effect LEM pressurization.

  On November 29, North American presented the results of docking simulations, which showed that the free flight docking mode was feasible and that the 45-kilogram (100-pound) service module (SM) reaction control system engines were adequate for the terminal phase of docking. The simulations also showed that overall performance of the maneuver was improved by providing the astronaut with an attitude display and some form of alignment aid, such as probe.

• Selection of lunar orbit rendezvous for Apollo explained to Kennedy - . Nation: USA. Related Persons: Webb. Program: Apollo. Spacecraft: Apollo LM, Apollo Lunar Landing, LM Mode Debate.

  NASA Administrator James E. Webb, in a letter to the President, explained the rationale behind the Agency's selection of lunar orbit rendezvous (rather than either direct ascent or earth orbit rendezvous) as the mode for landing Apollo astronauts on the moon. Arguments for and against any of the three modes could have been interminable: "We are dealing with a matter that cannot be conclusively proved before the fact," Webb said. "The decision on the mode . . . had to be made at this time in order to maintain our schedules, which aim at a landing attempt in late 1967."

• Apollo LEM docking study authorized - . Nation: USA. Program: Apollo. Spacecraft: Apollo LM, LM Crew Station. NASA authorized North American's Columbus, Ohio, Division to proceed with a LEM docking study..

• Apollo LEM's descent engine might create a dust storm on the lunar surface - . Nation: USA. Program: Apollo. Spacecraft: Apollo LM, LM Descent Propulsion. MSC prognosticated that, during landing, exhaust from the LEM's descent engine would kick up dust on the moon's surface, creating a dust storm. Landings should be made where surface dust would be thinnest..

• Grumman agreed to use existing Apollo components and subsystems in the LEM - . Nation: USA. Program: Apollo. Spacecraft: Apollo LM. Grumman agreed to use existing Apollo components and subsystems, where practicable, in the LEM This promised to simplify checkout and maintenance of spacecraft systems..

• Project Apollo lunar landing mission design - . Nation: USA. Program: Apollo. Spacecraft: Apollo LM. MSC prepared the Project Apollo lunar landing mission design. This plan outlined ground rules, trajectory analyses, sequences of events, crew activities, and contingency operations. It also predicted possible planning changes in later Apollo flights..

• Three Apollo operational procedures for the first phase of descent from lunar orbit analyzed - . Nation: USA. Program: Apollo. Spacecraft: Apollo LM, LM Guidance.

  The MSC Flight Operations Division's Mission Analysis Branch analyzed three operational procedures for the first phase of descent from lunar orbit:

  1. The first was a LEM-only maneuver. The LEM would transfer to an orbit different from that of the CSM but with the same period and having a pericynthion of 15,240 meters (50,000 feet). After one orbit and reconnaissance of the landing site, the LEM would begin descent maneuvers.
  2. The second method required the entire spacecraft (CSM/LEM) to transfer from the initial circular orbit to an elliptical orbit with a pericynthion of 15,240 meters (50,000 feet).
  3. The third technique involved the LEM's changing from the original 147-kilometer (80-nautical-mile) circular orbit to an elliptic orbit having a pericynthion of 15,240 meters (50,000 feet). The CSM, in turn, would transfer to an elliptic orbit with a pericynthion of 65 kilometers (30 nautical miles). This would enable the CSM to keep the LEM under observation until the LEM began its descent to the lunar surface.
  Comparisons of velocity changes and fuel requirements for the three methods showed that the second technique would use much more fuel than the others and, therefore, was not recommended for further consideration.

  (Apocynthion and pericynthion are the high and low points, respectively, of an object in orbit around the moon (as, for example, a spacecraft sent from earth). Apolune and perilune also refer to these orbital parameters, but these latter two words apply specifically to an object launched from the moon itself.)

• Contract to Bell for two Apollo lunar landing research vehicles - . Nation: USA. Program: Apollo. Spacecraft Bus: Apollo LM. Spacecraft: Apollo LLRV.

  NASA's Flight Research Center (FRC) announced the award of a $3.61 million contract to Bell Aerosystems Company of Bell Aerospace Corporation for the design and construction of two manned lunar landing research vehicles. The vehicles would be able to take off and land under their own power, reach an altitude of about 1,220 meters (4,000 feet), hover, and fly horizontally. A fan turbojet engine would supply a constant upward push of five-sixths the weight of the vehicle to simulate the one-sixth gravity of the lunar surface. Tests would be conducted at FRC.

• Conference on the Apollo LEM electrical power system (EPS) - . Nation: USA. Program: Apollo. Spacecraft: Apollo LM, LM Electrical.

  Following a technical conference on the LEM electrical power system (EPS), Grumman began a study to define the EPS configuration. Included was an analysis of EPS requirements and of weight and reliability for fuel cells and batteries. Total energy required for the LEM mission, including the translunar phase, was estimated at 61.3 kilowatt-hours. Upon completion of this and a similar study by MSC, Grumman decided upon a three-cell arrangement with an auxiliary battery. Capacity would be determined when the EPS load analysis was completed.

• Selection of four companies as major Apollo LEM subcontractors - . Nation: USA. Program: Apollo. Spacecraft: Apollo LM, LM Ascent Propulsion, LM Descent Propulsion, LM ECS, LM RCS.

  Grumman and NASA announced the selection of four companies as major LEM subcontractors:

  1. Rocketdyne for the descent engine
  2. Bell Aerosystems Company for the ascent engine
  3. The Marquardt Corporation for the reaction control system
  4. Hamilton Standard for the environmental control system

• Contract to Chance Vought for study of guidance of the Apollo LEM in a lunar landing abort - . Nation: USA. Program: Apollo. Spacecraft: Apollo LM, LM Guidance. MSC awarded a contract to Chance Vought Corporation for a study of guidance system techniques for the LEM in an abort during lunar landing..

• LLRV contract - . Nation: USA. Spacecraft Bus: Apollo LM. Spacecraft: Apollo LLRV.

  After conceptual planning and meetings with engineers from Bell Aerosystems, Buffalo, NY, a company with experience in vertical takeoff and landing (VTOL) aircraft, NASA issued Bell a $50,000 study contract in December 1961. Bell had independently conceived a similar, free-flying simulator, and out of this study came the NASA Headquarters' endorsement of the LLRV concept, resulting in a $3.6 million production contract awarded to Bell for delivery of the first of two vehicles for flight studies at the FRC within 14 months.

• Reorganization of Apollo SPO - . Nation: USA. Related Persons: Johnson, Caldwell, Maynard. Program: Apollo. Spacecraft: Apollo LM, CSM Guidance.

  In a reorganization of ASPO, MSC announced the appointment of two deputy managers. Robert O. Piland, deputy for the LEM, and James L. Decker, deputy for the CSM, would supervise cost, schedule, technical design, and production. J. Thomas Markley was named Special Assistant to the Apollo Manager, Charles W. Frick. Also appointed to newly created positions were Caldwell C. Johnson, Manager, Spacecraft Systems Office, CSM; Owen E. Maynard, Acting Manager, Spacecraft Systems Office, LEM; and David W. Gilbert, Manager, Spacecraft Systems Office, Guidance and Navigation.

• Discussions with Rocketdyne on a throttleable Apollo LEM descent engine - . Nation: USA. Program: Apollo. Spacecraft: Apollo LM, LM Descent Propulsion. Grumman began discussions with Rocketdyne on the development of a throttleable LEM descent engine. Engine specifications (helium injected, 10:1 thrust variation) had been laid down by MSC..

• Lunar Surface Experiments Panel - . Nation: USA. Program: Apollo. Spacecraft Bus: Apollo LM. Spacecraft: Apollo ALSEP. The MSC Lunar Surface Experiments Panel held its first meeting. This group was formed to study and evaluate lunar surface experiments and the adaptability of Surveyor and other unmanned probes for use with manned missions..

• Talks with Bell on development of the Apollo LEM ascent engine - . Nation: USA. Program: Apollo. Spacecraft: Apollo LM, LM Ascent Propulsion. Grumman began initial talks with the Bell Aerosystems Company on development of the LEM ascent engine. Complete specifications were expected by March 2..

• Orbital constraints on Apollo CSM - . Nation: USA. Program: Apollo. Spacecraft: Apollo LM, CSM Docking, LM Guidance.

  Two aerospace technologists at MSC, James A. Ferrando and Edgar C. Lineberry, Jr., analyzed orbital constraints on the CSM imposed by the abort capability of the LEM during the descent and hover phases of a lunar mission. Their study concerned the feasibility of rendezvous should an emergency demand an immediate return to the CSM.

  Ferrando and Lineberry found that, once abort factors are considered, there exist "very few" orbits that are acceptable from which to begin the descent. They reported that the most advantageous orbit for the CSM would be a 147-kilometer (80-nautical-mile) circular one.

• Alternate Apollo LEM descent propulsion system - . Nation: USA. Program: Apollo. Spacecraft: Apollo LM, LM Descent Propulsion.

  Aviation Daily reported an announcement by Frank Canning, Assistant LEM Project Manager at Grumman, that a Request for Proposals would be issued in about two weeks for the development of an alternate descent propulsion system. Because the descent stage presented what he called the LEM's "biggest development problem," Canning said that the parallel program was essential.

• Apollo Mission Planning Panel - . Nation: USA. Program: Apollo. Spacecraft: Apollo LM.

  The Apollo Mission Planning Panel held its organizational meeting at MSC. The panel's function was to develop the lunar landing mission design, coordinate trajectory analyses for all Saturn missions, and develop contingency plans for all manned Apollo missions.

  Membership on the panel included representatives from MSC, MSFC, NASA Headquarters, North American, Grumman, and MIT, with other NASA Centers being called on when necessary. By outlining the most accurate mission plan possible, the panel would ensure that the spacecraft could satisfy Apollo's anticipated mission objectives. Most of the panel's influence on spacecraft design would relate to the LEM, which was at an earlier stage of development than the CSM. The panel was not given responsibility for preparing operational plans to be used on actual Apollo missions, however.

• One-tenth scale model of the Apollo LEM for stage separation tests - . Nation: USA. Program: Apollo. Spacecraft: Apollo LM, LM Ascent Propulsion, LM Landing Gear.

  Grumman began fabrication of a one-tenth scale model of the LEM for stage separation tests. In launching from the lunar surface, the LEM's ascent engine fires just after pyrotechnic severance of all connections between the two stages, a maneuver aptly called "fire in the hole."

  Also, Grumman advised that, from the standpoint of landing stability, a five-legged LEM was unsatisfactory. Under investigation were a number of landing gear configurations, including retractable legs.

• Discussions with Hamilton Standard on Apollo LEM environmental control system - . Nation: USA. Program: Apollo. Spacecraft: Apollo LM, LM ECS. Grumman began initial discussions with Hamilton Standard on the development of the LEM environmental control system..

• Report on power sources for the Apollo LEM - . Nation: USA. Program: Apollo. Spacecraft: Apollo LM, LM Electrical.

  Grumman representatives presented their technical study report on power sources for the LEM. They recommended three fuel cells in the descent stage (one cell to meet emergency requirements), two sets of fluid tanks, and two batteries for peak power loads. For industrial competition to develop the power sources, Grumman suggested Pratt and Whitney Aircraft and GE for the fuel cells, and Eagle-Picher, Electrical Storage Battery, Yardney, Gulton, and Delco-Remy for the batteries.

• Grumman presented its first monthly progress report on the Apollo LEM - . Nation: USA. Program: Apollo. Spacecraft: Apollo LM.

  Grumman presented its first monthly progress report on the LEM. In accordance with NASA's list of high-priority items, principal engineering work was concentrated on spacecraft and subsystem configuration studies, mission plans and test program investigations, common usage equipment surveys, and preparation for implementing subcontractor efforts.

• First Apollo LM fire-in-the-hole model test - . Nation: USA. Program: Apollo. Spacecraft: Apollo LM, LM Ascent Propulsion. Grumman completed its first "fire-in-the-hole" model test. Even though preliminary data agreed with predicted values, they nonetheless planned to have a support contractor, the Martin Company, verify the findings..

• Definitive contract formalized for the Apollo Lunar Excursion Module - . Nation: USA. Program: Apollo. Spacecraft: Apollo LM.

  NASA announced signing of the contract with Grumman for development of the LEM. Company officials had signed the document on January 21 and, following legal reviews, NASA Headquarters had formally approved the agreement on March 7. Under the fixed-fee contract (NAS 9-1100) ($362.5 million for costs and $25.4 million in fees) Grumman was authorized to design, fabricate, and deliver nine ground test and 11 flight vehicles. The contractor would also provide mission support for Apollo flights. MSC outlined a developmental approach, incorporated into the contract as "Exhibit B, Technical Approach," that became the "framework within which the initial design and operational modes" of the LEM were developed.

• Contract talks with Marquardt for Apollo LEM reaction control system - . Nation: USA. Program: Apollo. Spacecraft: Apollo LM, LM RCS. Grumman began early contract talks with the Marquardt Corporation for development of the LEM reaction control system..

• Bidders' conference for Apollo LEM mechanically throttled descent engine - . Nation: USA. Program: Apollo. Spacecraft: Apollo LM, LM Descent Propulsion, LM RCS.

  A bidders' conference was held at Grumman for a LEM mechanically throttled descent engine to be developed concurrently with Rocketdyne's helium injection descent engine. Corporations represented were Space Technology Laboratories; United Technology Center, a division of United Aircraft Corporation; Reaction Motors Division, Thiokol Chemical Corporation; and Aerojet-General Corporation. Technical and cost proposals were due at Grumman on April 8.

• Firm requirements for the lunar landing mission - . Nation: USA. Program: Apollo. Spacecraft: Apollo LM.

  The Apollo Mission Planning Panel set forth two firm requirements for the lunar landing mission. First, both LEM crewmen must be able to function on the lunar surface simultaneously. MSC contractors were directed to embody this requirement in the design and development of the Apollo spacecraft systems. Second, the panel established duration limits for lunar operations. These limits, based upon the 48-hour LEM operation requirement, were 24 hours on the lunar surface and 24 hours in flight on one extreme, and 45 surface hours and 3 flight hours on the other. Grumman was directed to design the LEM to perform throughout this range of mission profiles.

• Stowage of crew equipment in both the Apollo CM and LEM worked out - . Nation: USA. Program: Apollo. Spacecraft: A7L, Apollo LM, CSM Cockpit, LM Structural.

  MSC reported that stowage of crew equipment, some of which would be used in both the CM and the LEM, had been worked out. Two portable life support systems and three pressure suits and thermal garments were to be stowed in the CM. Smaller equipment and consumables would be distributed between modules according to mission phase requirements.

• Preliminary plans for Apollo scientific instrumentation - . Nation: USA. Program: Apollo. Spacecraft Bus: Apollo LM. Spacecraft: Apollo ALSEP.

  MSC reported that preliminary plans for Apollo scientific instrumentation had been prepared with the cooperation of NASA Headquarters, Jet Propulsion Laboratory, and the Goddard Space Flight Center. The first experiments would not be selected until about December 1963, allowing scientists time to prepare proposals. Prime consideration would be given to experiments that promised the maximum return for the least weight and complexity, and to those that were man-oriented and compatible with spacecraft restraints. Among those already suggested were seismic devices (active and passive), and instruments to measure the surface bearing strength, magnetic field, radiation spectrum, soil density, and gravitational field. MSC planned to procure most of this equipment through the scientific community and through other NASA and government organizations.

• MSC sent MIT and Grumman radar configuration requirements for the Apollo LEM - . Nation: USA. Program: Apollo. Spacecraft: Apollo LM, CSM Guidance, LM Guidance.

  MSC sent MIT and Grumman radar configuration requirements for the LEM. The descent equipment would be a three-beam doppler radar with a two-position antenna. Operating independently of the primary guidance and navigation system, it would determine altitude, rate of descent, and horizontal velocity from 7,000 meters (20,000 feet) above the lunar surface. The LEM rendezvous radar, a gimbaled antenna with a two-axis freedom of movement, and the rendezvous transponder mounted on the antenna would provide tracking data, thus aiding the LEM to intercept the orbiting CM. The SM would be equipped with an identical rendezvous radar and transponder.

• Study on ablative versus regenerative cooling for the Apollo LEM ascent engine - . Nation: USA. Program: Apollo. Spacecraft: Apollo LM, LM Ascent Propulsion.

  RCA completed a study on ablative versus regenerative cooling for the thrust chamber of the LEM ascent engine. Because of low cooling margins available with regenerative cooling, Grumman selected the ablative method, which permitted the use of either ablation or radiation cooling for the nozzle extension.

• Preliminary design specifications for the Apollo LEM communications system - . Nation: USA. Program: Apollo. Spacecraft: Apollo LM, LM Communications.

  Grumman met with representatives of North American, Collins Radio Company, and Motorola, Inc., to discuss common usage and preliminary design specifications for the LEM communications system. These discussions led to a simpler design for the S-band receiver and to modifications to the S-band transmitter (required because of North American's design approach).

• Grumman began Lunar Hover and Landing Simulation IIIA tests - . Nation: USA. Program: Apollo. Spacecraft: Apollo LM, LM Simulator.

  Grumman began "Lunar Hover and Landing Simulation IIIA," a series of tests simulating a LEM landing. Crew station configuration and instrument panel layout were representative of the actual vehicle.

  Through this simulation, Grumman sought primarily to evaluate the astronauts' ability to perform the landing maneuver manually, using semiautomatic as well as degraded attitude control modes. Other items evaluated included the flight control system parameters, the attitude and thrust controller configurations, the pressure suit's constraint during landing maneuvers, the handling qualities and operation of LEM test article 9 as a freeflight vehicle, and manual abort initiation during the terminal landing maneuver.

• Preliminary configuration freeze for the Apollo LEM - . Nation: USA. Program: Apollo. Spacecraft: Apollo LM, LM Landing Gear.

  At a mechanical systems meeting at MSC, customer and contractor achieved a preliminary configuration freeze for the LEM. Several features of the design of the two stages were agreed upon:

  Descent

  four cylindrical propellant tanks (two oxidizer and two fuel); four- legged deployable landing gear

  Ascent

  a cylindrical crew cabin (about 234 centimeters (92 inches) in diameter) and a cylindrical tunnel (pressurized) for equipment stowage; an external equipment bay.

  Additional Details: here....

• Apollo LEM reaction control system (RCS) to be equipped with dual interconnected tanks - . Nation: USA. Program: Apollo. Spacecraft: Apollo LM, LM RCS.

  Grumman recommended that the LEM reaction control system (RCS) be equipped with dual interconnected tanks, separately pressurized and employing positive expulsion bladders. The design would provide for an emergency supply of propellants from the main ascent propulsion tanks. The RCS oxidizer to fuel ratio would be changed from 2.0:1 to 1.6:1. MSC approved both of these changes.

• Grumman studies on common usage of Apollo CSM/LM communications - . Nation: USA. Program: Apollo. Spacecraft: Apollo LM, CSM Television, LM Communications, LM Television. Grumman reported to MSC the results of studies on common usage of communications. Television cameras for the two spacecraft would be identical; the LEM transponder would be as similar as possible to that in the CSM..

• Rocketdyne gvien go ahead for Apollo LEM descent engine - . Nation: USA. Program: Apollo. Spacecraft: Apollo LM, LM Descent Propulsion.

  Grumman reported that it had advised North American's Rocketdyne Division to go ahead with the lunar excursion module descent engine development program. Negotiations were complete and the contract was being prepared for MSC's review and approval. The go-ahead was formally issued on May 2.

• CM television camera made compatible with that in the Apollo LEM - . Nation: USA. Program: Apollo. Spacecraft: Apollo LM, CSM Television, LM Television.

  NASA, North American, Grumman, and RCA representatives determined the alterations needed to make the CM television camera compatible with that in the LEM: an additional oscillator to provide synchronization, conversion of operating voltage from 115 AC to 28 DC, and reduction of the lines per frame from 400 to 320.

• Apollo LEM manual control simulated - . Nation: USA. Related Persons: Armstrong, Carpenter, Conrad, McDivitt, Schirra, See, White, Young. Program: Apollo. Spacecraft: Apollo LM, CSM Guidance, LM Simulator.

  Astronauts M. Scott Carpenter, Walter M. Schirra, Jr., Neil A. Armstrong, James A. McDivitt, Elliot M. See, Jr., Edward H. White II, Charles Conrad, Jr., and John W. Young participated in a study in LTV's Manned Space Flight Simulator at Dallas, Tex. Under an MSC contract, LTV was studying the astronauts' ability to control the LEM manually and to rendezvous with the CM if the primary guidance system failed during descent.

• Reorganization of Apollo SPO - . Nation: USA. Related Persons: Johnson, Caldwell. Program: Apollo. Spacecraft: Apollo LM.

  MSC announced a reorganization of ASPO:

  Acting Manager:

  Robert O. Piland

  Deputy Manager, Spacecraft:

  Robert O. Piland

  Assistant Deputy Manager for CSM:

  Caldwell C. Johnson

  Deputy Manager for System Integration:

  Alfred D. Mardel

  Deputy Manager LEM:

  James L. Decker

  Manager, Spacecraft Systems Office:

  David W. Gilbert

  Manager, Project Integration Office:

  J. Thomas Markley

• The first meeting of the Apollo LEM Flight Technology Systems Panel was held at MSC - . Nation: USA. Program: Apollo. Spacecraft: Apollo LM, LM ECS, LM Weight.

  The first meeting of the LEM Flight Technology Systems Panel was held at MSC. The panel was formed to coordinate discussions on all problems involving weight control, engineering simulation, and environment. The meeting was devoted to a review of the status of LEM engineering programs.

• STL to build the mechanically throttled descent engine for the Apollo LEM - . Nation: USA. Program: Apollo. Spacecraft: Apollo LM, LM Descent Propulsion. Grumman selected Space Technology Laboratories (STL) to develop and fabricate a mechanically throttled descent engine for the LEM, paralleling Rocketdyne's effort. Following NASA and MSC concurrence, Grumman began negotiations with STL on June 1..

• Quality Control Program Plan for the Apollo LEM - . Nation: USA. Program: Apollo. Spacecraft: Apollo LM. Grumman submitted to NASA a Quality Control Program Plan for the LEM, detailing efforts in management, documentation, training, procurement, and fabrication..

• LLRV could be used to test Apollo LEM hardware - . Nation: USA. Program: Apollo. Spacecraft Bus: Apollo LM. Spacecraft: Apollo LLRV.

  Grumman, reporting on the Lunar Landing Research Vehicle's (LLRV) application to the LEM development program, stated the LLRV could be used profitably to test LEM hardware. Also included was a development schedule indicating the availability of LEM equipment and the desired testing period.

• Status report on the Apollo LEM landing gear design and Apollo LEM stowage height - . Nation: USA. Program: Apollo. Spacecraft: Apollo LM, LM Landing Gear.

  At a meeting on mechanical systems at MSC, Grumman presented a status report on the LEM landing gear design and LEM stowage height. On May 9, NASA had directed the contractor to consider a more favorable lunar surface than that described in the original Statement of Work. Additional Details: here....

• Grumman representatives met with the Apollo ASPO Electrical Systems Panel (ESP) - . Nation: USA. Program: Apollo. Spacecraft: A7L, Apollo LM, CSM Communications, LM Communications.

  Grumman representatives met with the ASPO Electrical Systems Panel (ESP). From ESP, the contractor learned that the communications link would handle voice only. Transmission of physiological and space suit data from the LEM to the CM was no longer required. VHF reception of this data and S-band transmission to ground stations was still necessary. In addition, Grumman was asked to study the feasibility of a backup voice transmitter for communications with crewmen on the lunar surface should the main VHF transmitter fail.

• Apollo LEM and CSM to incorporate phase-coherent S-band transponders - . Nation: USA. Program: Apollo. Spacecraft: Apollo LM, CSM SPS, LM Communications.

  NASA Headquarters, MSC, Jet Propulsion Laboratory, MSFC, North American, and Grumman agreed that the LEM and CSM would incorporate phase-coherent S-band transponders. (The S-band system provides a variety of communications services. Being phase-coherent meant that it could also provide Mission Control Center with information about the vehicle's velocity and position, and thus was a means of tracking the spacecraft.) Each would have its own allocated frequencies and would be compatible with Deep Space Instrumentation Facilities.

• Major redesign of the Apollo guidance computer - . Nation: USA. Program: Apollo. Spacecraft: Apollo LM, CSM Guidance, LM Guidance. MIT suggested a major redesign of the Apollo guidance computer to make the CM and LEM computers as similar as possible. NASA approved the redesign and the Raytheon Company, subcontractor for the computer, began work..

• Apollo LEM-space suit interface problems - . Nation: USA. Program: Apollo. Spacecraft: Apollo LM, LM Electrical.

  Meeting in Bethpage, N. Y., officials from MSC, Grumman, Hamilton Standard, International Latex, and North American examined LEM-space suit interface problems. This session resulted in several significant decisions:

  • Suit evaluation would include a vehicle mockup in an aircraft flying zero and one-sixth g trajectories.
  • The suit assembly emergency oxygen supply would serve also as the backup pressurization and oxygen supply during crew transfer from the CM to the LEM.
  • The four-hour operating requirement for the portable life support system (PLSS) should not be considered for normal operation.
  • Pending final design of a waste management system, Grumman would retain provisions for stowage of human wastes.
  • The thermal garment would not normally be worn inside the LEM.
  • The PLSS battery would be charged before earth launch.
  • Prototype Apollo space suits were to be delivered to Grumman as soon as possible for evaluation and vehicle design.

• Grumman presented its Apollo LEM engineering and simulation plans - . Nation: USA. Program: Apollo. Spacecraft: Apollo LM.

  Grumman presented its LEM engineering and simulation plans to MSC, stating that their existing facilities and contracted facilities at North American in Columbus, Ohio, and at LTV would be used throughout 1963. Two part-task LEM simulators would be operational at Grumman early in 1964, with a complete mission simulator available in 1965. MSC had approved the contractor's procurement of two visual display systems for use in the simulators.

• Apollo LEM descent engine development program - . Nation: USA. Program: Apollo. Spacecraft: Apollo LM, LM Descent Propulsion.

  Rocketdyne reported to Grumman on the LEM descent stage engine development program. Revised measurements for the engine were: diameter, 137 centimeters (54 inches); length, 221 centimeters (87 inches) (30.5 centimeters (twelve inches) more than the original constraint that Grumman had imposed on Rocketdyne).

• Grumman studied use of the PLSS lithium hydroxide cartridges in the Apollo LEM ECS - . Nation: USA. Program: Apollo. Spacecraft: A7L, Apollo LM, LM ECS.

  Grumman studied the possibility of using the portable life support system lithium hydroxide cartridges in the LEM environmental control system, and determined that such common usage was feasible. This analysis would be verified by tests at Hamilton Standard.

• Grumman completed the Apollo LEM M-1 mockup - . Nation: USA. Program: Apollo. Spacecraft: Apollo LM. Grumman completed the LEM M-1 mockup and began installing equipment in the vehicle. Also, the contractor began revising cabin front design to permit comparisons of visibility..

• Titanium selected for the propellant tanks for the Apollo LEM descent stage - . Nation: USA. Program: Apollo. Spacecraft: Apollo LM, LM Descent Propulsion. After a detailed comparison of titanium and aluminum propellant tanks for the LEM descent stage, Grumman selected the lighter titanium..

• First estimates of reliability for the Apollo LEM - . Nation: USA. Program: Apollo. Spacecraft: Apollo LM. In its first estimates of reliability for the LEM, Grumman reported a 0.90 probability for mission success and 0.994 for crew safety. (The probabilities required by NASA were 0.984 and 0.9995, respectively.).

• Length of the spacecraft-Saturn V adapter had been increased from 8.077 meters to 8.89 meters - . Nation: USA. Program: Apollo. Spacecraft: Apollo LM, LM Landing Gear. MSC informed MSFC that the length of the spacecraft-Saturn V adapter had been increased from 807.7 centimeters to 889 centimeters (318 inches to 350 inches). The LEM would be supported in the adapter from a fixed structure on the landing gear..

• MSC and Grumman assessed crew visibility requirements for the Apollo LEM - . Nation: USA. Program: Apollo. Spacecraft: Apollo LM, LM Crew Station.

  MSC and Grumman assessed crew visibility requirements for the LEM. The study included a series of helicopter flights in which simulated earthshine lighting conditions and LEM window configurations were combined with helicopter landings along representative LEM trajectories. These flights simulated the LEM's attitude, velocity, range, and dive angle in the final approach trajectory.

• Apollo LEM crew to stand - . Nation: USA. Program: Apollo. Spacecraft: Apollo LM, LM Crew Station.

  MSC reported that crew systems engineers at the Center were assessing feasibility of having the LEM crew stand rather than sit. MSC requested Grumman also to look into having the crew fly the vehicle from a standing position. The concept was formally proposed at the August 27 crew systems meeting and was approved at the NASA-Grumman review of the LEM M-1 mockup on September 16-18.

• Apollo LEM guidance and navigation system coordination meeting - . Nation: USA. Program: Apollo. Spacecraft: Apollo LM, LM Guidance.

  MSC met with those contractors participating in the development of the LEM guidance and navigation system. Statements of Work for the LEM design concept were agreed upon. (Technical directives covering most of the work had been received earlier by the contractors.)

• Apollo LEM landing gear design freeze - . Nation: USA. Program: Apollo. Spacecraft: Apollo LM, LM Landing Gear.

  MSC Director Robert R. Gilruth reported to the MSF Management Council that the LEM landing gear design freeze was now scheduled for August 31. Grumman had originally proposed a LEM configuration with five fixed legs, but LEM changes had made this concept impractical. The weight and overall height of the LEM had increased, the center of gravity had been moved upward, the LEM stability analysis had expanded to cover a wider range of landing conditions, the cruciform descent stage had been selected, and the interpretation of the lunar model had been revised. These changes necessitated a larger gear diameter than at first proposed. This, in turn, required deployable rather than fixed legs so the larger gear could be stored in the Saturn V adapter. MSC had therefore adopted a four-legged deployable gear, which was lighter and more reliable than the five-legged configuration.

• RCA named as subcontractor for Apollo LEM electronics subsystems and for engineering support - . Nation: USA. Program: Apollo. Spacecraft: Apollo LM, LM Communications, LM Guidance.

  NASA announced its concurrence in Grumman's selection of RCA as subcontractor for the LEM electronics subsystems and for engineering support. Under the $40 million contract, RCA was responsible for five LEM subsystem areas: systems engineering support, communications, radar, inflight testing, and ground support. RCA would also fabricate electronic components of the LEM stabilization and control system. (Engineers and scientists from RCA had been working at Grumman on specific projects since February.)

• Apollo LTV abort simulation negotiations with Grumman completed - . Nation: USA. Program: Apollo. Spacecraft: Apollo LM, LM Simulator. Planning and final details of LTV abort simulation negotiations with Grumman were completed. The abort experiments, to be conducted at LTV's aerospace simulation facility in Dallas, Tex., were scheduled to begin in October..

• Two portable life support systems to be stowed in the Apollo LEM and one in the CM - . Nation: USA. Program: Apollo. Spacecraft: A7L, Apollo LM, CSM ECS, LM Electrical.

  MSC reported that two portable life support systems would be stowed in the LEM and one in the CM. Resupplying water, oxygen, and lithium hydroxide could be done in a matter of minutes; however, battery recharging took considerably longer, and detailed design of a charger was continuing.

• Grumman completed the Apollo LEM circuit design for suit and cabin pressure control systems - . Nation: USA. Program: Apollo. Spacecraft: Apollo LM, LM ECS. Grumman completed the LEM circuit design for suit and cabin pressure control systems. Also the contractor formulated a detailed plan for the evaluation of red and white cockpit lighting; equipment for the test had already been received..

• STL go-ahead to develop a parallel descent engine for the Apollo LEM - . Nation: USA. Program: Apollo. Spacecraft: Apollo LM, LM Ascent Propulsion, LM Descent Propulsion.

  Space Technology Laboratories received Grumman's go-ahead to develop the parallel descent engine for the LEM. At the same time, Grumman ordered Bell Aerosystems Company to proceed with the LEM ascent engine. The contracts were estimated at $18,742,820 and $11,205,415, respectively.

• Study on Apollo LEM visibility - . Nation: USA. Program: Apollo. Spacecraft: Apollo LM, LM Crew Station.

  Grumman presented the results of a study on LEM visibility. A front-face configuration with triangular windows was tentatively accepted by MSC for the ascent stage. Further investigation would be directed toward eliminating the "dead spots" to improve the configuration's visibility.

• Extendable boom for Apollo docking - . Nation: USA. Program: Apollo. Spacecraft: Apollo LM, CSM Docking, LM Crew Station.

  MSC directed North American to concentrate on the extendable boom concept for CSM docking with the LEM. The original impact type of docking had been modified:

  1. The primary mode employed an extendable probe. It would establish initial contact and docking at a separation distance sufficient to prevent dangerous impact as a result of pilot error.
  2. The backup mode consisted of free-flying the two modules together. Mean relative impact velocities established during free-flying docking simulation studies would be used as the design impact velocities.
  North American and Grumman began a hardware testing and flight simulation program in late September to evaluate the feasibility of several types of extendable probe tether systems. The two companies were to determine the stiffness required of the docking structure for compatibility with the stabilization and control system.

• Apollo portable life support system (PLSS) to have three attaching points for stowage - . Nation: USA. Program: Apollo. Spacecraft: A7L, Apollo LM.

  North American, Grumman, and Hamilton Standard, meeting at MSC with Crew Systems Division engineers, agreed that the portable life support system (PLSS) would have three attaching points for stowage in the spacecraft. In addition, it was agreed that the PLSS should not be used for shoulder restraint in the LEM.

• Pratt and Whitney to develop fuel cells for the Apollo LEM - . Nation: USA. Program: Apollo. Spacecraft: Apollo LM, LM Electrical.

  Grumman selected Pratt and Whitney to develop fuel cells for the LEM. Current LEM design called for three cells, supplemented by a battery for power during peak consumption beyond what the cells could deliver. Grumman and Pratt and Whitney completed contract negotiations on August 27, and MSC issued a letter go-ahead on September 5. Including fees and royalties, the contract was worth $9.411 million.

• Marquardt begins development of the Apollo LEM reaction control thrusters - . Nation: USA. Program: Apollo. Spacecraft: Apollo LM, LM RCS. Grumman directed the Marquardt Corporation to begin development of the LEM reaction control system thrusters. Negotiations had begun on March 11 on the definitive subcontract, a cost-plus-incentive-fee type with a total estimated cost of $10,871,186..

• Hamilton Standard began development of the ECS for the Apollo LEM - . Nation: USA. Program: Apollo. Spacecraft: Apollo LM, LM ECS.

  Grumman authorized Hamilton Standard to begin development of the environmental control system (ECS) for the LEM. The cost-plus-incentive-fee contract was valued at $8,371,465. The parts of the ECS to be supplied by Hamilton Standard were specified by Grumman.

• Grumman to design identical connectors for both ends of the space suit hoses in the Apollo LEM - . Nation: USA. Program: Apollo. Spacecraft: A7L, Apollo LM.

  ASPO ordered Grumman to design identical connectors for both ends of the space suit hoses in the LEM. This arrangement, called the "buddy concept," would permit one portable life support system to support two crewmen and thus would eliminate the need for a special suit-to-suit hose.

• Installation of the inertial measurement unit and optical telescope in the Apollo LEM discussed - . Nation: USA. Program: Apollo. Spacecraft: Apollo LM, LM Guidance.

  MIT and Grumman representatives discussed installing the inertial measurement unit and the optical telescope in the LEM. Of several possible locations, the top centerline of the cabin seemed most promising. Grumman agreed to provide a preliminary structural arrangement of the guidance components so that MIT could study problems of installation and integration.

• Three methods of Apollo descent from lunar parking orbit reviewed - . Nation: USA. Related Persons: Hohmann, Bernhard. Program: Apollo. Spacecraft: Apollo LM, LM Weight.

  North American, NASA, and Grumman representatives discussed three methods of descent from lunar parking orbit:

  1. descent of the LEM only (the minimum energy Hohmann transfer),
  2. the combined descent of both spacecraft, and
  3. the synchronous equal period method.
  While neither contractor felt that weight factors should be of primary concern, Grumman favored the Hohmann transfer and North American the combined descent, which represented the extremes of energy requirements. After considering reliability, fuel consumption, and operational flexibility, NASA chose the synchronous method as the prime mission mode but recommended continued investigation of the other two techniques.

• Grumman to design the LEM to have a thrusting capability with the Apollo CSM attached - . Nation: USA. Program: Apollo. Spacecraft: Apollo LM, CSM SPS.

  North American asked MSC if Grumman was designing the LEM to have a thrusting capability with the CSM attached and, if not, did NASA intend to require the additional effort by Grumman to provide this capability. North American had been proceeding on the assumption that, should the service propulsion system (SPS) fail during translunar flight, the LEM would make any course corrections needed to ensure a safe return trajectory. Additional Details: here....

• Increased Apollo LEM mission energy requirement - . Nation: USA. Program: Apollo. Spacecraft: Apollo LM, LM Electrical.

  At a meeting on the LEM electrical power system, Grumman presented its latest load analysis, which placed the LEM's mission energy requirements at 76.53 kilowatt-hours. The control energy level for the complete LEM mission had been set at 54 kilowatt-hours and the target energy level at 47.12 kilowatt-hours. Grumman and MSC were jointly establishing ground rules for an electrical power reduction program.

• Ad Hoc Rendezvous Working Group formed - . Nation: USA. Program: Apollo. Spacecraft: Apollo LM, CSM Communications, LM Communications, LM Guidance. An Ad Hoc Rendezvous Working Group was formed at MSC to study the possibility of substituting a unified S-band system for the rendezvous X-band radar on the LEM and CSM..

• MSC received proposals for the visual displays for the Apollo LEM simulator - . Nation: USA. Program: Apollo. Spacecraft: Apollo LM, LM Crew Station.

  MSC received proposals for the visual displays for the LEM simulator. Because of the changed shape of that vehicle's windows, however, Grumman had to return those proposals to the original bidders, sending revised proposals to MSC in December. Farrand Optical Company was selected to develop the display, and the Center approved Grumman's choice. Negotiations between Grumman and Farrand were completed during March 1964.

• Apollo LEM crew systems meeting - . Nation: USA. Program: Apollo. Spacecraft: Apollo LM, LM Weight.

  A LEM crew systems meeting was held at Grumman. The standing arrangement proposed for the crew promised to reduce the weight of the LEM by as much as 27.2 kilograms (60 pounds), and would improve crew mobility, visibility, control accessibility, and ingress-egress. Pending more comprehensive analysis, crew systems designers also favored the revised front-face configuration.

• Full-scale cardboard model of the Apollo LEM - . Nation: USA. Program: Apollo. Spacecraft: Apollo LM, LM Landing Gear, LM RCS.

  Grumman built a full-scale cardboard model of the LEM to aid in studying problems of cockpit geometry, specifically the arrangement of display panels. This mockup was reviewed by MSC astronauts and the layout of the cockpit was revised according to some of their suggestions.

  Also Grumman reported that a preliminary analysis showed the reaction control system plume heating of the LEM landing gear was not a severe problem. (This difficulty had been greatly alleviated by the change from five to four landing legs on the vehicle.

• Apollo LEM test articles LTA-8 and LTA-9 - . Nation: USA. Program: Apollo. Spacecraft: Apollo LM, LM Structural.

  At a meeting at MSC, Grumman representatives submitted the cost proposal for LEM test articles LTA-8 and LTA-9, and suggested a testing program for the two vehicles: LTA-8 should be used for restrained integrated systems testing in the altitude propulsion test facilities at the Atlantic Missile Range; LTA-9 should be used for manned atmospheric tethered operation tests. The contractor also recommended an early flight demonstration program to verify the helicopter tether operation potential, which promised greatly increased mission test capability over fixed-base tether facilities. The tether method (helicopter or fixed- base) should be determined after the verification. LTA-8 should be considered as a constraint to LEM-5, and LTA-9 as a constraint to the lunar landing mission.

• Study to define the stability limits of a 4.57 m radius Apollo LEM gear configuration - . Nation: USA. Program: Apollo. Spacecraft: Apollo LM, LM Landing Gear.

  MSC began a study to define the stability limits of a 457-centimeter (180inch) radius LEM gear configuration. The study, in two phases, sought to examine factors affecting stability (such as lunar slope, touchdown velocity and direction, and the effects of soil mechanics) in direct support of the one-sixth model and full-scale drop test programs and to complete definition of landing capabilities of the LEM.

• Inspection of first Apollo LEM ascent stage mockup - . Nation: USA. Program: Apollo. Spacecraft: Apollo LM.

  NASA representatives held a formal review of Grumman's LEM M-1 mockup, a full-scale representation of the LEM's crew compartment. MSC decided that (1) the window shape (triangular) and visibility were satisfactory; (2) a standing position for the crew was approved, although, in general, it was believed that restraints restricted crew mobility; (3) the controllers were positioned too low and lacked suitable arm support for fine control; and (4) crew station arrangement was generally acceptable, although specific details required further study.

• LTV presented the preliminary results of a manual rendezvous simulation study - . Nation: USA. Program: Apollo. Spacecraft: Apollo LM, LM Simulator.

  LTV presented the preliminary results of a manual rendezvous simulation study. Their studies indicated that a pilot trained in the technique could accomplish lunar launch and rendezvous while using only two to three percent more fuel than the automatic system.

• Apollo space suit umbilical disconnects redesigned for interchangeability - . Nation: USA. Program: Apollo. Spacecraft: A7L, Apollo LM, CSM Cockpit.

  The space suit umbilical disconnects were being redesigned to the "buddy concept" and for interchangeability between the CM and the LEM. MSC was reviewing methods for a crewman to return to the LEM following space suit failure on the lunar surface.

• Ablative nozzle primary design for Apollo LEM's ascent engine - . Nation: USA. Program: Apollo. Spacecraft: Apollo LM, LM Ascent Propulsion. Grumman directed Bell Aerosystems Company to establish the ablative nozzle extension as the primary design for the LEM's ascent stage engine. The radiation-cooled nozzle design, a weight-saving alternative, must be approved by NASA..

• Program reviewed for thermal testing for the Apollo LEM - . Nation: USA. Program: Apollo. Spacecraft: Apollo LM, LM Structural.

  MSC representatives reviewed Grumman's program for thermal testing for the LEM, to be conducted with the test model 2 (TM-2) vehicle. Because the vehicle's configuration had changed so extensively, the Center canceled the currently planned TM-2 ascent stage and ordered another stage to be substituted. TM-2's descent stage needed only small design changes to make it suitable for the program.

• Apollo mission plans - . Nation: USA. Program: Apollo. Spacecraft: Apollo LM.

  OMSF, MSC, and Bellcomm representatives, meeting in Washington, D.C., discussed Apollo mission plans: OMSF introduced a requirement that the first manned flight in the Saturn IB program include a LEM. ASPO had planned this flight as a CSM maximum duration mission only.

  • Bellcomm was asked to develop an Apollo mission assignment program without a Saturn I.
  • MSFC had been asking OMSF concurrence in including a restart capability in the S-IVB (second) stage during the Saturn IB program.
  ASPO would agree to this, but only if the H-1 engine were uprated from 85,275 to 90,718 kilograms (188,000 to 200,000 pounds) of thrust, resulting in a 907-kilogram (2,000-pound) payload gain.

• Evaluation of the Apollo space suit integration into the LEM - . Nation: USA. Program: Apollo. Spacecraft: A7L, Apollo LM, LM Weight.

  MSC representatives visited Grumman for a preliminary evaluation of the Apollo space suit integration into the LEM. A suit failure ended the exercise prematurely. Nonetheless, leg and foot mobility was good, but the upper torso and shoulder needed improvement.

  On October 11, MSC Crew Systems Division (CSD) tested the suit's mobility with the portable life support system (PLSS). CSD researchers found that the PLSS did not restrict the wearer's movement because the suit supported the weight of the PLSS. Shifts in the center of gravity appeared insignificant. The PLSS controls, because of their location, were difficult to operate, which demanded further investigation.

• Apollo LEM electrical power system changes recommended - . Nation: USA. Program: Apollo. Spacecraft: Apollo LM, LM Electrical.

  At a meeting at MSC, Grumman representatives presented 18 configurations of the LEM electrical power system, recommending a change from three to two fuel cells, still supplemented by an auxiliary battery system, with continued study on tankage design. On December 10, ASPO authorized the contractor to proceed with this configuration.

• Portable life support system in the Apollo CM be deleted - . Nation: USA. Program: Apollo. Spacecraft: A7L, Apollo LM, CSM Cockpit. North American recommended that the portable life support system in the CM be deleted. Current planning placed two units in the LEM and one in the CM..

• Contract to study Apollo experiments for lunar surface - . Nation: USA. Program: Apollo. Spacecraft Bus: Apollo LM. Spacecraft: Apollo ALSEP. MSC awarded Texas Instruments, Inc., a $194,000 contract to study experiments and equipment needed for scientific exploration of the lunar surface. The analysis was to be completed by the end of May 1964..

• Interrelationships between all major Apollo LEM test vehicles clarified - . Nation: USA. Program: Apollo. Spacecraft: Apollo LM, LM Structural.

  The interrelationships between all major LEM test vehicles, including all test constraints and documentation requirements, were developed. This logic study, prepared by Grumman and forwarded to MSC, stressed the feasibility of alterations in the LEM test program as needed.

• Preliminary configuration freeze for the Apollo LEM-adapter arrangement - . Nation: USA. Program: Apollo. Spacecraft: Apollo LM, LM Descent Propulsion, LM Landing Gear.

  At a LEM Mechanical Systems Meeting in Houston, Grumman and MSC agreed upon a preliminary configuration freeze for the LEM-adapter arrangement. The adapter would be a truncated cone, 876 centimeters (345 inches) long. The LEM would be mounted inside the adapter by means of the outrigger trusses on the spacecraft's landing gear. This configuration provided ample clearance for the spacecraft, both top and bottom (i.e., between the service propulsion engine bell and the instrument unit of the S-IVB).

  At this same meeting, Grumman presented a comparison of radially and laterally folded landing gears (both of 457-centimeter (180-inch) radius). The radial-fold configuration, MSC reported, promised a weight savings of 22-2 kilograms (49 pounds). MSC approved the concept, with an 876-centimeter (345-inch) adapter. Further, an adapter of that length would accommodate a larger, lateral fold gear (508 centimeters (200 inches)), if necessary. During the next several weeks, Grumman studied a variety of gear arrangements (sizes, means of deployment, stability, and even a "bending" gear). At a subsequent LEM Mechanical Systems Meeting, on November 10, Grumman presented data (design, performance, and weight) on several other four-legged gear arrangements - a 457-centimeter (180-inch), radial fold "tripod" gear (i.e., attached to the vehicle by three struts), and 406.4-centimeter (160-inch) and 457-centimeter (180-inch) cantilevered gears. As it turned out, the 406.4-centimeter (160-inch) cantilevered gear, while still meeting requirements demanded in the work statement, in several respects was more stable than the larger tripod gear. In addition to being considerably lighter, the cantilevered design offered several added advantages:

  • A reduced stowed height for the LEM from 336.5 to 313.7 centimeters (132.5 to 123.5 inches).
  • A shorter landing stroke (50.8 instead of 101.6 centimeters) (20 instead of 40 inches).
  • Better protection from irregularities (protuberances) on the surface.
  • An alleviation of the gear heating problem (caused by the descent engine's exhaust plume).
  • Simpler locking mechanisms.
  • A better capability to handle various load patterns on the landing pads.
  Because of these significant (and persuasive) factors, MSC approved Grumman's change to the 406.4- centimeter (160-inch) cantilevered arrangement as the design for the LEM's landing gear. By mid- November, MSC reported to OMSF that Grumman was pursuing the 406.4-centimeter (160-inch) cantilevered gear. Although analyses would not be completed for some weeks, the design was "shown . . . to be the lightest gear available to date. . . . Tentative estimates indicate a gear stowed height reduction of about 9" (22.9 centimeters), which will still accommodate the 180" (45.7 centimeter) cantilever or 200" (508-centimeter) lateral fold gear as growth potential." Grumman's effort continued at "firming up" the design, including folding and docking mechanisms.

• Guidelines for Apollo scientific investigations of the moon - . Nation: USA. Program: Apollo. Spacecraft Bus: Apollo LM. Spacecraft: Apollo ALSEP.

  Verne C. Fryklund, Jr., of NASA's Office of Space Sciences (OSS), in a memorandum to MSC Director Robert R. Gilruth, recommended some general guidelines for Apollo scientific investigations of the moon (which OSS already was using). "These guidelines," Fryklund told Gilruth, ". . . should be followed in the preparation of your plans," and thus were "intended to place some specific constraints on studies. . . . The primary scientific objective of the Apollo project," Fryklund said, was, of course, the "acquisition of comprehensive data about the moon." With this as a starting point, he went on, ". . . it follows that the structure of the moon's surface, gross body properties and large-scale measurements of physical and chemical characteristics, and observation of whatever phenomena may occur at the actual surface will be the prime scientific objectives." Basically, OSS's guidelines spelled out what types of activity were and were not part of Apollo's immediate goals. These activities were presumed to be mostly reconnaissance, "to acquire knowledge of as large an area as possible, and by as simple a means as possible, in the limited time available." The three principal scientific activities "listed in order of decreasing importance" were: (1) "comprehensive observation of lunar phenomena," (2) "collection of representative samples," and (3) "emplacement of monitoring equipment."

  These guidelines had been arrived at after extensive consultation within NASA as a whole as well as with the scientific community.

• Tethered docking of the LEM and Apollo CSM - . Nation: USA. Program: Apollo. Spacecraft: Apollo LM, CSM Docking, LM Crew Station.

  At MSC, the Spacecraft Technology Division reported to ASPO the results of a study on tethered docking of the LEM and CSM. The technology people found that a cable did not reduce the impact velocities below those that a pilot could achieve during free flyaround, nor was fuel consumption reduced. In fact, when direct control of the spacecraft was attempted, the tether proved a hindrance and actually increased the amount of fuel required.

• Results of tests performed by astronauts in the Manned Space Flight Mission Simulator - . Nation: USA. Program: Apollo. Spacecraft: Apollo LM, CSM Guidance, LM Guidance.

  LTV announced the results of tests performed by astronauts in the Manned Space Flight Mission Simulator in Dallas, Tex. These indicated that, should the primary guidance and navigation system fail, LEM pilots could rendezvous with the CM by using a circular slide rule to process LEM radar data.

• Commonality of displays and controls between Apollo CSM and LEM - . Nation: USA. Program: Apollo. Spacecraft: Apollo LM, LM Crew Station. MSC discussed commonality of displays and controls with its two principal spacecraft contractors. A review of panel components suggested that Grumman might use the same vendors as North American for such items as switches, potentiometers, and indicators..

• Selection of five organizations for Apollo LEM guidance and navigation equipment - . Nation: USA. Program: Apollo. Spacecraft: Apollo LM, CSM Guidance, LM Guidance.

  NASA Headquarters announced the selection of five organizations for contract negotiations totaling $60 million for the development, fabrication, and testing of LEM guidance and navigation equipment: (1) MIT, overall direction; (2) Raytheon, LEM guidance computer; (3) AC Spark Plug, inertial measurement unit, gyroscopes, navigation base, power and servo assembly, coupling display unit, and assembly and testing of the complete guidance and navigation system; (4) Kollsman Instrument Corporation, scanning telescope, sextant, and map and data viewer; and (5) Sperry Gyroscope Company, accelerometers. (All five had responsibility for similar equipment for the CSM as well.)

• Systems and ground rules outlined for the Apollo lunar landing mission - . Nation: USA. Program: Apollo. Spacecraft: Apollo LM.

  MSC Flight Operations Division defined systems and outlined ground rules for the lunar landing mission. System definitions were: (1) primary, most efficient or economic; (2) alternate, either redundant (identical to but independent of the primary) or backup (not identical but would perform the same function); (3) critical (failure would jeopardize crew safety); (4) repairable (for which tools and spares were carried and which the crew could service in flight); and (5) operational, which must be working to carry out a mission.

  Mission rules established crew safety as the major consideration in all mission decisions and detailed actions to be taken in the event of a failure in any system or subsystem.

• Contract to Hughes for a study of backup high gain antenna for Apollo LEM lunar surface equipment - . Nation: USA. Program: Apollo. Spacecraft: Apollo LM, LM Communications. MSC Instrumentation and Electronic Systems Division awarded a $50,000 contract to the Hughes Aircraft Company for a study of backup high gain directable antennas for the LEM lunar surface equipment..

• Apollo LEM landing site selection studied - . Nation: USA. Program: Apollo. Spacecraft: Apollo LM, LM Landing Gear.

  Because OMSF had requested OSSA to provide lunar surface microrelief and bearing strength data to support LEM landing site selection and to permit LEM landing-gear design validation, the Ad Hoc Working Group on Follow-On Surveyor Instrumentation met at NASA Headquarters. Attending were Chairman Verne C. Fryklund, Clark Goodman, Martin Swetnick, and Paul Brockman of the NASA Office of Space Sciences and Applications; Harry Hess and George Derbyshire of the National Acadamy of Sciences; Dennis James of Bellcomm (for OMSF); and Milton Beilock of the Jet Propulsion Laboratory (JPL). The group proposed "a fresh look at the problem of instrumenting payloads of Surveyor spacecraft that may follow the currently approved developmental and operational flights, so that these spacecraft will be able to determine that a particular lunar site is suitable for an Apollo landing." The study was assigned to JPL.

• Apollo LEM manned environmental control system development tests scheduled - . Nation: USA. Program: Apollo. Spacecraft: Apollo LM, LM ECS.

  MSC directed Grumman to schedule manned environmental control system (ECS) development tests, using a welded-shell cabin boilerplate and air lock. At about the same time, the company was also requested to quote cost and delivery schedule for a second boilerplate vessel, complete with prototype ECS. Although this vessel would be used by the MSC Crew Systems Division for in-house investigation and evaluation of ECS development problems, its major purpose was to serve as a tool for trouble-shooting during the operational phase.

• Major reorganization of NASA - . Nation: USA. Program: Apollo. Spacecraft: Apollo LM.

  NASA Associate Administrator for Manned Space Flight George E. Mueller notified the Directors of MSC, MSFC, and LOC that he intended to plan a flight schedule which would have a good chance of being met or exceeded. To this end, he directed that "all-up" spacecraft and launch vehicle tests be started as soon as possible; all Saturn IB flights would carry CSM and CSM LEM configurations; and two successful unmanned flights would be flown before a manned mission on either the Saturn IB or Saturn V.

  On November 18, Mueller further defined the flight schedule planning. Early Saturn IB flights might not be able to include the LEM, but every effort must be made to phase the LEM into the picture as early as possible. Launch vehicle payload capability must be reached as quickly as practicable. Subsystems for the early flights should be the same as those intended for lunar missions. To conserve funds, the first Saturn V vehicle would be used to obtain reentry data early in the Saturn test program.

  By December 31 the official schedule showed:

  Final Saturn I flight (SA-10):

  June 1965

  First Saturn IB flight (SA-201):

  first quarter, 1966

  First manned Saturn IB flight:

  either SA-203, third quarter of 1966, or SA-207, third quarter of 1967

  First Saturn V flight (SA-501):

  first quarter, 1967

  First manned Saturn V flight:

  either SA-503, third quarter of 1967, or SA-507, second quarter of 1968.

• Go-ahead to RCA to develop the Apollo LEM radar - . Nation: USA. Program: Apollo. Spacecraft: Apollo LM, LM Communications, LM Guidance.

  Grumman issued a go-ahead to RCA to develop the LEM radar. Negotiations on the $23.461 million cost- plus-fixed-fee contract were completed on December 10. Areas yet to be negotiated between the two companies were LEM communications, inflight test, ground support, and parts of the stabilization and control systems.

• Evaluation of propellant feed systems for the Apollo LEM ascent stage - . Nation: USA. Program: Apollo. Spacecraft: Apollo LM, LM Weight.

  ASPO reviewed Grumman's evaluation of series and parallel propellant feed systems for the LEM ascent stage. Because of the complications involved in minimizing propellant residuals in a parallel system, a series feed appeared preferable, despite an increase in LEM structural weight. Further study of the vehicle showed the feasibility of a two-tank configuration which would be lighter and have about the same propellant residual as the four-tank series-feed arrangement.

• Means for reducing the weight of the Apollo LEM - . Nation: USA. Program: Apollo. Spacecraft: Apollo LM, LM Electrical, LM RCS.

  After careful study, Grumman proposed to MSC 15 possible means for reducing the weight of the LEM. These involved eliminating a number of hardware items in the spacecraft; two propellant tanks in the vehicle's ascent stage and consequent changes in the feed system; two rather than three fuel cells; and reducing reaction control system propellants and, consequently, velocity budgets for the spacecraft. If all these proposed changes were made, Grumman advised, the LEM could be lightened significantly, perhaps by as much as 454 kilograms (1000 pounds).

• Apollo subcontract with Rocketdyne for the LEM descent engine - . Nation: USA. Program: Apollo. Spacecraft: Apollo LM, LM Descent Propulsion. MSC approved Grumman's $19,383,822 cost-plus-fixed-fee subcontract with Rocketdyne for the LEM descent engine development program..

• 10 lunar landing areas recommended for the Apollo program - . Nation: USA. Program: Apollo. Spacecraft: Apollo LM, LM ECS.

  MSC's Space Environment Division (SED) recommended (subject to reconnaissance verification) 10 lunar landing areas for the Apollo program:

  1. 36 degrees 55' E. 1 degree 45' N.
  2. 31 degrees E. 0 degrees N.
  3. 28 degrees 22' E. 1 degree 10' N.
  4. 24 degrees 10' E. 0 degrees 10' N.
  5. 12 degrees 50' E. 0 degrees 20' N.
  6. 1 degree 28'W. 0 degrees 30' S.
  7. 13 degrees 15' W. 2 degrees 45' N.
  8. 28 degrees 15' W. 2 degrees 45' N.
  9. 31 degrees 30' W. 1 degree 05' S.
  10. 41 degrees 30'W. 1 degree 10' S.
  SED chose these sites on the basis of regional slopes, surface texture and strength, landmarks, isolated features, and the size, shape, and position of the various areas. The list included several sites that the Division had designated earlier in the year.

• Velocity budgets for the Apollo spacecraft reduced - . Nation: USA. Related Persons: Hohmann, Bernhard, Shea. Program: Apollo. Spacecraft: Apollo LM, LM Ascent Propulsion, LM Descent Propulsion.

  ASPO Manager Joseph F. Shea asked NASA Headquarters to revise velocity budgets for the Apollo spacecraft. (Studies had indicated that those budgets could be reduced without degrading performance.) He proposed that the 10 percent safety margin applied to the original budget be eliminated in favor of specific allowances for each identifiable uncertainty and contingency; but, to provide for maneuvers which might be desired on later Apollo missions, the LEM's propellant tanks should be oversized.

  The ASPO Manager's proposal resulted from experience that had arisen because of unfortunate terminology used to designate the extra fuel. Originally the fuel budget for various phases of the mission had been analyzed and a 10 percent allowance had been made to cover - at that time, unspecified - contingencies, dispersions, and uncertainties. Mistakenly this fuel addition became known as a "10% reserve"! John P. Mayer and his men in the Mission Planning and Analysis Division worried because engineers at North American, Grumman, and NASA had "been freely 'eating' off the so-called 'reserve'" before studies had been completed to define what some of the contingencies might be and to apportion some fuel for that specific situation. Mayer wanted the item labeled a "10% uncertainty."

  Shea recommended also that the capacity of the LEM descent tanks be sufficient to achieve an equiperiod orbit, should this become desirable. However, the spacecraft should carry only enough propellant for a Hohmann transfer. This was believed adequate, because the ascent engine was available for abort maneuvers if the descent engine failed and because a low altitude pass over the landing site was no longer considered necessary. By restricting lunar landing sites to the area between ±5 degrees latitude and by limiting the lunar stay time to less than 48 hours, a one-half-degree, rather than two-degree, plane change was sufficient.

  In the meantime, Shea reported, his office was investigating how much weight could be saved by these propellant reductions.

• Apollo mission plan development study - . Nation: USA. Program: Apollo. Spacecraft: Apollo LM. After a meeting with Grumman officials on November 27, ASPO directed the contractor to begin a Grumman-directed Apollo mission plan development study..

• Apollo LEM tethered flight vehicle considered - . Nation: USA. Program: Apollo. Spacecraft: Apollo LM. MSC directed Grumman to halt work on LEM test article 9, pending determination of its status as a tethered flight vehicle. As a result, the proposed flight demonstration of the tether coupler, using an S-64A Skycrane helicopter, was canceled..

• AiResearch to supply cryogenic storage tanks for the Apollo LEM electrical power system - . Nation: USA. Program: Apollo. Spacecraft: Apollo LM, LM Descent Propulsion.

  Grumman selected AiResearch Manufacturing Company to supply cryogenic storage tanks for the LEM electrical power system. Final negotiations on the cost-plus-incentive-fee contract were held in June 1964.

  On this same date, Grumman concluded negotiations with Allison Division of General Motors Corporation for design and fabrication of the LEM descent engine propellant storage tanks (at a cost of $5,479,560).

• Apollo LEM Little Joe II configuration aerodynamically unstable - . Nation: USA. Program: Apollo. Spacecraft: Apollo LM.

  As a result of wind tunnel tests, Langley Research Center researchers found the LEM Little Joe II configuration to be aerodynamically unstable. To achieve stability, larger booster fins were needed. However, bigger fins caused more drag, shortening the length of the flight. MSC was investigating the possibility of using more powerful rocket engines to overcome this performance degradation.

• Redundant gimbal actuation system in the Apollo LEM's descent engine deleted - . Nation: USA. Program: Apollo. Spacecraft: Apollo LM, LM Descent Propulsion.

  ASPO concurred in Grumman's recommendation to delete the redundant gimbal actuation system in the LEM's descent engine. A nonredundant configuration would normally require mission abort in case of actuator failure. Consequently, in making this change, Grumman must ensure that mission abort and the associated staging operation would not compromise crew survival and mission reliability.

• Grumman proposed a two-tank ascent stage configuration for the Apollo LEM - . Nation: USA. Program: Apollo. Spacecraft: Apollo LM, LM Ascent Propulsion, LM Weight.

  Grumman proposed a two-tank ascent stage configuration for the LEM. On January 17, 1964, ASPO formally concurred and authorized Grumman to go ahead with the design. The change was expected to reduce spacecraft weight by about 45 kilograms (100 pounds) and would make for a simpler, more reliable ascent propulsion system. ASPO also concurred in the selection of titanium for the two propellant tanks.

• Hamilton Standard contract for Apollo LEM environmental control system - . Nation: USA. Program: Apollo. Spacecraft: Apollo LM, LM ECS. MSC announced that Grumman and Hamilton Standard had signed an $8,371,465 definitive contract for the LEM environmental control system. A go-ahead had been issued to Hamilton Standard on July 23..

• MSC defined the Apollo LEM terminal rendezvous maneuvers - . Nation: USA. Program: Apollo. Spacecraft: Apollo LM, CSM RCS, LM Ascent Propulsion, LM RCS.

  MSC defined the LEM terminal rendezvous maneuvers. That phase of the mission would begin at a range of 9.3 kilometers (five nautical miles) from the CSM and terminate at a range of 152.4 meters (500 feet). Before rendezvous initiation, closing velocity should be reduced to 61 meters (200 feet) per second by use of the ascent engine. The reaction control system should be used exclusively thereafter.

• Apollo television cameras for the LEM to be government-furnished - . Nation: USA. Program: Apollo. Spacecraft: Apollo LM, LM Descent Propulsion, LM Television.

  MSC decided to supply television cameras for the LEM as government-furnished items. Grumman was ordered to cease its effort on this component.

  Resizing of the LEM propulsion tanks was completed by Grumman. The cylindrical section of the descent tank was extended 34.04 millimeters (1.34 inches), for a total of 36.27 centimeters (14.28 inches) between the spherical end bells. The ascent tanks (two-tank series) were 1240.54 centimeters (48.84 inches) in diameter.

• Ryan selected for Apollo landing radar - . Nation: USA. Program: Apollo. Spacecraft: Apollo LM, LM Guidance. RCA, contractor to Grumman for the LEM rendezvous and landing radars, chose Ryan Aeronautical Company as vendor for the landing radar. The contract was signed March 16, 1964..

• Apollo contractors joint report on spacecraft test plan - . Nation: USA. Program: Apollo. Spacecraft: Apollo LM, LM Descent Propulsion.

  North American, Grumman, and MIT Instrumentation Laboratory summarized results of a six-week study, conducted at ASPO's request, on requirements for a Spacecraft Development Program. Purpose of the study was to define joint contractor recommendations for an overall development test plan within resource constraints set down by NASA. ASPO required that the plan define individual ground test and mission objectives, mission descriptions, hardware requirements (including ground support equipment), test milestones, and individual subsystem test histories.

  Intermediate objectives for the Apollo program were outlined: the qualification of a manned CSM capable of earth reentry at parabolic velocities after an extended space mission; qualification of a manned LEM both physically and functionally compatible with the CSM; and demonstration of manned operations in deep space, including lunar orbit. The most significant basic test plan objective formulated during the study was the need for flexibility to capitalize on unusual success or to compensate for unexpected difficulties with minimum impact on the program.

  Only one major issue in the test plan remained unresolved - lunar descent radar performance and actual lunar touchdown. Two possible solutions were suggested:

  1. Landing of an unmanned spacecraft. If this failed, however, there would be little or no gain, since there was not yet a satisfactory method for instrumenting the unmanned vehicle for necessary failure data. If the landing were successful, it would prove only that the LEM was capable of landing at that particular location.
  2. Designing the LEM for a reasonably smooth surface. This would avoid placing too stringent a requirement on the landing criteria to accommodate all lunar surface unknowns. A block change to the LEM design could then be planned for about mid-1966. By that time, additional lunar data from Ranger, Surveyor, and Lunar Orbiter flights would be available. The group agreed the second solution was more desirable.
  The contractors recommended:
  1. ASPO concur with the proposed plan as a planning basis for implementation;
  2. ASPO issue a Development Test Plan to all three contractors (preferably within 30 to 60-days);
  3. each contractor analyze the effect of the plan upon spacecraft, facility, and equipment contracts; and
  4. ASPO and the contractors conduct periodic reviews of the plan once it was formalized.
  In addition, the test plan should be coordinated with the lunar landing mission study, as well as development testing and systems engineering for the complete Apollo program.

  The complete findings of this joint study were contained in a five-volume report issued by North American and submitted to MSC early in February 1964. (This document became known informally as the "Project Christmas Present Report.")

• Grumman to implement changes to space suit oxygen umbilical hoses - . Nation: USA. Program: Apollo. Spacecraft: A7L, Apollo LM.

  ASPO directed Grumman to implement a number of recommendations on space suit oxygen umbilical hoses discussed at a joint Grumman/North American meeting and forwarded to ASPO on December 4, 1963:

  1. adopt a design that would permit use of CM hose sets in the LEM after crew transfer;
  2. place connectors on short hoses permanently attached to the suit, because suit vision and arm mobility did not permit use of on-suit connectors;
  3. determine exact placement and hose angles to route the suit portable life support system umbilicals between the legs of the suit;
  4. build the "buddy concept" into the umbilical design by ensuring that one of the LEM hoses had valve and safety provisions; and
  5. design the CM and LEM oxygen hose umbilicals to be interchangeable. (MSC would select a contractor for the connectors.)

• Apollo LEM translation and descent engine thrust controllers - . Nation: USA. Program: Apollo. Spacecraft: Apollo LM, LM Descent Propulsion, LM RCS.

  MSC directed Grumman to integrate LEM translation and descent engine thrust controllers. The integrated controller would be lighter and easier to install; also it would permit simultaneous reaction control system translation and descent engine control. Grumman had predicted that such a capability might be required for touchdown.

• Apollo LEM extravehicular suit telemetry and communications system review - . Nation: USA. Program: Apollo. Spacecraft: A7L, Apollo LM.

  The Flight Data Systems Branch of the Engineering and Development Directorate provided ASPO's Lunar Mission Planning Branch with information about the LEM extravehicular suit telemetry and communications system. No line of sight (LOS) communications were possible, and there would be no ground wave propagation and no atmospheric reflection. The link between astronaut and LEM would be limited to LOS of the two antennas, and surface activities by an extravehicular astronaut must be planned accordingly.

• Criteria for redundancy of controls and displays in the Apollo LEM crew station - . Nation: USA. Program: Apollo. Spacecraft: Apollo LM, LM Crew Station.

  Based on the LEM mockup review of September 16-18, 1963, MSC established criteria for redundancy of controls and displays in the LEM crew station. Within the framework of apportioned reliability requirements for mission success and crew safety, these guidelines applied:

  1. the LEM must be provisioned so that hover to touchdown could be flown manually by the crew;
  2. no single failure in the controls and displays should cause an abort; and
  3. the unknowns associated with lighting conditions or dust caused by rocket exhaust impingement on the lunar surface might require a joint effort by the crew.
  Although duplication of all equipment was not required, dual flight controls and windows, as well as gross attitude, attitude error, and vehicle rates information, were necessary. Other flight displays should be dual or be readable from either station.

• Apollo LEM manual orientation 36,600 meters above the moon - . Nation: USA. Program: Apollo. Spacecraft: Apollo LM, LM Guidance. ASPO asked the Flight Crew Operations Directorate to study whatever was necessary to ensure that the LEM crew could reorient their spacecraft manually in an abort 36,600 meters (120,000 feet) above the moon..

• Recommendations for Apollo LEM bioinstrumentation - . Nation: USA. Program: Apollo. Spacecraft: Apollo LM, LM Crew Station.

  MSC's Center Medical Office was reevaluating recommendations for LEM bioinstrumentation. The original request was for three high-frequency channels (two electrocardiogram and one respiration) that could be switched to monitor all crew members. Grumman wanted to provide one channel for each astronaut with no switching.

• Crushable aluminum honeycomb for Apollo LEM landing gear - . Nation: USA. Program: Apollo. Spacecraft: Apollo LM, LM ECS, LM Landing Gear.

  Bendix Products Aerospace Division was awarded a 99973 contract by MSC to study crushable aluminum honeycomb, a lightweight, almost non-elastic, shock-absorbing material for LEM landing gears. Bendix would test the honeycomb structures in a simulated lunar environment.

• Apollo LEM's electrical power system planned - . Nation: USA. Program: Apollo. Spacecraft: Apollo LM, LM ECS, LM Electrical.

  Representatives of Grumman, MSC's Instrumentation and Electronics Systems Division, ASPO, and Resident Apollo Spacecraft Program Office (RASPO) at Bethpage met at Grumman to plan the LEM's electrical power system. The current configuration was composed of three fuel cell generators with a maximum power output of 900 watts each, spiking stabilizing batteries, one primary general-purpose AC inverter, and a conventional bus arrangement. To establish general design criteria, the primary lunar mission of the LEM-10 vehicle was analyzed. This "critical" mission appeared to be the "worst case" for the electrical power system and established maximum power and usage rate requirements.

  Those attending the meeting foresaw a number of problems:

  • Grumman allowed only 10 percent margin for all contingencies and errors in energy requirements.
  • Fuel cells and cryogenic fuels needed testing in a simulated space environment.
  • Grumman depended upon its subcontractors to develop component testing procedures.
  • Optimum power supply modes and motors for the environmental control system were still to be selected.
  • "Essential loads" needed standardizing to allow the proper bus loading structure.
  • Proper charging rates and equipment for the portable life support system extravehicular suit batteries needed to be selected.

• First monthly progress report on the Lunar Mission Planning Study - . Nation: USA. Program: Apollo. Spacecraft: Apollo LM.

  Grumman presented to MSC the first monthly progress report on the Lunar Mission Planning Study. The planning group, designated the Apollo Mission Planning Task Force (AMPTF), established ground rules and constraints to serve as a base line around which mission flexibilities and contingency analyses could be built. Main topics of discussion at the meeting were the reference mission, study ground rules, task assignments, and future plans. The following week, MSC Flight Operations Directorate provided a reference trajectory for the AMPTF's use. Major constraints were daylight launch, translunar injection during the second earth parking orbit, free-return trajectory, daylight landing near the lunar equator, 24-hour lunar surface staytime, and a water landing on earth.

• First full-throttle firing of STL Apollo LEM descent engine - . Nation: USA. Program: Apollo. Spacecraft: Apollo LM, LM Descent Propulsion.

  The first full-throttle firing of Space Technology Laboratories' LEM descent engine (being developed as a parallel effort to the Rocketdyne engine) was carried out. The test lasted 214 seconds, with chamber pressures from 66.2 to 6.9 newtons per square centimeter (96 to 10 psi). Engine performance was about five percent below the required level.

• North American design concept for the Apollo Block II - . Nation: USA. Program: Apollo. Spacecraft: Apollo LM, CSM Block II, LM Weight.

  North American gave a presentation at MSC on the block change concept with emphasis on Block II CSM changes. These were defined as modifications necessary for compatibility with the LEM, structural changes to reduce weight or improve CSM center of gravity, and critical systems changes. (Block I spacecraft would carry no rendezvous and docking equipment and would be earth-orbital only. Block II spacecraft would be flight-ready vehicles with the final design configuration for the lunar missions.)

• Second phase of docking simulation studies ended - . Nation: USA. Program: Apollo. Spacecraft: Apollo LM, LM Simulator. The second phase of docking simulation studies ended at North American- Columbus (Ohio). Tests included 170 runs simulating transposition and lunar orbital docking with stable and unstable targets, and two extendible probe concepts: cable and rigid boom..

• AiResearch and Linde to manufacture high-pressure insulated tanks for the Apollo LEM - . Nation: USA. Program: Apollo. Spacecraft: Apollo LM, LM Descent Propulsion.

  MSC authorized AiResearch Manufacturing Company and the Linde Company to manufacture high- pressure insulated tanks. This hardware, to be available about May 15, would be used in a study of the feasibility of a supercritical helium pressurization system for the LEM.

• Attitude control of docked vehicles using the Apollo LEM's RCS - . Nation: USA. Related Persons: Hohmann, Bernhard. Program: Apollo. Spacecraft: Apollo LM, LM RCS.

  ASPO asked Grumman to study whether attitude control of the docked vehicles was practicable using the LEM's stabilization and control system (RCS). Grumman also was to evaluate the RCS fuel requirements for a five-minute alignment period to permit two star sightings. ASPO further directed the contractor to determine RCS fuel requirements for a second alignment of the LEM's inertial measurement unit during descent coast. This second alignment was needed for the required landing accuracy from a Hohmann descent.

• Apollo LEM's capability as active vehicle for lunar orbit docking - . Nation: USA. Program: Apollo. Spacecraft: Apollo LM, LM Crew Station.

  Studies on the LEM's capability to serve as the active vehicle for lunar orbit docking showed the forward docking tunnel to be the best means of accomplishing this. ASPO requested Grumman to investigate the possibility of this docking approach and the effect it might have on the spacecraft's configuration.

• Preliminary analysis of the probabilities of mission success if Apollo spacecraft hit by meteoroids - . Nation: USA. Program: Apollo. Spacecraft: Apollo LM, CSM Heat Shield, LM Weight.

  MSC and North American representatives discussed preliminary analysis of the probabilities of mission success if the spacecraft were hit by meteoroids. The contractor believed that pressurized tankage in the SM must be penetrated before a failure was assumed. To MSC, this view appeared overly optimistic. MSC held that, as the failure criterion, no debris should result from meteoroid impact of the SM outer structure. (This change in criteria would cost several hundred pounds in meteoroid protection weight in the SM and LEM.) North American thought that penetration of one half the depth of the heatshield on the conical surface of the CM was a failure. Here, MSC thought the contractor too conservative; full penetration could probably be allowed.

• All-ablative concept for the Apollo LEM ascent engine - . Nation: USA. Program: Apollo. Spacecraft: Apollo LM, LM Ascent Propulsion.

  Grumman began initial talks with Bell Aerosystems Company looking toward concentrating on the all-ablative concept for the LEM's ascent engine, thus abandoning the hope of using the lighter, radiatively cooled nozzle extension. These talks culminated in July, when Bell submitted to Grumman a revised development and test plan for the engine, now an all-ablative design.

• Apollo Program Review told that metabolic rate in an unpressurized suit twice that in clothes - . Nation: USA. Related Persons: Faget. Program: Apollo. Spacecraft: Apollo LM, LM ECS, LM Weight.

  At an Apollo Program Review held at MSC, Maxime A. Faget reported that Crew Systems Division had learned that the metabolic rate of a man walking in an unpressurized suit was twice that of a man in everyday clothes. When the suit was pressurized to 1.8 newtons per square centimeter (3.5 psi), the rate was about four times as much. To counteract this, a watercooled undergarment developed by the British Ministry of Aviation's Royal Aircraft Establishment was being tested at Hamilton Standard. These "space-age long johns" had a network of small tubes through which water circulated and absorbed body heat. Advantages of the system were improved heat transfer, low circulating noise levels, and relatively moderate flow rates required. An MSC study on integration of the suit with the LEM environmental control system showed a possible weight savings of 9 kilograms (20 pounds).

• Grumman reevaluated its testing concept for the Apollo LEM - . Nation: USA. Program: Apollo. Spacecraft: Apollo LM.

  Grumman received MSC's response to the "Project Christmas Present Report", and accordingly reevaluated its testing concept for the LEM. On February 19, the contractor proposed to ASPO Manager Joseph F. Shea a flight program schedule, which was tentatively approved. ASPO's forthcoming proposal was identical to Grumman's proposal. It called for 11 LEMs (which were now renumbered consecutively) and two flight test articles. All LEMs were to have full mission capability, but numbers one through three had to be capable of either manned or unmanned flight.

• Grumman to stop all work on the Apollo LEM Little Joe II program - . Nation: USA. Program: Apollo. Spacecraft: Apollo LM. MSC directed Grumman to stop all work on the LEM Little Joe II program. This action followed the ASPO Manager's decision against a testing program for the LEM comparable to that for the CSM..

• Apollo LEM to use an inertial reference system - . Nation: USA. Program: Apollo. Spacecraft: Apollo LM, LM Guidance.

  ASPO directed Grumman to provide an abort guidance system (AGS) in the LEM using an inertial reference system attached to the structure of the vehicle. Should the spacecraft's navigation and guidance system fail, the crew could use the AGS to effect an abort. Such a device eliminated the need for redundancy in the primary guidance system (and proved to be a lighter and simpler arrangement).

• Harness system for the Apollo LEM - . Nation: USA. Program: Apollo. Spacecraft: Apollo LM, LM Weight.

  NASA gave credit to two MSC engineers, George C. Franklin and Louie G. Richard, for designing a harness system for the LEM that enabled the crew to fly the vehicle from a standing position. Eliminating the seats reduced the LEM's weight and gave the crew better visibility and closer observation of controls and instruments.

• Studies on post-Apollo lunar exploration - . Nation: USA. Program: Apollo. Spacecraft: Apollo LM.

  MSC issued Requests for Proposals to more than 50 firms asking for studies and recommendations on how the lunar surface should be explored. Studies should show how lunar surveys could be performed and how points on the lunar surface might be located for future lunar navigation. Maximum use of equipment planned for the LEM and CM was expected. Part of the scientific apparatus aboard the LEM would be selenodetic equipment. The study would not include actual fabrication of hardware but might give estimates of cost and development times.

• Grumman subcontracts for engines for the Apollo LEM - . Nation: USA. Program: Apollo. Spacecraft: Apollo LM, LM Ascent Propulsion, LM Descent Propulsion.

  MSC gave its formal consent to two of Grumman's subcontracts for engines for the LEM: (1) With Bell Aerosystems for the ascent engine ($11,205,416 incentive-fee contract) (2) With Space Technology Laboratories for a descent engine to parallel that being developed by Rocketdyne ($18,742,820 fixed-fee contract).

• Apollo LEM's reaction control system propellant tank contract - . Nation: USA. Program: Apollo. Spacecraft: Apollo LM, LM RCS. Grumman completed negotiations with Bell Aerosystems Company for the LEM's reaction control system propellant tanks..

• Three tests on the Apollo CSM fuel cell - . Nation: USA. Program: Apollo. Spacecraft: Apollo LM, CSM Fuel Cell, LM Electrical.

  North American conducted three tests (4, 20, and 88 hours) on the CSM fuel cell. The third ended prematurely because of a sudden drop in output. (Specification life on the modules was 100 hours.)

  During this same week, Pratt and Whitney Aircraft tested a LEM-type fuel cell for 400 hours without shutdown and reported no leaks.

• Backup mode for the crew getting from the Apollo LEM back to the CM. - . Nation: USA. Program: Apollo. Spacecraft: Apollo LM, CSM Hatch, LM Crew Station.

  ASPO decided upon transfer through free space as the backup mode for the crew's getting from the LEM back to the CM if the two spacecraft could not be pressurized. North American had not designed the CM for extravehicular activity nor for passage through the docking tunnel in a pressurized suit. Thus there was no way for the LEM crew to transfer to the CM unless docking was successfully accomplished. ASPO considered crew transfer in a pressurized suit both through the docking tunnel and through space to be a double redundancy that could not be afforded.

• Weight and power tradeoff study on the Apollo LEM's radar systems - . Nation: USA. Program: Apollo. Spacecraft: Apollo LM, LM Guidance.

  RCA presented results of a weight and power tradeoff study on the LEM's radar systems, which were over Grumman's specification in varying amounts from 100 to 300 percent. RCA proposed that the accuracy requirements be relaxed to cope with this problem. MSC requested Grumman, on the basis of this report, to estimate a slippage in the schedule and the effects of additional weight and power.

• Contract on the Apollo LEM communications subsystem - . Nation: USA. Program: Apollo. Spacecraft: Apollo LM, LM Communications. Grumman and RCA signed a contract on the LEM communications subsystem..

• Design Engineering Inspection of the Apollo LEM timing equipment - . Nation: USA. Program: Apollo. Spacecraft: Apollo LM, LM Guidance. MSC conducted a Design Engineering Inspection of the LEM timing equipment at the Elgin National Watch Company..

• Capability of the Apollo LEM landing radar - . Nation: USA. Program: Apollo. Spacecraft: Apollo LM, LM Guidance.

  A joint Grumman, RCA, Ryan Aeronautical Company, ASPO, and Flight Crew Support Division (FCSD) meeting was held at Bethpage to review capability of the LEM landing radar to meet FCSD's requirements for ascent and for orbit circularization. A preliminary (unfunded) Ryan study (requested by ASPO earlier in the month) indicated some doubt that those accuracy requirements could be met. RCA advised that it would be possible to make these measurements with the rendezvous radar, if necessary. A large weight penalty, about 38 to 56 kilograms (84 to 124 pounds), would be incurred if the landing radar were moved from the descent to the ascent stage to become part of the abort guidance system. Adding this weight to the ascent stage would have to be justified either by improved abort performance or added crew safety. MSC authorized RCA and Ryan to study this problem at greater length. In the meantime, ASPO and FCSD would analyze weights, radar accuracies, and abort guidance performance capability.

• Study on the Apollo LEM ascent engine - . Nation: USA. Program: Apollo. Spacecraft: Apollo LM, LM Ascent Propulsion.

  The MSC Primary Propulsion Branch (PPB) completed a study on the current LEM ascent engine and performance that might be gained if the chamber pressure and characteristic exhaust velocity efficiency were increased. PPB also evaluated the use of hard versus soft chamber throats. A study by Bell Aerosystems Company had predicted a slightly lower performance than the MSC investigation (which estimated a drop of about six points below specification values if the current design were retained). PPB thought that specifications might be reached by increasing the chamber pressure to 82.7 newtons per square centimeter (120 psia) and the exhaust velocity efficiency to 97.3 percent, and by using a hard, rather than a soft, throat.

• Funds for scientific instruments for lunar exploration - . Nation: USA. Program: Apollo. Spacecraft Bus: Apollo LM. Spacecraft: Apollo ALSEP.

  MSC received an additional $1.035 million in Fiscal Year 1964 funds to cover development of equipment and operational techniques for scientific exploration of the moon:

  • Power supplies for long-life equipment to be installed on the lunar surface during Apollo missions.
  • Telemetry and Deep Space Instrumentation Facility requirements for this equipment.
  • Tools and materials needed for examining, packaging, and transporting lunar samples.
  • Cameras and film suitable for use on the moon by a space-suited astronaut.
  • Methods of obtaining and returning lunar samples without contaminating or changing them.
  • Techniques and instrumentation for geological mapping in the lunar environment.
  • Processes for obtaining water, hydrogen, and oxygen from indigenous material on the moon.
  Additionally, MSC would evaluate current techniques in seismology used to determine subsurface structural conditions.

• Common usage of Apollo ground support equipment (GSE) - . Nation: USA. Program: Apollo. Spacecraft: Apollo LM.

  Grumman and North American began working out ways for common usage of ground support equipment (GSE). Through informal meetings and telephone discussions, the two prime contractors agreed to a formal procedure for the GSE's use, maintenance, and training procedures.

• Yardney Electric selected for an auxiliary battery for the Apollo LEM - . Nation: USA. Program: Apollo. Spacecraft: Apollo LM, LM Electrical. Grumman completed negotiations with Yardney Electric Corporation for an auxiliary battery for the LEM. A contract would be awarded when size requirements were determined by Grumman and MSC..

• Apollo LEM propulsion as backup to the SM engine - . Nation: USA. Program: Apollo. Spacecraft: Apollo LM, LM RCS.

  North American was directed by NASA to study feasibility of using the LEM propulsion system as backup to the SM propulsion system. The most important item in the contractor's analysis was strength of the docking structure and its ability to withstand LEM main-engine and reaction control system thrusting.

• Kearfott to build the Apollo LEM rate gyro assembly - . Nation: USA. Program: Apollo. Spacecraft: Apollo LM, LM Guidance. Grumman completed negotiations with Kearfott Products Division, General Precision, Inc., for the LEM rate gyro assembly, and a contract was awarded later in the month..

• Pressure in the Apollo LEM's descent stage helium tank reduced - . Nation: USA. Program: Apollo. Spacecraft: Apollo LM, LM Weight. Primarily as a weight-saving measure, the gas storage pressure in the LEM's descent stage helium tank was reduced from 3,103 to 2,413 newtons per square centimeter (4,500 to 3,500 psia). This allowed the thickness of the tank wall to be reduced..

• Apollo LM weight saving program - . Nation: USA. Program: Apollo. Spacecraft: Apollo LM, LM Electrical, LM Weight. ASPO notified Grumman that certain items were no longer to be considered in the weight saving program: guidance and navigation components, drinking water tankage, scientific equipment, pyrotechnic batteries, among others..

• RCA to build the Apollo LEM lunar landing radar - . Nation: USA. Program: Apollo. Spacecraft: Apollo LM, LM Guidance. Ryan Aeronautical Company signed a contract with RCA for the LEM lunar landing radar. Ryan was instructed to design for altitudes of 21,300 meters (70,000 feet) and accuracies of 0.5 percent..

• Progress report on Apollo lunar surface experiments study - . Nation: USA. Program: Apollo. Spacecraft Bus: Apollo LM. Spacecraft: Apollo ALSEP.

  Texas Instruments, Inc., presented a progress report on their lunar surface experiments study to the MSC Lunar Surface Experiments Panel. Thus far, the company had been surveying and rating measurements to be made on the lunar surface. Areas covered included soil mechanics, mapping, geophysics, magnetism, electricity, and radiation. Equipment for gathering information, such as hand tools, sample return containers, dosimeters, particle spectrometers, data recording systems, seismometers, gravity meters, cameras, pentrometers, and mass spectrometers had been considered. The next phase of the study involved integrating and defining the measurements and instruments according to implementation problems, mission needs, lunar environment limitations, and relative importance to a particular mission. Texas Instruments would recommend a sequence for performing the experiments.

• Projected load growth for the Apollo LEM electrical power system - . Nation: USA. Program: Apollo. Spacecraft: Apollo LM, LM Electrical.

  Grumman reported to MSC the current load status and projected load growth for the LEM's electrical power system, requesting a mission profile of 121 kilowatt-hours total energy. The company also presented its latest recommendation for the LEM power generation subsystem configuration: two 900-watt fuel cells, a descent stage peaking battery, an ascent stage survival battery, and four cryogenic storage tanks. To compensate for voltage drops in the power distribution subsystem, Grumman recommended that two cells be added to the current fuel cell stack; however, on March 23 ASPO directed the contractor to continue development of the 900-watt, three-fuel-cell assembly and a five-tank cryogenic storage system. MSC's position derived from the belief that the load growth would make the two-cell arrangement inadequate. Also the three-cell configuration, through greater redundancy, afforded greater safety and chances of mission success: the mission could continue in spite of a failure in one of the cells; should two cells fail, the mission could be aborted on the final power source. The cryogenic tanks should be sized for a usable total energy of 121 kilowatt-hours to permit immediate tank procurement.

• Apollo missions defined - . Nation: USA. Program: Apollo. Spacecraft: Apollo LM, CSM Heat Shield.

  OMSF outlined launch vehicle development, spacecraft development, and crew performance demonstration missions, using the Saturn IB and Saturn V:

  1. Launch vehicle and unmanned CSM (at least two flights planned).
  2. CSM long-duration.
  3. CSM and LEM (two flights planned).
  4. Launch vehicle and heatshield (at least two flights).
  5. Lunar mission simulation.
  6. Lunar exploration.
  Missions (1) through (3) would use the Saturn IB and (4) through (6) the Saturn V. Additional launch vehicles and spacecraft would be provided for contingency or repeated flights. If necessary, repeat flights could provide additional crew training.

• Apollo LEM mockup TM-1 inspection and review - . Nation: USA. Program: Apollo. Spacecraft: Apollo LM, LM Hatch.

  The first formal inspection and review of the LEM test mockup TM-1 was held at Grumman. TM-1 allowed early assessment of crew mobility, ingress, and egress. It was a full-size representation of crew stations, support and restraint systems, cabin equipment arrangement, lighting, display panels and instrument locations, and hatches. The TM-1 evaluation became the basis for the final LEM mockup, TM-5, from which actual hardware fabrication would be made. Additional Details: here....

• LLRV's shipped to NASA - . Nation: USA. Spacecraft Bus: Apollo LM. Spacecraft: Apollo LLRV. The two LLRV's were shipped from Bell to the NASA FRC, with program emphasis on vehicle No. 1. It was first readied for captured flight on a tilt table constructed at the FRC to test the engines without actually flying..

• Revisions to Apollo's communications requirements - . Nation: USA. Program: Apollo. Spacecraft: Apollo LM, LM Communications, LM Guidance.

  The MSC Operations Planning Division (OPD) reviewed recent revisions by OMSF to Apollo's communications requirements:

  • Elimination of the requirement for continuous tracking of the spacecraft during translunar injection
  • Sequential rather than simultaneous transmission of data from the ground to the two spacecraft (to be compatible with the Manned Space Flight Network)
  • A five-kilometer (three-nautical-mile) communications range on the lunar surface (to be compatible with the design of the portable life support system)
  • Elimination of the requirement for direct transmission to the CSM from an extravehicular astronaut; instead, such transmission would be relayed via the LEM.
  Thus were resolved, OPD reported, a number of conflicting items (i.e., incompatibilities between OMSF's requirements and the capabilities of the two spacecraft). Two other items that OMSF made into firm requirements were already compatible with the design of the spacecraft:
  1. A radar in the CSM capable of tracking the LEM (provided the LEM had a compatible transponder)
  2. Three-way communications between an astronaut on the moon, his fellow crewman inside the LEM, and with mission control.

• Static firing of the Apollo LEM descent engine - . Nation: USA. Program: Apollo. Spacecraft: Apollo LM, LM Descent Propulsion. Space Technology Laboratories (STL) began using its new San Juan Capistrano, Calif., test facility to static fire the firm's LEM descent engine. Hereafter, the bulk of STL's development firings were made at this site..

• Contract to AiResearch for design of cryogenic tank assemblies for Apollo LEM fuel cells - . Nation: USA. Program: Apollo. Spacecraft: Apollo LM, LM Electrical. Grumman issued a letter contract to AiResearch Manufacturing Company to start design of cryogenic tank assemblies for the LEM fuel cells. AiResearch received the formal contract on June 23..

• First of two Apollo lunar landing research vehicles completed - . Nation: USA. Program: Apollo. Spacecraft Bus: Apollo LM. Spacecraft: Apollo LLRV. Bell Aerosystems Company completed the first of two lunar landing research vehicles, to be delivered to the NASA Flight Research Center for testing..

• Specific instructions on insulating wiring in the Apollo LEM - . Nation: USA. Program: Apollo. Spacecraft: Apollo LM, LM Electrical.

  ASPO gave Grumman specific instructions on insulating wiring in the LEM: Teflon-insulated wiring was mandatory in a pure oxygen atmosphere. If the standard-thickness Teflon insulation was too heavy, a thin- wall Teflon-insulated wiring with abrasion-resistant coating should be considered. Teflon-insulated wiring should also be used outside the pressurized cabin, wherever that wiring was exposed. Any approved spacecraft insulation could be used within subsystem modules which were hermetically sealed in an inert gas atmosphere or potted within the case.

• Flight attitude indicator and associated equipment for the Apollo LEM approved - . Nation: USA. Program: Apollo. Spacecraft: Apollo LM, LM Crew Station. ASPO gave Grumman a go-ahead on procurement of the flight attitude indicator ("8-ball") and associated equipment for the LEM..

• Apollo LEM environmental control system water management configuration study - . Nation: USA. Program: Apollo. Spacecraft: Apollo LM, LM ECS.

  Grumman completed an environmental control system water management configuration study and concluded that a revised design would significantly improve the probability of mission success and crew safety. This design would combine water tanks for the water management functions into one easily accessible package.

• Demonstration of space suits using the LEM TM-1 mockup - . Nation: USA. Program: Apollo. Spacecraft: A7L, Apollo LM, LM Hatch.

  MSC Crew Systems Division representatives attended a demonstration at Grumman of Apollo Phase B and Gemini space suits using the LEM TM-1 mockup and a mockup portable life support system. Tests demonstrated ingress egress capability through the forward and top hatches, operation of controls and displays, and methods of getting out on the lunar surface and returning to the spacecraft. Generally, the A7L Space Suit proved sufficiently mobile for all these tasks, though there was no great difference between its performance and that of the Gemini suit during these trials.

• Manned Apollo LEM drop tests - . Nation: USA. Program: Apollo. Spacecraft: Apollo LM, LM Structural.

  Grumman conducted manned drop tests to determine the LEM crew's ability to land the spacecraft from a standing position. All tests were run with the subject in an unpressurized suit in a "hands off" standing position with no restraint system or arm rests.

• First firing of a prototype thrust chamber for Apollo LEM descent engine - . Nation: USA. Program: Apollo. Spacecraft: Apollo LM, LM Descent Propulsion. Rocketdyne conducted the first firing of the prototype thrust chamber assembly for its LEM descent engine..

• Grumman redesigned Apollo LEM environmental control system to use PLSS cartridges for emergencies - . Nation: USA. Program: Apollo. Spacecraft: A7L, Apollo LM, LM ECS.

  Grumman redesigned the LEM environmental control system to incorporate a replaceable lithium hydroxide cartridge with a portable life support system cartridge in parallel for emergency backup. The LEM cartridge would be replaced once during a two-day mission.

  Also MSC advised Grumman that estimates of the metabolic rates for astronauts on the lunar surface had been increased. The major effect of this change was an increase in the requirements for oxygen and water for the portable life support system.

• Deletion of the Apollo LEM's front docking capability - . Nation: USA. Related Persons: See, White. Program: Apollo. Spacecraft: Apollo LM, LM Ascent Propulsion, LM Descent Propulsion, LM ECS, LM Hatch.

  Representatives from a number of elements within MSC (including systems and structural engineers, advanced systems and rendezvous experts, and two astronauts, Edward H. White II and Elliot M. See, Jr.) discussed the idea of deleting the LEM's front docking capability (an idea spawned by the recent TM-1 mockup review). Rather than nose-to-nose docking, the LEM crew might be able to perform the rendezvous and docking maneuver, docking at the spacecraft's upper (transfer) hatch, by using a window above the LEM commander's head to enable him to see his target. Additional Details: here....

• Apollo manual abort simulations - . Nation: USA. Program: Apollo. Spacecraft: Apollo LM, LM Simulator. To train astronauts in various mission procedures, LTV had completed simulations of manual abort and, within a week, would be able to conduct simulated final maneuver phases of a rendezvous..

• Apollo Logistic Support System Office investigates extensions of Apollo hardware. - . Nation: USA. Spacecraft Bus: Apollo LM. Spacecraft: Apollo LM Truck.

  The recent creation of the Apollo Logistic Support System Office in Washington prompted the formal investigation of a variety of extensions of Apollo hardware to achieve greater scientific and exploratory dividends from Apollo hardware. Director of Special Manned Space Flight Studies William B. Taylor suggested to William E. Stoney and others in Houston that Grumman receive a study contract to investigate possible modifications to the lunar excursion module (LEM) to create a LEM truck (concepts which the company had already investigated preliminarily on an in-house basis). The time was appropriate, Taylor said, for more intensive and formal efforts along these lines.

• Ground rules for lunar excursion module guidance and control system firmly defined - . Nation: USA. Program: Apollo. Spacecraft: Apollo LM, LM Guidance. Ground rules for lunar excursion module guidance and control system firmly defined..

• Plan for testing the Apollo LEM rendezvous and landing radar - . Nation: USA. Program: Apollo. Spacecraft: Apollo LM, LM Guidance.

  Representatives from Grumman Aircraft Engineering Corporation, North American Aviation, Inc., and Massachusetts Institute of Technology's (MIT) Instrumentation Laboratory, three of the Manned Spacecraft Center's (MSC) principal contractors, met with radar and guidance and navigation experts from Houston and Cape Kennedy. They formulated a detailed plan for testing and checkout of the lunar excursion module (LEM) rendezvous and landing radar systems both at the factory and at the launch site.

• Auxiliary battery for the Apollo LEM recommended - . Nation: USA. Program: Apollo. Spacecraft: Apollo LM, LM Electrical.

  On the basis of new abort criteria (failure of one fuel cell), extended operating periods, and additional data on fuel cell performance, Grumman recommended a 20.4 kg (45-lb), 1,800 watt-hour auxiliary battery for the LEM. MSC approved the recommendation and Grumman completed the redesign of the electrical power distribution system and resizing of the battery during late October and early November.

• Formal review of the Apollo LEM mockup M-5 - . Nation: USA. Related Persons: Faget, Kraft, Slayton. Program: Apollo. Spacecraft: Apollo LM, LM Ascent Propulsion, LM Descent Propulsion, LM Electrical, LM Landing Gear.

  NASA conducted a formal review of the LEM mockup M-5 at the Grumman factory. This inspection was intended to affirm that the M-5 configuration reflected all design requirements and to definitize the LEM configuration. Members of the Mockup Review Board were Chairman Owen E. Maynard, Chief, Systems Engineering Division, ASPO; R. W. Carbee, LEM Subsystem Project Engineer, Grumman; Maxime A. Faget, Assistant Director for Engineering and Development, MSC; Thomas J. Kelly, LEM Project Engineer, Grumman; Christopher C. Kraft, Jr. (represented by Sigurd A. Sjoberg), Assistant Director for Flight Operations, MSC; Owen G. Morris, Chief, Reliability and Quality Assurance Division, ASPO; William F. Rector III, LEM Project Officer, ASPO; and Donald K. Slayton, Assistant Director for Flight Crew Operations, MSC.

  The astronauts' review was held on October 5 and 6. It included demonstrations of entering and getting out of the LEM, techniques for climbing and descending the ladder, and crew mobility inside the spacecraft. The general inspection was held on the 7th and the Review Board met on the 8th. Those attending the review used request for change (RFC) forms to propose spacecraft design alterations. Before submission to the Board, these requests were discussed by contractor personnel and NASA coordinators to assess their effect upon system design, interfaces, weight, and reliability.

  The inspection categories were crew provisions; controls, displays, and lighting; the stabilization and control system and the guidance and navigation radar; electrical power; propulsion (ascent, descent, reaction control system, and pyrotechnics ; power generation cryogenic storage and fuel cell assemblies ; environmental control; communications and instrumentation; structures and landing gear; scientific equipment; and reliability and quality' control. A total of 148 RFCs were submitted. Most were aimed at enhancing the spacecraft's operational capability; considerable attention also was given to quality and reliability and to ground checkout of various systems. No major redesigns of the configuration were suggested.

  As a result of this review, the Board recommended that Grumman take immediate action on those RFC's which it had approved. Further, the LEM contractor and MSC should promptly investigate those items which the Board had assigned for further study. On the basis of the revised M-5 configuration, Grumman could proceed with LEM development and qualification. This updated mockup would be the basis for tooling and fabrication of the initial hardware as well.

• Contract for the Apollo LEM attitude translation control assembly - . Nation: USA. Program: Apollo. Spacecraft: Apollo LM, LM Communications, LM Guidance, LM RCS.

  Radio Corporation of America's (RCA) Aerospace Systems Division received a 9 million contract from Grumman for the LEM attitude translation control assembly (ATCA). The ATCA, a device to maintain the spacecraft's attitude, would fire the reaction control system motors in response to signals from the primary guidance system.

• Configuration established of the reaction control system engines - . Nation: USA. Program: Apollo. Spacecraft: Apollo LM, CSM Block I, LM RCS.

  MSC established the configuration of the reaction control system engines for both the service module (SM) and the LEM, and informed North American and Grumman accordingly. The Center also directed North American to propose a design for an electric heater that would provide thermal control in lunar orbit and during contingency operations. The design would be evaluated for use in Block I spacecraft as well.

• Weight of the Apollo LEM rendezvous radar 319.8 kg - . Nation: USA. Program: Apollo. Spacecraft: Apollo LM, LM Guidance. RCA reduced the weight of the LEM rendezvous radar from 39.9 to 31.98 kg (88 to 70.5 lbs)..

• Electroluminescent lighting on the Apollo LEM for Block II CMs - . Nation: USA. Program: Apollo. Spacecraft: Apollo LM, CSM Block II, LM Crew Station. North American representatives visited the Grumman plant to discuss design features and to inspect the electroluminescent lighting on the LEM. North American intended to adopt this same feature on Block II CMs..

• Weight reduction program for the Apollo LEM - . Nation: USA. Program: Apollo. Spacecraft: Apollo LM, LM Weight.

  NASA and Grumman representatives discussed a weight reduction program for the LEM. Changes approved at the M-5 mockup review portended an increase in LEM separation weight of from 68 to 453 kg (150 to 1,000 lbs). Both parties agreed to evaluate the alternatives of either resizing the spacecraft or finding ways to lighten it about nine percent, thus keeping the improved LEM within the present control weight.

• Selection of Airite to supply the Apollo LEM helium tanks - . Nation: USA. Program: Apollo. Spacecraft: Apollo LM, LM Descent Propulsion. NASA approved Grumman's selection of Airite to supply the LEM helium tanks, and the two firms started negotiations..

• Contract with Arma for the Apollo LEM caution and warning electronics assembly - . Nation: USA. Program: Apollo. Spacecraft: Apollo LM, LM Crew Station. Grumman completed contract negotiations with Arma Division, American Bosch Arma Corporation, for the LEM caution and warning electronics assembly..

• Self-luminous materials found them feasible for use in Apollo LEM docking lighting - . Nation: USA. Program: Apollo. Spacecraft: Apollo LM, LM Crew Station. Grumman lighting experts evaluated self-luminous materials produced by the Minnesota Mining and Manufacturing Company and found them feasible for use in docking lighting..

• Apollo CSM-LM active docking interfaces discussed - . Nation: USA. Program: Apollo. Spacecraft: Apollo LM, CSM RCS, LM RCS.

  At a North American-Grumman interface meeting on September 23-24, two possible relative role alignments for CSM-active docking were agreed upon. The major item blocking final selection was the effect of the SM's reaction control system engines upon the LEM antennas. ASPO requested Grumman to investigate the problem, to analyze the design penalties of the two-attitude docking mode, and to report any other factors that would influence the final attitude selection.

• Apollo LEM guidance and navigation ground rules for the coasting phase of the mission - . Nation: USA. Program: Apollo. Spacecraft: Apollo LM, CSM Guidance, LM Guidance.

  MSC notified Grumman of several additional LEM guidance and navigation ground rules that were applicable to the coasting phase of the mission. During this portion of the flight, the LEM abort guidance system must be capable of giving attitude information and of measuring velocity changes. Navigational data required to take the LEM out of the coasting phase and to put it on an intercept course with the CSM would be provided by the CSM's rendezvous radar and its guidance and navigation system, and through the Manned Space Flight Network back on earth.

• Elimination of propellant dispersal systems for the Apollo SM and LEM accepted by USAF - . Nation: USA. Program: Apollo. Spacecraft: Apollo LM, CSM SPS.

  The Air Force Eastern Test Command concurred in the elimination of propellant dispersal systems for the SM and the LEM. Costs, schedules, and spacecraft designs, NASA felt, would all benefit from this action. ASPO thus notified the appropriate module contractors.

• Apollo LM fuel cell assembly thermal study - . Nation: USA. Program: Apollo. Spacecraft: Apollo LM, LM Electrical.

  Grumman completed the fuel cell assembly thermal study and was preparing a specific directive to Pratt and Whitney Aircraft Company which would incorporate changes recommended by the study. These changes would include the cooling of electrical components with hydrogen and the shifting of other components (water shutoff valves, and oxygen purge valve) so that they would operate at their higher design temperatures.

• Remote operation of the Apollo CSM's rendezvous radar transponder and SCS not necessary - . Nation: USA. Program: Apollo. Spacecraft: Apollo LM, CSM Docking, LM Guidance.

  Remote operation of the CSM's rendezvous radar transponder and its stabilization and control system (SCS) was not necessary, ASPO told North American. Should the CSM pilot be incapacitated, it was assumed that he could perform several tasks before becoming totally disabled, including turning on the transponder and the SCS. No maneuvers by the CSM would be required during this period. However, the vehicle would have to be stabilized during LEM ascent, rendezvous, and docking.

• Consequences of eliminating the Apollo CSM rendezvous radar - . Nation: USA. Program: Apollo. Spacecraft: Apollo LM, CSM Guidance, LM Descent Propulsion, LM Guidance.

  MSC's Systems Engineering Division reported on the consequences of eliminating the command and service module (CSM) rendezvous radar:

  Coasting period:

  During this phase of the mission, the rendezvous radar on the CSM would be used to track the LEM and the rendezvous radar on the LEM would be used to track the CSM. With the use of Mission Control through the Manned Space Flight Network (MSFN), three sources of information could be used as a vote for guidance system monitoring. Without the CSM rendezvous radar, the monitoring task would become more difficult; however, this was not to imply that it was impossible. The conclusion was that CSM rendezvous radar was highly desirable, but not absolutely necessary.

  Lunar descent and ascent:

  During powered flight, the CSM would be tracking the LEM. This was desirable because if the LEM guidance computer (LGC) failed, it was very doubtful that the astronauts could manually acquire radar lock-on with the CSM. Also, if the LEM rendezvous radar failed, CSM lock-on would be highly desirable. There were several alternative solutions to this problem. First of all, Mission Control through the MSFN could relieve the problem. If this did not satisfy all requirements, it was possible for the LEM rendezvous radar to track the CSM during powered descent and ascent. If the LGC then failed, the tracking acquisition would no longer be a problem. In summary, there did appear to be other ways of fulfilling the functions of the CSM rendezvous radar during the powered phases.

  Lunar surface:

  While the LEM was on the lunar surface, it would be tracked with the CSM rendezvous radar in order to update launch conditions. This could be accomplished by the LEM tracking the CSM and the MSFN.

  Rendezvous:

  This was the most critical phase for the use of the rendezvous radar on the CSM. If the LEM primary guidance system should fail (i.e., the LGC, inertial measurement unit (IMU), and LEM rendezvous radar), navigation information for long-range midcourse corrections would be provided by the rendezvous radar on the CSM. The MSFN, however, could supply this information. The terminal rendezvous maneuver would become a problem if the LEM rendezvous radar failed and there was not a rendezvous radar on the CSM. It had not been established that the MSFN could supply the required terminal rendezvous information. If MSFN could, a restricted mission profile would have to be employed. There were other methods of supplying terminal rendezvous information such as optical tracking. The scanning telescope or sextant on the CSM could be used with the IMU and Apollo guidance computer on the CSM to derive navigation information, meaning that the LEM would require flashing lights. There was a delta-V penalty associated with using angle-only information in place of range range rate and angle information, its importance depending on the accuracy of the angle data and the range/range rate data.

• Joint MSC-Grumman meeting on Apollo LEM communications - . Nation: USA. Program: Apollo. Spacecraft: Apollo LM, LM Communications.

  A number of outstanding points were resolved at a joint MSC-Grumman meeting on LEM communications. Most significant, the VHF key mode was deleted, and it was decided that, during rendezvous, voice links must have priority over all other VHF transmissions. Further, the echo feature of the current configuration (i.e., voice sent to the LEM by the ground operational support system, then relayed back via the S-band link) was undesirable.

• Decisions on Apollo crew transfer and space suit procedures - . Nation: USA. Program: Apollo. Spacecraft: A7L, Apollo LM, LM ECS.

  Representatives from the MSC Astronaut Office, and ASPO's Systems Engineering, Crew Systems, and Mission Planning divisions made several significant decisions on crew transfer and space suit procedures:

  • Crew transfer, both pressurized and unpressurized, would be accomplished using the environmental control system umbilicals. The CM and LEM umbilicals would be designed accordingly. Crew Systems would request the necessary engineering changes.
  • The requirement for "quick-don" capability for the space suit would be reevaluated by Systems Engineering people. If the probability of a rapid decompression of the spacecraft during "noncritical" mission phases was negligible, "quick-don" capability might be eliminated. This would ease several design constraints on the suit.
  • The question of a crossover valve in the CM, for ventilation during open-faceplate operation, was postponed pending the decompression study and ventilation tests at Hamilton Standard.

• Problem of Apollo CSM stabilization if the crewman disabled - . Nation: USA. Program: Apollo. Spacecraft: Apollo LM, CSM Docking, LM Guidance.

  In a letter on August 25, 1964, the LEM Project Office had requested Grumman to define the means by which CSM stabilization and rendezvous radar transponder operation could be provided remotely in the event the CSM crewman was disabled.

  In another letter on October 16, the Project Office notified Grumman that no requirement existed for remote operation of either the rendezvous radar transponder or the stabilization and control system. The letter added, however, that the possibility of an incapacitated CSM astronaut must be considered and that for design purposes Grumman should assume that the astronaut would perform certain functions prior to becoming completely disabled. These functions could include turning on the transponder and the SCS. No CSM maneuvers would be required during the period in which the CSM astronaut was disabled but the CSM must remain stabilized during LEM ascent coast and rendezvous and docking phases.

• Work stopped on Apollo LTA 10 - . Nation: USA. Program: Apollo. Spacecraft: Apollo LM. MSC ordered Grumman to halt work on the LEM test article (LTA) 10. The LTA-10's descent stage would be replaced with one cannibalized from LEM test mockup 5..

• ASPO deleted the requirement for Apollo LEM checkout during the translunar phase of the mission - . Nation: USA. Program: Apollo. Spacecraft: Apollo LM, CSM ECS.

  ASPO deleted the requirement for LEM checkout during the translunar phase of the mission. Thus the length of time that the CM must be capable of maintaining pressure in the LEM (for normal leakage in the docked configuration) was reduced from 10 hours to three.

• Trajectory summary of Apollo Design Reference Mission sent to Grumman - . Nation: USA. Program: Apollo. Spacecraft: Apollo LM, LM Weight.

  The trajectory summary of the Design Reference Mission (DRM) prepared by the Apollo Mission Planning Task Force was sent to Grumman by the LEM Project Office with a note that the operational sequence-of-events would be forwarded in November.

  It was acknowledged that a single mission could not serve to "completely define all the spacecraft functional requirements" but "such a mission has considerable value as a standard for various purposes on the Apollo Program."

  Specifically, the DRM would be used for weight reporting, electrical power reporting, reliability modeling, engineering simulation, crew task analyses, mission-related Interface Control Documents, and trade-off studies.

• Single-point failures that would cause loss of crew during an Apollo mission - . Nation: USA. Program: Apollo. Spacecraft: Apollo LM. ASPO requested Grumman to list all single-point failures that would cause loss of the crew during a lunar orbit rendezvous mission. Grumman was to consider only the equipment that it was responsible for..

• Apollo drops the buddy system concept - . Nation: USA. Program: Apollo. Spacecraft: A7L, Apollo LM, CSM ECS, LM ECS.

  Because of the redesign of the portable life support system that would be required, MSC directed Grumman and North American to drop the "buddy system" concept for the spacecraft environmental control system (ECS) umbilicals. The two LEM crewmen would transfer from the CM while attached to that module's umbilicals. Hookup with the LEM umbilicals, and ventilation from the LEM ECS, would be achieved before disconnecting the first set of lifelines. MSC requested North American to cooperate with Grumman and Hamilton Standard on the design of the fetal end of the umbilicals. Also, the two spacecraft contractors were directed jointly to determine umbilical lengths and LEM ECS control locations required for such transfer.

• Testing of the first flight-weight Apollo LEM fuel cell - . Nation: USA. Program: Apollo. Spacecraft: Apollo LM, LM Electrical.

  Testing of the first flight-weight 15-cell stack of the LEM fuel cell assembly began. Although the voltage was three percent below design, the unit had a 980-watt capability. Earlier, the unit completed 150 hours of operation, and single cell life had reached 662 hours.

• Tests on the welding of the Apollo LEM cabin's thin-gauge aluminum alloy - . Nation: USA. Program: Apollo. Spacecraft: Apollo LM, LM ECS.

  Grumman reported to MSC the results of development tests on the welding of the LEM cabin's thin-gauge aluminum alloy. The stress and corrosion resistance of the metal, Grumman found, was not lessened by environments of pure oxygen, varying temperatures, and high humidity.

• Apollo hard shell meteoroid garment - . Nation: USA. Program: Apollo. Spacecraft: A7L, Apollo LM.

  The MSC Meteoroid Technology Branch inspected a hard shell meteoroid garment built by the Center's Crew Systems Division. It was only a crude prototype, yet it in no way hampered mobility of the pressurized suit. The Meteoroid Technology people were satisfied that, should a hard garment be necessary for protection of the Apollo extravehicular mobility unit, this concept was adequate. The garment might present stowage problems, however, and investigations were underway to determine the minimum area in the LEM that would be required.

• LLRV first flight - . Nation: USA. Spacecraft Bus: Apollo LM. Spacecraft: Apollo LLRV.

  Initial tests were from the old South Base area of Edwards. Research pilot Joe Walker flew it three times for a total of just under 60 seconds to a peak altitude of ten ft (3 m). Later flights were shared between Walker; another Center pilot, Don Mallick; the Army's Jack Kleuver; and NASA Manned Spacecraft Center, Houston, pilots Joseph Algranti and H.E. 'Bud' Ream.

• Apollo LEM environmental control system (ECS) umbilical arrangements - . Nation: USA. Program: Apollo. Spacecraft: Apollo LM, LM ECS.

  MSC spelled out additional details of the LEM environmental control system (ECS) umbilical arrangements. The hoses were to be permanently bonded to the ECS; a crossover valve, to permit flow reversal, was mandatory; and a bypass relief would be added, if necessary, to prevent fan surge. Grumman was to coordinate with North American to ensure that all umbilicals were long enough for crew transfer and to determine the optimum location for the spacecraft's ECS switches.

• Battery charger for Apollo LEM - . Nation: USA. Program: Apollo. Spacecraft: Apollo LM, CSM Electrical, LM Electrical. MSC authorized Grumman to proceed with procurement of a battery charger for the LEM, to replenish the portable life support system's power source. On the following day, Houston informed North American such a device was no longer needed in the CSM..

• Coverage requirements for Apollo LEM's S-band radio reviewed - . Nation: USA. Program: Apollo. Spacecraft: Apollo LM, LM Communications.

  Engineers from Grumman and the MSC Instrumentation and Electronics Systems Division (IESD) reviewed the coverage requirements for the LEM's S-band radio and the incompatibility of those requirements with the present location of the steerable antenna. Most observers felt that a deployable boom was the only feasible solution. The two groups therefore recommended that IESD verify with ASPO the S-band coverage requirements and that Grumman analyze the design effects of such a boom. In the meantime, Dalmo-Victor, the antenna vendor, should continue its design effort on the basis of the current location.

• All-battery electrical power system for the Apollo LEM - . Nation: USA. Program: Apollo. Spacecraft: Apollo LM, LM Electrical.

  ASPO officials completed a preliminary evaluation of the design and weight implications of an all-battery electrical power system (EPS) for the LEM. Investigators reviewed those factors that resulted in the decision (in March 1963) to employ fuel cells; also, they surveyed recent technological improvements in silver-zinc batteries.

  At about the same time, Grumman was analyzing the auxiliary battery requirements of the spacecraft. The contractor found that, under the worst possible conditions (i.e., lunar abort), the LEM would need about 1,700 watt-hours of auxiliary power. Accordingly, Grumman recommended one 1,700 watt-hour or two 850 watt-hour batteries (23 and 29.5 kg (50 and 65 lbs), respectively) in the spacecraft's ascent stage.

• All major Apollo LEM subcontracts issued - . Nation: USA. Program: Apollo. Spacecraft: Apollo LM.

• Significant milestones for the Apollo LEM planned - . Nation: USA. Program: Apollo. Spacecraft: Apollo LM, LM Structural.

  NASA anticipated five significant milestones for the LEM during the forthcoming year:

  1. A major review of the entire LEM program (with especial emphasis upon the fiscal picture for 1965 and 1966)
  2. Start of production on LEM-1 (the first LEM flight article)
  3. Delivery of LEM Test Article (LTA)-2 (a dynamic test article) to Huntsville
  4. Start of vibration and static testing on the complete LEM structure
  5. Sea level and altitude qualification testing in the continuing development of the LEM's propulsion systems.

• Apollo LEM LTA-10 test program reviewed - . Nation: USA. Program: Apollo. Spacecraft: Apollo LM, LM Structural.

  MSC's Structures and Mechanics Division and ASPO reviewed the LTA-10 test program to resolve the stop-work imposed upon Grumman. The review resulted in an agreement to have LTA-10 remain in the program with a modified configuration. LTA-10 would be used by North American at Tulsa, Oklahoma, for adapter/LEM modal and separation testing and would consist only of descent stage structure. Subsystems for LTA-10 which were eliminated were the ascent stage, landing gear, ascent propulsion and descent propulsion.

• Shorting a problem in the Apollo LEM fuel cells - . Nation: USA. Program: Apollo. Spacecraft: Apollo LM, LM Electrical. Shorting had become a significant problem in the LEM fuel cells, and exemplified the continuing difficulties that plagued the system's development..

• Program to resize the Apollo LEM - . Nation: USA. Program: Apollo. Spacecraft: Apollo LM, LM Electrical.

  MSC analyzed Grumman's report on their program to resize the LEM. On the basis of this information, ASPO recommended that the propellant tanks be resized for separation and lunar liftoff weights of 14,742 and 4,908 kg (32,500 and 10,820 lbs), respectively. Studies should investigate the feasibility of an optical rendezvous device and the substitution of batteries for fuel cells. And finally, engineering managers from both Grumman and MSC should examine a selected list of weight reduction changes to determine whether they could immediately be implemented.

• Apollo LLRV first successful flight - . Nation: USA. Program: Apollo. Spacecraft Bus: Apollo LM. Spacecraft: Apollo LLRV.

  NASA test pilot Joseph A. Walker flew the LLRV for the second time. The first attempted liftoff, into a 9.26-km (5-nm) breeze, was stopped because of excessive drift to the rear. The vehicle was then turned to head downwind and liftoff was accomplished. While airborne the LLRV drifted with the wind and descent to touchdown was accomplished. Touchdown and resulting rollout (at that time the vehicle was on casters) took the LLRV over an iron-door-covered pit. One door blew off but did not strike the vehicle.

• Apollo inflight metabolic simulator - . Nation: USA. Program: Apollo. Spacecraft: Apollo LM, CSM ECS, LM ECS.

  Crew Systems Division (CSD) was proceeding with procurement of an inflight metabolic simulator in response to a request by Systems Engineering Division. The simulator would be used to support the LEM mission for SA-206 and would be compatible for use in the CM. Responsibility for the project had been assigned to the Manager of the LEM Environmental Control System Office. It was projected that the Statement of Work would be completed by January 15, 1965; the proposals evaluated by April 1; the contract awarded by June 1, 1965; the prototype delivered by April 1, 1966, with two qualified simulator deliveries by July 1, 1966.

• Radioisotope generators considered for Apollo lunar surface experiments - . Nation: USA. Program: Apollo. Spacecraft: Apollo LM, LM Electrical.

  MSC was giving serious thought to using radioisotope generators to power the Apollo lunar surface experiments packages. If some method could be found to control waste heat, such a device would be the lightest source of power available. Accordingly, the Center asked Grumman to study the feasibility of incorporating it into the LEM's scientific payload. The company should analyze thermal and radiological problems, as well as methods of stowage, together with the possibility of using the generator for power and heat during the flight. To minimize the problem of integration, Grumman was allowed much flexibility in designing the unit. Basically, however, it would measure about 0.07 cu m (2.5 cu ft) and would weigh between 13 and 18 kg (30 and 40 lbs). Its energy source (plutonium 238) would produce about 50 watts of electricity (29 volts, direct current).

• Alignment agreed for the two Apollo spacecraft during docking maneuvers - . Nation: USA. Program: Apollo. Spacecraft: Apollo LM, CSM Cockpit, LM Crew Station. North American and Grumman agreed on the alignment of the two spacecraft during docking maneuvers: the LEM's overhead window would be aligned with right-hand docking window of the CM..

• Redesigned landing gear on the resized Apollo LEM - . Nation: USA. Program: Apollo. Spacecraft: Apollo LM, LM Landing Gear.

  To ensure that the redesigned landing gear on the resized LEM would be consistent with earlier criteria, MSC sent to Grumman revisions to those design criteria:

  • Maximum rate of descent - 3.05 m (10 ft) per sec
  • Maximum horizontal velocity - 1.22 m (4 ft) per sec
  • Maximum attitude rates (any axis) - 3 degrees per sec

• Flights evaluate removal of scientific packages from the Apollo LEM - . Nation: USA. Program: Apollo. Spacecraft: Apollo LM.

  In flights that simulated the moon's gravity, MSC technicians evaluated the astronaut's ability to remove scientific packages from the descent stage of the LEM. They affirmed the relative ease with which large containers (about 0.226 cu m (8 cu ft) and weighing 81.65 kg (180 lbs)) could be extracted and carried about.

• Problem with thrust buildup time for the Apollo LEM ascent engine - . Nation: USA. Program: Apollo. Spacecraft: Apollo LM, LM Ascent Propulsion.

  The current thrust buildup time for the LEM ascent engine was 0.3 second. To avoid redesigning the engine valve-which was already the pacing item in the ascent engine's development - MSC directed Grumman simply to change the specification value from 0.2 to 0.3 second.

  At the same time, engineers at the Center began studying ways to increase the engine's thrust. Because of the LEM's weight gains, the engine must either be uprated or it would have to burn longer. Preliminary studies showed that, by using a phase "B" chamber (designed for a chamber pressure of 689.5 kilonewtons per sq m (100 psia)), thus producing chamber pressure of about 792.9 kilonewtons (115 psia), the thrust could be increased from 1,587 to 1,814 kg (3,500 to 4,000 lbs). Moreover, this could be accomplished with the present pressurization and propellant feed systems.

• Apollo LEM subsystem test logic - . Nation: USA. Program: Apollo. Spacecraft: Apollo LM.

  MSC and Grumman representatives reviewed individual subsystem test logics for the LEM and agreed on test logic and associated hardware requirements for the entire subsystem development. Agreement was also reached on the vehicle ground test program which Grumman proposed to implement with their respective subcontractors during December. Cost and effort associated with the revised program would be jointly reviewed by MSC and Grumman during January and February 1965.

• Prototype for a lunar sample return container - . Nation: USA. Program: Apollo. Spacecraft: Apollo LM.

  MSC asked Grumman to design and fabricate a prototype for a lunar sample return container. This effort would explore handling procedures and compatibility with both spacecraft. Concurrently, the Center's Advanced Spacecraft Technology Division was studying structural and packaging requirements for such a container.

• Ground test program for the Apollo LEM guidance and navigation subsystem - . Nation: USA. Program: Apollo. Spacecraft: Apollo LM, CSM Guidance, LM Guidance.

  MSC and Grumman reviewed the ground test program for the LEM guidance and navigation subsystem (including radar). All major milestones for hardware qualification would be met by the revised test logic, and both LEM and CSM radar were expected to be delivered on time. The major problem area was permissible deviations from fully qualified parts for pre-production equipment. Since this was apparently true for all LEM electronics equipment, it was recommended that an overall plan be approved by ASPO.

• New hardware delivery schedule for the Apollo LEM ground development test program - . Nation: USA. Program: Apollo. Spacecraft: Apollo LM.

  Grumman and MSC representatives met at Bethpage, New York, to establish requirements for a new hardware delivery schedule for the LEM ground development test program. This program would involve changes in the workload at the subcontractors, WSMR, AEDC, and Grumman. New delivery schedules for flight engines were also finalized at the meeting.

• Apollo LEM descent engine subcontractors reviewed - . Nation: USA. Related Persons: Faget, Shea. Program: Apollo. Spacecraft: Apollo LM, LM Descent Propulsion.

  ASPO Manager Joseph F. Shea informed Apollo Program Director Samuel C. Phillips that it was his desire to review the progress of the two subcontractors (Space Technology Laboratory and Rocketdyne) prior to the final evaluation and selection of a subcontractor for the LEM descent engine.

  Shea had asked MSC's Maxime A. Faget to be chairman of a committee to accomplish the review, and would also ask the following individuals to serve: C. H. Lambert, W. F. Rector III, and J. G. Thibodaux, all of MSC; L. F. Belew, MSFC; M. Dandridge and J. A. Gavin, Grumman; I. A. Johnsen, Lewis Research Center; C. H. King, OMSF; Maj. W. R. Moe, Edwards Rocket Research Laboratory; and A. O. Tischler, NASA Office of Advanced Research and Technology.

  The Committee should

  1. establish review criteria during a planning meeting at MSC during the week of November 30, 1964;
  2. visit the two subcontractors' facilities during the week of December 7, 1964, for review of technical status, manufacturing resources, and test facilities; and
  3. prepare a written report and brief appropriate NASA personnel on their findings by December 18, 1964.
  "Both GAEC and NASA will be parties to the final selection and it is not my intent to usurp GAEC's responsibility in this matter; but I do feel we should have the intelligence at our disposal to appreciate all ramifications of GAEC's final selection," Shea said.

• Emergency nitrogen deluge into the SM and SLA studied - . Nation: USA. Program: Apollo. Spacecraft: Apollo LM.

  MSC's Flight Operations Directorate accepted KSC's proposal for emergency nitrogen deluge into the SM and spacecraft LEM adapter (SLA) in case of a hydrogen leak on the pad. The proposal was based upon no changes to the spacecraft and insertion to the SM SLA area in about three minutes. However, errors in volume estimation and inlet conditions in the spacecraft required reevaluation of the proposal to assure that insertion could be accomplished in a reasonable length of time without changes in the spacecraft.

• High-performance injector for the Apollo LEM ascent engine tested - . Nation: USA. Program: Apollo. Spacecraft: Apollo LM, LM Ascent Propulsion.

  Bell Aerosystems Company tested a high-performance injector for the LEM ascent engine. The new design was similar to the current one, except that the mixture ratio of the barrier flow along the chamber wall had been changed from 0.85 to 1.05. Bell reported a performance increase of 0.8 percent (about 2.5 sec of specific impulse). Subsequent testing, however, produced excessive erosion in the ablative wall of the thrust chamber caused by the higher temperature. The MSC Propulsion and Power Division (PPD) felt this method of increasing the ascent engine's performance might not be practicable.

  At the same time, PPD reported that Bell had canceled its effort to find a lighter ablative material (part of the weight reduction program). A number of tests had been conducted on such materials; none was successful.

• Leach to supply data storage electronics assemblies for the Apollo LEM - . Nation: USA. Program: Apollo. Spacecraft: Apollo LM, LM Guidance.

  Grumman selected the Leach Corporation to supply data storage electronics assemblies for the LEM. Conclusion of contract negotiations was anticipated about February 1, 1965. The resident Apollo office at Grumman gave its approval to the selection, with only two conditions:

  1. because of its toxic characteristics, beryllium must not be used in the assemblies; and
  2. Leach should demonstrate the feasibility of the proposed time-voice multiplexing scheme.

• Six flights of the Apollo Lunar Landing Research Vehicle - . Nation: USA. Program: Apollo. Spacecraft Bus: Apollo LM. Spacecraft: Apollo LLRV.

  Six flights of the Lunar Landing Research Vehicle (LLRV) were made during the month, bringing the total number to seven. The project pilot, Joseph Walker, made all flights and demonstrated a rapid increase in the ease and skill with which he handled the craft as the flights progressed.

  Altitudes to between 18 and 21 m (60 and 70 ft) and flight duration up to three minutes were attained. Additional Details: here....

• Apollo LEM's ascent engine redesigned for a longer firing duration - . Nation: USA. Program: Apollo. Spacecraft: Apollo LM, LM Ascent Propulsion. After studying increased thrust versus increased burn time, Grumman ordered Bell Aerosystems Company to redesign the LEM's ascent engine for a longer firing duration..

• Apollo LEM to be the active vehicle during lunar rendezvous - . Nation: USA. Program: Apollo. Spacecraft: Apollo LM, CSM RCS, LM RCS. MSC advised Grumman that, normally, the LEM would be the active vehicle during lunar rendezvous. This would conserve reaction control system propellants aboard the CSM..

• Communications during LEM and Apollo CSM rendezvous - . Nation: USA. Program: Apollo. Spacecraft: Apollo LM, CSM Communications, LM Communications.

  Representatives of MSC's Information and Electronic Systems Division, Flight Operations Division, Flight Crew Operations Division, Guidance and Control Division, Astronaut Office, and ASPO, Goddard Space Flight Center, and Bellcomm, Inc., met to discuss communications during LEM and CSM rendezvous.

  Capability of the Manned Space Flight Network (MSFN) to provide data for rendezvous was studied. Aaron Cohen of ASPO stated sufficient data could be collected, processed, and transmitted via MSFN to the LEM to achieve rendezvous. Dr. F. O. Vonbun of Goddard showed that MSFN data did little to improve data already available in the LEM before launch. Although five tracking stations would communicate with the LEM during ascent and the first 10 minutes of orbit, there would be only a slight improvement in spacecraft position and motion data over the data already contained in the LEM computer. No decision was made concerning the MSFN's capability.

  Alternate rendezvous methods were discussed.

• Use of one auxiliary battery for the Apollo LEM - . Nation: USA. Program: Apollo. Spacecraft: Apollo LM, LM Electrical. MSC approved the use of one 23.68-kg (50-lb) auxiliary battery for the LEM, as recommended by Grumman, and preparations began for negotiations with Yardney Electric Corp..

• LEM split bus distribution system - . Nation: USA. Program: Apollo. Spacecraft: Apollo LM, LM Electrical.

  Grumman and LEM Project Office representatives met to discuss the split bus distribution system. They decided there would be two circuit breaker panels similar to those of Mockup 5. All power distribution system controls would be located on the system engineer's center side console with remote controls and valves on the commander's center side console.

• Weight allocation for the Apollo LEM's R&D instrumentation - . Nation: USA. Program: Apollo. Spacecraft: Apollo LM, LM Weight. MSC revised the weight allocation for the LEM's R&D instrumentation to bring it in line with current mission planning. Limitations established were 295 kg (650 lbs) for 206A and 181 kg (400 lbs) for all other missions..

• Criteria for firing times of the SM RCS - . Nation: USA. Program: Apollo. Spacecraft: Apollo LM, LM RCS.

  Grumman received from Houston criteria for firing times of the SM reaction control system (RCS). These served as a basis for the design of the LEM's steerable antenna. The thermal design proposed by Dalmo-Victor, the vendor, appeared feasible to watchdogs in MSC's Instrumentation and Electronic Systems Division. On the other hand, the unbalanced wind torque produced by the RCS engines was still a problem. RCA and Dalmo-Victor's estimates of the amount of torque varied considerably, and Grumman consequently undertook a study of this problem.

• Plugging eliminated the Apollo LEM's fuel cell assembly - . Nation: USA. Program: Apollo. Spacecraft: Apollo LM, LM Electrical.

  By improving filling and preparation procedures and by using nickel foil in the oxygen electrode, Pratt and Whitney eliminated both short- and long-term plugging in the LEM's fuel cell assembly. Since then, Pratt and Whitney had consistently operated single cells for over 400 hours and - as far as the company was concerned - felt this settled the matter.

• Apollo LEM abort guidance section - . Nation: USA. Program: Apollo. Spacecraft: Apollo LM, LM Guidance.

  MSC directed Grummann to provide a LEM abort guidance section (AGS) having

  • a computer memory of 4096 words
  • the provision for in-flight null bias gyro drift compensation
  • a general purpose input output device
  • Bell 3B accelerometers
  • input registers for rendezvous radar information such that a future interface could be mechanized if desired
  • an interface between the primary navigation and guidance system (PNGS) and the AGS for position and velocity updating of the AGS from the PNGS.

• Updated criteria for the Apollo LEM's landing gear - . Nation: USA. Program: Apollo. Spacecraft: Apollo LM, LM Descent Propulsion, LM Landing Gear, LM RCS.

  From MSC, Grumman received updated criteria to be used in the design of the LEM's landing gear. The gear must be designed to absorb completely the landing impact; it must also provide adequate stability for the vehicle under varying surface conditions, which were spelled out in precise detail.) Maximum conditions that MSC anticipated at touchdown were:

  vertical velocity - 3.05 m (10 ft) per sec

  horizontal velocity - 1.22 m (4 ft) per sec

  spacecraft attitude

  pitch - 3 degrees

  roll - 3 degrees

  yaw - random

  attitude rates - 3 degrees per sec

  At touchdown, all engines (descent and reaction control would be off. "It must be recognized," MSC emphasized, "that the vertical and horizontal velocity values . . . are also constraints on the flight control system."

• Thermal-demanded weight increases for the Apollo LEM's steerable antenna - . Nation: USA. Program: Apollo. Spacecraft: Apollo LM, CSM RCS, LM RCS, LM Weight.

  Dalmo-Victor studied thermal-demanded weight increases for the LEM's steerable antenna. Investigators reported to Grumman and RCA that, in the plume of the CSM's reaction control engines, 1.18 kg (2.5 lbs) was necessary merely for the survival of the antenna; another 1.18 kg would be required for tracking during this impingement.

• Thermal status of antennas for the Apollo CSM and LEM spacecraft - . Nation: USA. Program: Apollo. Spacecraft: Apollo LM, CSM Heat Shield, CSM SPS, LM RCS, LM Weight.

  The Structures and Mechanics Division (SMD) summarized the thermal status of antennas for the Apollo spacecraft (both CSM and LEM). Generally, most troubles stemmed from plume impingement by the reaction control or radiation from the service propulsion engines. These problems, SMD reported, were being solved by increasing the weight of an antenna either its structural weight or its insulation; by shielding it from the engines' exhaust; by isolating its more critical components; or by a combination of these methods.

• New criteria for the landing gear of the Apollo LEM - . Nation: USA. Program: Apollo. Spacecraft: Apollo LM, CSM Recovery, LM Landing Gear.

  In response to MSC's new criteria for the landing gear of the LEM, Grumman representatives met with Center officials in Houston to revise the design. Grumman had formulated a concept for a 419-cm (165-in) radius, cantilever-type configuration, In analyzing its performance, Grumman and Structures and Mechanics Division (SMD) engineers, working separately, had reached the same conclusion: namely, that it did not provide sufficient stability nor did it absorb enough of the landing impact. Both parties to this meeting agreed that the gear's performance could be improved by redesigning the foot pads and beefing up the gear struts. Grumman was modifying other parts of the spacecraft's undercarriage accordingly.

  At the same time, Grumman advised MSC that it considered impractical a contrivance to simulate lunar gravity in the drop program for test Mockup 5. Grumman put forth another idea: use a full-sized LEM, the company said, but one weighing only one-sixth as much as a flight-ready vehicle. SMD officials were evaluating this latest idea, while they were reviewing the entire TM-5 program.

• Apollo LEM major subcontractors to revise test programs and hardware schedules - . Nation: USA. Program: Apollo. Spacecraft: Apollo LM, LM Descent Propulsion, LM Guidance.

  Grumman ordered its major subcontractors supplying electronic equipment for the LEM to implement revised test programs and hardware schedules (in line with the new design approach). A similar directive went to RCA to modify the attitude and translation and the descent engine control assemblies as required for the new concept of an integrated assembly for guidance, navigation, and control of the spacecraft.

• Apollo portable life support system (PLSS) power growth impacts LEM - . Nation: USA. Related Persons: Shea. Program: Apollo. Spacecraft: A7L, Apollo LM, LM Electrical.

  In September 1964, Hamilton Standard, manufacturer of the portable life support system (PLSS), had established a 108-watt-hour capacity for the system's batteries. And on the basis of that figure, Grumman had been authorized to proceed with the development of the LEM's battery charger. (The size of the charger was determined by several factors, but primarily by the size of the battery and time limits for recharging.)

  During November, however, Hamilton Standard and Crew Systems Division (CSD) engineers advised the Instrumentation and Electronic Systems Division (IESD) that the PLSS's power requirements had increased to about 200 watt-hours. (CSD had jurisdiction over the PLSS, including battery requirements; IESD was responsible for the charger.) Hamilton Standard placed most of the blame on the cooling pump motor, which proved far less efficient than anticipated, as well as on the addition of biosensor equipment. ASPO Manager Joseph F. Shea, reviewing the company's explanation, commented that "this says what happened . . . but is far from a justification - this is the type of thing we should understand well enough to anticipate." "How can this happen," he wondered, ". . . in an area which has been subjected to so much discussion and delay?"

  Representatives from Grumman and Hamilton Standard, meeting at MSC on December 17, redefined PLSS battery and charging requirements, and Grumman was directed to proceed with the development of the battery charger. This episode was accompanied by some sense of urgency, since Grumman had to have firm requirements before the end of year to prevent a schedule slippage.

• Study of manual control of the Apollo LEM - . Nation: USA. Program: Apollo. Spacecraft: Apollo LM, LM Guidance. MSC's Guidance and Control Division conducted a pilot simulation study to determine whether a pilot could take over manual control of the LEM between 4,572 and 3,048 m (15,000 and 10,000 ft) above the lunar surface and satisfactorily land the vehicle.. Additional Details: here....

• Apollo program review with MIT - . Nation: USA. Related Persons: Shea. Program: Apollo. Spacecraft: Apollo LM, LM Guidance.

  ASPO Manager Joseph F. Shea informed Apollo Program Director Samuel C. Phillips that he planned to conduct a program review with MIT during January 1965, similar to the North American, AC Spark Plug, and Grumman program reviews, but with certain differences, since MIT was a non- profit organization and the scope of its work much narrower than the prime hardware contractors. Shea pointed out that 1965 would be the most critical year of the MIT effort; during that year all drawings for the Block I, Block II, and LEM guidance navigation and control programs should be released. Consequently, the program review at MIT would examine only that one year.

  Shea said he would meet with C. Stark Draper on January 14 and discuss with him "where we stand with respect to the MIT work of the past and our concerns for the future." During the week of January 18, MSC would send 14 teams to MIT to meet with their counterparts, and the following week a review board, chaired by R. C. Duncan of MSC, would go over the work of the individual MIT-NASA teams in depth and agree upon the program for 1965. The 14 teams would be: Reliability and Quality Assurance, Field Operations, Documentation and Configuration Management, Systems Assembly and Test, Guidance and Mission Analysis, Simulation, Ground Support Equipment, Optics, Inertial Systems and Sensors, Computer, Radar, Training; Terms, Conditions, Rates and Factors; and Statement of Work Integration.

  Shea felt that the review would give MIT a clearer understanding of their part in the guidance, navigation, and control system development. He recommended that Phillips discuss the general nature of the program review with George E. Mueller and Robert C. Seamans, Jr., so they would both understand ASPO's objectives.

  Phillips forwarded the letter to Associate Administrator for Manned Space Flight George E. Mueller along with his comments on the proposal. He said, "I think it is a good plan and that the results will be beneficial to the program. I urge your support should it become necessary."

• Preliminary Design Review of the Apollo Block II CM - . Nation: USA. Program: Apollo. Spacecraft: Apollo LM, CSM Block II, LM Weight.

  The Preliminary Design Review of the Block II CM was held at North American's Downey, Calif., plant. Ten working groups evaluated the spacecraft design and resolved numerous minor details. They then reported to a review board of NASA and North American officials. Additional Details: here....

• Reviewing of the control-display systems of the Apollo CSM and LEM - . Nation: USA. Program: Apollo. Spacecraft: Apollo LM, CSM Cockpit, LM Crew Station. MSC was reviewing the control-display systems of the CSM and LEM to assess operational constraints. North American was requested to study all controls, displays, and systems functions for manned spacecraft to identify and eliminate single-point failures..

• Various designs for the extravehicular mobility unit - . Nation: USA. Program: Apollo. Spacecraft: Apollo LM, LM Structural.

  Grumman and Hamilton Standard were exploring various designs for the extravehicular mobility unit. On the basis of some early conclusions, the MSC Crew Systems Division (CSD) recommended that meteoroid and thermal protection be provided by a single garment. Preliminary hypervelocity tests placed the garment's reliability at 0.999. Each would weigh about 7.7 kg (17 lbs), about 2.3 kg (5 lbs) less than the two-garment design. CSD further recommended that the unit be stored either in the LEM's descent stage or in a jettisonable container in the ascent portion.

• Apollo LEM VHF communications requirements reviewed - . Nation: USA. Program: Apollo. Spacecraft: Apollo LM, LM Communications.

  MSC evaluated the VHF communications requirements and determined that there was no requirement for the LEM to communicate simultaneously over VHF with:

  1. the CSM in lunar orbit
  2. an extravehicular astronaut on the lunar surface.
  There also was no requirement for the CSM to communicate simultaneously over VHF with:
  1. an extravehicular astronaut
  2. an astronaut in the LEM.
  Grumman and North American were advised that voice communications during this mission phase would be maintained by the unified S-band equipment via the Manned Space Flight Network relay.

• Configuration Control Board - . Nation: USA. Related Persons: Maynard. Program: Apollo. Spacecraft: Apollo LM, CSM Block II, LM Guidance, LM Weight.

  The first meeting of the Configuration Control Board was held at MSC with ASPO Manager Joseph F. Shea as chairman. Approval was given to delete 10 Apollo guidance and navigation systems; and W. F. Rector III was directed to look into the use of computers and prototype units for electronic systems integration. In other actions, a decision on changes to CSM specifications to provide for the heavyweight LEM (a proposed increase from 12,705 to 14,515 kg (28,000 to 32,000 lbs)) was deferred until the next meeting; and Owen Maynard was directed to identify all Block II changes that must be implemented regardless of impact and have them ready for Board action by February 18, 1965.

• Alternates considered for Apollo S-band high-gain antenna - . Nation: USA. Program: Apollo. Spacecraft: Apollo LM, CSM Block II, LM Communications, LM Guidance.

  MSC was studying several approaches to the problems of automatic thermal control and automatic reacquisition of the earth by the S-band high-gain antenna while the CSM circled the moon. (The Block II spacecraft, MSC had stated, must have the ability to perform these functions wholly on its own. During an extended stay of the LEM on the lunar surface, when the CSM pilot needed uninterrupted sleep periods, antenna reacquisition was absolutely essential for telemetering data back to earth. And although the requirements for passive thermal control were not yet well defined, the spacecraft's attitude must likewise be automatically controlled.)

  Robert C. Duncan, chief of the MSC Guidance and Control Division, presented his section's recommendations for solving these problems, which ultimately won ASPO's concurrence. Precise spacecraft body rates, Duncan said, should be maintained by the stabilization and control system. The position of the S-band antenna should be telemetered to the ground, where the angle required for reacquisition would be computed. The antenna would then be repositioned by commands sent through the updata link.

• Low-burst factor for the gaseous helium tanks on the Apollo LEM approved - . Nation: USA. Program: Apollo. Spacecraft: Apollo LM, LM RCS.

  The Structures and Mechanics Division approved a low-burst factor for the gaseous helium tanks on the LEM (as recommended by Grumman). This change permitted a substantial lightening of the spacecraft's propulsion systems: descent 45 kg (99 lbs); ascent, 13 kg (29 lbs); reaction control, 2.3 kg (5 lbs).

• Requirement for extravehicular transfer from the Apollo LEM to the CM - . Nation: USA. Program: Apollo. Spacecraft: Apollo LM, CSM Hatch, LM Hatch.

  After reviewing the requirement for extravehicular transfer (EVT) from the LEM to the CM, MSC reaffirmed its validity. The Center already had approved additional fuel for the CM, to lengthen its rendezvousing range, and modifications of the vehicle's hatch to permit exterior operation. The need for a greater protection for the astronaut during EVT would be determined largely by current thermal tests of the pressure suit being conducted by NASA and Hamilton Standard. While the emergency oxygen system was unnecessary during normal transfer from one vehicle to the other, it was essential during EVT or lunar surface activities.

• Apollo LEM crew restraints tested in zero-g - . Nation: USA. Program: Apollo. Spacecraft: Apollo LM, LM Crew Station.

  In simulated zero-g conditions aboard KC-135s, technicians evaluated a number of different devices for restraining the LEM crewmen. These trials demonstrated clearly the need for a hip restraint and for a downward force to hold the astronaut securely to the cabin floor. In mid-February a second series of flights tested the combination that seemed most promising: Velcro shoes that would be used together with Velcropile carpeting on the cabin floor of the spacecraft; a harness that enveloped the astronaut's chest and, through an intricate system of cables and pulleys, exerted a constant downward pressure; and a waist strap that secured the harness to the lighting panel immediately facing the crewman. These evaluations permitted Grumman to complete the design of the restraint system.

• Combustion instability in the Apollo LEM ascent engine - . Nation: USA. Program: Apollo. Spacecraft: Apollo LM, LM Ascent Propulsion.

  The persistent problem of combustion instability in the LEM ascent engine, unyielding to several major injector redesigns, was still present during test firings at Bell Aerosystems. Following reviews by MSC and Grumman, the "mainstream effort" in the injector program was "reoriented" to a design that included baffles on the face of the injector. Largely because of this troublesome factor, it now appeared that the ascent engine's development cost, which only four months earlier Bell and Grumman had estimated at $20 million, would probably approach $34 million. Bell also forecast a 15.4-kg (34-lb) weight increase for the engine because of a longer burn design and a strengthened nozzle extension.

• Space Ordnance Systems selected for the explosive bolts for the Apollo LEM - . Nation: USA. Program: Apollo. Spacecraft: Apollo LM, LM Electrical. Space Ordnance Systems was selected to develop the explosive bolts that held the LEM's two stages together..

• STL sole contractor for the Apollo LEM descent engine - . Nation: USA. Program: Apollo. Spacecraft: Apollo LM, Apollo Lunar Landing, LM Descent Propulsion.

  Parallel development of the LEM descent engine was halted. Space Technology Laboratories was named the sole contractor; the Rocketdyne contract was canceled. Grumman estimated that the cost of Rocketdyne's program would be about $25 million at termination.

• Apollo LEM adapter panels might interfere with radio communications - . Nation: USA. Program: Apollo. Spacecraft: Apollo LM, LM Communications.

  The MSC-MSFC Mechanical Integration Panel discussed the possibility that, when deployed, the LEM adapter panels might interfere with radio communications via the S-band high-gain antenna. On earth-orbital missions, the panel found, the S-band antenna would be rendere useless. They recommended that MSC's Instrumentation and Electronic Systems Division investigate alternative modes for communications during the transposition and docking phase of the flight. During lunar missions, on the other hand, the panel found that, with panels deployed at a 45 degree angle, the high-gain antenna could be used as early as 15 minutes after translunar injection. Spacecraft-to-ground communications during transposition and docking could thus be available and manual tracking would not be needed. North American was informed that the high-gain antenna would be used during this maneuver, and was directed to fix the panel deployment angle for all Block II spacecraft at 45 degrees.

• Technique for Apollo LEM / S-IVB separation during manned mission approved - . Nation: USA. Program: Apollo. Spacecraft: Apollo LM, CSM Electrical, LM Electrical.

  ASPO approved the technique for LEM S-IVB separation during manned missions, a method recommended jointly by North American and Grumman. After the CSM docked with the LEM, the necessary electrical circuit between the two spacecraft would be closed manually. Explosive charges would then free the LEM from the adapter on the S-IVB.

• Operational requirement for propellant gauges in the Apollo LEM descent stage - . Nation: USA. Program: Apollo. Spacecraft: Apollo LM, LM Crew Station. ASPO established an operational requirement for propellant gauges in the LEM descent stage, the exact details to be worked out by Grumman. The gauges must be accurate to within one-half of one percent when less than one-fourth of the propellants remained..

• Dalmo-Victor freezes the design of the Apollo LEM S-band antenna - . Nation: USA. Program: Apollo. Spacecraft: Apollo LM, LM Communications. Dalmo-Victor, vendor of the LEM S-band antenna, was given firm requirements for tracking and coverage, thus enabling the company to freeze the antenna design..

• Apollo Lunar Landing Research Vehicle results - . Nation: USA. Related Persons: Gilruth. Program: Apollo. Spacecraft Bus: Apollo LM. Spacecraft: Apollo LLRV.

  Warren J. North, Chairman of the Lunar Landing Research Vehicle (LLRV) Coordination Panel, reported to MSC Director Robert R. Gilruth that the LLRV had been flown 10 times by Flight Research Center pilots - eight times by Joe Walker and twice by Don Mallick. Maximum altitude achieved was 91 m (300 ft) and maximum forward velocity was 12 m (40 ft) per sec. Additional Details: here....

• Device to detect failures in the reaction control system (RCS) for Block I Apollo CSMs cancelled - . Nation: USA. Program: Apollo. Spacecraft: Apollo LM, CSM Block II, LM RCS, LM Weight.

  MSC canceled plans (originally proposed by North American) for a device to detect failures in the reaction control system (RCS) for Block I CSMs. This was done partly because of impending weight, cost, and schedule penalties, but also because, given an RCS failure during earth orbit, the crew could detect it in time to return to earth safely even without the proposed device. This action in no way affected the effort to devise such a detection system for the Block II CSM or the LEM, however.

• Initial development testing of Apollo LEM restraint systems completed - . Nation: USA. Program: Apollo. Spacecraft: Apollo LM, LM Crew Station.

  Initial development testing of LEM restraint systems was completed. Under zero-g conditions, investigators found, positive restraints for the crew were essential. While the system must be further refined, it consisted essentially of a harness that secured the astronaut's hips (thus providing a pivot point) and held him firmly on the cabin floor.

• Scientific experiments for the first manned Apollo lunar landing mission - . Nation: USA. Program: Apollo. Spacecraft Bus: Apollo LM. Spacecraft: Apollo ALSEP.

  Nine areas of scientific experiments for the first manned Apollo lunar landing mission had been summarized and experimenters were defining them for NASA. Space sciences project group expected to publish the complete report by March 1, to be followed by requests for proposals from industry on designing and producing instrument packages. A major effort was under way by a NASA task force making a time-motion study of how best to use the limited lunar stay-time of two hours' minimum for the first flight.

• Grumman modified the Apollo LEM's forward hatch - . Nation: USA. Program: Apollo. Spacecraft: Apollo LM, LM Hatch.

  To make it easier to get in and out of the spacecraft, Grumman modified the LEM's forward hatch. During mobility tests on the company's mockup, a hinged, trapezoidal-shaped door had proved superior to the original circular hatch, so the earlier design was dropped.

• Constant attitude device added to the Apollo LEM's attitude control system - . Nation: USA. Program: Apollo. Spacecraft: Apollo LM, LM Crew Station.

  A device to maintain the spacecraft in a constant attitude was added to the LEM's primary attitude control system (ACS). The feature brought with it some undesirable handling characteristics, however: it would cause the vehicle to land long. Although this overshoot could be corrected by the pilot, and therefore was not dangerous operationally, it would require closer attention during final approach. The attitude hold, therefore, hardly eased the pilot's control task, which was, after all, its primary function. Instead of moving the device to the backup ACS (the abort section), the Engineering Simulation Branch of MSC's Guidance and Control Division recommended that the system be modified so that, if desired, the pilot could disengage the hold mechanism.

• Apollo LEM-active docking simulation reviewed - . Nation: USA. Program: Apollo. Spacecraft: Apollo LM, LM Crew Station.

  MSC, North American, and Grumman reviewed the results of Langley Research Center's LEM-active docking simulation. While the overhead mode of docking had been found to be acceptable, two items still caused some concern: (1) propellant consumption could exceed supply; and (2) angular rates at contact had occasionally exceeded specifications. Phase B (Grumman's portion) of the docking simulations, scheduled to begin in about two weeks, would further investigate these problems. Langley researchers also had evaluated several sighting aids for the LEM and recommended a projected image collimated (parallel in lines of direction) reticle as most practicable. Accordingly, on March 9, MSC directed Grumman to incorporate this type of sighting device into the design of their spacecraft.

• Electromagnetic compatibility testing of hardware aboard the Apollo CSM and LEM - . Nation: USA. Program: Apollo. Spacecraft: Apollo LM, CSM Block I, LM Electrical.

  ASPO and the MSC Instrumentation and Electronic Systems Division (IESD) formulated a program for electromagnetic compatibility testing of hardware aboard the CSM and LEM. The equipment would be mounted in spacecraft mockups, which would then be placed in the Center's anechoic chamber. In these tests, scheduled to begin about the first of September, IESD was to evaluate the compatibility of the spacecraft in docked and near-docked configurations, and of Block I spacecraft with the launch vehicle. The division was also to recommend testing procedures for the launch complex.

• Proposal for an all battery system for the Apollo LEM - . Nation: USA. Program: Apollo. Spacecraft: Apollo LM, LM Electrical.

  ASPO evaluated Grumman's proposal for an "all battery" system for the LEM descent stage. ASPO was aiming at a 35-hour lunar stay for the least weight; savings were realized by lessening battery capacities, by making the water tanks smaller, and by reducing some of the spacecraft's structural requirements.

• Three-foot probes on the Apollo LEM landing gear - . Nation: USA. Program: Apollo. Spacecraft: Apollo LM, LM Descent Propulsion, LM Landing Gear.

  Evaluations of the three-foot probes on the LEM landing gear showed that the task of shutting off the engine prior to actual touchdown was even more difficult than controlling the vehicle's rate of descent. During simulated landings, about 70 percent of the time the spacecraft was less than 0.3 m (1 ft) high when shutdown came; on 20 percent of the runs, the engine was still burning at touchdown. Some change, either in switch location or in procedure, thus appeared necessary to shorten the delay between contact light and engine cutoff (an average of 0.7 sec).

• Use of the Apollo LEM as a backup for the service propulsion system - . Nation: USA. Program: Apollo. Spacecraft: Apollo LM, LM ECS.

  To make room for a rendezvous study, MSC was forced to end, prematurely, its simulations of employing the LEM as a backup for the service propulsion system. Nonetheless, the LEM was evaluated in both manual and automatic operation. Although some sizable attitude changes were required, investigators found no serious problems with either steering accuracy or dynamic stability.

• Corrosion in the Apollo coolant loops due to glycol - . Nation: USA. Program: Apollo. Spacecraft: Apollo LM, CSM ECS, LM ECS.

  MSC's Systems Engineering Division (SED) requested support from the Structures and Mechanics Division in determining the existence or extent of corrosion in the coolant loops of the SM electrical power subsystem (EPS) and the CM and LEM environmental control subsystems (ECS), resulting from the use of water glycol as coolant fluid. Informal contact had been made with W. R. Downs of the Structures and Mechanics Division and he had been given copies of contractor reports and correspondence between MSC, North American, and MIT pertaining to the problem. The contractors had conflicting positions regarding the extent and seriousness of glycol corrosion.

  SED requested that a study be initiated to:

  1. determine the existence or extent of corrosion in the EPS and ECS coolant loops; and
  2. make recommendations regarding alternate materials, inhibitors, or fluids, and other tests or remedial actions if it were determined that a problem existed.

• Specialty areas for 13 astronauts not assigned to Gemini - . Nation: USA. Related Persons: Aldrin, Anders, Bassett, Bean, Cernan, Chaffee, Collins, Cunningham, Eisele, Freeman, Gordon, Schweickart, Scott, Williams, Clifton. Program: Apollo. Spacecraft: Apollo LM, CSM ECS, LM Communications, LM ECS, LM Guidance.

  MSC announced a realignment of specialty areas for the 13 astronauts not assigned to forthcoming Gemini missions (GT 3 through 5) or to strictly administrative positions:

  Operations and Training

  Edwin E. Aldrin, branch chief - mission planning

  Charles A. Bassett - operations handbooks, training, and simulators

  Alan L. Bean - recovery systems

  Michael Collins - pressure suits and extravehicular activity

  David R. Scott - mission planning and guidance and navigation

  Clifton C. Williams - range operations, deep space instrumentation, and crew safety.

  Project Apollo

  Richard F. Gordon, branch chief - overall astronaut activities in Apollo area and liaison for CSM development

  Donn F. Eisele - CSM and LEM

  William A. Anders - environmental control system and radiation and thermal systems

  Eugene A. Cernan - boosters, spacecraft propulsion, and the Agena stage

  Roger B. Chaffee - communications, flight controls, and docking

  R. Walter Cunningham - electrical and sequential systems and non-flight experiments

  Russell L. Schweickart - in-flight experiments and future programs.

• Apollo LEM tooling program behind schedule - . Nation: USA. Program: Apollo. Spacecraft: Apollo LM, LM Structural.

  In the first of a series of manufacturing review meetings at Bethpage, N.Y., it was learned that Grumman's tooling program was behind schedule (caused primarily by engineering changes). Tool manufacturing might recoup much of the lost time, but this process was highly vulnerable to further design changes. Completion of tooling for the ascent stage of LTA-3 was now set for late April, a production delay of about two months.

• Rendezvous radar delete from Block II Apollo CSMs - . Nation: USA. Program: Apollo. Spacecraft: Apollo LM, CSM Block II, LM Guidance.

  MSC directed North American to delete the rendezvous radar from Block II CSMs. On those spacecraft North American instead would install LEM rendezvous radar transponders. Grumman, in turn, was ordered to halt its work on the CSM rendezvous radar (both in-house and at RCA) as well as all support efforts. At the same time, however, the company was directed to incorporate a tracking light on the LEM (compatible with the CSM telescope sextant) and to modify the spacecraft's VHF equipment to permit range extraction in the CSM.

• Apollo EMU single garment for thermal and meteoroid protection - . Nation: USA. Program: Apollo. Spacecraft: Apollo LM, LM Structural.

  MSC's Crew Systems Division decreed that the extravehicular mobility unit (EMU) would employ a single garment for both thermal and meteoroid protection. By an earlier decision, the penetration probability requirement had been lowered from 0.9999 to 0.999. This change, along with the use of newer, more efficient materials, promised a substantial lightening of the garment (hopefully down to about 7.7 kg (17 lbs), excluding visors, gloves, and boots). The division also deleted the requirement for a separate meteoroid visor, because the thermal and glare visors provided ample protection against meteoroids as well. Tests by Ling-Temco-Vought confirmed the need for thermal protection over the pressure suit during extravehicular transfer by the LEM crewmen.

• Apollo LEM Test Article 2 shipped - . Nation: USA. Program: Apollo. Spacecraft: Apollo LM, LM Structural. LEM Test Article 2 was shipped to Marshall Space Flight Center to undergo a series of Saturn booster vibration tests..

• Philco to design a penetrometer for the Apollo program - . Nation: USA. Program: Apollo. Spacecraft Bus: Apollo LM. Spacecraft: Apollo ALSEP.

  NASA selected Philco's Aeronutronic Division to design a penetrometer for possible use in the Apollo program. Impacting on the moon, the device would measure the firmness and bearing strength of the surface. Used in conjunction with an orbiting spacecraft, the system could provide scientific information about areas of the moon that were inaccessible by any other means. Langley Research Center would negotiate and manage the contract, estimated to be worth $1 million.

• Deployment angle of the Apollo adapter panels changed - . Nation: USA. Program: Apollo. Spacecraft: Apollo LM, CSM Block II, LM Communications.

  To eliminate interference between the S-IVB stage and the instrument unit, MSC directed North American to modify the deployment angle of the adapter panels. Originally designed to rotate 170 degrees, the panels should open but 45 degrees (60 degrees during abort), where they were to be secured while the CSM docked with and extracted the LEM.

  But at this smaller angle, the panels now blocked the CM's four flush- mounted omnidirectional antennas, used during near-earth phases of the mission. While turning around and docking, the astronauts thus had to communicate with the ground via the steerable high gain antenna. For Block II spacecraft, therefore, MSC concurrently ordered North American to broaden the S-band equipment's capability to permit it to operate within 4,630 km (2,500 nm) of earth.

• Expected firing date for the heavyweight Apollo ascent rig slipped - . Nation: USA. Program: Apollo. Spacecraft: Apollo LM, LM Weight.

  William F. Rector III, MSC's LEM Project Officer, reported at an ASPO Manager's Staff Meeting that the expected firing date for the heavyweight ascent (HA) rig #3 at WSTF had been slipped from March 18, 1965, until April 13. Grumman personnel at White Sands said the slip was necessary because

  1. a propellant loading control assembly to be mounted on the rig could not be used in the planned location because it was not accessible for checkout and would require two weeks for refabrication of certain pipelines and further checkout;
  2. checkout of various wiring between the HA-3 rig and the facilities did not occur on schedule and two weeks would be required to complete the task; and
  3. adequate interfacing between the fluid and gaseous ground support equipment (GSE) and various facility pipes was not maintained with many pieces of GSE putting out higher pressure than the facility pipes design allowed.

• Exterior lighting scheme for the Apollo LEM - . Nation: USA. Program: Apollo. Spacecraft: Apollo LM, LM Crew Station.

  On the basis of in-house tests, Grumman recommended a scheme for exterior lighting on the LEM. The design copied standard aeronautical practice (i.e., red, port; green, starboard; and amber, underside). White lights marked the spacecraft, both fore and aft; to distinguish between the two white lights, the aft one contained a flasher.

• Tektites indicated the lunar surface may be sandy - . Nation: USA. Program: Apollo. Spacecraft: Apollo LM, LM Landing Gear.

  Louis Walter, Goddard Space Flight Center geochemist, reported that his research with tektites indicated the lunar surface may be sandlike. Waiter had discovered the presence of coesite in tektites, believed to be particles of the moon sent into space when meteorites impact the lunar surface. Coesite, also found at known meteorite craters, is a form of silicon dioxide - a major constituent of sand - produced under high pressure. "If we accept the lunar origin of tektites," Walter said, "this would prove or indicate that the parent material on the moon is something like the welded tuft that we find in Yellowstone Park, Iceland, New Zealand, and elsewhere." Welded tuft was said to have some of the qualities of beach sand.

• Three major problems with the Apollo LEM - . Nation: USA. Program: Apollo. Spacecraft: Apollo LM, LM Descent Propulsion.

  Grumman reported three major problems with the LEM:

  1. To enable the manufacturer to complete the design of the aft equipment bay, NASA must define the ground support equipment that would be supported by the LEM adapter platforms.
  2. Space Technology Laboratories' difficulties with the descent engine injector (the combustion instability in the variable-thrust engine)
  3. The need for a lightweight thrust chamber for the descent engine, one that would still meet the new duty cycle.

• All-battery Apollo LEM decision - replaces fuel cells - . Nation: USA. Program: Apollo. Spacecraft: Apollo LM, LM Electrical.

  MSC decided in favor of an "all-battery" LEM (i.e., batteries rather than fuel cells in both stages of the vehicle) and notified Grumman accordingly. Pratt and Whitney's subcontract for fuel cells would be terminated on April 1; also, Grumman would assume parenthood of GE's contract (originally let by Pratt and Whitney) for the electrical control assembly. Additional Details: here....

• Passive thermal control of all-battery Apollo LEM doubtful - . Nation: USA. Program: Apollo. Spacecraft: Apollo LM, LM Communications, LM Electrical.

  Preliminary investigation by Grumman indicated that, with an all-battery LEM, passive thermal control of the spacecraft was doubtful. (And this analysis did not include the scientific experiments package, which, with its radioisotope generator, only increased the problem. Grumman and MSC Structures and Mechanics Division engineers were investigating alternate locations for the batteries and modifications to the surface coatings of the spacecraft as possible solutions.

• No serious weight problems with the Apollo spacecraft - . Nation: USA. Related Persons: Shea. Program: Apollo. Spacecraft: Apollo LM, LM Weight.

  Missiles and Rockets reported a statement by Joseph F. Shea, ASPO manager, that MSC had no serious weight problems with the Apollo spacecraft. The current weight, he said, was 454 kg (1,000 lbs) under the 40,823 kg (90,000 lb) goal. Moreover, the increased payload of the Saturn V to 43,091 kg (95,000 lbs) permitted further increases. Shea admitted, however, that the LEM was growing; recent decisions in favor of safety and redundancy could raise the module's weight from 13,381 kg to 14,575 kg (29,500 lbs to 32,000 lbs).

• Recharger for the portable life support system (PLSS) batteries not required - . Nation: USA. Program: Apollo. Spacecraft: A7L, Apollo LM, LM Electrical.

  MSC notified Grumman that a device to recharge the portable life support system's (PLSS) batteries was no longer required in the LEM. Instead, three additional batteries would be stored in the spacecraft (bringing the total number of PLSS batteries to six).

• Studies of lunar landing conditions - . Nation: USA. Program: Apollo. Spacecraft: Apollo LM, LM Descent Propulsion, LM Landing Gear.

  MSC's Structures and Mechanics Division was conducting studies of lunar landing conditions. In one study, mathematical data concerning the lunar surface, LEM descent velocity, and physical properties of LEM landing gear and engine skirt were compiled. A computer was programmed with these data, producing images on a video screen, allowing engineers to review hypothetical landings in slow motion.

  In another study, a one-sixth scale model of the LEM landing gear was dropped from several feet to a platform which could be adjusted to different slopes. Impact data, gross stability, acceleration, and stroke of the landing gear were recorded. Although the platform landing surface could not duplicate the lunar surface as well as the computer, the drop could verify data developed in the computer program. The results of these studies would aid in establishing ground rules for lunar landings.

• Descent engine cutoff light during the Apollo LEM lunar touchdown - . Nation: USA. Program: Apollo. Spacecraft: Apollo LM, LM Descent Propulsion, LM Landing Gear, LM RCS.

  An evaluation was made of the feasibility of utilizing a probe-actuated descent engine cutoff light during the LEM lunar touchdown maneuver. The purpose of the light, to be actuated by a probe extending 0.9 m (3 ft) beyond the landing gear pads, was to provide an engine cutoff signal for display to the pilot. Results of the study indicated at least 20 percent of the pilots failed to have the descent engine cut off at the time of lunar touchdown. The high percentage of engine-on landings was attributed to

  1. poor location of the cutoff switch,
  2. long reaction time (0.7 sec) of the pilot to a discrete stimulus (a light), and
  3. the particular value of a descent rate selected for final letdown (4 ft per sec).
  It was concluded that a 0.9-m (3-ft) probe would be adequate to ensure pilot cutoff of the descent engine before touchdown provided the pilot reaction time could be reduced to 0.4 sec or less by improving the location of the cutoff switch.

• Tracking light on the Apollo LEM - . Nation: USA. Program: Apollo. Spacecraft: Apollo LM, LM Weight.

  MSC defined the functional and design requirements for the tracking light on the LEM:

  • The light must be compatible for use with CSM scan telescope sextant optics in visual mode during darkside lunar and earth operations.
  • The light must provide range capability of 324.1 km (175 nm) for darkside lunar operations when viewed with the CSM sextant.
  • The probability of detection within three-minute search time at maximum range when viewed with CSM sextant must exceed 99 percent for worst lunar background.
  • The light must flash at the optimum rate for ease of detection and tracking (60 flashes per minute ±5 fpm).
  • Brightness attenuation must be available for terminal phase operation and for minimizing spacecraft electrical energy drain.
  • The light must be capable of inflight operation for continuous periods of one hour duration over four cycles.
  • The light must have a total operating life of 30 hours at rated output with a shelf life of two years.
  • The light was not required to be maintainable at the component level.
  • The total system weight including cooling and electromagnetic interference shielding, if required, should not exceed 5.44 kg (12 lbs).

• Radioisotope power supply for the Apollo scientific equipment - . Nation: USA. Program: Apollo. Spacecraft: Apollo LM, LM Communications, LM Electrical.

  In November 1964, MSC asked Grumman to conduct a study on the feasibility of carrying a radioisotope power supply as part of the LEM's scientific equipment. The subsequent decision to use batteries in the LEM power system caused an additional heat load in the descent stage. Therefore, MSC requested the contractor to continue the study using the following ground rules: consider the radioisotope power supply a requirement for the purpose of preliminary design efforts on descent stage configuration; determine impact of the radioisotope power supply - in particular its effect on passive thermal control of the descent stage; and specify which characteristics would be acceptable if any existing characteristics of the radioisotope power supply had an adverse effect. The radioisotope power was used only to supply power for the descent stage.

• Adapter panels deployed to 45 degrees would block the command link with the Apollo LEM - . Nation: USA. Program: Apollo. Flight: Apollo 7. Spacecraft: Apollo LM.

  Because the adapter panels, when deployed to 45 degrees, would block the command link with the LEM, a command antenna system on the adapter was mandatory. MSC therefore directed North American to provide such a device on the adapters for spacecraft 014, 101, and 102. This would permit command acquisition of the LEM in the interval between panel deployment and the spacecraft's clearing the adapter.

• Oxygen storage systems for the Apollo LEM studied - . Nation: USA. Program: Apollo. Spacecraft: Apollo LM, LM Descent Propulsion, LM Electrical.

  Grumman officials presented their findings on supercritical versus gaseous oxygen storage systems for the LEM (supercritical: state of homogeneous mixture at a certain pressure and temperature, being neither gas nor liquid). After studying factors of weight, reliability, and thermal control, as well as cost and schedule impacts, they recommended gaseous tanks in the ascent stage and a supercritical tank in the descent stage. They stressed that this configuration would be about 35.66 kg (117 lbs) lighter than an all-gaseous one. Though these spokesmen denied any schedule impact, they estimated that this approach would cost about 2 million more than the all-gaseous mode. MSC was reviewing Grumman's proposal.

  During the latter part of the month, Crew Systems Division (CSD) engineers also looked into the several approaches. In contrast to Grumman, CSD calculated that, at most, an all-gaseous system would be but 4.08 kg (9 lbs) heavier than a supercritical one. CSD nonetheless recommended the former. It was felt that the heightened reliability, improved schedules, and "substantial" cost savings that accompanied the all-gaseous approach offset its slim weight disadvantage.

  During late April, MSC ordered Grumman to adopt CSD's approach (gaseous systems in both stages of the vehicle). (Another factor involved in this decision was the lessened oxygen requirement that followed substitution of batteries for fuel cells in the LEM.)

• Bell study to significantly increase simulation time for Apollo Lunar Landing Research Vehicle - . Nation: USA. Program: Apollo. Spacecraft Bus: Apollo LM. Spacecraft: Apollo LLRV.

  Bell Aerosystems Company reported that a study had been made to determine if it were practical to significantly increase simulation time without major changes to the Lunar Landing Research Vehicle (LLRV). This study had been made after MSC personnel had expressed an interest in increased simulation time for a trainer version of the LLRV. The current LLRV was capable of about 10 minutes of flight time and two minutes of lunar simulation with the lift rockets providing one-sixth of the lift. It was concluded that lunar simulation time approaching seven minutes could be obtained by doubling the 272-kg (600-lb) peroxide load and employing the jet engine to simulate one-half of the rocket lift needed for simulation.

  A major limiting factor, however, was the normal weather conditions at Houston, where such a training vehicle would be located. A study showed that in order to use a maximum peroxide load of 544 kg (1,200 lbs), the temperature could not exceed 313K (40 degrees F); and at 332K (59 degrees F) the maximum load must be limited to 465 kg (1,025 lbs) of peroxide. On the basis of existing weather records it was determined there would be enough days on which flights could be made in Houston on the basis of 544 kg (1,200 lbs) peroxide at 313K (40 degrees F), 465 kg (1,025 lbs) at 332K (59 degrees F), and 354 kg (775 lbs) at 353K (80 degrees F) to make provisions for such loads.

• Apollo LEM change to batteries eliminates the interstage fuel cells umbilical - . Nation: USA. Program: Apollo. Spacecraft: Apollo LM, LM Electrical.

  The change from LEM fuel cells to batteries eliminated the need for a hard-line interstage umbilical for that system and the effort on a cryogenic umbilical disconnect was canceled. The entire LEM pyrotechnic effort was redefined during the program review and levels of effort and purchased parts cost were agreed upon.

• Linear-shaped charge cutters for the Apollo LEM deleted - . Nation: USA. Program: Apollo. Spacecraft: Apollo LM, LM Electrical.

  MSC ordered Grumman to halt development of linear-shaped charge cutters for the LEM's interstage umbilical separation system, and to concentrate instead on redundant explosive-driven guillotines. By eliminating this parallel approach, and by capitalizing on technology already worked out by North American on the CSM umbilical cutter, this decision promised to simplify hardware development and testing. Further, it promised to effect significant schedule improvements and reductions in cost.

• Increased lifetime for the Apollo LEM's descent engine - . Nation: USA. Program: Apollo. Spacecraft: Apollo LM, LM Descent Propulsion. Grumman ordered Space Technology Laboratories to increase the lifetime of the thrust chamber in the LEM's descent engine. This required substantial redesigning and was expected to delay the engine's qualification date about seven months..

• Apollo LEM ascent engine environmental tests - . Nation: USA. Program: Apollo. Spacecraft: Apollo LM, LM Ascent Propulsion, LM ECS.

  MSC contacted Grumman with reference to the LEM ascent engine environmental tests at Arnold Engineering Development Center (AEDC), scheduled for cell occupancy there from May 1, 1965, until September 1, 1965. It was MSC's understanding that the tests might begin without a baffled injector. It was pointed out, however, that the first test was expected to begin July 1, and since the recent baffle injector design selection had been made, time remained for the fabrication of the injector, checkout of the unit, and shipment to AEDC for use in the first test.

  Since the baffled injector represented the final hardware configuration, it was highly desirable to use the design for these tests. MSC requested that availability of the injector constrain the tests and that Grumman take necessary action to ensure compliance.

• Boarding ladder on Apollo LEM reconfigured - . Nation: USA. Program: Apollo. Spacecraft: Apollo LM, LM Hatch, LM Landing Gear.

  After further design studies following the M-5 mockup review (October 5-8, 1964), Grumman reconfigured the boarding ladder on the forward gear leg of the LEM. The structure was flattened, to fit closer to the strut. Two stirrup-type steps were being added to ease stepping from the top rung to the platform or "porch" in front of the hatch.

• Grid-type landing point designator for the Apollo LEM - . Nation: USA. Program: Apollo. Spacecraft: Apollo LM, LM Crew Station.

  MSC decided upon a grid-type landing point designator for the LEM. Grumman would cooperate in the final design and would manufacture the device; MIT would ensure that the spacecraft's guidance equipment could accept data from the designator and thus change the landing point.

• Apollo LEM Project Officer replied to Grumman's weight reduction study - . Nation: USA. Program: Apollo. Spacecraft: Apollo LM, LM Ascent Propulsion, LM Descent Propulsion, LM Electrical, LM Landing Gear.

  William F. Rector, the LEM Project Officer in ASPO, replied to Grumman's weight reduction study (submitted to MSC on December 15, 1964). Rector approved a number of the manufacturer's suggestions:

  • Delete circuit redundancy in the pulse code modulation telemetry equipment
  • Eliminate the VHF lunar stay antenna
  • Delete one of two redundant buses in the electrical power system
  • Move the batteries for the explosive devices (along with the relay and fuse box assembly) from the ascent to the descent stage
  • Reduce "switchover" time (the length of time between switching from the oxygen and water systems in the descent stage to those in the ascent portion of the spacecraft and the actual liftoff from the moon's surface). Grumman had recommended that this span be reduced from 100 to 30 min; Rector urged Grumman to reduce it even further, if possible. He also ordered the firm to give "additional consideration" to the whole concept for the oxygen and water systems:
    1. in light of the decisions for an all-battery LEM during translunar coast; and
    2. possibility of transferring water from the CM to the LEM.
  But ASPO vetoed other proposals to lighten the spacecraft:
  • Delete the high intensity light. Because the rendezvous radar had been eliminated from the CSM, Rector stated flatly that the item could "no longer be considered as part of the weight reduction effort."
  • Combine the redundant legs in the system that pressurized the reaction control propellants, to modularize" the system. MSC held that the parallel concept must be maintained.
  • Delete the RCS propellant manifold.
  • Abridge the spacecraft's hover time. Though the Center was reviewing velocity budgets and control weights for the spacecraft, for the present ASPO could offer "no relief."
  And lastly, Rector responded to Grumman's proposals for staging components of the extravehicular mobility unit (EMU). These proposals had been made on the basis of a LEM crew integration systems meeting on January 27, at which staging had been explored. Those discussions were no longer valid, however. MSC had since required a capability for extravehicular transfer to the LEM. In light of this complicating factor, MSC engineers had reevaluated the entire staging concept. Although staging still offered "attractive" weight reductions, they determined that, at present, it was impractical. Accordingly, Rector informed Robert S. Mullaney, the LEM Program Manager at Grumman, that his firm must revert to the pre-January 27 position - i.e., the EMU and other assorted gear must be stored in the ascent stage of the spacecraft.

• Three flights with the Apollo Lunar Landing Research Vehicle (LLRV) - . Nation: USA. Program: Apollo. Spacecraft Bus: Apollo LM. Spacecraft: Apollo LLRV.

  Three flights were made with the Lunar Landing Research Vehicle (LLRV) for the purpose of checking the automatic systems that control the attitude of the jet engine and adjusting the throttle so the jet engine would support five-sixths of the vehicle weight.

  On March 11 representatives of Flight Research Center (FRC) visited MSC to discuss future programs with Warren North and Dean Grimm of Flight Crew Support Division. A budget for operating the LLRV at FRC through fiscal year 1966 was presented. Consideration was being given to terminating the work at FRC on June 30, 1966, and moving the vehicles and equipment to MSC. Additional Details: here....

• Apollo LEM descent engine problems - . Nation: USA. Program: Apollo. Spacecraft: Apollo LM, LM Descent Propulsion. Space Technology Laboratories' major problems with the LEM descent engine, Grumman reported, were attaining high performance and good erosion characteristics over the entire throttling range..

• Work resumed on the thrust chamber of the Apollo LEM ascent engine - . Nation: USA. Program: Apollo. Spacecraft: Apollo LM, LM Ascent Propulsion.

  Bell Aerosystems Company received Grumman's go-ahead to resume work on the thrust chamber of the LEM ascent engine. Bell conducted a dozen stability tests using an injector fitted with a 31.75 mm (1.25 in), Y-shaped baffle. Thus far, the design had recovered from every induced disturbance (including widely varied fuel-to-oxygen ratios). Also, to ease the thermal soakback problem, Bell planned to thicken the chamber wall.

• Supercritical helium to be used only in the descent stage of the Apollo LEM - . Nation: USA. Program: Apollo. Spacecraft: Apollo LM, LM Descent Propulsion. MSC directed Grumman to use supercritical helium only in the descent stage of the LEM; Grumman completed negotiations with AiResearch for the storage system..

• Apollo LEMs 1, 2, and 3 to have remote command of the transponder feature - . Nation: USA. Program: Apollo. Spacecraft: Apollo LM, LM Communications.

  MSC requested that Grumman incorporate in the command list for LEMs 1, 2, and 3 the capability for turning the LEM transponder off and on by real-time radio command from the Manned Space Flight Network. Necessity for capability of radio command for turning the LEM transponder on after LEM separation resulted from ASPO's decision that the LEM and Saturn instrument unit S-band transponders would use the same transmission and reception frequencies.

• Stroking gear pad recommended for the Apollo LEM - . Nation: USA. Program: Apollo. Spacecraft: Apollo LM, LM Landing Gear. Grumman recommended to MSC that the stroking gear pad be used on the LEM and that design effort to refine crushing performance should continue..

• Development program on the Apollo LEM landing gear - . Nation: USA. Program: Apollo. Spacecraft: Apollo LM, LM Landing Gear. Grumman reported the status of their development program on the LEM landing gear..

• All-battery electrical power system for the Apollo LEM - . Nation: USA. Program: Apollo. Spacecraft: Apollo LM, LM Electrical.

  Grumman presented to MSC its recommendations for an all-battery electrical power system for the LEM:

  • Two batteries in the ascent stage
  • Four batteries in the descent stage
  • A new power distribution system
  • Active cooling for the descent batteries and electrical control assemblies
  Following a review of cost and resources proposals, MSC approved Grumman's configuration, and on April 15 gave the LEM manufacturer a go-ahead. Additional Details: here....

• Systems engineering study of Apollo lunar landing dynamics - . Nation: USA. Program: Apollo. Spacecraft: Apollo LM, LM Guidance, LM Landing Gear.

  Apollo Program Director Samuel C. Phillips told ASPO Manager Joseph F. Shea that Bellcomm, Inc., was conducting a systems engineering study of lunar landing dynamics to determine "functional compatibility of the navigation, guidance, control, crew, and landing gear systems involved in Apollo lunar landing." Phillips asked that he be advised of any specific assignments in these areas which would prove useful in support of the ASPO operation.

  Shea replied, "We are currently evaluating the LEM lunar landing system with the Apollo contractors and the NASA Centers. We believe that the landing problem is being covered adequately by ourselves and these contractors." Shea added that a meeting would be held at Grumman April 21 and 22 to determine if there were any deficiencies in the program, and that he would be pleased to have Bellcomm attend the meeting and later make comments and recommendations.

• Revised Apollo LM ascent engine combustion chamber completed four test firings - . Nation: USA. Program: Apollo. Spacecraft: Apollo LM, LM Ascent Propulsion.

  H. I. Thompson Company's first combustion chamber with a tape-wrapped throat successfully withstood a series of four test firings. If further testing confirmed its performance, reported the resident Apollo office at Bethpage, N.Y., the design would be used in the LEM's ascent engine. (It would replace the current compression-molded throat, which suffered from excessive cracking.)

• Thrust mount for the Apollo LEM ascent engine cracked during testing - . Nation: USA. Program: Apollo. Spacecraft: Apollo LM, LM Ascent Propulsion.

  The thrust mount for the LEM ascent engine cracked during vibration testing. The mount would be strengthened.

  During the same period, Bell tested the first one-piece ablative chamber for the ascent engine (designed to replace the molded-throat design, which developed cracks during testing . In firings that totaled over eight minutes, Bell engineers found that the unit suffered only negligible throat erosion and decay of chamber pressure.

• Backup mode of entering and leaving the Apollo LEM while on the moon - . Nation: USA. Program: Apollo. Spacecraft: Apollo LM, LM Hatch.

  MSC and Grumman reviewed the requirement for a backup mode of entering and leaving the LEM while on the moon. The new rectangular hatch was deemed "inherently highly reliable," and the only failure that was even "remotely possible" was one of the hatch mechanism. The proposal to use the top (or transfer) hatch was impractical, because it would cost 13.6 kg (30 lb) and would impose an undue hazard on both the crew and the spacecraft's thermal shield.

• A LEM/Apollo CSM interface meeting uncovered a number of design problems - . Nation: USA. Program: Apollo. Spacecraft: Apollo LM, CSM RCS, LM Communications, LM RCS.

  A LEM/CSM interface meeting uncovered a number of design problems and referred them to the Systems Engineering Division (SED) for evaluation: the requirement for ground verification of panel deployment prior to LEM withdrawal; the requirement for panel deployment in earth orbit during the SA-206 flight; the absence of a backup to the command sequencer for jettisoning the CSM (Flight Projects Division (FPD) urged such a backup signal); and Grumman's opposition to a communications link with the LEM during withdrawal of the spacecraft (FPD felt that such a link was needed through verification of reaction control system ignition). SED's recommendations on these issues were anticipated by April 22.

• Pressure transducer for the Apollo LEM's ascent engine tested - . Nation: USA. Program: Apollo. Spacecraft: Apollo LM, LM Ascent Propulsion. Bell Aerosystems tested a pressure transducer for the LEM's ascent propulsion system (the first time such a device was ever used with hypergolic fuels). The transducer proved extremely accurate at sensing pressure differences between the propellant lines..

• Single garment selected for both thermal and micrometeoroid protection for Apollo astronauts - . Nation: USA. Program: Apollo. Spacecraft: Apollo LM, LM Weight.

  Crew Systems Division (CSD) decided on a single garment for both thermal and micrometeoroid protection for Apollo astronauts. CSD's Richard S. Johnston summarized factors underlying this decision:

  • The integrated garment would be easier to don and thus would simplify preparations for leaving the LEM; it would fit better and afford greater visibility, mobility, and access to suit controls.
  • The dual-purpose garment would weigh about 2.3 kg (5 lbs) less than would two separate protective covers. And because it would consume less storage space, the ascent stage of the spacecraft could be lightened by about three pounds. Involved here, also, was the abort weight of the LEM. It was assumed that the most adverse conditions would be encountered during an "immediate abort," before the crew could depressurize the cabin or jettison now-superfluous equipment (such as the thermal/meteoroid garment).
  • Conversely, separate protective garments - and the "staging" procedure they entailed - would require modifications to the spacecraft and would shorten the astronauts' stay outside the LEM. Moreover, and perhaps even more important, separate garments would limit rescue possibilities and would lessen crew safety.
  Johnston emphasized that, if for any reason the integration scheme proved impracticable, the division could still return to the concept of separate thermal and micrometeoroid garments.

• Recommendation for an up-data system in the Apollo LEM during manned missions - . Nation: USA. Program: Apollo. Spacecraft: Apollo LM, CSM Guidance, LM Guidance, LM Weight.

  Systems Engineering Division (SED) reviewed the Flight Operations Directorate's recommendation for an up-data system in the LEM during manned missions. (Currently the LEM's guidance computer received data either from the computer in the CSM or from MSC.) SED concluded that, because the equipment was not essential for mission success, an up-data system did not warrant the cost and weight penalties ($750,000 and 4.54 kg (10 lbs)) that it would entail.

• Apollo LEM fuel cell terminated - . Nation: USA. Program: Apollo. Spacecraft: Apollo LM, LM Electrical.

  The Apollo Program Director, Samuel C. Phillips, informed the Associate Administrator for Manned Space Flight, George E. Mueller, that action was underway by Grumman to terminate all Pratt & Whitney LEM fuel cell activity by June 30, 1965. Pratt & Whitney would complete testing of LEM fuel cell hardware already produced and one complete LEM fuel cell module plus spare parts would be sent to MSC for in- house testing.

  North American's Space and Information Systems Division would continue development at Pratt & Whitney on the CSM fuel cell for 18 months at a cost not to exceed $2.5 million, to ensure meeting the 400-hour lifetime requirement of the CSM system.

  MSC would contract directly with Pratt & Whitney for CSM cell development followed by complete CSM module testing for a 1,000-hour CSM module at a cost of approximately $2.5 million. Grumman was scheduled to propose to ASPO their battery contractor selection on April 29, 1965.

• First firing of the Apollo LEM ascent engine test rig - . Nation: USA. Program: Apollo. Spacecraft: Apollo LM, LM Ascent Propulsion.

  The first firing of the LEM ascent engine test rig (HA-3) was successfully conducted at White Sands Missile Range, New Mexico. A second firing on April 23 lasted 14.45 sec instead of 10 sec as planned. A third firing, lasting 30 sec, completed the test series. A helium pressurization system would be installed before additional testing could begin.

• Apollo LM engineering simulation program - . Nation: USA. Program: Apollo. Spacecraft: Apollo LM. Grumman reviewed the engineering simulation program. The total cost was anticipated at $9 million..

• Program for the Apollo LEM's reaction control system - . Nation: USA. Program: Apollo. Spacecraft: Apollo LM, LM RCS.

  MSC and Grumman reviewed the program for the LEM's reaction control system. The only issue outstanding was Grumman's in-house effort: MSC felt that that effort was "overestimated" and that the manufacturer alone should not handle support from subcontractors.

• RCA Apollo systems engineering subcontract terminated - . Nation: USA. Program: Apollo. Spacecraft: Apollo LM, LM Guidance.

  MSC's Systems Engineering Division requested that Grumman be advised to terminate the RCA systems engineering subcontract as soon as possible. It had been determined that this contract was no longer useful. Based on data presented by Grumman during a program review, an immediate and complete termination would save about $45,000.

• Effect of landing impacts on the structure of the Apollo LEM discussed - . Nation: USA. Program: Apollo. Spacecraft: Apollo LM, LM Ascent Propulsion, LM Descent Propulsion, LM Landing Gear.

  Grumman and MSC engineers discussed the effect of landing impacts on the structure of the LEM. Based on analyses of critical loading conditions, Grumman reported that the present configuration was inadequate. Several possible solutions were being studied jointly by Grumman and the Structures and Mechanics Division (SMD):

  • Strengthening the spacecraft's structure (which would increase the weight of the ascent and descent stages by 19 and 32 kg (42 and 70 lbs), respectively)
  • Modifying the gear
  • Reducing factors of safety and landing dynamics, including vertical velocity at touchdown
  A decision was expected from SMD by June 1.

  Also Grumman representatives summarized the company's study on the design of the footpads. They recommended that, rather than adopting a stroking-type design, the current rigid footpad should be modified. The modification, they said, would improve performance as much as would the stroking design, without entailing the latter's increased weight and complexity and lowered reliability. SMD was evaluating Grumman's recommendations.

• Electrical power system for the Apollo LEM - . Nation: USA. Program: Apollo. Spacecraft: Apollo LM, LM Electrical. MSC completed the program review on the electrical power system for the LEM and approved the cost through completion of the program (about $23.2 million)..

• Apollo LEM systems reviewed by the President's Scientific Advisory Committee - . Nation: USA. Program: Apollo. Spacecraft: Apollo LM, LM ECS.

  The LEM Project Officer notified Grumman that the President's Scientific Advisory Committee (PSAC) had established sub-panels to work on specific technical areas, beyond the full PSAC briefings. One of the sub-panels was concerned with the environmental control subsystem, including space suits. This group desired representation from Hamilton Standard to discuss with regard to the LEM-ECS its interpretation of the reliability design requirements, its implementation through development and test phases, its demonstration of reliability, and its frank assessment of confidence in these measures. Briefing material should be available to the sub-panel by May 17, 1965, with a primary discussion meeting to be held at Hamilton Standard on May 24.

• Common Apollo reaction control system propellant tanks - . Nation: USA. Program: Apollo. Spacecraft: Apollo LM, CSM RCS, LM RCS.

  Grumman was requested to attend a meeting at MSC and to present their reasons as to why the LEM reaction control system (RCS) propellant tanks could not be of common technology with the CSM RCS propellant tanks. Grumman was to also say why an additional development program was required for the LEM tanks.

• Data from the Bell Apollo LEM training vehicle more than a year away - . Nation: USA. Program: Apollo. Spacecraft: Apollo LLRV, Apollo LM. After reviewing the status of the LEM landing simulation program, the Guidance and Control Division reported that "significant data" from the Bell training vehicle were more than a year away..

• Analysis of failures in the Apollo LEM descent stage's propellant tanks - . Nation: USA. Program: Apollo. Spacecraft: Apollo LM, LM Descent Propulsion.

  Allison Division of General Motors Corporation completed an analysis of failures in the LEM descent stage's propellant tanks. Investigators placed the blame on brittle forgings. MSC's Propulsion and Power Division reported that "efforts are continuing to insure (that) future forgings will be satisfactory."

• Apollo LEM ground support equipment to field test sites - . Nation: USA. Program: Apollo. Spacecraft: Apollo LM, LM Landing Gear. Grumman was requested to ship ground support equipment and associated equipment to field test sites as soon as it was available..

• Design engineering inspection on Apollo LEM test article 10 - . Nation: USA. Program: Apollo. Spacecraft: Apollo LM.

  MSC and Grumman conducted the design engineering inspection on LEM test article 10. Structures and Mechanics Division called it "significant" that there were no requests for design changes. The vehicle was ready for shipment to Tulsa, Oklahoma, for static testing by North American, but, at the latter's request, delivery was delayed until May 28.

• Apollo LEM Test Program Requirement Review - . Nation: USA. Program: Apollo. Spacecraft: Apollo LM.

  ASPO announced that a LEM Test Program Requirement Review would be held at Grumman during the first week in June. The purpose of the review would be to reach agreement with Grumman on an overall Test Program Plan and to consider planned allocation of hardware, test schedules, and test logic in relationship to flight missions.

  The review would result in publication of a certification document which would define and catalog the program of testing, analysis, and rationalization which would form the basis for certification of flight spacecraft as capable of meeting requirements of flight missions. It would cover all formal qualification testing above the part level being done at subcontractors or vendors, component testing at Grumman, higher level of assembly testing conducted anywhere in support of a portion of test logic, and individual system test requirements to be conducted on integrated test vehicles such as LEM test article 1.

  The format for the review would consist of individual subsystem test program reviews by the respective MSC and Grumman Subsystem Managers. MSC Subsystem Managers would be supported by RASPO, ASPO, and GE personnel where appropriate. After their initial meeting, the MSC and Grumman managers would summarize their findings to a MSC Grumman review board, emphasizing deficiencies in the program (to include inadequate tests, hardware availability problems, and schedules which were inconsistent with flight support requirements).

• Problem of stowing portable life support systems in the Apollo CM - . Nation: USA. Program: Apollo. Spacecraft: A7L, Apollo LM, CSM Recovery.

  Portable life support systems (PLSS) stowed against the aft bulkhead in the CM would prevent the crew couch from stroking fully. This condition would be aggravated if, at impact, the bulkhead was forced inward. North American spokesmen maintained that, in a water landing, the bulkhead would give only slightly and that the couch struts would not compress to their limits. They argued, therefore, that this condition would be of concern only in a land landing. On the contrary, said MSC. Center officials were adamant that any interference was absolutely unacceptable: it would lessen the attenuation capability of the couch (thereby jeopardizing crew safety); possibly, the bulkhead might even be ruptured (with obviously disastrous results). Because of this problem - and because the capability for extravehicular transfer from the CM to the LEM was required - MSC invited representatives from the three contractors involved to meet in Houston to deal with the question of PLSS stowage.

• Redundant valves in the propellant system of Apollo LEM's ascent stage - . Nation: USA. Program: Apollo. Spacecraft: Apollo LM, LM Ascent Propulsion. Grumman recommended redundant pyrotechnic or solenoid valves in the propellant system of the LEM's ascent stage. Thus the firm could meet NASA's ground rule that no single failure would cause the mission to be aborted..

• Eagle-Picher selected for batteries in Apollo LEM - . Nation: USA. Program: Apollo. Spacecraft: Apollo LM, LM Electrical.

  Grumman advised MSC that it had selected the Eagle-Picher Company as vendor for batteries in both stages of the LEM. At the same time, because a proposal by Yardney Electric Company promised a sizable weight saving, this latter firm would produce "pre-production" models for the ascent stage.

• Apollo LM test scheduling at White Sands - . Nation: USA. Program: Apollo. Spacecraft: Apollo LM, LM Ascent Propulsion, LM Descent Propulsion.

  A tentative agreement was reached between Grumman and MSC propulsion personnel concerning the Propulsion System Development Facility's test scheduling at White Sands operations in regard to stand occupancy times relating to the ascent and descent development rigs. The tentative schedule showed that the ascent LEM Test Article (LTA)-5 vehicle would not start testing until April 1967. The PA-1 rig prototype ascent propulsion rig) would therefore be required to prove the final design and support early LEMs.

  The PA-1 rig was designed and was being fabricated to accommodate small propellant tanks, and there were no plans to update it with larger ones. Therefore, advantages of flexibility, running tests of longer sustained durations, and with the final tank outlet configurations would not be realized. Grumman was requested to take immediate action to have the rig accommodate the larger tanks and install the smaller tanks by use of adapters or other methods.

• All-battery-powered Apollo LEM requirements - . Nation: USA. Program: Apollo. Spacecraft: Apollo LM, CSM Heat Shield, LM Descent Propulsion, LM Electrical.

  As a result of the decision for an all-battery LEM, MSC advised Grumman that power for the entire pre- separation checkout of the spacecraft would be drawn from that module's batteries (instead of only during the 30 minutes prior to separation). This change simplified the electrical mating between the two spacecraft and obviated an additional battery charger in the CSM. From docking until the start of the checkout, however, the CSM would still furnish power to the LEM.

  TWX, James L. Neal, MSC, to GAEC, Attn: R. S. Mullaney. April 30, 1965.

  During the Month

  Grumman reported two major problems with the LEM's descent engine:

  1. Space Technology Laboratories (STL) asked that the thrust chamber be lengthened by 13.9 cm (5.5 in). Weight penalty would be 11.3 kg (25 lbs).
  2. STL concluded that, if used with Grumman's heatshield, the current nozzle extension would melt.

• Use of chamber technician's suit in Apollo AFRM 008 tests disputed - . Nation: USA. Program: Apollo. Spacecraft: Apollo LM, LM ECS.

  Systems Engineering Division did not concur in use of the chamber technician's suit by test subjects in AFRM 008 tests. AFRM 008 represented the only integrated spacecraft test under a simulated thermal- vacuum environment and was therefore considered a significant step in man-rating the overall system. For that reason use of the flight configuration Block I suit was a firm requirement for the AFRM 008 tests.

  The same rationale would be applicable to the LEM and Block II vehicle chamber tests. Only flight configured spacecraft hardware and extravehicular mobility unit garments would be used by test subjects.

• Apollo personnel appointments - . Nation: USA. Program: Apollo. Spacecraft: Apollo LM.

  R. Wayne Young was appointed Chief of the LEM Contract Engineering Branch, ASPO, to perform the functions of Project Officer for the LEM, effective May 3. At the same time M. E. Dell was appointed Chief of the G&N/ACE Contract Engineering Branch, ASPO, and would be responsible for all functions of Project Officer for the guidance and navigation, automatic checkout equipment-spacecraft, and Little Joe II systems for the Apollo spacecraft, and for technical management of the General Electric Support Contract.

• Communications between the Apollo CSM, LEM, and extravehicular astronauts were reviewed - . Nation: USA. Program: Apollo. Spacecraft: Apollo LM, CSM Block II, LM Communications, LM Guidance, LM Hatch.

  In response to a query, Apollo Program Director Samuel C. Phillips told NASA Associate Administrator for Manned Space Flight George E. Mueller that plans to use VHF communications between the CSM, LEM, and extravehicular astronauts and to use X-band radar for the CSM/LEM tracking were reviewed. Bellcomm reexamined the merits of using the Unified S-Band (USB) type which would be installed in the CSM and LEM for communication with and tracking by the earth.

  It was found that no appreciable weight saving or weight penalty would result from an all USB system in the Apollo spacecraft. Also, it was determined there would be no significant advantage or disadvantage in using the system. It was noted, however, that implementation of an all S-band system at that stage of development of the design of the CSM, LEM, and astronaut equipment would incur an obvious cost and schedule penalty.

  Memorandum, Phillips to Mueller, "Use of Only Unified S-Band Communication Equipment in Apollo Spacecraft," May 5, 1965.

  May 6

  After lengthy investigations of cost and schedule impacts, MSC directed North American to incorporate airlocks on CMs 008 and 014, 101 through 112, and 2H-1 and 2TV-1. The device would enable astronauts to conduct experiments in space without having to leave their vehicle. Initially, the standard hatches and those with airlocks were to be interchangeable on Block II spacecraft. During October, however, this concept was changed: the standard outer hatch would be structured to permit incorporation of an airlock through the use of a conversion kit (included as part of the airlock assembly); and when an airlock was installed, an interchangeable inner hatch would replace the standard one.

• Recommendation for an up-data link in the Apollo LEM overruled - . Nation: USA. Program: Apollo. Spacecraft: Apollo LM, LM Weight.

  ASPO overruled a recommendation by the Flight Operations Directorate for an up-data link in the LEM. Although an automated means of inserting data into the spacecraft's computer was deemed "highly desirable," there were prohibitive consequences:

  • Weight - 7.25 kg (16 lbs) in the ascent stage
  • Cost - $1.7 million
  • Schedule delay - five months
  This last effect ASPO termed "flatly unacceptable."

• Use of Apollo SLA to dissipate heat of radioisotope generators - . Nation: USA. Program: Apollo. Spacecraft: Apollo LM.

  Both General Electric and Radio Corporation of America studied the feasibility of using the spacecraft- LEM-adapter to dissipate heat from the radioisotope generator during initial phases of the mission. The generator would raise the temperature of the adapter about 30 degrees; radiation back to the spacecraft was not considered serious.

• Combination of modes for storing oxygen in the Apollo LEM's environmental control system considered - . Nation: USA. Program: Apollo. Spacecraft: Apollo LM, LM ECS, LM Weight.

  ASPO reviewed Grumman's recommendation for a combination of supercritical and gaseous modes for storing oxygen in the LEM's environmental control system (ECS). MSC engineers determined that such an approach would save only about 14.96 kg (33 lbs) over a high- pressure, all-gaseous design. Mission objectives demanded only four repressurizations of the LEM's cabin. On the basis of this criterion, the weight differential was placed at less than nine pounds.

  As a result of this analysis, MSC directed Grumman to design the LEM ECS with an all-gaseous oxygen storage system.

• Proposal to modify Apollo LEM radar programs - . Nation: USA. Program: Apollo. Flight: Apollo 10. Spacecraft: Apollo LM, LM Guidance. ASPO Assistant Manager William A. Lee heard a proposal to modify the LEM radar programs to reduce FY 1966 costs by $7 million. . Additional Details: here....

• Eagle-Picher contract to supply batteries for the ascent and descent stages of the Apollo LEM - . Nation: USA. Program: Apollo. Spacecraft: Apollo LM, LM Electrical.

  MSC instructed Grumman to negotiate award of a contract to supply batteries for the ascent and descent stages of the LEM with Eagle-Picher Company. Grumman had solicited and received proposals from Eagle-Picher and Yardney Electric Corporation. The bids, including fees, were: Eagle-Picher, $1,945,222; and Yardney, $1,101,673. Grumman evaluated the bids; made presentations to MSC personnel; and proposed on May 6 that they negotiate with Eagle-Picher for ascent and descent batteries; and with Yardney for development of a lighter ascent battery at a cost of approximately $600,000. MSC instructed Grumman not to place the proposed development contract with Yardney, stating that such work could be more appropriately done by MSC work with Yardney or other battery vendors.

• Stowing Apollo portable life support systems (PLSS) discussed - . Nation: USA. Program: Apollo. Spacecraft: A7L, Apollo LM, LM Hatch.

  Representatives from North American, Grumman, Hamilton Standard, and MSC discussed the problem of stowing the portable life support systems (PLSS).

  Current specifications called for two PLSSs under the crew couch in the CM at launch, one of which would be brought back to earth. This location presented some serious problems, however.

  MSC officials laid down several ground rules for the discussions:

  • The capability for extravehicular transfer must be maintained.
  • During translunar flight, the capability must exist for general extravehicular activity from the CM.
  • And upon landing, the PLSS must not interfere with the sweep of the crew couch.
  The participants explored a number of stowage options (and the complications involved), even exploring the possibilities of staging and of using a Gemini Extravehicular Life Support System. As a result of these talks, Hamilton Standard began studying the feasibility of repackaging the PLSS to fit underneath the side hatch of the CM and to determine whether the reshaped system would be compatible with both spacecraft.

  During the next few weeks, MSC concluded that, at earth launch, one PLSS would be stowed in each spacecraft. With the help of Hamilton Standard engineers, North American and Grumman designers worked out a stowage volume acceptable to all concerned. Hamilton Standard agreed to repackage the PLSS accordingly. MSC ordered North American to provide for stowage of one PLSS beneath the side hatch of the CM, again stressing that the system must not interfere with the crew couch during landing impact; also, the Center directed Grumman to plan for PLSS stowage in the LEM and to study ingress and egress with the reshaped backpack. (Studies by the Crew Systems Division had already indicated that, from the standpoints of compatibility and mobility, the new shape probably would be acceptable.)

• Evaluation of bidders for an optical rendezvous sensor for the Apollo LEM - . Nation: USA. Program: Apollo. Spacecraft: Apollo LM, LM Crew Station.

  AC Spark Plug officials presented to MSC their evaluation of bidders to design an optical rendezvous sensor for the LEM. Because three different approaches were planned, AC gained Guidance and Control Division's approval to let three subcontracts. The firms chosen were Perkin-Elmer, Hughes Aircraft, and the Itek Corporation.

• MSC to participate in Apollo LEM manned environmental control system tests - . Nation: USA. Related Persons: Anders. Program: Apollo. Spacecraft: Apollo LM, LM Communications, LM ECS.

  MSC informed Grumman it believed it would be beneficial to the LEM development program for MSC to participate in the manned environmental control system tests to be conducted in Grumman's Internal Environment Simulator. The following individuals were suggested to participate: Astronaut William A. Anders or an alternate to act as a test crewman for one or more manned runs; D. Owen Goons or an alternate to act as a medical monitor for the aforementioned astronaut; and John W. O'Neill or an alternate to monitor voice communications during the test and record astronaut comments.

• First design review on the S-band transponder for the Apollo LEM - . Nation: USA. Program: Apollo. Spacecraft: Apollo LM, LM Communications.

  Representatives from Motorola, RCA, Grumman, and MSC held the first design review on the S-band transponder for the LEM. Several areas were pointed out in which the equipment was deficient. Motorola was incorporating improved circuitry to ensure that the transponder met specifications.

• Apollo CSM to LEM water transfer scheme canceled. - . Nation: USA. Program: Apollo. Spacecraft: Apollo LM, LM Weight.

  Engineers from General Electric and MSC's Crew Systems and Systems Engineering Divisions determined that transferring water from the CSM to the LEM involved a 5.4-kg (12-lb) increase in the latter's separation weight. Grumman had placed the penalty at only l.8 kg (4 lbs). Because the LEM's weight was so critical, the water transfer scheme was canceled.

• Radar-aided Apollo powered descent - . Nation: USA. Program: Apollo. Spacecraft: Apollo LM, LM Guidance.

  To determine lunar touchdown velocity uncertainties, MIT studied radar-aided powered descent. From MIT's findings, Guidance and Control Division concluded that one or two sensors should provide velocity updates to the guidance system throughout the descent maneuver.

• Three vendor selections by the Apollo LEM manufacturer - . Nation: USA. Program: Apollo. Spacecraft: Apollo LM, LM Electrical.

  The Resident ASPO at Grumman approved three vendor selections by the LEM manufacturer:

  1. Mechanical Products, Inc. - circuit breakers. (MSC concurred in the use of hermetically sealed breakers.)
  2. Hartman Electric Co. - relays (also hermetically sealed).
  3. Electronic Products Division of Hughes Aircraft Co. - rectangular connectors.

• MSC concurred in Grumman's selection of the RF tracking mode for the Apollo LEM's steerable antenna - . Nation: USA. Program: Apollo. Spacecraft: Apollo LM, LM Guidance. MSC concurred in Grumman's selection of the RF tracking mode for the LEM's steerable antenna..

• Potential hazard in crew procedures inside the Apollo LEM - . Nation: USA. Related Persons: Slayton. Program: Apollo. Spacecraft: A7L, Apollo LM, LM ECS.

  Donald K. Slayton, Assistant Director for Flight Crew Operations, described a potential hazard involved in crew procedures inside the LEM. Two sets of umbilicals linked the Block II space suit to the environmental control system (ECS) and to the portable life support system (PLSS). Though slight, the possibility existed that when a hose was disconnected, the valve inside the suit might not seat. In that event, gas would escape from the suit. Should this occur while the LEM was depressurized, the astronaut's life would be in jeopardy. Consequently, Slayton cautioned, it would be unwise to disconnect umbilicals while in a vacuum. This in turn imposed several mission constraints:

  • PLSSs could not be recharged while the LEM was unpressurized.
  • If the astronauts were planning to leave the spacecraft, they had to switch to the PLSSs and disconnect the ECS hoses before depressurizing their vehicle.
  • Because the cooling circuit in the PLSS operated only in a vacuum, the crew must depressurize the LEM shortly after switching to their PLSSs.

• Contract with Westinghouse on gear for the Apollo LEM's television camera - . Nation: USA. Program: Apollo. Spacecraft: Apollo LM, LM Landing Gear.

  MSC completed contract negotiations with Westinghouse Electric Company on gear for the LEM's television camera (cables and connectors, stowage containers, and camera mockups). Because of technical requirements, the idea of using the same cable in both spacecraft was abandoned.

• Apollo LEM control weight revised - . Nation: USA. Program: Apollo. Spacecraft: Apollo LM, LM Descent Propulsion, LM Weight.

  ASPO requested the Apollo Program Director to revise the LEM control weight at translunar injection as follows:

  • Ascent stage - 2,193kg (4,835lbs)
  • Descent stage - 2,166kg (4,775lbs)
  • Total LEM (fueled) - 14,515kg (32,000lbs)
  The increase would be made possible by reductions of service propulsion system propellant requirements associated with the revised delta-V budget. ASPO pointed out that existing CSM and adapter control weight propellant requirements allowed a maximum LEM injected weight of 14,877 kg (32,800 lbs) with no increase in the launch vehicle payload requirement.

• Feasibility of abbreviated Apollo missions - . Nation: USA. Program: Apollo. Spacecraft: Apollo LM, CSM Recovery, LM Ascent Propulsion, LM Electrical.

  William A. Lee, ASPO Assistant Manager, asked Systems Engineering Division to study the feasibility of an abbreviated mission, especially during the initial Apollo flights. Because of the uncertainties involved in landing, Lee emphasized, the first LEMs should have the greatest possible reserves. This could be accomplished, he suggested, by shortening stay time; removing surplus batteries and consumables; and reducing the scientific equipment. Theoretically, this would enable the LEM pilot to hover over the landing site for an additional minute; also, it would increase the velocity budgets both of the LEM's ascent stage and of the CSM. He asked that the spacecraft's specifications be changed to fly a shorter mission:

  • Stay time - 10 hours
  • Exploration time - six man-hours
  • Scientific payload - 32 kg (70 lbs)
  • Lunar samples returned - 36 kg (80 lbs)
  Lee said that this modification would produce a spacecraft that could be adapted to short and long missions.

• Apollo LEM-1 would be an "all-up" spacecraft - . Nation: USA. Program: Apollo. Spacecraft: Apollo LM. Because correspondence from Grumman and the Resident ASPO there hinted at deleting some equipment from the first LEM, MSC reaffirmed that LEM-1 would be an "all-up" spacecraft, as specified in the SA-206A mission requirements..

• Apollo ASPO Manager Joseph F Shea reported the accomplishment of a number of important items: - . Nation: USA. Related Persons: Shea. Program: Apollo. Spacecraft: Apollo LM, LM Ascent Propulsion, LM Descent Propulsion, LM ECS. ASPO Manager Joseph F. Shea reported the accomplishment of a number of important items.. Additional Details: here....

• One-third scale model test of the Apollo LEM's antenna field - . Nation: USA. Program: Apollo. Spacecraft: Apollo LM, LM Communications. Using one-third scale models, Grumman tested the LEM's antenna field at the extremes of the frequency range. Data evaluation showed that the range was adequate; errors were well within expected values..

• Bell successfully cycled an Apollo LEM ascent engine propellant valve 500 times - . Nation: USA. Program: Apollo. Spacecraft: Apollo LM, LM Ascent Propulsion.

  Bell Aerosystems Company successfully cycled a LEM ascent engine propellant valve 500 times (double the specification requirement). Also, the company conducted a full-duration altitude firing with an ablative nozzle extension to verify heating characteristics.

• Formal Apollo LEM program review postponed - . Nation: USA. Program: Apollo. Spacecraft: Apollo LM.

  MSC postponed the formal LEM program review (wherein spacecraft requirements would be redefined and Grumman's contract converted to an incentive type). The Center directed the company to submit firm proposals for all contract change authorizations (CCA), which were promised by July 11. Grumman was preparing a revised estimate of total program cost. In the meantime, both parties were negotiating on all outstanding CCAs.

  Also, Grumman described its continuing cost reduction effort. To keep expenditures within limits "suggested" by MSC, the firm was preparing detailed budgets both for itself and its subcontractors. The company had made a number of changes to strengthen its administrative structure and, with Houston's support, was reviewing possible schedule changes with an eye toward eliminating some test vehicles.

• Three flights made with Apollo LLRV - . Nation: USA. Program: Apollo. Spacecraft Bus: Apollo LM. Spacecraft: Apollo LLRV.

  Three flights were made with the lunar landing research vehicle (LLRV) by FRC pilot Don Mallick for the purpose of checking the initial weighing, the thrust-to-weight, and the automatic throttle systems.

  General Electric would update the LLRV CF-700 jet engines at their Edwards AFB facility rather than at Lynn, Mass. The change in work location would mean an earlier delivery date and a significant cost reduction. The updating would make the engines comparable to the production engines and would add an additional 890 newtons (200 lbs) of thrust.

• Reduced preflight time for the Apollo lunar landing research vehicle (LLRV) - . Nation: USA. Program: Apollo. Spacecraft Bus: Apollo LM. Spacecraft: Apollo LLRV.

  In an attempt to reduce the overall preflight time in connection with lunar landing research vehicle (LLRV) activities, a meeting was held at Flight Research Center. Principal participants were Ray White, Leroy Frost, Leonard Ferrier, Joe Walker, Don Mallick, Cal Jarvis, Jim Adkins, Zeon Zwink, Wayne Ottinger, and Gene Matranga.

  The session commenced with an estimate of time required to perform each of the functions on the preflight checklist. Review indicated that preflight might be shortened in several ways:

  1. since the radar altimeter and doppler radar units did not affect safety of flights, it was suggested that radar checks on flight mornings be reduced to a minimum or be performed without inspection coverage;
  2. addition of ac and dc voltmeters in the cockpit would eliminate need for power checks during the avionics preflight;
  3. when the weight and drag computer had been properly checked in flight, the weight and drag preflight check could be streamlined down from the 30 minutes currently required; and
  4. investigate the need to refill H2O2 after prime.
  In general, though several operations were performed simultaneously during most of preflight, it appeared other operations could be performed in parallel and thereby reduce overall preflight time.

• Apollo ASPO reported a number of significant activities - . Nation: USA. Program: Apollo. Spacecraft: Apollo LM, LM Ascent Propulsion.

  ASPO reported a number of significant activities in its Weekly Activity Report.

  • The CSM design engineering inspection was satisfactorily conducted at North American June 8-10.
  • Qualification of the Apollo standard initiator was successfully completed by Space Ordnance Systems, Inc.
  • The first full systems firing of the LEM ascent engine was accomplished at Bell Aerosystems using the heavyweight ascent (HA)-2 propulsion test rig.
  • The LEM development program was revised and LEM test article (LTA)-4, LTA-5 ascent stage, flight test article (FTA)-1, and FTA-2 were eliminated.

• Revised velocity budgets for Apollo CSM and LM - . Nation: USA. Program: Apollo. Spacecraft: Apollo LM, LM Guidance.

  Apollo Program Director Samuel C. Phillips approved MSC's request for revised velocity budgets for the two spacecraft. It was understood that these new values would:

  1. still meet the free return trajectory constraint; and
  2. increase (to at least two degrees) the LEM's out-of-plane launch capability. MPAD/FOD provided the analysis and recommendations leading to this decision.

• Procurement of Apollo lunar surface experiments package authorized - . Nation: USA. Related Persons: Mueller. Program: Apollo. Spacecraft Bus: Apollo LM. Spacecraft: Apollo ALSEP.

  George E. Mueller, Associate Administrator for Manned Space Flight, approved procurement of the lunar surface experiments package (LSEP). The package, to be deployed on the moon by each LEM crew that landed there, would transmit geophysical and other scientific data back to earth. NASA's Office of Space Science and Applications would make the final selection of experiments. Mueller emphasized that the LSEP must be ready in time for the first lunar landing mission. Management responsibility for the project was assigned to MSC's Experiments Program Office.

• ECS in the Apollo LEM without adequate thermal control - . Nation: USA. Program: Apollo. Spacecraft: Apollo LM, LM ECS, LM Electrical.

  Crew Systems Division reported that, as currently designed, the environmental control system (ECS) in the LEM would not afford adequate thermal control for an all-battery spacecraft. Grumman was investigating several methods for improving the ECS's thermal capability, and was to recommend a modified configuration for the coolant loop.

• Gaseous oxygen storage for the Apollo LEM's environmental control system (ECS) - . Nation: USA. Program: Apollo. Spacecraft: A7L, Apollo LM, LM ECS, LM Weight.

  MSC ordered Grumman to propose a gaseous oxygen storage configuration for the LEM's environmental control system (ECS), including all oxygen requirements and system weights. Because no decision was yet made on simultaneous surface excursions by the crew, Grumman should design the LEM's ECS for either one-or two-man operations. And the Center further defined requirements for cabin repressurizations and replenishment of the portable life support systems. Oxygen quantities and pressures would be worked out on the basis of these ground rules.

• Data tape recorder probably not to be installed on Apollo LEM-1 - . Nation: USA. Program: Apollo. Spacecraft: Apollo LM, LM Weight. The question of whether a data tape recorder would be installed on LEM-1 had been discussed at several Apollo 206 Mission Operations Plan meetings and there was a strong possibility it would not be installed. . Additional Details: here....

• Communications systems specified for the first three R&D Apollo LEMs - . Nation: USA. Program: Apollo. Spacecraft: Apollo LM, LM Communications.

  Apollo Program Director Samuel C. Phillips listed the RE communications systems envisioned by NASA Headquarters on the first three R&D LEMs and requested ASPO Manager Joseph F. Shea's comments.

  The first three LEMs (LEM-1, LEM-2, and LEM-3) would be equipped with communications equipment in addition to that required in the LEM for lunar missions to provide:

  1. transmission of required engineering (R&D) data;
  2. redundant operational telemetry;
  3. updating of spacecraft equipment via an up-data command link; and
  4. redundant tracking capability.
  The LEM R&D communications system was essentially independent from the operational communications systems. It would be housed primarily in the equipment bay (which on operational flights would house the scientific payload equipment).

• Apollo LEM battery development issues - . Nation: USA. Program: Apollo. Spacecraft: Apollo LM, LM Electrical.

  Samuel C. Phillips, Apollo Program Director, noted MSC request for support from Goddard Space Flight Center on LEM battery development as well as Goddard's agreement to furnish limited support.

  Phillips suggested to ASPO Manager Joseph F. Shea that since MSFC had much experience in the design, development, and operational aspects of battery systems, it was important to use their experience and recommended MSFC be contacted if such action had not already occurred.

• Apollo LEM mockup used in mobility tests of the reconfigured portable life support system (PLSS) - . Nation: USA. Related Persons: Chaffee, Eisele. Program: Apollo. Spacecraft: A7L, Apollo LM.

  Using a LEM mockup at Grumman, and with the assistance of astronauts Roger B. Chaffee and Donn F. Eisele, engineers from Hamilton Standard performed mobility tests of the reconfigured portable life support system (PLSS). Crew Systems Division (CSD) reported that the reshaped back pack did not hinder entering or leaving the spacecraft; and while some interference problems were inescapable when the PLSSs were worn inside the spacecraft for any period of time, CSD believed that damage could be prevented through training and by limiting movement by the crew. Grumman, however, contended that the newer PLSSs had "serious implications" for mobility inside the LEM.

• Grumman and North American worked out interface between Apollo LM and CSM - . Nation: USA. Program: Apollo. Spacecraft: Apollo LM, LM ECS.

  In a series of meetings at Downey, Calif., MSC, Grumman, and North American worked out most of the interface between the two spacecraft. Among the most significant items yet unresolved were: the thermal environment of the LEM during boost; and the structural loads and bending modes between the docked spacecraft.

• Deviations in the Apollo CSM's roll attitude during docking to be limited to eight degrees or less - . Nation: USA. Program: Apollo. Spacecraft: Apollo LM, CSM Docking, LM Guidance. To prevent the CSM's contacting the LEM's radar antenna (a problem disclosed during docking simulations), deviations in the CSM's roll attitude would be limited to eight degrees or less..

• Two thermal problems with the Apollo LEM identified - . Nation: USA. Program: Apollo. Spacecraft: Apollo LM, LM ECS, LM RCS.

  Structures and Mechanics Division (SMD) reported that Grumman had found two thermal problems with the LEM:

  1. On the basis of current predictions, the spacecraft's skin and several antennas would overheat during the boost phase of the mission. SMD engineers, after analyzing the problem, believed that an "acceptable LEM environment" could be achieved by lessening the heat transferred from the inner panels of the adapter and by increasing that emitted by the outer panels.
  2. Also, Grumman had reported that, when exposed to exhaust plumes from the SM's reaction control engines, the LEM's skin would overheat in about five seconds. "Since the LEM withdrawal . . . requires 20 to 26 sec RCS firing," SMD understated, "it is apparent that a problem exists." One suggested solution involved improved insulation.

• Revised deployment angles of Apollo adapter panels - . Nation: USA. Program: Apollo. Spacecraft: Apollo LM. MSC ordered North American to revise the deployment angles of the adapter panels: 45 degrees for separation, docking, and LEM withdrawal; and - at most - 60 degrees for abort separation..

• Status of Apollo LEM-1 - . Nation: USA. Program: Apollo. Spacecraft: Apollo LM. At Bethpage, N.Y., officials from Grumman and the Flight Projects Division (FPD) discussed the status of LEM-1. . Additional Details: here....

• Apollo LEM to be able to telemeter data from the abort electronics assembly (AEA) - . Nation: USA. Program: Apollo. Spacecraft: Apollo LM, LM Guidance.

  MSC directed Grumman to modify the LEM's pulse code modulation and timing electronics assembly to enable it to telemeter data from the abort electronics assembly (AEA). Thus, if data from the AEA disagreed with those from the spacecraft's guidance computer, the two sets could be reconciled on the ground (using inputs from the Manned Space Flight Network), relieving the astronauts of this chore.

• Apollo experiments program discussed work on radioisotope generator - . Nation: USA. Program: Apollo. Spacecraft Bus: Apollo LM. Spacecraft: Apollo ALSEP. NASA representatives briefed officials from the Atomic Energy Commission on the Apollo experiments program and discussed means of coordinating the Commission's work on a radioisotope generator to power those experiments..

• Requirement to connect the space suit to the Apollo LEM's environmental system - . Nation: USA. Related Persons: Shea. Program: Apollo. Spacecraft: A7L, Apollo LM, LM ECS.

  Joseph F. Shea, ASPO Manager, established as a firm mission requirement the capability to connect the space suit to the LEM's environmental system and to the portable life support system while in a vacuum. This capability was essential for operational flexibility on the moon's surface.

• Flight tests to validate cabin layout of the Apollo LEM - . Nation: USA. Program: Apollo. Spacecraft: Apollo LM, LM ECS.

  Crew Systems Division (CSD) conducted a series of flight tests to determine whether the cabin layout of the LEM was suitable for crew performance in zero and one-sixth g environments. Together with its report of satisfactory results, the division made several observations that it thought "appropriate":

  • CSD suggested hand grips in a number of places to aid the crew
  • Additional restraints were needed to supplement the Velcro pile on the cabin floor
  • Some problems with crew performance and mobility, present during one-g simulations, were absent in low- or zero-g environments (e.g., moving from one crew station to another).

• Additional functions defined for Apollo LEM's abort guidance computer - . Nation: USA. Program: Apollo. Spacecraft: Apollo LM, LM Guidance.

  MSC advised Grumman of additional functions for the computer in the LEM's abort guidance section (to be added only if a part of its memory was left over after the basic requirements were digested). These functions, in order of priority, MSC listed as:

  • Midcourse corrections
  • Automatic abort from a coasting descent
  • Display of CSM-LEM range and range rate
  • Automatic terminal rendezvous (with manual velocity control).

• Analysis of Apollo LEM landing gear load-stroke requirements - . Nation: USA. Program: Apollo. Spacecraft: Apollo LM, LM Landing Gear.

  MSC completed a cursory analysis of LEM landing gear load-stroke requirements at touchdown velocities of 2.43 m (8 ft) per sec vertical and 1.22 m (4 ft) per sec horizontal. This study was conducted to determine the lowest crush loads at 8-4 velocity to which the gear could be designed and still meet its landing performance requirements.

• Apollo LEM weight control problems - . Nation: USA. Program: Apollo. Spacecraft: Apollo LM, LM Weight.

  Harry L. Reynolds, Assistant Manager of ASPO, said it was "becoming increasingly clear that we are going to have a difficult job keeping the LEM weight below the control weight." He said the Grumman effort was not adequate and suggested that R. Bullard of MSC be given LEM weight control as a full-time responsibility.

• Proposed location of the antenna for the radar transponder in the Apollo CSM approved - . Nation: USA. Program: Apollo. Spacecraft: Apollo LM, CSM Docking, LM Guidance.

  MSC approved North American's proposed location of the antenna for the radar transponder in the CSM, as well as the transponder's coverage. This action followed a detailed review of the relative positions of the two spacecraft during those mission phases when radar tracking of the LEM was required.

• Concerns over Apollo heat shield development - . Nation: USA. Program: Apollo. Spacecraft: Apollo LM, CSM Heat Shield. John H. Disher, Director of the OMSF Apollo Test Office, stressed two broad areas open to concern in the Apollo spacecraft heatshield development program.. Additional Details: here....

• Redundancy in the Apollo LEM's pulse code modulation telemetry system vetoed - . Nation: USA. Related Persons: Maynard. Program: Apollo. Spacecraft: Apollo LM, LM Weight.

  Owen E. Maynard, Chief of the Systems Engineering Division, vetoed a demand by the Flight Control Division for redundancy in the LEM's pulse code modulation telemetry system. Two factors determined Maynard's action:

  1. cost and schedule impacts, and
  2. the resultant weight and power increases that redundancy would impose. Also it would produce only a "marginal" increase in the total reliability of the spacecraft.

• Apollo LEM communications problem - . Nation: USA. Related Persons: Maynard. Program: Apollo. Spacecraft: Apollo LM, LM Communications, LM Descent Propulsion.

  Systems Engineering Division chief, Owen E. Maynard, reported to the Instrumentation and Electronic Systems Division (IESD) the results of a study on a LEM communications problem (undertaken by his own group at IESD's request). During phases of powered descent to certain landing sites (those in excess of 20 degrees east or west longitude), the structure of the spacecraft would block the steerable antenna's line of sight with the earth. Communications with the ground would therefore be lost. Maynard concurred with IESD that the problem could best be solved by rotating the LEM about its thrust axis.

• Apollo Lunar Landing Research Facility into operation - . Nation: USA. Program: Apollo. Spacecraft Bus: Apollo LM. Spacecraft: Apollo LLRF.

  Langley Research Center put into operation its 3.5 million Lunar Landing Research Facility. The huge structure (76.2 m (250 ft) high and 121.9 m (400 ft) long) would be used to explore techniques and to forecast various problems of landing on the moon. The facility would enable a test vehicle to be operated under one-sixth g conditions.

• Apollo LLRV capabilities - . Nation: USA. Program: Apollo. Spacecraft Bus: Apollo LM. Spacecraft: Apollo LLRV.

  In a memorandum to T. Tarbox, John Ryken, Bell Aerosystems Company LLRV Project Manager, said he understood that Dean Grimm of MSC believed that the LLRV was not configured to have the jet engine provide simulation of a constant-lift rocket thrust in addition to providing the 5/6th g lift. Ryken forwarded to Tarbox a copy of a report, "LLRV Automatic Control System Service and Maintenance Manual," plus notes on the system in the hope that these would help him and NASA personnel better understand the system. He also included suggestions about reducing aerodynamic moments which Grimm felt might interfere with LEM simulation.

• Oxygen storage systems for the Apollo LEM - . Nation: USA. Program: Apollo. Spacecraft: Apollo LM, LM ECS.

  Grumman completed its study of oxygen storage systems for the LEM and reviewed with MSC the company's recommendation (one 20,684-kilonewton per sq m (3,000 psi) tank in the descent stage, two 6,894-kilonewtons per sq m (1,000 psi) tanks in the ascent stage). One drawback to the design, which the Crew Systems Division termed an "apparently unavoidable bad feature," was that, by the time of the final cabin repressurization, the repressurization time would increase to about 12 minutes (though this was admittedly a conservative estimate). Although requesting more data from Grumman on temperatures and cabin pressures, the Center approved the configuration.

• Apollo CM 002 transferred within North American from manufacturing to the test organization - . Nation: USA. Program: Apollo. Spacecraft: Apollo LM, LM Electrical. The Weekly Activity Report for the period indicated progress in several areas.. Additional Details: here....

• Design review on the VHF radio equipment for the Apollo LEM - . Nation: USA. Program: Apollo. Spacecraft: Apollo LM, LM Structural.

  At a design review on the VHF radio equipment for the LEM, conducted by RCA, Grumman refused to vote its approval. Grumman's most serious objection centered on thermal loads, which under extreme conditions could far exceed specification limits. RCA thereupon began exploring several approaches, including new materials, relocation of components, and redesigned heat sinks. Grumman was asked to keep MSC well informed on problems, corrective actions, and anticipated impacts.

• Controlling the amount of bacteria vented from the Apollo LEM - . Nation: USA. Program: Apollo. Spacecraft: Apollo LM, LM ECS, LM Weight.

  Crew Systems Division (CSD) completed its study on the feasibility of controlling the amount of bacteria vented from the LEM. Division researchers found that, by placing special filters in the environmental control system (ECS) of the spacecraft, emission levels could be greatly lowered. This reduction would be meaningless, however, in view of effluents from the extravehicular mobility unit (EMU) - the moon would still be contaminated by the space travelers. Because of weight penalties - and because of their dubious value - CSD recommended that bacteria filters not be added to the LEM's ECS. The Division further advised that, at present, neither the amount of bacteria emitted from the EMU nor a means of controlling this effluence was yet known.

• Meteoroid protection figures for the Apollo CSM - . Nation: USA. Program: Apollo. Spacecraft: Apollo LM, CSM Block II.

  Structures and Mechanics Division (SMD) presented meteoroid protection figures for the Apollo CSM. (During April, General Electric (GE) had developed reliability estimates for the LEM, based on revised design criteria, for the 8.3-day reference mission. The probability for mission success, GE had found, was 0.9969.) SMD'S figures were:

  	Block I (14-day earth orbital flight)	Block II (8.3-day lunar mission)
  CM	0.99987	0.99989
  SM	0.9943	0.9941

  The division consequently placed the meteoroid protection for the entire mission at 0.99417 (Block I, CSM only) and 0.99089 (Block II, CSM and LEM). Apollo's goal was 0.99.

  All of the above figures, both GE's and SMD's, were derived from the inherent protection afforded by the spacecraft's structure. Thus no additional meteoroid shielding was needed. (Meteoroid protection would still be required, of course, during extravehicular operations.)

• Request to relax Apollo LEM qualification requirements rejected - . Nation: USA. Related Persons: Shea. Program: Apollo. Flight: Apollo 10. Spacecraft: Apollo LM.

  ASPO Manager Joseph F. Shea informed Grumman that a proposal they had made during the LEM Program Review on July 6 regarding broader qualification scheduling and parts deviations had been reviewed by NASA and it was considered "not in the best interests of the program to relax the requirements to the extent proposed by GAEC. Additional Details: here....

• Apollo LEM as backup for the service propulsion system - . Nation: USA. Program: Apollo. Spacecraft: Apollo LM, CSM SPS.

  In order to use the LEM as a backup for the service propulsion system (SPS) to abort the mission during the 15-hour period following translunar injection, Grumman informed North American that some redesign of the spacecraft's helium system would likely be required. This information prompted North American designers to undertake their own analysis of the situation. On the basis of their own findings, this latter group disagreed with the LEM manufacturer. Additional Details: here....

• Grumman to provide stowage within Apollo LEM for extravehicular tools - . Nation: USA. Program: Apollo. Spacecraft: Apollo LM, CSM Cockpit, LM Crew Station. MSC directed Grumman to provide stowage within the LEM for those tools needed for transfer between the two spacecraft (either intra- or extravehicular). The tool kit, similar to that in the CM, would be stored in the LEM at earth launch..

• Total Apollo LEM weight 14,515 kg - . Nation: USA. Program: Apollo. Spacecraft: Apollo LM, LM Weight.

  MSC directed Grumman to implement changes in weights of the LEM:

  Total LEM	14,515 kg (32,000 lbs)
  Ascent stage inert	2,193 kg (4,835 lbs)
  Descent stage inert	2,166 kg (4,775 lbs)

  Memorandum, James L. Neal, MSC, to GAEC, Attn: John C. Snedeker,

• Apollo LEM-1 review - . Nation: USA. Program: Apollo. Spacecraft: Apollo LM. At a LEM-1 review held at Bethpage, N.Y., Grumman briefed MSC officials on the status of design drawings and hardware procurement. Also, the company prepared a detailed schedule for manufacturing and installation of various systems on the spacecraft..

• Apollo experiments package would be left on the moon - . Nation: USA. Program: Apollo. Spacecraft: Apollo LM, LM Communications, LM Weight.

  MSC officially notified Grumman that, as part of the Apollo scientific program, an experiments package would be left on the moon by the crewmen of the LEM. The Center outlined weight and storage requirements for the package, which would be stored in the descent stage of the vehicle along with the lunar geological equipment. And MSC emphasized the need for dissipating waste heat given off by the system's radioisotope generator. (The radioisotope generator was a firm requirement, despite the fear voiced by many scientists that the radiation it gave off would disrupt the experiments.)

• Apollo LEM landing envelope discussed - . Nation: USA. Program: Apollo. Spacecraft: Apollo LM, LM Landing Gear. MSC and Grumman discussed the LEM landing gear design and determined the landing velocity touchdown envelope..

• Briefing on the Apollo LEM optical tracker - . Nation: USA. Program: Apollo. Spacecraft: Apollo LM, LM Guidance.

  Agreements and decisions reached at the MSC briefing on the LEM optical tracker were:

  • Development of the LEM rendezvous radar should be continued.
  • One contractor should be selected for development of the optical tracker with schedules to support installation in early LEMs.
  • A decision on the rendezvous radar versus the optical tracker was deferred.

• Significant hardware Apollo changes - . Nation: USA. Program: Apollo. Flight: Apollo 204. Spacecraft: Apollo LM, LM ECS, LM Guidance, LM RCS. MSC authorized North American to make a number of significant hardware changes.. Additional Details: here....

• Functions defined for the Apollo LEM's abort guidance section - . Nation: USA. Program: Apollo. Spacecraft: Apollo LM, LM Guidance.

  MSC defined for Grumman the functions that the LEM's abort guidance section (AGS) must perform during earth orbital flights:

  • When both spacecraft were unmanned, the AGS must be able to hold the LEM's attitude during coast or while thrusting; it would not, however, have to control thrusting itself.
  • During manned missions, whether or not the LEM itself actually was manned, the AGS must afford closed-loop control of the vehicle, again both while coasting and thrusting. Thrusting phases of these flights would demonstrate the section's guidance and navigational capabilities.
  The basic lunar mission program still would be used. False position, velocity, and gravity data would be inserted to make the AGS behave as if it were flying around the moon. Finally, MSC emphasized that neither the AGS hardware, its permanent or "hardwired" memory, nor delivery schedules must be altered to meet this earth orbital capability.

• Landing touchdown studies in the Apollo LEM landing simulator - . Nation: USA. Program: Apollo. Spacecraft: Apollo LM, LM Simulator.

  Several astronauts participated in landing touchdown studies conducted in the LEM landing simulator to verify data collected in previous studies and to determine changes in controls and displays to improve the touchdown envelope. Studies involved landing runs from an altitude of 305 m (1,000 ft) with manual takeover at 213 m (700 ft), at which time the pilot could select a precise landing site.

• Apollo LEM schedule changes cause confusion - . Nation: USA. Related Persons: Shea. Program: Apollo. Spacecraft: Apollo LM, CSM Recovery.

  ASPO Manager Joseph F. Shea informed LEM Subsystems Managers that recent LEM schedule changes and program review activities had led to some confusion with regard to schedule requirements and policies. Shea pointed out that in some instances subsystem delivery schedules had been established which were inconsistent with the overall program. Where this had occurred, prompt action by the Subsystems Managers was required to recover lost ground. Shea then laid down specific ground rules to be followed, and requested that waivers of these ground rules be submitted no later than August 15, along with a demonstration that reasonable alternatives had been investigated. Only the ASPO Manager would approve any waivers.

• Three competing Apollo Block II space suits evaluated - . Nation: USA. Program: Apollo. Spacecraft: A7L, Apollo LM, LM Structural. Crew Systems Division completed evaluation of the three Block II space suits submitted by Hamilton Standard, David Clark, and International Latex.. Additional Details: here....

• Two change orders were issued to Grumman under the Apollo LEM contract - . Nation: USA. Program: Apollo. Spacecraft: Apollo LM. Two change orders were issued to Grumman under the LEM contract, which brought the total estimated cost and fixed fee to $573,246,377..

• Restrictions for the scientific equipment packages for the Apollo LEM - . Nation: USA. Program: Apollo. Spacecraft: Apollo LM, LM Weight. MSC informed Grumman of package dimensions and weight restrictions for the scientific equipment and packages to be stored in the LEM..

• Plans to install Apollo Unified S-Band System equipment at Corpus Christi tracking station - . Nation: USA. Program: Apollo. Spacecraft: Apollo LM, CSM Television, LM Communications, LM Television.

  NASA announced plans to install Apollo Unified S-Band System equipment at its Corpus Christi, Tex., tracking station. The Unified S-Band equipment included a 9-m (30-ft) diameter parabolic antenna and would enable handling of seven different types of communications with two different vehicles, the CM and the LEM. The communications would: track the spacecraft; command its operations and confirm that the command had been executed; provide two-way voice conversation with three astronauts; keep a continuous check on the astronauts' health; make continuous checks on the spacecraft and its functions; supply a continuous flow of information from the Apollo onboard experiments; and transmit television of the astronauts and the exploration of the moon.

• ALSEP Prototypes to be built by three firms. - . Nation: USA. Program: Apollo. Spacecraft Bus: Apollo LM. Spacecraft: Apollo ALSEP.

  NASA named three firms, Bendix Systems Division, TRW Systems Group, and Space-General Corporation to design prototypes of the Apollo Lunar Surface Experiments Package (ALSEP). Each company received a $500,000, six-month contract. After delivery of the prototypes, MSC would select one of the three to develop the ALSEP flight hardware.

• Grumman reported the status of its effort to lighten the Apollo LEM - . Nation: USA. Program: Apollo. Spacecraft: Apollo LM, LM Electrical.

  Grumman reported the status of its effort to lighten the LEM. Despite some relief afforded by recent program changes (e.g., revised velocity budgets and the replacing of fuel cells with batteries), the contractor admitted that significant increases resulted as the design of the spacecraft matured. Grumman recommended, and MSC approved, a Super Weight Improvement Program (SWIP) similar to the one that the company had used in its F-111 aircraft program. By the end of the month, the company reported that SWIP had trimmed about 45 kg (100 lbs) from the ascent and about 25 kg (55 lbs) from the descent stages of the spacecraft. Grumman assured MSC that the SWIP team's attack on the complete vehicle, including its equipment, would be completed prior to the series of LEM design reviews scheduled for late in the year.

• Interface problems between Apollo LEM and portable life support system - . Nation: USA. Program: Apollo. Spacecraft: A7L, Apollo LM, LM ECS.

  Crew Systems Division (CSD) reported that changing the method for storing oxygen in the LEM (from cryogenic to gaseous) had complicated the interface between the spacecraft's environmental control system (ECS) and the portable life support system (PLSS). Very early, the maximum temperature for oxygen at the PLSS recharge station had been placed at 80 degrees. Recent analyses by Grumman disclosed that, in fact, the gas temperature might be double that figure. Oxygen supplied at 160 degrees, CSD said, would limit to 2½ hours the PLSS operating period. Modifying the PLSS, however, would revive the issue of its storage aboard both spacecraft.

  Seeking some answer to this problem, CSD engineers began in-house studies of temperature changes in the spacecraft's oxygen. There was some optimism that Grumman's estimates would be proved much too high, and MSC thus far had made no changes either to the ECS or to the PLSS.

• Schedule dates set for detailed Apollo LEM test plans - . Nation: USA. Program: Apollo. Spacecraft: Apollo LM. ASPO forwarded to Grumman the schedule dates which should be used for submission of detailed vehicle test plans.. Additional Details: here....

• Concept for a panel retention system in the Apollo LEM adapter rejected - . Nation: USA. Program: Apollo. Spacecraft: Apollo LM, LM Weight.

  MSC rejected North American's second design concept for a panel retention system in the LEM adapter. (The contractor's first proposal had drawn an unsatisfactory verdict early in June.) These successive rejections, largely on the basis of weight and vibration factors, illustrated the company's continuing difficulties with the system. MSC "suggested" to North American that it circumvent these problems by attaching the retention cable directly to the skin of the adapter.

• All-gaseous oxygen supply system in the Apollo LEM - . Nation: USA. Program: Apollo. Spacecraft: A7L, Apollo LM, LM ECS.

  Grumman received approval from Houston for an all-gaseous oxygen supply system in the LEM. While not suggesting any design changes, MSC desired that portable life support systems (PLSS) be recharged with the cabin pressurized. And because the oxygen pressure in the descent stage tanks might be insufficient for the final recharge, the PLSSs could be "topped off" with oxygen from one of the tanks in the vehicle's ascent stage if necessary.

• Operation Scrape to lighten the Apollo LEM - . Nation: USA. Program: Apollo. Spacecraft: Apollo LM, LM Weight.

  At a third status meeting on LEM-1, Grumman put into effect "Operation Scrape," an effort to lighten that spacecraft by about 57 kg (125 lbs). "Scrape" involved an exchange of parts between LEM-1 and LTA-3. The former vehicle thus would be heavier than the latter; LTA-3, on the other hand, would have the same structural weight as LEMs 2 and forthcoming.

• Apollo LEM Mission Programmer Program Reader Assembly deleted - . Nation: USA. Related Persons: Maynard. Program: Apollo. Spacecraft: Apollo LM. Owen E. Maynard, Chief of the Systems Engineering Division, asked that part of the LEM Mission Programmer, the Program Reader Assembly, be deleted. The assembly was no longer needed, Maynard said, to meet Apollo mission requirements..

• Two Apollo LEM test articles to be used - . Nation: USA. Program: Apollo. Spacecraft: Apollo LM, LM Structural. MSC assigned two LEM test articles (numbers 10 and 2, respectively) to the SA-501 and SA-502 missions. Prior to flight, the spacecraft would be refurbished by Grumman, which would require four to five months' work on each vehicle..

• Apollo spacecraft contractors plan extensive ground- based test program - . Nation: USA. Program: Apollo. Spacecraft: Apollo LM.

  MSC and Apollo spacecraft contractors were in process of planning and implementing an extensive ground- based test program to certify the spacecraft for flight. All possible efforts were being made to benefit from the experience of related spacecraft programs in planning the Apollo test program. In view of the similarities of the Surveyor mission and the LEM mission, Jet Propulsion Laboratory was asked to cooperate by providing: (1) background information concerning the manner in which their qualification test program had been performed, (2) the major complete vehicle and partial vehicles used in the ground test programs, and (3) significant results obtained from such programs.

• Review of the Apollo LEM landing and docking dynamic environments - . Nation: USA. Program: Apollo. Spacecraft: Apollo LM, LM ECS, LM Guidance.

  MSC requested that Grumman review the current LEM landing and docking dynamic environments to assure: (1) no loss of the abort guidance system attitude reference due to angular motion exceeding its design limit of 25 degrees per second during indicated mission phases; and (2) a mission angular acceleration environment, exceeding the gyro structural tolerances, would not be realized.

• Prelaunch heat loads on Apollo LEM-1 - . Nation: USA. Program: Apollo. Spacecraft: Apollo LM, LM Electrical. Grumman advised that prelaunch heat loads on LEM-1 exceeded the capability of the spacecraft's prelaunch Freon boiler. . Additional Details: here....

• Qualification testing was completed on the Apollo LEM's helium storage tank - . Nation: USA. Program: Apollo. Spacecraft: Apollo LM. Qualification testing was completed on the LEM's helium storage tank..

• Guidelines for Apollo developmental missions - . Nation: USA. Related Persons: Maynard. Program: Apollo. Spacecraft: Apollo LM.

  Owen E. Maynard, Chief of the Systems Engineering Division (SED), drafted a set of guidelines for Apollo developmental missions. While these guidelines pertained mostly to Block II development, and were so labeled, to some extent they dealt with Block I flights as well. These Development Mission Guidelines covered the overall mission, as well as specific phases, with one section devoted solely to the LEM. (Maynard was careful to distinguish these guidelines from "ground rules" in that, rather than being mandatory requirements, their intent was "to afford test planning a guide and somewhat of an envelope . . . and not hard and fast rules.")

  SED was considering including these guidelines in the Apollo Spacecraft Master Test Plan when that document was next revised.

• Several important activities were noted during Apollo reporting period - . Nation: USA. Program: Apollo. Spacecraft: Apollo LM, LM RCS.

  Several important activities were noted during the reporting period: (1) Qualification of the new reefing line cutters was progressing satisfactorily and scheduled for completion in October 1965. (The cutter had been used successfully on the last two earth landing system tests conducted at El Centro); (2) the helium storage tank for the LEM reaction control subsystem successfully passed qualification tests; and (3) the Aero Spacelines' new aircraft, "Super Guppy," made its maiden flight from Van Nuys, Calif., to Mojave Airfield, Calif. The new aircraft had the capability of airlifting the spacecraft-LEM-adapter as well as providing vital backup for the "Pregnant Guppy" aircraft.

• Apollo LEM landing point designator pushed - . Nation: USA. Program: Apollo. Spacecraft: Apollo LM, LM Crew Station.

  At an implementation meeting at MSC on the LEM's guidance and control system, Grumman again made a pitch for its concept for the landing point designator (i.e., scale markings on the vehicle's window). On September 13, the company received MSC's go-ahead. Grumman was told to coordinate closely with both MSC and MIT on the designator's design to ensure that the scale markings would be compatible with the spacecraft's computer.

• Explosion damaged Apollo LEM reaction control system - . Nation: USA. Program: Apollo. Spacecraft: Apollo LM, LM RCS. An explosion damaged a LEM reaction control system thruster being fired in an up attitude in altitude tests at MSC..

• Radiation levels predicted for Apollo LEM-3 crew - . Nation: USA. Program: Apollo. Flight: Apollo 9. Spacecraft: Apollo LM, LM Crew Station.

  Grumman completed an analysis of radiation levels that would be encountered by the LEM-3 crew during their earth orbital mission. Grumman advised that doses would not be harmful. To lessen these levels even further, the contractor recommended that during some parts of the mission the two astronauts climb back into the CM; also, the planned orbit for the LEM (556 by 2,500 km (300 by 1,350 nm)) could be changed to avoid the worst part of the Van Allen Belt.

• 13 flights made in the Apollo LLRV - . Nation: USA. Program: Apollo. Spacecraft Bus: Apollo LM. Spacecraft: Apollo LLRV. A total of 13 flights were made in the LLRV, including one in which the lunar simulation mode was flown for the first time..

• Apollo LEM's descent engine problems - . Nation: USA. Program: Apollo. Spacecraft: Apollo LM, LM Descent Propulsion.

  Grumman advised MSC of major troubles plaguing development of the LEM's descent engine. These included problems of weight, chamber erosion, mixtures, valves, combustion instability, and throttle mechanisms (which Grumman said could delay delivery of LEM 1 and the start of qualification testing).

• Apollo LEM ascent engine exploded during firings - . Nation: USA. Program: Apollo. Spacecraft: Apollo LM, LM Ascent Propulsion.

  A LEM ascent engine exploded during altitude firings at Arnold Engineering Development Center (AEDC). In subsequent investigations, Bell Aerosystems researchers concluded that the failure probably resulted from raw propellants being accidentally forced into the engine at the end of the second run, thus damaging the injector. Additional Details: here....

• Abort feasibility for the AS-206 mission - . Nation: USA. Program: Apollo. Spacecraft: Apollo LM, LM Guidance. MSC's Flight Operations Division requested an investigation of the feasibility of performing an abort from an inoperative S-IVB booster on the AS-206 unmanned LEM mission..

• Status of the Apollo LEM tracking systems described - . Nation: USA. Program: Apollo. Spacecraft: Apollo LM, LM Guidance.

  NASA Associate Administrator for Manned Space Flight George E. Mueller summarized for Administrator James E. Webb the status of the LEM tracking systems. The LEM rendezvous radar system, which had been under development since 1963, was expected to be available when needed for flight missions. Technical studies had shown that an Optical Tracker System offered weight and reliability advantages with no reduction in LEM performance. Hughes Aircraft Company was developing an Optical Tracking System as a back-up to the rendezvous radar.

• Grumman to review Apollo ascent and descent system components - . Nation: USA. Program: Apollo. Spacecraft: Apollo LM, LM Ascent Propulsion, LM Descent Propulsion.

  MSC requested Grumman to review the following ascent and descent pressurization system components in the propulsion subsystem for materials compatibility with certain propellants:

  1. helium explosive valve;
  2. pressure regulator;
  3. latching solenoid valve;
  4. pressure relief and burst disc; and
  5. quad check valve.
  Recent reports from various programs had shown that propellant vapors had seeped into mid-portions of their pressurization systems, causing corrosion and leakage problems. The SM and LEM had recently revised portions of their programs to incorporate this compatibility requirement.

• Apollo LEM vehicle as an electrical ground - . Nation: USA. Program: Apollo. Spacecraft: Apollo LM, LM Weight.

  Assistant ASPO Manager William A. Lee told the General Instrumentation Branch of the Instrumentation and Electronic Systems Division Grumman was preparing a proposal for use of the LEM vehicle as an electrical ground. The plan was to adopt a single wire system selectively for those circuits not susceptible to electrical transients. Lee said Grumman estimated a weight savings of 27 kg (60 lbs) in the ascent stage and 9 kg (20 lbs) in the descent stage. The proposal was expected to be available to NASA by October 1 and Lee had committed NASA to a decision within three weeks of receipt of the plan.

• Strenuous Apollo LM weight reduction effort - . Nation: USA. Program: Apollo. Spacecraft: Apollo LM, LM Landing Gear.

  William A. Lee, ASPO, pointed out to the MSC Thermo-Structures Branch that Grumman was engaged in a strenuous weight reduction effort and that, when feasible, MSC should accept the proposed changes. In the area of thermal control, Grumman was investigating the use of etched aluminum surfaces to replace thermal paint. It was expected that the change was feasible and that approximately 11 kg (24 lbs) of inert weight would be saved on each stage of the LEM. In addition, Grumman was investigating the applicability of this technique to the landing gear components.

  Grumman was also studying substitution of an aluminum-mylar nonrigid outer heatshield with plastic standoffs for current rigid ascent and descent heatshields. The potential inert weight saving would be about 84 kg (185 lbs). Lee requested that Thermo-Structures Branch stay in close contact with these developments.

• Guillotine developed for Apollo LEM's interstage umbilical - . Nation: USA. Program: Apollo. Spacecraft: Apollo LM, LM Electrical.

  MSC requested Grumman and North American to study the possibility of taking the guillotine that Grumman had developed for the LEM's interstage umbilical and using it as well to sever the two umbilicals linking the LEM to the adapter. In this manner, North American's effort to develop these cutters might be eliminated; LEM-adapter interface would be simplified; and a significant monetary savings could be effected without schedule impact.

• Major technical problems plaguing Apollo designers - . Nation: USA. Related Persons: Maynard, Shea. Program: Apollo. Spacecraft: Apollo LM, LM Weight.

  Owen E. Maynard, Chief of Systems Engineering Division, advised ASPO Manager Joseph F. Shea of the major technical problems currently plaguing Apollo designers:

  Spacecraft weight growths

  these, Maynard said, exceeded predictions "by a serious margin." Pessimistically, he added that the performance of many systems was but "marginally acceptable."

  Lunar landing criteria

  the unknowns involved precluded conservative thinking on the LEM.

  Integration of scientific experiments

  Maynard blamed the "piece-meal" integration of experiments for the lack of comprehensive planning and for many late hardware changes.

  Water landing criteria

  because of the range of variables, present design margins were questionable.

  Land landing

  i.e., development of the landing rockets.

  Thermal design

  conflicts existed between temperature control and attitude constraints for the spacecraft.

  Propulsion performance

  no unit, Maynard reported, had yet achieved the specific impulse which was required of it.

  Space suit development

  design of the suit, and of the thermal-meteoroid garment and the portable life support system, Maynard said, had "gyrated violently, resulting in spacecraft design compromises to accommodate questionable space suit performance."

• Apollo LEM-1 ascent stage four weeks behind schedule - . Nation: USA. Program: Apollo. Spacecraft: Apollo LM, LM Ascent Propulsion. At a status meeting at Grumman on LEM-1, MSC learned that, as a result of welding problems, the vehicle's ascent stage was about four weeks behind schedule..

• Apollo LM PCMTEA changes - . Nation: USA. Program: Apollo. Spacecraft: Apollo LM, LM Guidance, LM Weight.

  The Assistant Chief for Electronic Systems notified ASPO that the proposed Grumman plan to repackage the LEM pulse command modulated and timing electronic assembly (PCMTEA) had been discussed and investigated and that the Instrumentation and Electronic Systems Division (IESD) concurred with the proposal. Additional Details: here....

• Design review on the attitude controller for the Apollo LEM - . Nation: USA. Program: Apollo. Spacecraft: Apollo LM, LM Weight. A design review on the attitude controller for the LEM was held at Honeywell. Flight Crew Support Division reported that the device seemed "highly optimized functionally, operationally, and weight wise.".

• Radioisotope thermoelectric generators for Apollo ALSEP - . Nation: USA. Program: Apollo. Spacecraft Bus: Apollo LM. Spacecraft: Apollo ALSEP. NASA and the Atomic Energy Commission (AEC) agreed that AEC would provide radioisotope thermoelectric generators which would power each Apollo Lunar Surface Experiments Package for an operating period of one year on the lunar surface..

• Design parameters for the Apollo LEM landing gear - . Nation: USA. Program: Apollo. Spacecraft: Apollo LM, LM Landing Gear. Grumman established the final design parameters for the landing gear of the LEM (both primary and secondary struts). It was anticipated that this newer design would be between 9 and 14 kg (20 and 30 lbs) lighter than the earlier gear..

• Reducing landing velocity requirements for the Apollo LEM spacecraft - . Nation: USA. Program: Apollo. Spacecraft: Apollo LM, LM Guidance.

  On the basis of studies by both MSC and Grumman on LEM landing criteria, Engineering and Development Directorate determined that contractor and customer alike favored reducing landing velocity requirements for the spacecraft. The two did not see eye to eye on how far these requirements should be reduced, however, and MSC would study the problem further.