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Saturn I

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Saturn 1 Geneology
Credit: © Mark Wade

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AKA: Juno V;Saturn C-1. Status: Retired 1975. First Launch: 1963-03-28. Last Launch: 1965-07-30. Number: 7 . Payload: 9,000 kg (19,800 lb). Thrust: 6,690.00 kN (1,503,970 lbf). Gross mass: 509,660 kg (1,123,600 lb). Height: 55.00 m (180.00 ft). Diameter: 6.52 m (21.39 ft). Apogee: 185 km (114 mi).

The Saturn launch vehicle was the penultimate expression of the Peenemuende Rocket Team's designs for manned exploration of the moon and Mars. The designs were continuously developed and improved, starting from the World War II A11 and A12 satellite and manned shuttle launcher, through the designs made public in the Collier's Magazine series of the early 1950's, until the shock of the first Sputnik launch brought sudden real interest from the U.S. government. On December 30 1957 Von Braun produced a 'Proposal for a National Integrated Missile and Space Vehicle Development Plan'. This had the first mention of a 1,500,000 lbf booster (Juno V, later Saturn I). By July of the following year Huntsville had in hand the contract from ARPA to proceed with design of the Juno V.

Following transfer of the Peenemuende Rocket Team from the US Army to NASA, a year after the first plan was mooted, Von Braun briefed NASA on plans for booster development at Huntsville with objective of manned lunar landing. It was initially proposed that 15 Juno V (Saturn I) boosters assemble a 200,000 kg payload in earth orbit for direct landing on moon. NASA produced two months later, on February 15, 1959, its plan for development in the next decade of Vega (later cancelled after NASA discovered the USAF was secretly developing the similar Hustler (Agena) upper stage), Centaur, Saturn, and Nova launch vehicles (Juno V renamed Saturn I at this point). Throughout the initial planning, Presidential decision, and landing mode debate for the Apollo lunar landing goal, a variety of Saturn and Nova configurations were considered. Of these, only the C-1 and C-5 were taken through to further development.

The political maneuvering that resulted in the Saturn I configuration is described by ABMA commander Medaris in his autobiography:

We had gone through the whole process of selecting upper stages and had made our recommendations to ARPA. We had indicated very clearly that we were willing to accept either the Atlas or Titan as the basis for building the second stage. The real difference was that in one case we would be using the Atlas engines and associated equipment, built by North American, while in the other case, we would be using the Titan power plant built by Aerojet. Largely because of the multitude of different projects that had been saddled on the Atlas, we favor the Titan. Convair builds the Atlas, and we had great confidence in Convair's engineering, but this was over shadowed in our mind by the practical difficulties of getting enough Atlas hardware. However, we assured ARPA that we would take either one.

The time scale was important. In order to get an operational vehicle in the air as soon as possible, and be able to match and possibly exceed Russia's capabilities, we recommended that the first flying vehicle to be made up of Saturn as the first stage and a second stage built with a Titan power plant. We also recommended using the tooling available at Martin for the airframe. We felt that by the time we got through the second-stage tests, the powerful new Centaur oxygen-hydrogen engine would be in good enough shape to become the third stage. We then calculated that a, year afterwards, or perhaps a little later, could begin to come up with a second-generation satellite vehicle that would cluster the Centaur engine for second stage.

Our people made extensive presentations to ARPA and NASA during the late spring of 1959, always taking the position that we could work with either combination that was agreed to by both. We were anxious to have them agree, because it seemed obvious to us that the nation could not afford more than one very large booster project. We believed that the resulting vehicle would be enormously useful both to the Defense Department for advanced defense requirements, and NASA for its scientific and civilian exploration of space.

We finally got a decision. - - We were told that we could begin designing the complete vehicle along the lines that we had recommended, namely, with the Titan as the basis for the second stage. So far there was no sign of trouble. Remembering the difficulties that we had had in connection with our requirements for North American engines for Jupiter, with the North American people largely under control of the Air Force, we knew that if we were to get on with the job properly we had to make our contract direct with Martin for the second stage work, and with the Convair-Pratt & Whitney group for the adaptation of Centaur to the third stage. We asked the Air Force for clearance to negotiate these matters with the companies concerned The Air Force (BMD) refused, and insisted that we let them handle all areas with the contractor. They used the old argument that they as a group could handle the responsibility much better, and that if they didn't handle it, there were bound to be priority problems connected with the military programs for Titan and others. We knew that the Air Force had no technical capacity of their own to put into this project, and that if we gave them the whole job, they would be forced to use the Ramo-Wooldridge organization, now known as the Space Technology Laboratories, as their contract agent to exercise technical supervision and co-ordination. While we knew and respected a few good men in STL, we felt we had ample cause to lack confidence in the organization as such. As a matter of fact, when the House Committee on Government Operations looked askance at STL with respect to their position as a profit-making organization, some of the best men had left the organization. We threw this one out on the table and said that we would not, under any circumstances, tolerate the interference of STL in this project. We knew that we had all the technical capability that was needed to supervise the overall system, and could not stand the delays and arguments that would most assuredly result were that organization to be thrown in also. Both sides presented their arguments to ARPA…Mr. Roy Johnson ruled that we could go ahead and contract directly Martin and others as required. It is understandable that the Air Force took this decision with poor grace. It represented a major setback to the system of absolute control over their own contractors, no matter for whom those contractors happened to be doing work. It also left them pretty much on the side- lines with respect to major participation in or control over any portion of the Saturn as a space vehicle.

With the amount of money still available to us from fiscal year 1960 and with our authorization from ARPA, we proceeded immediately to negotiate engineering contracts with Martin. We thought that since Mr. Johnson had complete control over this program, we had gotten over the last important hurdle and could get on about our business. Little did we realize the hornet's nest that had been stirred up, and less did we realize that winning that battle was finally to mean that we would lose the war, and would lose von Braun's entire organization.

We had only a few weeks of peace and quiet. From events that occurred later, I think I can make a fair estimate of what happened during this short period. Having been overruled by Johnson, the Air Force took a new approach. They decided that in view of the importance and power that was given the Deputy Secretary of Defense for Research and Engineering by the 1958 changes in the defense organization, Dr. York represented their best avenue of approach through which to get back in the war.

For reasons of economy we had recommended, and it had been approved, that in building the second stage, we would use the same diameter as the Titan first stage -- 120 inches. The major costs of tooling for the fabrication of missile tanks and main structure is related to the diameter. Changes in length cost little or nothing in tooling. How the tanks are divided internally, or the structure reinforced inside, or the kind of structural detail that is used at the end in order to attach the structure to a big booster below, or to a different size stage above, have very little effect on tooling problems. However, a change in diameter sets up a major question of tools, costs, and time.

Suddenly, out of the blue came a directive to suspend work on the second stage, and a request for a whole new series of cost and time estimates, including consideration of increasing the second stage diameter to 160 inches. It appeared that Dr. York had entered the scene, and had pointed up the future requirements of Dynasoar as being incompatible with the 120-inch diameter. He had posed the question of whether it was possible for the Saturn to be so designed as to permit it to be the booster for that Air Force project.

We were shocked and stunned. This was no new problem, and we could find no reason why it should not have been considered, if necessary, during the time that the Department of Defense and NASA were debating the whole question of what kind of upper stages we should use. Nevertheless, we very speedily went about the job of estimating the project on the basis of accepting the 160-inch diameter. At the same time it was requested that we submit quotations for a complete operational program to boost the Dynasoar for a given number of flights. As usual, we were given two or three numbers, rather than one fixed quantity, and asked to estimate on each of them.

By this time, my nose was beginning to sniff a strange odor of "fish." I put my bird dogs to work to try to find out what was going on and with whom we had to compete. We discovered that the Air Force had proposed a wholly different and entirely new vehicle as the booster for Dynasoar, using a cluster of Titan engines and upgrading their performance to get the necessary first-stage thrust for take-off. This creature was variously christened the Super Titan, or the Titan C. No work had been done on this vehicle other than a hasty engineering outline. Yet the claim was made that the vehicle in a two-stage or three-stage configuration could be flown more quickly than the Saturn, on which we had already been working hard for many months. Dates and estimates were attached to that proposal which at best ignored many factors of costs, and at worst were strictly propaganda.

Developments of the Saturn IB launch vehicle were detailed in some depth in the late 1960's. There was a large payload gap between the Saturn IB's 19,000 kg low-earth orbit capacity and the two-stage Saturn V 100,000 kg capability. How to fill it was the result of an exhaustive series of Marshall and contractor trade studies.

The configurations shown were the most promising. The best solution was to add two or four UA1205 five segment solid rocket motors already developed for the Titan launch vehicle. This would boost payload to 40,000 kg. Use of seven segment motors developed for Titan 3M would bring the payload up to 48,000 kg but would require stretching the S-1B first stage by 20 feet. A more modest ten foot stretch, with Minuteman first stage motors for thrust augmentation, would bring a modest payload improvement to 23,000 kg.

In the end, no further orders for Saturns were placed. Of the 12 Saturn IB's built, only nine were flown, the remaining three becoming NASA museum pieces. If Saturn production had continued, it is likely the Saturn IB would have been discontinued anyway, and Saturn II variants would have been used for any intermediate payload requirements.

LEO Payload: 9,000 kg (19,800 lb) to a 185 km orbit at 28.00 degrees. Payload: 2,200 kg (4,800 lb) to a translunar trajectory. Development Cost $: 838.100 million. Launch Price $: 76.000 million in 1963 dollars in 1967 dollars.

Stage Data - Saturn I

• Stage 1. 1 x Saturn I. Gross Mass: 432,681 kg (953,898 lb). Empty Mass: 45,267 kg (99,796 lb). Thrust (vac): 7,582.100 kN (1,704,524 lbf). Isp: 289 sec. Burn time: 150 sec. Isp(sl): 255 sec. Diameter: 6.52 m (21.39 ft). Span: 6.52 m (21.39 ft). Length: 24.48 m (80.31 ft). Propellants: Lox/Kerosene. No Engines: 8. Engine: H-1. Status: Out of Production.

• Stage 2. 1 x Saturn IV. Gross Mass: 50,576 kg (111,500 lb). Empty Mass: 5,217 kg (11,501 lb). Thrust (vac): 400.346 kN (90,001 lbf). Isp: 410 sec. Burn time: 482 sec. Diameter: 5.49 m (18.01 ft). Span: 5.49 m (18.01 ft). Length: 12.19 m (39.99 ft). Propellants: Lox/LH2. No Engines: 6. Engine: RL-10. Status: Out of Production.

• Stage 3. 1 x Centaur C. Gross Mass: 15,600 kg (34,300 lb). Empty Mass: 1,996 kg (4,400 lb). Thrust (vac): 133.448 kN (30,000 lbf). Isp: 425 sec. Burn time: 430 sec. Diameter: 3.05 m (10.00 ft). Span: 3.05 m (10.00 ft). Length: 9.14 m (29.98 ft). Propellants: Lox/LH2. No Engines: 2. Engine: RL-10A-1. Status: Out of Production.

Juno V-A American orbital launch vehicle. By 1958 the Super-Jupiter was called Juno V and the 4 E-1 engines were abandoned in favor of clustering 8 Jupiter IRBM engines below existing Redstone/Jupiter tankage. The A version had a Titan I ICBM as the upper stages. Masses, payload estimated.

Juno V-B American orbital launch vehicle. A proposed version of the Juno V for lunar and planetary missions used a Titan I ICBM first stage and a Centaur high-energy third stage atop the basic Juno V cluster. Masses, payload estimated.

Saturn A-1 American orbital launch vehicle. Projected first version of Saturn I, to be used if necessary before S-IV liquid hydrogen second stage became available. Titan 1 first stage used as second stage, Centaur third stage. Masses, payload estimated.

Saturn A-2 American orbital launch vehicle. More powerful version of Saturn I with low energy second stage consisting of cluster of four IRBM motors and tankage, Centaur third stage. Masses, payload estimated.

Saturn B-1 American orbital launch vehicle. Most powerful version of Saturn I considered. New low energy second stage with four H-1 engines, S-IV third stage, Centaur fourth stage. Masses, payload estimated.

Saturn C-1 American orbital launch vehicle. Original flight version with dummy upper stages, including dummy Saturn S-V/Centaur (never flown).

Saturn C-2 American orbital launch vehicle. The launch vehicle initially considered for realizing the Apollo lunar landing at the earliest possible date. 15 launches and rendezvous required to assemble direct landing spacecraft in earth orbit.

Saturn I Blk2 American orbital launch vehicle. Second Block of Saturn I, with substantially redesigned first stage and large fins to accommodate Dynasoar payload.

Saturn I RIFT American nuclear orbital launch vehicle. In the first half of the 1960's it was planned to make suborbital tests of nuclear propulsion for upper stages using a Saturn IB first stage to boost a Rover-reactor powered second stage on a suborbital trajectory. The second stage would impact the Atlantic Ocean down range from Cape Canaveral.

Saturn IB American orbital launch vehicle. Improved Saturn I, with uprated first stage and Saturn IVB second stage (common with Saturn V) replacing Saturn IV. Used for earth orbit flight tests of Apollo CSM and LM.

Saturn IB-A American orbital launch vehicle. Douglas Studies, 1965: S-IB with 225 k lbf H-1's; S-IVB stretched with 350,000 lbs propellants; Centaur third stage.

Saturn IB-B American orbital launch vehicle. Douglas Studies, 1965: S-IB with 225 k lbf H-1's; S-IVB stretched with 350,000 lbs propellants and HG-3 high performance engine.

Saturn IB-C American orbital launch vehicle. Douglas Studies, 1965: 4 Minuteman strap-ons; standard S-IB, S-IVB stages.

Saturn IB-CE American orbital launch vehicle. Douglas Studies, 1965: Standard Saturn IB with Centaur upper stage.

Saturn IB-D American orbital launch vehicle. Douglas Studies, 1965: Standard Saturn IB with Titan UA1205 5-segment strap-on motors.

Saturn INT-05 American orbital launch vehicle. NASA Study, 1965: Half length 260 inch solid motor with S-IVB upper stage.

Saturn INT-05A American orbital launch vehicle. UA Study, 1965: Full length 260 inch solid motor with S-IVB upper stage.

Saturn INT-11 American orbital launch vehicle. Chrysler Studies, 1966: S-IB with 4 Titan UA1205 with standard S-IB stage, S-IVB stage, or 4 Titan UA1207 strap-ons with 20-foot stretched S-IB stage, S-IVB stage. S-IB ignition at altitude.

Saturn INT-12 American orbital launch vehicle. Chrysler Studies, 1966: S-IB with only 4 H-1 motors, with 4 Titan UA1205 with standard length S-IB stage, S-IVB stage, or 4 Titan UA1207 strap-ons with 20-foot stretched S-IB stage, S-IVB stage. S-IB ignition at sea level at same time as strap-ons.

Saturn INT-14 American orbital launch vehicle. Chrysler Studies, 1966: S-IB with 4 Minuteman motors as strap-ons, with no, 10, or 20-foot stretch S-IB stages, S-IVB stage. S-IB ignition at sea level at same time as strap-ons.

Saturn INT-15 American orbital launch vehicle. Chrysler Studies, 1966: S-IB with 8 Minuteman motors as strap-ons, with no, 10, or 20-foot stretch S-IB stages, S-IVB stage. S-IB ignition at sea level at same time as strap-ons.

Saturn INT-16 American orbital launch vehicle. UA Studies, 1966: S-IVB upper stage with from 2 to 5 Titan UA1205, 1206, or 1207 motors as first stage, clustered around from 1 to 3 of the same motors as a second stage. S-IVB upper stage.

Saturn INT-27 American orbital launch vehicle. UA study, 1965. Saturn variant using various combinations of 156 inch rocket motors as first and second stages, with S-IVB upper stage.

Super-Jupiter American orbital launch vehicle. The very first design that would lead to Saturn. A 1.5 million pound thrust booster using four E-1 engines - initial consideration of using a single USAF F-1 engine abandoned because of development time. Existing missile tankage was clustered above the engines.

Uprated Saturn I American orbital launch vehicle. Initial version of Saturn IB with old-design Saturn IB first stage.

Photo Gallery

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Saturn 1 Credit: © Mark Wade

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Saturn I (1959) Saturn I configuration for Project Horizon Credit: US Army

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Saturn I Stages Saturn I , stages 1 to 3, configuration for Project Horizon (1959) Credit: US Army

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Saturn I As conceived for Project Horizon, 1958. Credit: © Mark Wade

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E-1 Engine Credit: © Mark Wade

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Juno-5 Airlift The Juno-5 was designed to be air-transportable and assembled at austere launch pads.

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Juno-5 Parallel Stag A parallel staging scheme was considered for the Juno-5. This would have resulted in a vehicle similar to the Russian R-7 launcher.

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Juno-5 Recovery Full recovery and reuse of the Juno-5 was planned. The structural provisions were retained in the earliest Saturn I test vehicles, but never used.

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Juno-5 on Test Stand The very first Juno-5 test article firing on the stand at the Redstone Arsenal.

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Saturn A-1 to C-5 Credit: © Mark Wade

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Saturn 1B Credit: © Mark Wade

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J-2 Credit: © Mark Wade

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Saturn 1B LC34 Credit: NASA

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Saturn 1B LC39 Credit: NASA

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Saturn 1B with LM Saturn 1B with LM Payload Credit: NASA

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Saturn 1B rad Credit: NASA

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Saturn IB-INT-5B Credit: © Mark Wade

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Saturn 1B/4 SRBs Saturn 1B with 4 solids replacing S-1B Credit: © Mark Wade

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Saturn 1B/MM SRB Saturn 1B with Minuteman strapons Credit: © Mark Wade

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• Studies of a large clustered-engine booster - . Nation: USA. Related Persons: von Braun. Program: Apollo.

  The U.S. Army Ballistic Missile Agency, Redstone Arsenal, Ala., began studies of a large clustered-engine booster to generate 1.5 million pounds of thrust, as one of a related group of space vehicles. During 1957-1958, approximately 50,000 man-hours were expended in this effort.

• Follow-on ballistic missiles and space programs - .

  AFBMD presented the Air Force Scientific Advisory Board's Ad Hoc Committee with a summary of follow-on ballistic missile weapon systems and advanced space programs that could be undertaken. Included among the programs was the proposed development of high-thrust space vehicles for orbital and lunar flights.

• National Integrated Missile and Space Vehicle Development Program - . Nation: USA. Program: Horizon.

  The Army Ballistic Missile Agency completed and forwarded to higher authority the first edition of A National Integrated Missile and Space Vehicle Development Program, which had been in preparation since April 1957. Included was a "short-cut development program" for large payload capabilities, covering the clustered-engine booster of 1.5 million pounds of thrust to be operational in 1963. The total development cost of $850 million during the years 1958-1963 covered 30 research and development flights, some carrying manned and unmanned space payloads. One of six conclusions given in the document was that "Development of the large (1520 K-pounds thrust) booster is considered the key to space exploration and warfare." Later vehicles with greater thrust were also described.

• Saturn I first proposed. - . Nation: USA. Related Persons: von Braun. Program: Apollo. Von Braun produces 'Proposal for a National Integrated Missile and Space Vehicle Development Plan'. First mention of 1,500,000 lbf booster (Saturn I).

• Juno V heavy space launch design - . Nation: USA. The Von Braun team's Super-Jupiter evolved into the Juno V. The 4 E-1 engines were abandoned in favor of clustering 8 Jupiter IRBM engines below existing Redstone/Jupiter tankage..

• Saturn I initial contract. - . Nation: USA. Related Persons: von Braun. Program: Apollo. ARPA gives Von Braun team contract to develop Saturn I (called 'cluster's last stand' due to design concept)..

• Saturn I project initiated by ARPA. - . Nation: USA. Related Persons: von Braun. Program: Apollo.

  The Advanced Research Projects Agency ARPA provided the Army Ordnance Missile Command (AOMC) with authority and initial funding to develop the Juno V (later named Saturn launch vehicle. ARPA Order 14 described the project: "Initiate a development program to provide a large space vehicle booster of approximately 1.5 million pounds of thrust based on a cluster of available rocket engines. The immediate goal of this program is to demonstrate a full-scale captive dynamic firing by the end of calendar year 1959." Within AOMC, the Juno V project was assigned to the Army Ballistic Missile Agency at Redstone Arsenal Huntsville, Ala.

• Redstone Arsenal begins Saturn I design studies. - . Nation: USA. Related Persons: von Braun. Program: Apollo. Saturn design studies authorized to proceed at Redstone Arsenal for development of 1.5-million-pound-thrust cluster first stage..

• Letter contract for the development of the Saturn H-1 rocket engine - . Nation: USA. Program: Apollo. A letter contract was signed by NASA with NAA's Rocketdyne Division for the development of the H-1 rocket engine, designed for use in a clustered-engine booster..

• Juno V project objective changed to multistage carrier vehicle - . Nation: USA. Related Persons: Johnson, Roy, Medaris, von Braun. Program: Horizon.

  Following a Memorandum of Agreement between Maj. Gen. John B. Medaris of Army Ordnance Missile Command (AOMC) and Advanced Research Projects Agency (ARPA) Director Roy W. Johnson on this date and a meeting on November 4, ARPA and AOMC representatives agreed to extend the Juno V project. The objective of ARPA Order 14 was changed from booster feasibility demonstration to "the development of a reliable high performance booster to serve as the first stage of a multistage carrier vehicle capable of performing advanced missions."

• Contract for development of the H-1 engine - . Nation: USA. Program: Apollo. Pioneer I, intended as a lunar probe, was launched by a Thor-Able rocket from the Atlantic Missile Range, with the Air Force acting as executive agent to NASA. The 39-pound instrumented payload did not reach escape velocity..

• ABMA Briefing to NASA - . Nation: USA. Related Persons: von Braun. Program: Apollo. Class: Manned. Type: Manned space station. Von Braun briefs NASA on plans for booster development at Huntsville with objective of manned lunar landing. Initally proposed using 15 Juno V (Saturn I) boosters to assemble 200,000 kg payload in earth orbit for direct landing on moon..

• Saturn H-1 engine first full-power firing - . Nation: USA. Program: Apollo. The H-1 engine successfully completed its first full-power firing at NAA's Rocketdyne facility in Canoga Park, Calif..

• Military and NASA consider future launch vehicles - . Nation: USA. Related Persons: von Braun. Program: Apollo.

  Representatives of Advanced Research Projects Agency, the military services, and NASA met to consider the development of future launch vehicle systems. Agreement was reached on the principle of developing a small number of versatile launch vehicle systems of different thrust capabilities, the reliability of which could be expected to be improved through use by both the military services and NASA.

• NASA Large Booster Review Committee - . Nation: USA. Related Persons: von Braun. Program: Apollo.

  The Army Ordnance Missile Command (AOMC), the Air Force, and missile contractors presented to the ARPA-NASA Large Booster Review Committee their views on the quickest and surest way for the United States to attain large booster capability. The Committee decided that the Juno V approach advocated by AOMC was best and NASA started plans to utilize the Juno V booster.

• Booster name changed from Juno V to Saturn - . Nation: USA. Related Persons: Johnson, Roy, von Braun. Program: Apollo. The Army proposed that the name of the large clustered-engine booster be changed from Juno V to Saturn, since Saturn was the next planet after Jupiter. Roy W. Johnson, Director of the Advanced Research Projects Agency, approved the name on February 3..

• Early agreement required on Saturn upper stages - . Nation: USA. Related Persons: Johnson, Roy, Medaris, von Braun. Program: Apollo.

  Maj. Gen. John B. Medaris of the Army Ordnance Missile Command (AOMC) and Roy W. Johnson of the Advanced Research Projects Agency (ARPA) discussed the urgency of early agreement between ARPA and NASA on the configuration of the Saturn upper stages. Several discussions between ARPA and NASA had been held on this subject. Johnson expected to reach agreement with NASA the following week. He agreed that AOMC would participate in the overall upper stage planning to ensure compatibility of the booster and upper stages.

• Use of Titan for Saturn upper stages - . Nation: USA. Program: Apollo.

  In response to a request by the DOD-NASA) Saturn Ad Hoc Committee, the Army Ordnance Missile Command (AOMC) sent a supplement to the "Saturn System Study" to the Advanced Research Projects Agency ARPA describing the use of Titan for Saturn upper stages. Additional Details: here....

• Unmanned Lunar Soft Landing Vehicle - . Nation: USA. Related Persons: von Braun. Program: Apollo. Spacecraft: Surveyor. The Army Ordnance Missile Command submitted to NASA a report entitled "Preliminary Study of an Unmanned Lunar Soft Landing Vehicle," recommending the use of the Saturn booster..

• First H-1 engine for the Saturn delivered - . Nation: USA. Program: Apollo.

  The first Rocketdyne H-1 engine for the Saturn arrived at the Army Ballistic Missile Agency (ABMA ). The H-1 engine was installed in the ABMA test stand on May 7, first test-fired on May 21, and fired for 80 seconds on May 29. The first long-duration firing - 151.03 seconds - was on June 2.

• National booster program, Dyna-Soar, and Mercury discussed - . Nation: USA. Related Persons: Faget, Low, George. Program: Apollo. Spacecraft: Mercury.

  The national booster program, Dyna-Soar, and Project Mercury were discussed by the Research Steering Committee. Members also presented reviews of Center programs related to manned space flight. Maxime A. Faget of STG endorsed lunar exploration as the present goal of the Committee although recognizing the end objective as manned interplanetary travel. George M. Low of NASA Headquarters recommended that the Committee:

  • Adopt the lunar landing mission as its long-range objective.
  • Investigate vehicle staging so that Saturn could be used for manned lunar landings without complete reliance on Nova.
  • Make a study of whether parachute or airport landing techniques should be emphasized.
  • Consider nuclear rocket propulsion possibilities for space flight.
  • Attach importance to research on auxiliary power plants such as hydrogen-oxygen systems.

• First H-1 engine for Saturn I fired. - . Nation: USA. Program: Apollo. ABMA static fired a single H-1 Saturn engine at Redstone Arsenal, Ala..

• Construction begins of the first Saturn launch complex - . Nation: USA. Related Persons: von Braun. Program: Apollo. Construction of the first Saturn launch area, Complex 34, began at Cape Canaveral, FIa..

• Saturn I launch complex construction starts. - . Nation: USA. Program: Apollo.

• NASA funded study of a lunar exploration program based on Saturn - . Nation: USA. Program: Apollo.

  NASA authorized $150,000 for Army Ordnance Missile Command studies of a lunar exploration program based on Saturn-boosted systems. To be included were circumlunar vehicles, unmanned and manned; close lunar orbiters; hard lunar impacts; and soft lunar landings with stationary or roving payloads.

• Lunar mission studies under way at the Army - . Nation: USA. Related Persons: von Braun. Program: Horizon. Spacecraft: Mercury. During the Research Steering Committee meeting, John H. Disher of NASA Headquarters discussed the lunar mission studies under way at the Army Ballistic Missile Agency (ABMA).. Additional Details: here....

• Transfer to NASA of the Army Ballistic Missile Agency's Development Operations Division - . Nation: USA. Related Persons: Eisenhower, von Braun. Program: Apollo.

  After a meeting with officials concerned with the missile and space program, President Dwight D. Eisenhower announced that he intended to transfer to NASA control the Army Ballistic Missile Agency's Development Operations Division personnel and facilities. The transfer, subject to congressional approval, would include the Saturn development program.

• Transfer of Saturn I project to NASA announced. - . Nation: USA. Related Persons: Eisenhower, von Braun. Program: Apollo. President Eisenhower announced his intention of transferring the Saturn project to NASA, which became effective on March 15, 1960..

• Plan for transferring the Army Ballistic Missile Agency and Saturn to NASA - . Nation: USA. Related Persons: Eisenhower, Glennan, von Braun. Program: Apollo.

  The initial plan for transferring the Army Ballistic Missile Agency and Saturn to NASA was drafted. It was submitted to President Dwight D. Eisenhower on December 1 1 and was signed by Secretary of the Army Wilber M. Brucker and Secretary of the Air Force James H. Douglas on December 16 and by NASA Administrator T. Keith Glennan on December 17.

• Engineering and cost study for a new Saturn configuration - . Nation: USA. Related Persons: von Braun. Program: Apollo.

  The Advanced Research Projects Agency ARPA and NASA requested the Army Ordnance Missile Command AOMC to prepare an engineering and cost study for a new Saturn configuration with a second stage of four 20,000-pound-thrust liquid-hydrogen and liquid-oxygen engines (later called the S-IV stage) and a modified Centaur third stage using two of these engines later designated the S-V stage). Additional Details: here....

• Army Ballistic Missile Agency mission possibilities - . Nation: USA. Related Persons: von Braun. Program: Apollo.

  H. H. Koelle told members of the Research Steering Committee of mission possibilities being considered at the Army Ballistic Missile Agency. These included an engineering satellite, an orbital return capsule, a space crew training vehicle, a manned orbital laboratory, a manned circumlunar vehicle, and a manned lunar landing and return vehicle. He described the current Saturn configurations, including the "C" launch vehicle to be operational in 1967. The Saturn C (larger than the C-1) would be able to boost 85,000 pounds into earth orbit and 25,000 pounds into an escape trajectory.

• Goett Committee - . Nation: USA. Program: Apollo. Class: Manned. Type: Manned space station. Committee formed to recommend post-Mercury space program. After four meetings, and studying earth-orbit assembly using Saturn II or direct ascent using Nova, tended to back development of Nova..

• Saturn upper stage study. - . Nation: USA. Related Persons: von Braun. Program: Apollo. NASA team completed study design of upper stages of Saturn launch vehicle..

• Lunar Exploration Program Based Upon Saturn Systems - . Nation: USA. Program: Apollo.

  The Army Ballistic Missile Agency submitted to NASA the study entitled "A Lunar Exploration Program Based Upon Saturn-Boosted Systems." In addition to the subjects specified in the preliminary report of October 1, 1959, it included manned lunar landings.

• Eleven companies submitted contract proposals for the Saturn second stage - . Nation: USA. Program: Apollo.

  Eleven companies submitted contract proposals for the Saturn second stage (S-IV): Bell Aircraft Corporation; The Boeing Airplane Company; Chrysler Corporation; General Dynamics Corporation, Convair Astronautics Division; Douglas Aircraft Company, Inc.; Grumman Aircraft Engineering Corporation; Lockheed Aircraft Corporation; The Martin Company; McDonnell Aircraft Corporation; North American Aviation, Inc.; and United Aircraft Corporation.

• Saturn I transferred to NASA. - . Nation: USA. Related Persons: von Braun. Program: Apollo.

  The Army Ballistic Missile Agency's Development Operations Division and the Saturn program were transferred to NASA after the expiration of the 60-day limit for congressional action on the President's proposal of January 14. (The President's decision had been made on October 21, 1959.) By Executive Order, the President named the facilities the "George C. Marshall Space Flight Center." Formal transfer took place on July 1.

• Two H-1's fired together. - . Nation: USA. Program: Apollo. Two of Saturn's first-stage engines passed initial static firing test of 7.83 seconds duration at Huntsville, Ala..

• Guidelines for an advanced manned spacecraft program presented by STG - . Nation: USA. Program: Apollo. Spacecraft: Apollo CSM, CSM ECS, CSM Source Selection.

  Members of STG presented guidelines for an advanced manned spacecraft program to NASA Centers to enlist research assistance in formulating spacecraft and mission design.

  To open these discussions, Director Robert R. Gilruth summarized the guidelines: manned lunar reconnaissance with a lunar mission module, corollary earth orbital missions with a lunar mission module and with a space laboratory, compatibility with the Saturn C-1 or C-2 boosters (weight not to exceed 15,000 pounds for a complete lunar spacecraft and 25,000 pounds for an earth orbiting spacecraft), 14-day flight time, safe recovery from aborts, ground and water landing and avoidance of local hazards, point (ten square-mile) landing, 72-hour postlanding survival period, auxiliary propulsion for maneuvering in space, a "shirtsleeve" environment, a three-man crew, radiation protection, primary command of mission on board, and expanded communications and tracking facilities. In addition, a tentative time schedule was included, projecting multiman earth orbit qualification flights beginning near the end of the first quarter of calendar year 1966.

• Guidelines for the advanced manned spacecraft program - . Nation: USA. Program: Apollo.

  STG's Robert O. Piland, during briefings at NASA Centers, presented a detailed description of the guidelines for missions, propulsion, and flight time in the advanced manned spacecraft program:

  1. The spacecraft should be capable ultimately of manned circumlunar reconnaissance. As a logical intermediate step toward future goals of lunar and planetary landing many of the problems associated with manned circumlunar flight would need to be solved.
  2. The lunar spacecraft should be capable of earth orbit missions for initial evaluation and training. The reentry component of this spacecraft should be capable of missions in conjunction with space laboratories or space stations. To accomplish lunar reconnaissance before a manned landing, it would be desirable to approach the moon closer than several thousand miles. Fifty miles appeared to be a reasonable first target for study purposes.
  3. The spacecraft should be designed to be compatible with the Saturn C-1 or C-2 boosters for the lunar mission. The multiman advanced spacecraft should not weigh more than 15,000 pounds including auxiliary propulsion and attaching structure.
  4. A flight-time capability of the spacecraft for 14 days without resupply should be possible. Considerable study of storage batteries, fuel cells, auxiliary power units, and solar batteries would be necessary. Items considered included the percentage of the power units to be placed in the "caboose" (space laboratory), preference for the use of storage batteries for both power and radiation shielding, and redundancy for reliability by using two different types of systems versus two of the same system.

• Four H-1's fired together. - . Nation: USA. Program: Apollo. Four of the eight H-1 engines of the Saturn C-1 first-stage booster were successfully static-fired at Redstone Arsenal for seven seconds..

• Douglas to build the second stage (S-IV) of the Saturn C-1 - . Nation: USA. Program: Apollo. NASA announced the selection of the Douglas Aircraft Company to build the second stage (S-IV) of the Saturn C-1 launch vehicle..

• All eight H-1 engines of the Saturn C-1 first stage ground-tested simultaneously - . Nation: USA. Program: Apollo. At Redstone Arsenal, all eight H-1 engines of the first stage of the Saturn C-1 launch vehicle were static-fired simultaneously for the first time and achieved 1.3 million pounds of thrust..

• First public demonstration of the H-1 engine - . Nation: USA. Program: Apollo. Eight H-1 engines of the first stage of the Saturn C-1 launch vehicle were static-fired for 35.16 seconds, producing 1.3 million pounds of thrust. This first public demonstration of the H-1 took place at Marshall Space Flight Center..

• Assembly of the first Saturn flight booster began - . Nation: USA. Related Persons: von Braun. Program: Apollo. Assembly of the first Saturn flight booster, SA-1, began at Marshall Space Flight Center..

• Full Saturn I engine cluster full duration test. - . Nation: USA. Program: Apollo. Complete eight-engine static firing of Saturn successfully conducted for 110 seconds at MSFC, the longest firing to date..

• Saturn C-1 first stage completed test series - . Nation: USA. Related Persons: von Braun. Program: Apollo. The Saturn C-1 first stage successfully completed its first series of static tests at the Marshall Space Flight Center with a 122-second firing of all eight H-1 engines..

• Space Exploration Program Council - . Nation: USA. Program: Apollo.

  The third meeting of the Space Exploration Program Council was held at NASA Headquarters. The question of a speedup of Saturn C-2 production and the possibility of using nuclear upper stages with the Saturn booster were discussed. The Office of Launch Vehicle Programs would plan a study on the merits of using nuclear propulsion for some of NASA's more sophisticated missions. If the study substantiated such a need, the amount of in-house basic research could then be determined.

• Apollo Study Bidder's Conference - . Nation: USA. Program: Apollo. Class: Moon. Type: Manned lunar spacecraft. Spacecraft: Apollo CSM, Apollo Lunar Landing, CSM ECS, CSM Source Selection. Bidder's conference for circumlunar Apollo. Specification: Saturn C-2 compatability (6,800 kg mass for circumlunar mission); 14 day flight time; three-man crew in shirt-sleeve environment..

• Space Exploration Program Council - . Nation: USA. Related Persons: Low, George. Program: Apollo.

  The fourth meeting of the Space Exploration Program Council was held at NASA Headquarters. The results of a study on Saturn development and utilization was presented by the Ad Hoc Saturn Study Committee. Objectives of the study were to determine (1) if and when the Saturn C-2 launch vehicle should be developed and (2) if mission and spacecraft planning was consistent with the Saturn vehicle development schedule. No change in the NASA Fiscal Year 1962 budget was contemplated. The Committee recommended that the Saturn C-2 development should proceed on schedule (S-II stage contract in Fiscal Year 1962, first flight in 1965). The C-2 would be essential, the study reported, for Apollo manned circumlunar missions, lunar unmanned exploration, Mars and Venus orbiters and capsule landers, probes to other planets and out-of- ecliptic, and for orbital starting of nuclear upper stages. Additional Details: here....

• Saturn I static firing. - . Nation: USA. Related Persons: von Braun. Program: Apollo. First of new series of static firings of Saturn considered only 50 percent successful in 2-second test at MSFC..

• Saturn transport barge commissioned. - . Nation: USA. Program: Apollo. Palaemon, a 180-foot barge built to transport the Saturn launch vehicle from MSFC to Cape Canaveral by water, was formally accepted by MSFC Director from Maj. Gen. Frank S. Besson, Chief of Army Transportation..

• USAF need for a space launch vehicle with 15,000 lb payload - . Headquarters USAF instructed AFBMD to continue its efforts to define the need for a space launch vehicle with a payload capacity between the Atlas/Centaur (9,000 lbs) and the early Saturn (19,000 lbs).

• Saturn C-1 changed to a two-stage configuration - . Nation: USA. Related Persons: von Braun. Program: Apollo. Wernher von Braun, Director of Marshall Space Flight Center, proposed that the Saturn C-1 launch vehicle be changed from a three-stage to a two-stage configuration to meet Apollo program schedules. The planned third stage (S-V) would be dropped..

• Saturn first stage recovery system study - . Nation: USA. Related Persons: von Braun. Program: Apollo. Marshall Space Flight Center awarded contracts to NAA and Ryan Aeronautical Corporation to investigate the feasibility of recovering the first stage (S-I) of the Saturn launch vehicle by using a Rogallo wing paraglider..

• Final report of the Low Committee - . Nation: USA. Related Persons: Seamans. Program: Apollo. Spacecraft: Apollo Lunar Landing.

  The Manned Lunar Landing Task Group (Low Committee) transmitted its final report to NASA Associate Administrator Robert C. Seamans, Jr. The Group found that the manned lunar landing mission could be accomplished during the decade, using either the earth orbit rendezvous or direct ascent technique. Multiple launchings of Saturn C-2 launch vehicles would be necessary in the earth orbital mode, while the direct ascent technique would require the development of a Nova-class vehicle. Information to be obtained through supporting unmanned lunar exploration programs, such as Ranger and Surveyor, was felt to be essential in carrying out the manned lunar mission. Total funding for the program was estimated at just under $7 billion through Fiscal Year 1968.

• Current Saturn launch vehicle configurations announced - . Nation: USA. Related Persons: von Braun. Program: Apollo.

  The current Saturn launch vehicle configurations were announced:

  C-1:

  S-I stage eight H-1 engines, 1.5 million pounds of thrust; S-IV stage four (LR-119 engines, 70,000 pounds of thrust); and S-V stage (two LR-119 engines, 35,000 pounds of thrust).

  C-2 (four-stage version):

  S-1 stage (same as first stage of the C-1); S-II (not determined); S-IV (same as second stage of the C-1); S-V (same as third Stage of C- 1).

  C-2 (three-stage version):

  S-I (same as first stage of C-1); S-II (not determined); and S-IV (same as third stage of C-1).

• First flight Saturn I on test stand. - . Nation: USA. Program: Apollo. First flight model of Saturn booster (SA-1) installed on static test stand for preflight checkout, Marshall Space Flight Center, Huntsville..

• Configuration changes for the Saturn C-1 launch vehicles - . Nation: USA. Related Persons: von Braun. Program: Apollo.

  Representatives of Marshall Space Flight Center recommended configuration changes for the Saturn C-1 launch vehicles to NASA Headquarters. These included:

  • Elimination of third-stage development, since two stages could put more than ten tons into earth orbit.
  • Use of six LR-115 (15,000-pound) Centaur engines (second-stage thrust thus increased from 70,000 to 90,000 pounds).
  • Redesign of the first stage (S-1) to offer more safety for manned missions.
  Plans were also presented to accelerate the development of the Saturn C- 2, and a recommendation was made that a prime contractor be selected to work on the second stage (S-II) of the C-2. NASA Headquarters approved the C-2 plans on March 31.

• RIFT flight briefed to contractors. - . Nation: USA. Program: NERVA. Reactor-in-flight-test system (Rift) study, a part of the NASA-AEC program on nuclear rockets, was briefed by contractors at NASA headquarters..

• Dynasoar launch by Saturn I studied. - . Nation: USA. Related Persons: von Braun. Class: Manned. Type: Manned spaceplane. Spacecraft: Dynasoar. Final NASA report on the study proposed for Saturn for use as Dyna-Soar booster was presented to the Air Force..

• Saturn I fight qualification. - . Nation: USA. Program: Apollo. The first successful flight qualification test of the Saturn SA-1 booster took place in an eight-engine test lasting 30 seconds..

• Air transport of the Saturn C-1 second stage feasible - . Nation: USA. Related Persons: von Braun. Program: Apollo. The Douglas Aircraft Company reported that air transport of the Saturn C-1 second stage (S-IV) was feasible..

• Ad Hoc Task Group for a Manned Lunar Landing Study - . Nation: USA. Program: Apollo.

  NASA Associate Administrator Robert C. Seamans, Jr., established the Ad Hoc Task Group for a Manned Lunar Landing Study, to be chaired by William A. Fleming of NASA Headquarters. The study was expected to produce the following information:

  • All tasks associated with the mission.
  • Interdependent time-phasing of the tasks.
  • Areas requiring considerable technological advancements from the current state of the art.
  • Tasks for which multiple approach solutions were advisable.
  • Important action and decision points in the mission plan.
  • A refined estimate by task and by fiscal year of the dollar resources required for the mission.
  • Refined estimates of in-house manpower requirements, by task and by fiscal year
  • Tentative in-house and contractor task assignments accompanying the dollar and manpower resource requirements.
  The study began on May 8 and the final report was submitted on June 16. Guidelines served as a starting point for the study:
  • The manned lunar landing target date was 1967.
  • Intermediate missions of multiman orbital satellites and manned circumlunar missions were desirable at the earliest possible time.
  • Man's mission on the moon as it affected the study was to be determined by the Ad Hoc Task Group - i.e., the time to be spent on the lunar surface and the tasks to be performed while there.
  • In establishing the mission plan, the use of the Saturn C-2 launch vehicle was to be evaluated as compared with an alternative launch vehicle having a higher thrust first stage and C-2 upper-stage components.
  • The mission plan was to include parallel development of liquid and solid propulsion leading to a Nova vehicle 400,000 pounds in earth orbit and should indicate when the decision should be made on the final Nova configuration.
  • Nuclear-powered launch vehicles should not be considered for use in the first manned lunar landing mission.
  • The flight test program should be laid out with enough launchings to meet the needs of the program considering the reliability requirements.
  • Alternative approaches should be provided in critical areas - e.g., upper stages and mission modes.

  The engineering sketch drawn by John D. Bird of Langley Research Center on May 3, 1961, indicated the thinking of that period: By launching two Saturn C-2's, the lunar landing mission could be accomplished by using both earth rendezvous and lunar rendezvous at various stages of the mission.

• S-IV satisfactory for Apollo missions - . Nation: USA. Program: Apollo.

  After study and discussion by STG and Marshal! Space Flight Center officials, STG concluded that the current 154-inch diameter of the second stage (S-IV) adapter for the Apollo spacecraft would be satisfactory for the Apollo missions on Saturn flights SA-7, SA-8, SA-9, and SA-10.

• Change in the Saturn C-1 configuration - . Nation: USA. Related Persons: von Braun. Program: Apollo.

  NASA announced a change in the Saturn C-1 vehicle configuration. The first ten research and development flights would have two stages, instead of three, because of the changed second stage (S-IV) and, starting with the seventh flight vehicle, increased propellant capacity in the first stage (S-1) booster.

• Saturn I transport route interdicted. - . Nation: USA. Program: Apollo. Collapse of a lock in the Wheeler Dam below Huntsville on the Tennessee River interdicted the planned water route of the first Saturn space booster from Marshall Space Flight Center to Cape Canaveral on the barge Palaemon..

• Saturn I launch complex completed. - . Nation: USA. Related Persons: von Braun. Program: Apollo.

  Huge Saturn launch complex at Cape Canaveral dedicated in brief ceremony by NASA, construction of which was supervised by the Army Corps of Engineers. Giant gantry, weighing 2,800 tons and being 310 feet high, is largest movable land structure in North America.

• Lundin Committee recommended earth orbit rendezvous mode - . Nation: USA. Related Persons: Seamans. Program: Apollo. Spacecraft: Apollo Lunar Landing.

  'The Lundin Committee completed its study of various vehicle systems for the manned lunar landing mission, as requested on May 25 by NASA associate Administrator Robert C. Seamans, Jr. The Committee had considered alternative methods of rendezvous: earth orbit, lunar orbit, a combination of earth and lunar orbit, and lunar surface. Launch vehicles studied were the Saturn C-2 and C-3. Conclusion was that 43,000 kg stage (85% fuel) was needed for a lunar landing mission. The concept of a low- altitude earth orbit rendezvous using two or three C-3's was clearly preferred by the Committee. Reasons for this preference were the small number of launches and orbital operations required and the fact that the Saturn C- 3 was considered to be an efficient launch vehicle of great utility and future growth.

• First decision on Apollo launch vehicles - . Nation: USA. Related Persons: Webb. Program: Apollo. Class: Manned. Type: Manned space station. Spacecraft: Apollo Lunar Landing.

  Meeting with Webb/Dryden, work on Saturn C-2 stopped; preliminary design of C-3 and continuing studies of larger vehicles for landing missions requested. STG push for 4 x 6.6 m diameter solid cluster first stage rejected for safety and ground handling reasons.

• Saturn C-1 to be operational in 1964 - . Nation: USA. Related Persons: von Braun. Program: Apollo. NASA announced that the Saturn C-1 launch vehicle, which could place ten-ton payloads in earth orbit, would be operational in 1964..

• Saturn C-2 discontinued - . Nation: USA. Related Persons: von Braun. Program: Apollo. Spacecraft: Apollo Lunar Landing.

  NASA announced that further engineering design work on the Saturn C-2 configuration would be discontinued and that effort instead would be redirected toward clarification of the Saturn C-3 and Nova concepts. Investigations were specifically directed toward determining capabilities of the proposed C-3 configuration in supporting the Apollo mission.

• Saturn I barge replacement. - . Nation: USA. Program: Apollo. A Navy YFNB barge was obtained by NASA to serve as a replacement for the Palaemon in transporting of the Saturn booster to Cape Canaveral..

• Changes in Saturn launch vehicle configurations - . Nation: USA. Related Persons: von Braun. Program: Apollo. Changes in Saturn launch vehicle configurations were announced :

  C-1:

  Stages S-I (1.5 million pounds of thrust) and S-IV

  C-2:

  Stages S-I, S-II, and S-IV

  C-3:

  Stages S-IB (3 million pounds of thrust), S-II, and S-IV.

  .

• NASA invitation to bids for Apollo prime contract - . Nation: USA. Program: Apollo. Spacecraft: Apollo CSM, CSM Original Specification, CSM Source Selection.

  NASA invited 12 companies to submit prime contractor proposals for the Apollo spacecraft by October 9: The Boeing Airplane Company, Chance Vought Corporation, Douglas Aircraft Company, General Dynamics/Convair, the General Electric Company, Goodyear Aircraft Corporation, Grumman Aircraft Engineering Corporation, Lockheed Aircraft Corporation, McDonnell Aircraft Corporation, The Martin Company, North American Aviation, Inc., and Republic Aviation Corporation. Additional Details: here....

• The NASA-DoD Large Launch Vehicle Planning Group. - . The NASA-DoD Large Launch Vehicle Planning Group met to study policy management and requirements for launch vehicles up to the size of Saturn..

• First Saturn I leaves factory. - . Nation: USA. Related Persons: von Braun. Program: Apollo. First Saturn (SA-1) booster began water trip to Cape Canaveral on Navy barge Compromise after overland detour around Wheeler Dam..

• First Saturn I arrives at Cape Canaveral. - . Nation: USA. Related Persons: von Braun. Program: Apollo. Navy barge Compromise, carrying first Saturn booster, stuck in the mud in the Indian River just south of Cape Canaveral. Released several hours later, the Saturn was delayed only 24 hours in its 2,200-mile journey from Huntsville..

• Nation: USA. Agency: NASA. Apogee: 136 km (84 mi).

  Largest known rocket launch to date, the Saturn I 1st stage booster, successful on first test flight from Atlantic Missile Range. With its eight clustered engines developing almost 1.3 million pounds of thrust at launch, the Saturn (SA-1) hurled waterfilled dummy upper stages to an altitude of 84.8 miles and 214.7 miles down range. In a postlaunch statement, Administrator Webb said: "The flight today was a splendid demonstration of the strength of our national space program and an important milestone in the buildup of our national capacity to launch heavy payloads necessary to carry out the program projected by President Kennedy on May 25.".

• Contract issued for build of 20 Saturn I's. - . Nation: USA. Related Persons: von Braun. Program: Apollo.

  NASA announced that the Chrysler Corporation had been chosen to build 20 Saturn first-stage (S-1) boosters similar to the one tested successfully on October 27 . They would be constructed at the Michoud facility near New Orleans, La. The contract, worth about $200 million, would run through 1966, with delivery of the first booster scheduled for early 1964.

• Kiwi B-1A tests completed. - . Nation: USA. Program: NERVA.

  Power run completed the test series on the Kiwi B-1A reactor system being conducted at the Nevada Test Site by AEC's Los Alamos Scientific Laboratory. Fourth in a series of test reactors in the joint AEC-NASA nuclear rocket propulsion program, Kiwi B-1A was disassembled for examination at the conclusion of the test runs.

• Support service contractor selected for Michoud. - . Nation: USA. Program: Apollo.

  NASA selected Mason-Rust as the contractor to provide support services at NASA's Michoud plant near New Orleans, providing housekeeping services through June 30, 1962 for the three contractors who would produce the Saturn S-I and S-IB boosters and the Rift nuclear upper-stage vehicle.

• Nation: USA. Agency: NASA. Apogee: 145 km (90 mi).

  Second suborbital test of Saturn I. The Saturn SA-2 first stage booster was launched successfully from Cape Canaveral. The rocket was blown up intentionally and on schedule about 2.5 minutes after liftoff at an altitude of 65 miles, dumping the water ballast from the dummy second and third stages into the upper atmosphere. The experiment, Project Highwater, produced a massive ice cloud and lightning-like effects. The eight clustered H-1 engines in the first stage produced 1.3 million pounds of thrust and the maximum speed attained by the booster was 3,750 miles per hour. Modifications to decrease the slight fuel sloshing encountered near the end of the previous flight test were successful.

• S-IV successfully static-fired for the first time - . Nation: USA. Related Persons: von Braun. Program: Apollo. The second stage (S-IV) of the Saturn C-1 launch vehicle was successfully static-fired for the first time in a ten-second test at the Sacramento, Calif., facility by the Douglas Aircraft Company..

• Nation: USA. Agency: NASA. Apogee: 167 km (103 mi).

  Third suborbital test of Saturn I. Saturn-Apollo 3 (Saturn C-1, later called Saturn I) was launched from the Atlantic Missile Range. Upper stages of the launch vehicle were filled with 23000 gallons of water to simulate the weight of live stages. At its peak altitude of 167 kilometers (104 miles), four minutes 53 seconds after launch, the rocket was detonated by explosives upon command from earth. The water was released into the ionosphere, forming a massive cloud of ice particles several miles in diameter. By this experiment, known as "Project Highwater," scientists had hoped to obtain data on atmospheric physics, but poor telemetry made the results questionable. The flight was the third straight success for the Saturn C-1 and the first with maximum fuel on board.

• Unmanned Apollo spacecraft to be flown on Saturn C-1 - . Nation: USA. Program: Apollo. MSC and OMSF agreed that an unmanned Apollo spacecraft must be flown on the Saturn C-1 before a manned flight. SA-10 was scheduled to be the unmanned flight and SA-111, the first manned mission..

• Saturn engine-out capability investigated - . Nation: USA. Program: Apollo.

  At a meeting of the MSC-MSFC Flight Mechanics Panel, it was agreed that Marshall would investigate "engine-out" capability (i.e., the vehicle's performance should one of its engines fail) for use in abort studies or alternative missions. Not all Saturn I, IB, and V missions included this engine-out capability. Also, the panel decided that the launch escape system would be jettisoned ten seconds after S-IV ignition on Saturn I launch vehicles.

• North American completed Apollo boilerplate (BP) 9 - . Nation: USA. Program: Apollo. Spacecraft: Apollo CSM, CSM LES.

  North American completed construction of Apollo boilerplate (BP) 9, consisting of launch escape tower and CSM. It was delivered to MSC on March 18, where dynamic testing on the vehicle began two days later. On April 8, BP-9 was sent to MSFC for compatibility tests with the Saturn I launch vehicle.

• First long-duration static test of Saturn SA-5 first stage - . Nation: USA. Program: Apollo.

  The first stage of the Saturn SA-5 launch vehicle was static fired at MSFC for 144.44 seconds in the first long-duration test for a Block II S-1. The cluster of eight H-1 engines produced 680 thousand kilograms (1.5 million pounds) of thrust. An analysis disclosed anomalies in the propulsion system. In a final qualification test two weeks later, when the engines were fired for 143.47 seconds, the propulsion problems had been corrected.

• Nation: USA. Agency: NASA. Apogee: 129 km (80 mi).

  Fourth suborbital test of Saturn I. The S-I Saturn stage reached an altitude of 129 kilometers (80 statute miles) and a peak velocity of 5,906 kilometers (3,660 miles) per hour. This was the last of four successful tests for the first stage of the Saturn I vehicle. After 100 seconds of flight, No. 5 of the booster's eight engines was cut off by a preset timer. That engine's propellants were rerouted to the remaining seven, which continued to burn. This experiment confirmed the "engine-out" capability that MSFC engineers had designed into the Saturn I.

• Large Solid Rocket Motor Program (Program 623A) begun. - .

  The Defense Department announced the selection of Thiokol Chemical Corporation, Aerojet-General Corporation, and Lockheed Propulsion Company to conduct work on the development of large solid-propellant motors as part of the Space Systems Division's Large Solid Rocket Motor Program (Program 623A). Development work was divided into four tasks: (1) Thiokol and Aerojet-General were to develop 260-inch diameter, solid rocket motors of 3 million pounds of thrust for demonstration static firings; (2) Thiokol was to work on a 156-inch, 3 million-pound thrust, two-segment solid rocket motor; (3) Thiokol was to develop and static fire a 156-inch, one-segment solid rocket motor of one million pounds thrust demonstrating thrust vector control (TVC) through movable nozzles; and (4) Lockheed was to static fire a 156-inch, single segment solid rocket motor of one million pounds thrust that demonstrated TVC through jet tabs.

• First static firing test of Saturn S-IV stage for SA-5 - . Nation: USA. Program: Apollo.

  In what was to have been an acceptance test, the Douglas Aircraft Company static fired the first Saturn S-IV flight stage at Sacramento, Calif. An indication of fire in the engine area forced technicians to shut down the stage after little more than one minute's firing. A week later the acceptance test was repeated, this time without incident, when the vehicle was fired for over seven minutes. (The stage became part of the SA-5 launch vehicle, the first complete Saturn I to fly.)

• Apollo launch escape system modified - . Nation: USA. Program: Apollo. The launch escape system was modified so that, under normal flight conditions, the crew could jettison the tower. On unmanned Saturn I flights, tower jettison was initiated by a signal from the instrument unit of the S-IV (second) stage..

• 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.

• Manned Saturn I earth orbital flights canceled - . Nation: USA. Related Persons: Mueller, Webb. Program: Apollo. Spacecraft: Apollo Lunar Landing.

  NASA canceled four manned earth orbital flights with the Saturn I launch vehicle. Six of a series of 10 unmanned Saturn I development flights were still scheduled. Development of the Saturn IB for manned flight would be accelerated and "all-up" testing would be started. This action followed Bellcomm's recommendation of a number of changes in the Apollo spacecraft flight test program. The program should be transferred from Saturn I to Saturn IB launch vehicles; the Saturn I program should end with flight SA-10. All Saturn IB flights, beginning with SA-201, should carry operational spacecraft, including equipment for extensive testing of the spacecraft systems in earth orbit.

  Associate Administrator for Manned Space Flight George E. Mueller had recommended the changeover from the Saturn I to the Saturn IB to NASA Administrator James E. Webb on October 26. Webb's concurrence came two days later.

• Uprated H-1 engine for the first stage of the Saturn IB - . Nation: USA. Program: Apollo.

  MSFC directed Rocketdyne to develop an uprated H-1 engine to be used in the first stage of the Saturn IB. In August, Rocketdyne had proposed that the H-1 be uprated from 85,275 to 90,718 kilograms (188,000 to 200,000 pounds) of thrust. The uprated engine promised a 907-kilogram (2,000 pound) increase in the Saturn IB's orbital payload, yet required no major systems changes and only minor structural modifications.

• Saturn 5 - . Payload: Saturn-SA 5. Mass: 17,100 kg (37,600 lb). Nation: USA. Agency: NASA Huntsville. Program: Apollo. Class: Technology. Type: Re-entry test vehicle. Spacecraft: Jupiter nose cone. Decay Date: 1966-04-30 . USAF Sat Cat: 744 . COSPAR: 1964-005A. Apogee: 740 km (450 mi). Perigee: 274 km (170 mi). Inclination: 31.40 deg. Period: 94.80 min.

  First first mission of Block II Saturn with two live stages. SA-5, a vehicle development flight, was launched from Cape Kennedy Complex 37B at 11:25:01.41, e.s.t. This was the first flight of the Saturn I Block II configuration (i.e., lengthened fuel tanks in the S-1 and stabilizing tail fins), as well as the first flight of a live (powered) S-IV upper stage. The S-1, powered by eight H-1 engines, reached a full thrust of over 680,400 kilograms (1.5 million pounds) the first time in flight. The S-IV's 41,000 kilogram (90,000-pound-thrust cluster of six liquid-hydrogen RL-10 engines performed as expected. The Block II SA-5 was also the first flight test of the Saturn I guidance system.

• American challenge - . Nation: Russia. Related Persons: Popovich, Tereshkova. Program: Lunar L1.

  Popovich has left on a tour of Australia, and Tereshkova is in England. The propaganda front of the Soviet space program is going well. But Kamanin is disquieted by the American testing of the Saturn I rocket. Its 17 tonne payload is more than double that of any Soviet booster. Greater efforts are needed, instead he is wasting his time editing Tereshkova's new book...

• 156-inch solid-propellant rocket motor fired for the first time. - .

  Lockheed Propulsion Company test fired a 156-inch diameter, solid-propellant rocket motor for the first time. The one-segment test motor (156-3-L), with tab jet thrust vector control, produced more than 900,000 pounds of thrust during its 110-second firing. The test was conducted as part of the Space Systems Division's Large Solid Rocket Motor research and development program (Program 623A).

• Saturn 6 - . Payload: Apollo CSM Boilerplate 13. Mass: 16,900 kg (37,200 lb). Nation: USA. Agency: NASA Houston. Program: Apollo. Class: Moon. Type: Manned lunar spacecraft. Spacecraft Bus: Apollo. Spacecraft: Apollo CSM, CSM Structural. Decay Date: 1964-06-01 . USAF Sat Cat: 800 . COSPAR: 1964-025A. Apogee: 204 km (126 mi). Perigee: 179 km (111 mi). Inclination: 31.70 deg. Period: 88.20 min. Apollo Saturn Mission A-101, using CM BP-13 atop SA-6 Saturn I launch vehicle, launched at Cape Kennedy, Fla., to prove spacecraft/launch vehicle compatibility. Boilerplate CSM, LM adapter, LES. LES jettison demonstrated..

• Saturn 7 - . Payload: Apollo CSM Boilerplate 15. Mass: 16,700 kg (36,800 lb). Nation: USA. Agency: NASA Houston. Program: Apollo. Class: Moon. Type: Manned lunar spacecraft. Spacecraft Bus: Apollo. Spacecraft: Apollo CSM, CSM Structural. Decay Date: 1964-09-22 . USAF Sat Cat: 883 . COSPAR: 1964-057A. Apogee: 215 km (133 mi). Perigee: 181 km (112 mi). Inclination: 31.70 deg. Period: 88.50 min. Apollo systems test. Third orbital test. First closed-loop guidance test..

• Second test firing of a 156-inch diameter, solid-propellant motor. - . In a second test firing, Lockheed Propulsion Company fired a 156-inch diameter, solid-propellant motor (156-4-L) for 140 seconds, and it produced over one million pounds of thrust..

• First 156-inch solid rocket motor fired - .

  Thiokol Chemical Corporation's Wasatch Division fired its first 156-inch, one-segment, solid rocket motor (156-1-T) with gimballed nozzle thrust vector control. The motor produced approximately 1.3 million pounds of thrust for two minutes. This was the third test firing of a 156-inch solid rocket motor in Space Systems Division's Large Solid Rocket Motor Program (Program 623A).

• Requirements for Apollo spacecraft launched by Saturn IB assessed - . Nation: USA. Related Persons: Phillips, Samuel. Program: Apollo.

  At the request of Maj. Gen. Samuel C. Phillips, Apollo Program Director, ASPO reexamined the performance requirements for spacecraft slated for launch with Saturn IBs. MSC currently assessed that the launch vehicle was able to put 16,102 kg (35,500 lbs) into a circular orbit 105 nm above the earth. Based on the spacecraft control weights, however, it appeared that the total injected weight of the modules would exceed this amount by some 395 kg (870 lbs). Additional Details: here....

• Pegasus 1 - . Payload: Pegasus 1. Mass: 10,400 kg (22,900 lb). Nation: USA. Agency: NASA Huntsville. Program: Apollo. Class: Earth. Type: Micrometeoroid satellite. Spacecraft: Pegasus satellite. Decay Date: 1978-09-17 . USAF Sat Cat: 1085 . COSPAR: 1965-009A. Apogee: 726 km (451 mi). Perigee: 510 km (310 mi). Inclination: 31.70 deg. Period: 97.00 min.

  A Saturn I vehicle SA-9 launched a multiple payload into a high 744 by 496 km (462 by 308 mi) earth orbit. The rocket carried a boilerplate (BP) CSM (BP-16) and, fitted inside the SM, the Pegasus I meteoroid detection satellite. This was the eighth successful Saturn flight in a row, and the first to carry an active payload. BP-16's launch escape tower was jettisoned following second-stage S-IV ignition. After attaining orbit, the spacecraft were separated from the S-IV. Thereupon the Pegasus I's panels were deployed and were ready to perform their task, i.e., registering meteoroid impact and relaying the information to the ground.

• Apollo-Model 3 - . Payload: Apollo CSM Boilerplate 16. Nation: USA. Agency: NASA Houston. Program: Apollo. Class: Moon. Type: Manned lunar spacecraft. Spacecraft: Apollo CSM, CSM Structural. Decay Date: 1985-07-10 . USAF Sat Cat: 1088 . COSPAR: 1965-009B. Apogee: 736 km (457 mi). Perigee: 500 km (310 mi). Inclination: 31.70 deg. Period: 97.06 min.

• Chrysler contract for support services for the Saturn I and IB launch programs modified - . Nation: USA. Program: Apollo. KSC supplemented Chrysler Corporation's contract for support services for the Saturn I and IB launch programs. Effective through June 30, 1968, the agreement would cost NASA $41 million plus an award fee..

• Static-fireing of a two-segment, 156-inch diameter, 100-foot long solid-propellant rocket motor - .

  The Thiokol Chemical Corporation (Brunswick Division) static-fired a two-segment, 156-inch diameter, 100-foot long solid-propellant rocket motor (156-2-T). This 900,000-pound motor, the largest solid-propellant motor yet fired, generated over three million pounds of thrust for one minute, more than twice as much as any previous motor. This test firing was intended to validate design criteria for the 260-inch motor program that was officially transferred from Space Systems Division management to that of NASA's Lewis Research Center (LeRC) on 1 March.

• 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.

• First stage of the Saturn IB first static firing at MSFC - . Nation: USA. Program: Apollo.

  The first stage of the Saturn IB booster (the S-IB-1) underwent its first static firing at Huntsville, Alabama. The stage's eight uprated H-1 engines produced about 71,168-kilonewtons (1.6 million lbs) thrust. On April 23, Marshall and Rocketdyne announced that the uprated H-1 had passed qualification testing and was ready for flight.

• Thrust of the H-1 engine uprated - . Nation: USA. Program: Apollo. MSFC informed MSC that the thrust of the H-1 engine was being uprated to 1,000 kilonewtons (205,000 lbs), thus increasing the Saturn IB's payload capability..

• Mission directive for Apollo-Saturn 201 - . Nation: USA. Related Persons: Phillips, Samuel. Program: Apollo. Spacecraft: Apollo CSM. Samuel C. Phillips, Apollo Program Director, issued the mission directive for Apollo-Saturn 201. The mission would flight-test the Saturn IB and the Apollo CSM..

• Pegasus 2 - . Payload: Pegasus 2. Mass: 10,464 kg (23,069 lb). Nation: USA. Agency: NASA Huntsville. Program: Apollo. Class: Earth. Type: Micrometeoroid satellite. Spacecraft: Pegasus satellite. Decay Date: 1979-11-03 . USAF Sat Cat: 1381 . COSPAR: 1965-039A. Apogee: 740 km (450 mi). Perigee: 502 km (311 mi). Inclination: 31.70 deg. Period: 97.00 min.

  Pegasus 2 was a meteoroid detection satellite. The Saturn I launch vehicle (SA-8) placed the spacecraft, protected by a boilerplate CSM (BP-26), into a 740-by-509-km (460-by-316-mi) orbit. Once in orbit, the dummy CSM was jettisoned. Pegasus 2, still attached to the second stage of the launch vehicle, then deployed its 29-m (96-ft) winglike panels. Within several hours, the device began registering meteoroid hits.

• Apollo-Model 4 - . Payload: Apollo CSM Boilerplate 26. Nation: USA. Agency: NASA Houston. Program: Apollo. Class: Moon. Type: Manned lunar spacecraft. Spacecraft: Apollo CSM, CSM Structural. Decay Date: 1989-07-08 . USAF Sat Cat: 1385 . COSPAR: 1965-039B. Apogee: 739 km (459 mi). Perigee: 511 km (317 mi). Inclination: 31.70 deg. Period: 97.21 min.

• 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....

• Reduced Apollo Block II service propulsion system for Saturn IB missions - . Nation: USA. Program: Apollo. Spacecraft: Apollo CSM, CSM Block II.

  Independent studies were made at MSC and North American to determine effects and impact of off-loading certain Block II service propulsion system components for Saturn IB missions. The contractor was requested to determine the weight change involved and schedule and cost impact of removing one oxidizer tank, one fuel tank, one helium tank and all associated hardware (fuel and oxidizer transfer lines, propellant quantity sensors and certain gaging wire harnesses) from CSM 101 and CSM 103. The MSC study was oriented toward determining technical problems associated with such a change and the effects on spacecraft operational requirements. The North American study indicated that removing the equipment would save about 690 000, along with a weight reduction of approximately 454 kg (1,000 lbs). Additional Details: here....

• Planned missions for the Saturn IB - . Nation: USA. Program: Apollo.

  Officials from Bellcomm, MSFC, and the Apollo offices in Houston and in Washington planned primary and alternate missions for the Saturn IB (applicable to SA-201 through SA-208). On July 16, the Office of Manned Space Flight specified launch vehicles (both Saturn IB and V hardware) for Apollo missions.

• Col Bolender Mission Director for the first and second Apollo/Saturn IB flights - . Nation: USA. Program: Apollo. NASA announced the appointment of Col. C. H. Bolender as Mission Director for the first and second Apollo/Saturn IB flights. Bolender was assigned to the Mission Operations Organization in the Office of Manned Space Flight, NASA..

• No structural changes required for uprated Saturn IB's H-1 engine - . Nation: USA. Program: Apollo.

  North American reported to MSC that no structural changes to the spacecraft would be required for uprating the thrust of the Saturn IB's H-1 engine from 90,718 to 92,986 kg (200,000 to 205,000 lbs). Effects on the performance of the launch escape vehicle would be negligible.

• Performance of the Apollo launch escape vehicle evaluated - . Nation: USA. Program: Apollo.

  During the preceding six months, officials in ASPO and the Engineering and Development Directorate evaluated the performance of the launch escape vehicle (LEV) during aborts on and near the launch pad. That performance, they had determined, was inadequate. To solve this problem, MSC ordered North American to incorporate a number of design changes in both the LEV and the spacecraft:

  • provide the capability for manual override of the main parachute deployment timer and for manual deployment of those parachutes (for both Saturn IB and V flights)
  • Provide for dumping helium from the CM's reaction control system (RCS) automatically
  • Modify the CM RCS to permit rapid dumping of its fuel (similar to the existing oxidizer dump). But fuel and oxidizer must not be dumped simultaneously. (This change applied only to Block II CMs.)
  • Provide the capability to cut out the LEV's pitch control motor on Block I vehicles (similar to that already in Block II spacecraft)
  • Design a removable device that, while on the pad, would keep the launch escape motor's propellant temperature above 70 degrees.

• Pegasus 3 - . Payload: Pegasus 3. Mass: 10,500 kg (23,100 lb). Nation: USA. Agency: NASA Huntsville. Program: Apollo. Class: Earth. Type: Micrometeoroid satellite. Spacecraft: Pegasus satellite. Decay Date: 1969-08-04 . USAF Sat Cat: 1467 . COSPAR: 1965-060A. Apogee: 449 km (278 mi). Perigee: 441 km (274 mi). Inclination: 28.90 deg. Period: 93.40 min.

  NASA launched Pegasus 3, third of the meteoroid detection satellites, as scheduled at 8:00 a.m. EST, from Cape Kennedy. As earlier, an Apollo spacecraft (boilerplate 9) served as the payload's shroud. This flight (SA-10) marked the end of the Saturn I program, which during its seven-year lifetime had achieved 10 straight successful launches and had contributed immeasurably to American rocket technology.

• Apollo-Model 5 - . Payload: Apollo CSM Boilerplate 9A. Nation: USA. Agency: NASA Houston. Program: Apollo. Class: Moon. Type: Manned lunar spacecraft. Spacecraft: Apollo CSM, CSM Structural. Decay Date: 1975-11-22 . USAF Sat Cat: 1468 . COSPAR: 1965-060B. Apogee: 536 km (333 mi). Perigee: 521 km (323 mi). Inclination: 28.80 deg. Period: 95.21 min.

• Launch schedule for Apollo-Saturn IB flights revised - . Nation: USA. Related Persons: Phillips, Samuel. Program: Apollo. Spacecraft: Apollo CSM, CSM Block I.

  Samuel C. Phillips, Apollo Program Director, notified the Center directors and Apollo program managers in Houston, Huntsville, and Cape Kennedy that OMSF's launch schedule for Apollo-Saturn IB flights had been revised, based on delivery of CSMs 009 and 011:

  • AS-201 - January 1966
  • AS-202 - June 1966
  Schedules for AS-203 through 205 (July and October 1966, and January 1967) were unchanged.

• Firing of the first flight-weight, 156-inch diameter, solid-propellant rocket motor - . Lockheed Propulsion Company test fired the first flight-weight, 156-inch diameter, solid-propellant rocket motor (156-5-L) of three million pounds of thrust. This was the fifth 156-inch motor test fired in the program, and the third Lockheed motor..

• Land impact program for the Apollo CM Block I deleted - . Nation: USA. Program: Apollo. Spacecraft: Apollo CSM, CSM Block II.

  A decision made at a Program Management Review eliminated the requirement for a land impact program for the CM to support Block I flights. Post-abort CM land impact for Saturn IB launches had been eliminated from Complex 37 by changes to the sequence timers in the launch escape system abort mode. The Certification Test Specification and related Certification Test Requirements would reflect the new Block II land impact requirements.

• Lockheed Propulsion Company fired its fourth 156-inch diameter, solid-propellant rocket motor. - .

  Motor 156-6-L was a monolithic motor with a high burn rate propellant and submerged nozzle. During its one minute test firing, the motor generated over three million pounds of thrust. This was the sixth test firing in Space Systems Division's Large Solid Rocket Motor Program (Program 623A).

• Apollo 201 (AS-201) - . Nation: USA. Agency: NASA. Apogee: 488 km (303 mi).

  Apollo-Saturn 201 was launched from Cape Kennedy, with liftoff of an Apollo Block I spacecraft (CSM 009) on a Saturn IB launch vehicle at 11:12:01 EST. Launched from Launch Complex 34, the unmanned suborbital mission was the first flight test of the Saturn IB and an Apollo spacecraft. Total launch weight was 22,000 kilograms.

  Spacecraft communications blackout lasted 1 minute 22 seconds. Reentry was initiated with a space-fixed velocity of 29,000 kilometers per hour. CM structure and heatshields performed adequately. The CM was recovered by the USS Boxer from the Atlantic about 72 kilometers uprange from the planned landing point. (8.18 S x 11.15 W).

• Changes in Saturn/Apollo nomenclature - . Nation: USA. Program: Apollo. Spacecraft: Apollo LM.

  A memo to KSC, MSC, and MSFC from the NASA Office of Manned Space Flight reported that the NASA Project Designation Committee had concurred in changes in Saturn/Apollo nomenclature recommended by Robert C. Seamans, Jr., George E. Mueller, and Julian Scheer:

  • lunar excursion module to be called lunar module.
  • Saturn IB to become the "uprated Saturn I."
  The memo instructed that the new nomenclature be used in all future news releases and announcements.

• Apollo 203 - . Payload: Saturn S-IVB-203. Mass: 26,500 kg (58,400 lb). Nation: USA. Agency: NASA Huntsville. Program: Apollo. Decay Date: 1966-07-05 . USAF Sat Cat: 2289 . COSPAR: 1966-059A. Apogee: 212 km (131 mi). Perigee: 183 km (113 mi). Inclination: 31.90 deg. Period: 88.50 min.

  First orbital test Saturn IB; no spacecraft. AS-203 lifted off from Launch Complex 37, Eastern Test Range, at 10:53 a.m. EDT in the second of three Apollo-Saturn missions scheduled before manned flight in the Apollo program. All objectives - to acquire flight data on the S-IVB stage and instrument unit - were achieved.

  The uprated Saturn I - consisting of an S-IB stage, S-IVB stage, and an instrument unit - boosted an unmanned payload into an original orbit of 185 by 189 kilometers. The inboard engine cutoff of the first stage occurred after 2 minutes 18 seconds of flight and the outboard engine cutoff was 4 seconds later. The S-IVB engine burned 4 minutes 50 seconds. No recovery was planned and the payload was expected to enter the earth's atmosphere after about four days.

• Chrysler uprated Saturn I first-stage production contract changed - . Nation: USA. Program: Apollo.

  NASA signed a supplemental agreement with Chrysler Corp.'s Space Division at New Orleans, La., converting the uprated Saturn I first-stage production contract from cost-plus-fixed-fee to cost-plus-incentive-fee. Under the agreement, valued at $339 million, the amount of the contractor's fee would be based on ability to perform assigned tasks satisfactorily and meet prescribed costs and schedules. The contract called for Chrysler to manufacture, assemble and test 12 uprated Saturn I first stages and provide system engineering, integration support, ground support equipment, and launch services.

• Apollo 202 (AS-202) - . Nation: USA. Agency: NASA. Apogee: 1,143 km (710 mi).

  Spacecraft 011 was essentially a Block I spacecraft with the following exceptions: couches, crew equipment, and the cabin postlanding ventilation were omitted; and three auxiliary batteries, a mission control programmer, four cameras, and flight qualification instrumentation were added.

  Of six primary test objectives assigned to the mission, the objectives for the environmental control, electrical power, and communications subsystems were not completely satisfied. All other spacecraft test objectives were successfully accomplished.

• First Apollo manned flight announced - . Nation: USA. Related Persons: Chaffee, Grissom, McDivitt, Schweickart, Scott, White. Program: Apollo. Flight: Apollo 204. Apollo-Saturn 204 was to be the first manned Apollo mission, NASA announced through the manned space flight Centers. . Additional Details: here....

• Apollo 204 - . Call Sign: Apollo 1. Crew: Chaffee, Grissom, White. Backup Crew: Cunningham, Eisele, McDivitt, Schirra, Schweickart, Scott. Payload: CSM-012. Nation: USA. Program: Apollo. Flight: Apollo 204. Spacecraft: Apollo CSM, Apollo Lunar Landing, CSM ECS, CSM Electrical.

  The first manned flight of the Apollo CSM, the Apollo C category mission, was planned for the last quarter of 1966. Numerous problems with the Apollo Block I spacecraft resulted in a flight delay to February 1967. The crew of Virgil I. Grissom, Edward H. White II, and Roger B. Chaffee, was killed in a fire while testing their capsule on the pad on 27 January 1967, still weeks away from launch. The designation AS-204 was used by NASA for the flight at the time; the designation Apollo 1 was applied retroactively at the request of Grissom's widow.

• Apollo AS-204 first steps - . Nation: USA. Related Persons: Shea. Program: Apollo. Flight: Apollo 204. Spacecraft: Apollo CSM, CSM Block I. Fire sweeping through command module 012 atop its Saturn IB launch vehicle at Launch Complex 34, KSC, took the lives of the three-man crew scheduled for the first manned Apollo space flight. . Additional Details: here....

• Apollo spacecraft delivery dates - . Nation: USA. Program: Apollo. Flight: Apollo 7. Spacecraft: Apollo LM, LM Structural. Spacecraft delivery date and ground rule discussions were summarized by MSC ASPO Manager George M. Low in a letter to North American Aviation's Apollo Program Manager Dale D. Myers. . Additional Details: here....

• Ninth 156-inch diameter, solid-propellant motor in Large Solid Rocket Motor Program fired. - .

  Thiokol Chemical Corporation's Wasatch Division test fired the ninth 156-inch diameter, solid-propellant motor in Space Systems Division's Large Solid Rocket Motor Program (Program 623A). Motor 156-9-T demonstrated a flexible seal thrust vector control system while generating more than one million pounds of thrust for one minute.

• AS-208 - . Payload: LM-2. Nation: USA. Program: Apollo. Class: Moon. Type: Manned lunar lander. Spacecraft: Apollo LM. Before fire, planned in-orbit test of LM. CSM-101 would dock with and crew would maneuver together..

• Minuteman strap-one for the Saturn IB were canceled. - . Nation: USA. Program: Skylab. Minuteman strap-one for the Saturn IB were canceled as part of the AAP. The studies for AAP on the feasibility of the Minuteman strap-one were terminated. .

• Designation Saturn IB approved - . Nation: USA. Related Persons: Webb. Program: Apollo. NASA Administrator James E. Webb approved the designation "Saturn IB" as the standard way of referring to that launch vehicle in public statements, congressional testimony, and similar materials, rather than "Uprated Saturn I.".

• Apollo 5 - . Payload: Apollo LM-1. Mass: 14,360 kg (31,650 lb). Nation: USA. Agency: NASA Houston. Program: Apollo. Class: Moon. Type: Manned lunar lander. Spacecraft: Apollo LM. Decay Date: 1968-02-12 . USAF Sat Cat: 3107 . COSPAR: 1968-007B. Apogee: 374 km (232 mi). Perigee: 169 km (105 mi). Inclination: 31.60 deg. Period: 89.90 min.

  NASA launched Apollo 5 - the first, unmanned LM flight - on a Saturn IB from KSC Launch Complex 37B at 5:48:08 p.m. EST. Mission objectives included verifying operation of the LM structure itself and its two primary propulsion systems, to evaluate LM staging, and to evaluate orbital performances of the S-IVB stage and instrument unit. Flight of the AS-204 launch vehicle went as planned, with nosecone (replacing the CSM) jettisoned and LM separating. Flight of LM-1 also went as planned up to the first descent propulsion engine firing. Because velocity increase did not build up as quickly as predicted, the LM guidance system shut the engine down after only four seconds of operation, boosting the LM only to a 171 x 222 km orbit. Mission control personnel in Houston and supporting groups quickly analyzed the problem. They determined that the difficulty was one of guidance software only (and not a fault in hardware design) and pursued an alternate mission plan that ensured meeting the minimum requirements necessary to achieve the primary objectives of the mission. The ascent stage separated and boosted itself into a 172 x 961 km orbit. After mission completion at 2:45 a.m. EST January 23, LM stages were left in orbit to reenter the atmosphere later and disintegrate. Apollo program directors attributed success of the mission to careful preplanning of alternate ways to accomplish flight objectives in the face of unforeseen events.

• 10th, and final, 156-inch diameter, solid-propellant rocket motor fired. - .

  Thiokol-Wasatch Division test fired the 10th, and final, 156-inch diameter, solid-propellant rocket motor (156-8-T). The motor developed one million pounds of thrust during its 118-second firing, which tested a segmented fiberglass case and non-hydroclaved nozzle provided by the Air Force Materials Laboratory (AFML). This test firing completed the Large Solid Rocket Motor Program (Program 623A) begun under Space Systems Division management in 1963.

• Check out and launch the remaining Saturn IB vehicle inventory. - . Nation: USA. Program: Skylab.

  MSFC and KSC officials agreed upon procedures for maintaining the capability to check out and launch the remaining Saturn IB vehicle inventory. Their joint recommendations included a phasedown on contractor activity following the AS 205 launch; deactivation of Launch Complexes 34 and 37 to allow maximum storage of equipment and minimum maintenance on items remaining in place; and continuance of KSC analysis of manpower required to support the AAP dual launch requirement, with contractor participation at the earliest date.

• All changes to Apollo 7 as a result of Apollo 1 fire completed - . Nation: USA. Program: Apollo. Flight: Apollo 7. Spacecraft: Apollo CSM, CSM Block II. NASA Apollo Mission Director William C. Schneider reported completion of all action items pertinent to Apollo 7 assigned by Apollo Program Director Samuel C. Phillips as a result of recommendations by the Apollo Crew Safety Review Board on May 27, 1968.. Additional Details: here....

• Apollo 7 - . Call Sign: Apollo 7. Crew: Cunningham, Eisele, Schirra. Backup Crew: Cernan, Stafford, Young. Payload: Apollo CSM 101 / S-IVB-205. Mass: 14,674 kg (32,350 lb). Nation: USA. Agency: NASA Houston. Program: Apollo. Class: Moon. Type: Manned lunar spacecraft. Flight: Apollo 7. Spacecraft: Apollo CSM. Duration: 10.84 days. Decay Date: 1968-10-22 . USAF Sat Cat: 3486 . COSPAR: 1968-089A. Apogee: 306 km (190 mi). Perigee: 229 km (142 mi). Inclination: 31.60 deg. Period: 89.90 min.

  Apollo 7 (AS-205), the first manned Apollo flight, lifted off from Launch Complex 34 at Cape Kennedy Oct. 11, carrying Walter M. Schirra, Jr., Donn F. Eisele, and R. Walter Cunningham. The countdown had proceeded smoothly, with only a slight delay because of additional time required to chill the hydrogen system in the S-IVB stage of the Saturn launch vehicle. Liftoff came at 11:03 a.m. EDT. Shortly after insertion into orbit, the S-IVB stage separated from the CSM, and Schirra and his crew performed a simulated docking with the S-IVB stage, maneuvering to within 1.2 meters of the rocket. Although spacecraft separation was normal, the crew reported that one adapter panel had not fully deployed. Two burns using the reaction control system separated the spacecraft and launch stage and set the stage for an orbital rendezvous maneuver, which the crew made on the second day of the flight, using the service propulsion engine.

  Crew and spacecraft performed well throughout the mission. During eight burns of the service propulsion system during the flight, the engine functioned normally. October 14, third day of the mission, witnessed the first live television broadcast from a manned American spacecraft.

• Management of the Saturn IB project and AAP-assigned spacecraft was transferred from the Apollo program to AAP. - . Nation: USA. Program: Skylab.

  Management of the Saturn IB project and AAP-assigned spacecraft was transferred from the Apollo program to AAP. This transfer of management responsibility included Saturn IB launch vehicles SA-206 through SA-212 and Saturn IB unique spares and unique facilities. The Apollo program would continue to fund the Saturn IB effort through FY 1969, except for that effort unique to AAP. Beginning in FY 1970, the Saturn IB funding would be an AAP responsibility. This transfer of responsibilities placed management of the Saturn IB project under control of the program that would use it and relieved Apollo management of some responsibilities, allowing more time for concentration on the mainline Apollo program.

• Saturn IB AAP launches from LC-37 - . Nation: USA. Program: Skylab.

  KSC officials and AAP managers recommended to the Manned Space Flight Management Council that the Saturn IB AAP launches take place from LC-37 rather than LC-34. They were incorporating the recommendation into the latest program operating plan proposals. If the recommendation were accepted, LC-34 would be partially deactivated and placed in a 'down- mode' condition.

• Study on launching S-IB vehicles from LC-39. - . Nation: USA. Program: Skylab.

  A major study was performed by KSC, The Boeing Company, and Chrysler Corporation to determine the feasibility of launching S-IB vehicles from LC-39. Major facilities and equipment needed to convert LC-39 to an elevated pedestal configuration were studied, as well as estimated cost figures, program schedules, and interrelationships with other NASA programs. The study indicated that use of the elevated pedestal concept in LC-39 appeared technically and operationally feasible. However, because of the close operational coupling of the Apollo and AAP if this concept were implemented, it was decided to defer further consideration of this concept.

• LC-34 would be used for Saturn IB-related AAP manned launches. - . Nation: USA. Related Persons: Debus. Program: Skylab.

  KSC Director Kurt H. Debus announced that LC-34 would be used for Saturn IB-related AAP manned launches (scheduled to begin in mid-1972), while LC-37 would be placed in a semi- deactivated 'minimum maintenance' condition. Thomas W. Morgan, AAP Manager of the Florida Center, said that design of modifications to LC-34 to meet the needs of AAP would begin on 1 January 1970, while the modifications to the pad itself would begin around the end of the summer. The current estimate for the cost of modifying the complex and bringing it to a state of readiness was about $3.7 million.

• NASA Hq announced that both the manned and unmanned (Saturn IB and Saturn V) launches of the Skylab Program would be from KSC LC-39. - . Nation: USA. Program: Skylab.

  NASA Hq announced that both the manned and unmanned (Saturn IB and Saturn V) launches of the Skylab Program would be from KSC LC-39. Previous plans were to conduct the Saturn IB launches from LC-34, a part of the U.S. Air Force Eastern Test Range used by NASA, a tenant at Cape Canaveral Air Force Station, Florida. However, program studies showed the feasibility of the pedestal concept of launching the Saturn IB from LC-39 and indicated a cost savings of $13.5 million. The pedestal would be of standard steel structural design; however, there were unique conditions considered. One of these was the requirement to withstand engine exhaust temperatures of 3000 K (5000°F). Another dealt with winds. The pedestal was designed to launch an S-IB at maximum vehicle allowed winds (59.4 km) and to withstand a 200-km per hr hurricane without the launch vehicle. Launch Complex 34, which became operational in 1961, was placed in a standby condition after the Apollo 7 flight in October 1968. It would have required extensive updating of equipment and repairs to ready it for the Skylab Program.

• Launch Complex 34/37 Phaseout Plan - . Nation: USA. Program: Skylab. Spacecraft: Skylab.

  With the issuance of the Launch Complex 34/37 Phaseout Plan, Skylab Program management responsibility- for these two launch complexes was terminated. Although use of Launch Complex 37 for Space Shuttle engine testing had been considered, other options were chosen, and the complexes were to be removed from NASA operational facilities inventory.

• MSFC modified a contract with Chrysler Corporation to authorize additional work in the Saturn IB program. - . Nation: USA. Program: Skylab.

  MSFC modified a contract with Chrysler Corporation to authorize additional work in the Saturn IB program. Chrysler was the prime contractor for the first stage of the Saturn IB, which was assembled at the Michoud Assembly Facility in New Orleans. Under the current modification, the company would maintain nine Saturn IB boosters in storage. Three of the nine vehicles were for the Skylab Program and would be launched in 1973. Those three, plus a fourth that would serve as a backup, would be maintained and modified as necessary under terms of this contract. Prelaunch checkout of the Skylab vehicles would also be accomplished under this modification. The period of performance was from 1 January 1971 to 15 August 1973. Six of the vehicles were located at the Michoud Facility; the other three were at MSFC in Huntsville.

• Four S-IB booster stages to be used in the Skylab Program - . Nation: USA. Program: Skylab.

  MSFC awarded Chrysler's Space Division a contract modification for additional work on Saturn IB launch vehicle booster stages. The contract extension would run through 31 January 1974. The additional work was to refurbish four S-IB booster stages that would be used in the Skylab Program in 1973. The fourth vehicle (SA-209) would be assigned as a backup. All four stages had been in storage for several years. The major portion of the work would be removing the stages from storage, preparing them for delivery to KSC, and providing launch support to them throughout the Skylab launch readiness period, which would end in early 1974. Most of the work would be done at the Michoud Assembly Facility in New Orleans, but some work would be done at MSFC.

• Skylab 2 spacecraft transferred to Launch Complex 39B in preparation for launch. - . Nation: USA. Program: Skylab. Flight: Skylab 2.

  The Skylab 2 spacecraft, mated to its launch vehicle, was transferred 27 February from the KSC Vehicle Assembly- Building to Launch Complex 39B in preparation for launch. The SL-2 space vehicle consisted of the following major components: an S-IB (the first stage); an S-IVB (the second stage, which comprised the propulsion stages); an IU; a CSM; and an SLA. Additional Details: here....

• Skylab 2 - . Call Sign: Skylab. Crew: Conrad, Kerwin, Weitz. Backup Crew: McCandless, Musgrave, Schweickart. Payload: Apollo CSM 116. Mass: 19,979 kg (44,046 lb). Nation: USA. Agency: NASA Houston. Program: Skylab. Class: Moon. Type: Manned lunar spacecraft. Flight: Skylab 2. Spacecraft: Apollo CSM. Duration: 28.03 days. Decay Date: 1973-06-22 . USAF Sat Cat: 6655 . COSPAR: 1973-032A. Apogee: 440 km (270 mi). Perigee: 425 km (264 mi). Inclination: 50.00 deg. Period: 93.20 min.

  Epic repair mission which brought Skylab into working order. Included such great moments as Conrad being flung through space by the whiplash after heaving on the solar wing just as the debris constraining it gave way; deployment of a lightweight solar shield, developed in Houston in one week, which brought the temperatures down to tolerable levels. With this flight US again took manned spaceflight duration record.

  Skylab 2 , consisting of a modified Apollo CSM payload and a Saturn IB launch vehicle, was inserted into Earth orbit approximately 10 minutes after liftoff. The orbit achieved was 357 by 156 km and, during a six-hour period following insertion, four maneuvers placed the CSM into a 424 by 415 km orbit for rendezvous with the Orbital Workshop. Normal rendezvous sequencing led to stationkeeping during the fifth revolution followed by a flyaround inspection of the damage to the OWS. The crew provided a verbal description of the damage in conjunction with 15 minutes of television coverage. The solar array system wing (beam) 2 was completely missing. The solar array system wing (beam) 1 was slightly deployed and was restrained by a fragment of the meteoroid shield. Large sections of the meteoroid shield were missing. Following the flyaround inspection, the CSM soft-docked with the OWS at 5:56 p.m. EDT to plan the next activities. At 6:45 p.m. EDT the CSM undocked and extravehicular activity was initiated to deploy the beam 1 solar array. The attempt failed. Frustration of the crew was compounded when eight attempts were required to achieve hard docking with the OWS. The hard dock was made at 11:50 p.m. EDT, terminating a Skylab 2 first-day crew work period of 22 hours.

• Skylab 3 space vehicle was moved to pad. - . Nation: USA. Program: Skylab. Flight: Skylab 3.

  The Skylab 3 space vehicle was moved to KSC Launch Complex 39, Pad B, on 11 June in preparation for launch. The space vehicle consisted of a Saturn IB launch vehicle S-IB-207 first stage, S-IVB-207 second stage, and a S-IU-208 instrument unit; a CSM; and a spacecraft lunar module adapter. Additional Details: here....

• Skylab 3 - . Call Sign: Skylab. Crew: Bean, Garriott, Lousma. Backup Crew: Brand, Lenoir, Lind. Payload: Apollo CSM 117. Mass: 20,121 kg (44,359 lb). Nation: USA. Agency: NASA Houston. Program: Skylab. Class: Moon. Type: Manned lunar spacecraft. Flight: Skylab 3. Spacecraft: Apollo CSM. Duration: 59.46 days. Decay Date: 1973-09-25 . USAF Sat Cat: 6757 . COSPAR: 1973-050A. Apogee: 442 km (274 mi). Perigee: 422 km (262 mi). Inclination: 50.00 deg. Period: 93.20 min.

  Continued maintenance of the Skylab space station and extensive scientific and medical experiments. Installed twinpole solar shield on EVA; performed major inflight maintenance; doubled record for length of time in space. Completed 858 Earth orbits and 1,081 hours of solar and Earth experiments; three EVAs totalled 13 hours, 43 minutes.

  The space vehicle, consisting of a modified Apollo command and service module payload on a Saturn IB launch vehicle, was inserted into a 231.3 by 154.7 km orbit. Rendezvous maneuvers were performed during the first five orbits as planned. During the rendezvous, the CSM reaction control system forward firing engine oxidizer valve leaked. The quad was isolated. Station-keeping with the Saturn Workshop began approximately 8 hours after liftoff, with docking being performed about 30 minutes later.

• Skylab 4 - . Call Sign: Skylab. Crew: Carr, Gibson, Edward, Pogue. Backup Crew: Brand, Lenoir, Lind. Payload: Apollo CSM 118. Mass: 20,847 kg (45,959 lb). Nation: USA. Agency: NASA Houston. Program: Skylab. Class: Moon. Type: Manned lunar spacecraft. Flight: Skylab 4. Spacecraft: Apollo CSM. Duration: 84.05 days. Decay Date: 1974-02-08 . USAF Sat Cat: 6936 . COSPAR: 1973-090A. Apogee: 437 km (271 mi). Perigee: 422 km (262 mi). Inclination: 50.00 deg. Period: 93.10 min.

  Final Skylab mission; included observation and photography of Comet Kohoutek among numerous experiments. Completed 1,214 Earth orbits and four EVAs totalling 22 hours, 13 minutes. Increased manned space flight time record by 50%. Rebellion by crew against NASA Ground Control overtasking led to none of the crew ever flying again. Biological experiments included two Mummichog fish (Fundulus heteroclitus).

  The space vehicle consisted of a modified Apollo CSM and a Saturn IB launch vehicle. All launch phase events were normal, and the CSM was inserted into a 150.1- by 227.08-km orbit. The rendezvous sequence was performed according to the anticipated timeline. Stationkeeping was initiated about seven and one-half hours after liftoff, and hard docking was achieved about 30 minutes later following two unsuccessful docking attempts. Planned duration of the mission was 56 days, with the option of extending it to a maximum of 84 days.

• Plans for the Skylab rescue capability discontinued. - . Nation: USA. Program: Skylab. Spacecraft Bus: Apollo CSM. Spacecraft: Apollo Rescue CSM.

  KSC was directed to discontinue plans for the Skylab rescue capability and to move the rescue vehicle (SA-209 and CSM-119) back to the Vehicle Assembly Building. Upon completion of this action, Headquarters responsibility for the SA-209 and CSM-119 would be transferred to the Program Director of the Apollo-Soyuz Test Program.

• Apollo (ASTP) - . Call Sign: Apollo. Crew: Brand, Slayton, Stafford. Backup Crew: Bean, Evans, Lousma. Payload: Apollo CSM 111. Mass: 14,768 kg (32,557 lb). Nation: USA. Agency: NASA Houston. Program: ASTP. Class: Moon. Type: Manned lunar spacecraft. Flight: Apollo (ASTP), Soyuz 19 (ASTP). Spacecraft: Apollo CSM. Duration: 9.06 days. Decay Date: 1975-07-24 . USAF Sat Cat: 8032 . COSPAR: 1975-066A. Apogee: 166 km (103 mi). Perigee: 152 km (94 mi). Inclination: 51.70 deg. Period: 87.60 min.

  This flight marked the culmination of the Apollo-Soyuz Test Project, a post-moon race 'goodwill' flight to test a common docking system for space rescue. 15 July 1975 began with the flawless launch of Soyuz 19. Apollo followed right on schedule. Despite a stowaway - a 'super Florida mosquito' - the crew accomplished a series of rendezvous manoeuvres over the next day resulting in rendezvous with Soyuz 19. At 11:10 on 17 July the two spacecraft docked. The crew members rotated between the two spacecraft and conducted various mainly ceremonial activities. Stafford spent 7 hours, 10 minutes aboard Soyuz, Brand 6:30, and Slayton 1:35. Leonov was on the American side for 5 hours, 43 minutes, while Kubasov spent 4:57 in the command and docking modules.

  After being docked for nearly 44 hours, Apollo and Soyuz parted for the first time and were station-keeping at a range of 50 meters. The Apollo crew placed its craft between Soyuz and the sun so that the diameter of the service module formed a disk which blocked out the sun. This artificial solar eclipse, as viewed from Soyuz, permitted photography of the solar corona. After this experiment Apollo moved towards Soyuz for the second docking.

  Three hours later Apollo and Soyuz undocked for the second and final time. The spacecraft moved to a 40 m station-keeping distance so that the ultraviolet absorption (UVA MA-059) experiment could be performed. This was an effort to more precisely determine the quantities of atomic oxygen and atomic nitrogen existing at such altitudes. Apollo, flying out of plane around Soyuz, projected monochromatic laser-like beams of light to retro-reflectors mounted on Soyuz. On the 150-meter phase of the experiment, light from a Soyuz port led to a misalignment of the spectrometer, but on the 500-meter pass excellent data were received; on the 1,000-meter pass satisfactory results were also obtained.

  With all the joint flight activities completed, the ships went on their separate ways. On 20 July the Apollo crew conducted earth observation, experiments in the multipurpose furnace (MA-010), extreme ultraviolet surveying (MA-083), crystal growth (MA-085), and helium glow (MA-088). On 21 July Soyuz 19 landed safely in Kazakhstan. Apollo continued in orbit on 22-23 July to conduct 23 independent experiments - including a doppler tracking experiment (MA-089) and geodynamics experiment (MA-128) designed to verify which of two techniques would be best suited for studying plate tectonics from earth orbit.

  After donning their space suits, the crew vented the command module tunnel and jettisoned the docking module. The docking module would continue on its way until it re-entered the earth's atmosphere and burned up in August 1975.

• Saturn S-IVB-210 - . Payload: Saturn S-IVB-210. Nation: USA. Agency: NASA Huntsville. Program: ASTP. Decay Date: 1975-07-16 . USAF Sat Cat: 8033 . COSPAR: 1975-066B. Apogee: 166 km (103 mi). Perigee: 152 km (94 mi). Inclination: 51.70 deg. Period: 87.60 min.

• Docking Module 2 - . Payload: Apollo DM-2. Mass: 2,012 kg (4,435 lb). Nation: USA. Agency: NASA Houston. Program: ASTP. Spacecraft Bus: Apollo CSM. Spacecraft: Apollo ASTP Docking Module. Decay Date: 1975-08-02 . USAF Sat Cat: 8042 . COSPAR: 1975-066C. Apogee: 222 km (137 mi). Perigee: 201 km (124 mi). Inclination: 51.70 deg. Period: 88.73 min.