Titan 2 Credit - (c) Don Boelling Media Gallery

ICBM, developed also as the launch vehicle for the manned Gemini spacecraft in the early 1960's. When the ICBM's were retired in the 1980's they were refurbished and a new series of launches began.

The Titan 1 ICBM had been developed by Martin and Aerojet as technical insurance if the Atlas, built by Convair and Rocketdyne, had failed. The Martin team had been instructed to use the liquid oxygen/kerosene propellants used for the Atlas, even though Aerojet's prior experience was primarily with storable propellants. As early as 1957 Martin and Aerojet proposed a number of improvements to the basic Titan design, which would make the follow-on missile a much more useful weapon system. Storable propellants would eliminate the loading, just prior to launch, of the cryogenic liquid oxygen needed by the Atlas and Titan 1. A storable-propellant missile could remain fueled, stored in a silo, ready for launch at a moment's notice. The complicated elevator and fuelling apparatus of the immense Titan 1 complexes could be eliminated. The Aerojet storable propellant engines would be immensely simplified compared to the cryogenic Titan 1 engines. A new AC Spark Plug inertial navigation system would make the missile more accurate and impervious to jamming. With the new propellants, and a constant missile diameter, the improved missile would fit in the same silo and transport envelope, but have 50% greater takeoff mass, and nearly triple the payload.

The Air Force authorized Martin to proceed with the Titan 2 ICBM in June 1960. In January 1961 the Titan 2 was selected to boost the Dynasoar manned spaceplane on suborbital tests, and in July 1961, to orbit the manned Gemini spacecraft. Therefore during development the ICBM had also to be man-rated. This caused some difficulties, as a pogo problem encountered in flight tests was acceptable to the Air Force for a weapon system, but unacceptable to NASA for a manned booster. The problem was solved to NASA's satisfaction, and the Titan went on to a perfect launch record during the Gemini program. Meanwhile Titan 2's were deployed in 54 fixed silos at three bases by the end of 1964. The missile was equipped with the immense W53 nuclear warhead and penetration aids to ensure that it would get through the evolving Soviet anti-ballistic missile systems around Moscow. Throughout the Cold War, the Titan 2 was the main threat to the Soviet leadership in Moscow, even within their subterranean command bunkers. It represented only 5% of America's ICBM's, but over 30% of the deliverable megatonnage.

However solid propellant missiles were more attractive to Defense Secretary McNamara, and the Atlas and Titan 1 ICBM's were all decommissioned by 1966 after short service lives. But the Russians had unveiled their equivalent of the Titan 2, the awesome SS-9 Scarp (R-36) "city buster". It was politically imprudent to decommission the only American equivalent, and so the Titan 2 soldiered on as the only American liquid-propellant ICBM. It was not until 1987 that it was replaced by the solid-propellant Peacekeeper. By then the Cold War had only three more years to run. The Peacekeeper, developed at incredible expense, had a very short service life, being outlawed under missile reduction agreements after a few years service.

The decommissioned Titan 2's were refurbished and used as space launchers until the last was finally expended in 2003. Modifications of the Titan 2 continued in production as the core for the Titan 3, 34, and 4 series of space launchers, until the last was finally launched in 2005.

During its life the storable propellants, which resulted in a simple and extremely reliable vehicle, became prohibitively expensive. This was because they were toxic, and environmental regulations made them, eventually, unprofitable to produce and difficult to handle. Outside of the United States the forces of Environmental Correctness were not as strong. The same propellants continued in use into the 21st Century in the Ariane 4 boosters for France, the GSLV for India, the Proton and Dnepr of Russia, and the CZ series in China.

The only major improvement fitted to the ICBM version of the missile during its service life was installation of the Universal Space Guidance System, developed for the Titan 3 space launcher. Otherwise the missile continued to perform with remarkable reliability in both operational missie tests and as a space booster. Total Titan 2 production and disposition was as follows:

Manufacturer: Martin Marietta. Launches: 106. Failures: 7. Success Rate: 93.40%. First Launch Date: 1962-03-16. Last Launch Date: 2003-10-18. Launch data is: continuing. LEO Payload: 3,100 kg (6,800 lb). to: 185 km Orbit. Associated Spacecraft: Advanced Tiros N , Clementine, Coriolis, DMSP Block 5D-2, DMSP Block 5D-3, Landsat 6, QuikScat, Singleton, Tiros N. Liftoff Thrust: 1,893.400 kN (425,653 lbf). Total Mass: 154,000 kg (339,000 lb). Core Diameter: 3.05 m (10.00 ft). Total Length: 31.40 m (103.00 ft). Span: 3.05 m (10.00 ft). Maximum range: 11,690 km (7,260 mi). Number Standard Warheads: 1. Standard RV: Mk. 6. Standard warhead: W53. Standard warhead yield: 8,900 KT. Standard warhead CEP: 1.61 km (1.00 mi). Cruise Propulsion: Liquid (stor). Guidance: Inertial. Maximum speed: 29,030 kph (18,030 mph). Ceiling: 1,287,800 m (4,225,000 ft). Development Cost $: 400.000 million. in: 1963 average dollars. Recurring Price $: 16.389 million. Total Number Built: 131. Total Development Built: 23. Total Production Built: 108. Flyaway Unit Cost $: 3.158 million. in: 1969 unit dollars.

Space launch version of Titan 2 ICBM, obtained through minimal modification of ICBM (new wiring and avionics only, and use of existing ICBM re-entry vehicle shroud). Proposed in the late 1980's but never developed.

LEO Payload: 3,175 kg (6,999 lb). to: 185 km Orbit. at: 28.60 degrees. Liftoff Thrust: 2,090.000 kN (469,850 lbf). Total Mass: 154,000 kg (339,000 lb). Core Diameter: 3.05 m (10.00 ft). Total Length: 31.40 m (103.00 ft).

Space launch version, obtained through minimal refurbishment of decommissioned ICBM's.

The decommissioned ICBM's received a new payload interfaces (a conical structure that provided 0.91 m, 1.42 m, and 3.05 m payload ring adapters), an attitude control system taken from the Titan 3, replacement of the second-stage verniers with retrorockets to improve payload separation, and a Titan 3 fairing, 3.05 m diameter and 6.1 to 9.2 m long. With solid propellant kick stages, the Titan 2G could put 3,028 kg into a 546 km sun synchronous orbit, of 1,043 kg into a geosynchronous transfer orbit.

The Titan 2 ICBM had been outfitted with a Delco Carousel- type guidance similar to that used in the Titan 3 while it was still deployed as a ballistic missile. That same guidance system, using the same equipment was used on the Titan 2 space booster, modified to handle telemetry. These guidance systems each had thousands of hours of operating time as a result of use on ICBM's and probably set an operating time record for such space launch hardware.

The Titan 2 vehicles were not completely dismantled as was done with the Atlas E and Atlas F space boosters. A new rate gyro package was added to the second stage (after testing proved that using just the output from the HIG gyros would not work - and by that time the first vehicle had already been delivered to Vandenberg AFB. The top of the second stage was modified for the 3.05-m-diameter fairing, destruct, tracking, and telemetry equipment were added, but that was about all. The engines were test fired but not overhauled.

Although 55 surplus ICBM's were available for use as space launchers, only the original 14 contracted in 1986-1987 were ever refurbished and launched, due to the inexplicably high cost of the minimal refurbishment.

LEO Payload: 3,175 kg (6,999 lb). to: 185 km Orbit. at: 28.60 degrees. Payload: 2,177 kg (4,799 lb). to a: 185 km polar orbit trajectory. Liftoff Thrust: 2,090.000 kN (469,850 lbf). Total Mass: 154,000 kg (339,000 lb). Core Diameter: 3.05 m (10.00 ft). Total Length: 31.40 m (103.00 ft). Launch Price $: 34.000 million. in: 1994 price dollars. Total Number Built: 131. Flyaway Unit Cost $: 26.000 million. in: 1987 unit dollars. Cost of design, development, launch complex development, and first 8 refurbished ICBM's in 1986 was $ 529 million. Next 6 cost $ 155 million = $ 26 million each. Refurbishment and launch of 14 surplus ICBM's in 1997 was $ 660 million = $ 47 million per launch.

Version of refurbished Titan 2 ICBM with two liquid propellant strap-on stages. Proposed in the late 1980's but never developed.

No technical details available on the liquid boosters.

Manufacturer: Martin. LEO Payload: 8,165 kg (18,000 lb). to: 185 km Orbit. at: 28.60 degrees. Core Diameter: 3.05 m (10.00 ft). Total Length: 35.00 m (114.00 ft).

Version of refurbished Titan 2 ICBM with two to eight Castor 4A solid-propellant strap-on stages. Proposed in the late 1980's but never developed.

Larger GEM-40 motors were also proposed. Would have required development of a new skirt for the first stage for attachment of the solid boosters.

Manufacturer: Martin. LEO Payload: 9,000 kg (19,800 lb). to: 185 km Orbit. at: 28.60 degrees. Total Mass: 247,000 kg (544,000 lb). Core Diameter: 3.05 m (10.00 ft). Total Length: 35.00 m (114.00 ft). Span: 9.60 m (31.40 ft).

Original ICBM design.

Payload: 3,700 kg (8,100 lb). to a: 10,000 km range trajectory. Apogee: 1,380 km (850 mi). Liftoff Thrust: 2,000.000 kN (449,600 lbf). Total Mass: 150,000 kg (330,000 lb). Core Diameter: 3.05 m (10.00 ft). Total Length: 31.10 m (102.00 ft).

Version for launch of Gemini manned spacecraft. Developed in parallel with ICBM version. Differed in having redundancy features in systems and MDS (Malfunction Detection System) installed.

Modifications to Titan II for use as the Gemini Launch Vehicle included:

• Malfunction detection system added to detect and transmit booster performance information to the crew.
• Back-up flight control system added to provide a secondary system if primary system fails.
• Radio guidance substituted for inertial guidance.
• Retro and vernier rockets deleted.
• New second stage equipment truss added.
• New second stage forward oxidizer skirt assembly added.
• Trajectory tracking requirements simplified.
• Electrical hydraulic and instrument systems modified.

LEO Payload: 3,600 kg (7,900 lb). Apogee: 300 km (180 mi). Liftoff Thrust: 2,090.000 kN (469,850 lbf). Total Mass: 150,530 kg (331,860 lb). Core Diameter: 3.05 m (10.00 ft). Total Length: 32.80 m (107.60 ft). Flyaway Unit Cost $: 3.158 million. in: 1965 unit dollars.

• Stage Number: 1. 1 x Stage: Titan 2-1. Gross Mass: 117,866 kg (259,850 lb). Empty Mass: 6,736 kg (14,850 lb). Thrust (vac): 2,172.231 kN (488,337 lbf). Isp: 296 sec. Burn time: 139 sec. Isp(sl): 258 sec. Diameter: 3.05 m (10.00 ft). Span: 3.05 m (10.00 ft). Length: 22.28 m (73.09 ft). Propellants: N2O4/Aerozine-50. No Engines: 2. Engine: LR-87-7. Status: Study 1961.

• Stage Number: 2. 1 x Stage: Titan 2-2. Gross Mass: 28,939 kg (63,799 lb). Empty Mass: 2,404 kg (5,299 lb). Thrust (vac): 444.819 kN (99,999 lbf). Isp: 316 sec. Burn time: 180 sec. Isp(sl): 160 sec. Diameter: 3.05 m (10.00 ft). Span: 3.05 m (10.00 ft). Length: 7.86 m (25.78 ft). Propellants: N2O4/Aerozine-50. No Engines: 1. Engine: LR-91-7. Status: Study 1961.

1958 July - Launch Vehicle: Titan 2.

• Advanced Titan considered. USAF reviews improvements (inertial guidance, storable fuel, 1 x 9 basing, both stages constant 3.05 m diameter, in silo launch) to the Titan I.

• Silo-launched Titan approved. Major General Schriever approves conversion of future Titan facilities from silo-lift to in-silo launch.

• Dyna-Soar contractors Boeing and Martin selected. Nation: USA. Spacecraft: Dynasoar. The Dyna-Soar source selection board completed its evaluation of the proposals of the Boeing Airplane Company and the Martin Company. The board recommended the development of the Boeing glider but also favored the employment of the orbtal Titan C booster offered by Martin.

• Martin awarded a contract to develop the Titan 2 ICBM.

• Martin to develop the Dyna-Soar booster airframe. Nation: USA. Spacecraft: Dynasoar. The Air Force gave the Martin Company responsibility for the development of the Dyna-Soar booster airframe.

• Aero-Jet to develop booster engines for the Dyna-Soar system. Spacecraft: Dynasoar. The Air Force authorized the Aero-Jet General Corporation to develop booster engines for the Dyna-Soar system.

• Titan II instead of Titan I for Dyna-Soar. Nation: USA. Spacecraft: Dynasoar. The Assistant Secretary of the Air Force requested ARDC to examine the feasiblity of employing Titan II instead of Titan I for Dyna-Soar suborbital flights.

• Titan II to be the Dyna-Soar suborbital Step I booster. Nation: USA. Spacecraft: Dynasoar. Air Force headquarters announced that Titan II would be the suborbital Step I booster.

• USAF changes Dynasoar launch vehicle to Titan II Nation: USA. Class: Manned. Type: Spaceplane. Spacecraft: Dynasoar. References: 26.

• Beginning of Gemini Nation: USA. Program: Gemini. Class: Manned. Type: Spacecraft. Spacecraft: Gemini. First formal NASA/McDonnell discussions on Mercury Mark II (Gemini). References: 26.

• Titan II proposed for lunar landing program Nation: USA. Program: Apollo. Spacecraft: Gemini LOR. Albert C. Hall of The Martin Company proposed to Robert C. Seamans, Jr., NASA's Associate Administrator, that the Titan II be considered as a launch vehicle in the lunar landing program. Although skeptical, Seamans arranged for a more formal presentation the next day. Abe Silverstein, NASA's Director of Space Flight Programs, was sufficiently impressed to ask Director Robert R. Gilruth and STG to study the possible uses of Titan II. Silverstein shortly informed Seamans of the possibility of using the Titan II to launch a scaled-up Mercury spacecraft.References: 16.

• Martin briefed NASA on the Titan II weapon system. Nation: USA. Program: Gemini. Spacecraft: Gemini, Mercury Mark I. Martin Company personnel briefed NASA officials in Washington, D.C., on the Titan II weapon system. Albert C. Hall of Martin had contacted NASA's Associate Administrator, Robert C. Seamans, Jr., on April 7 to propose the Titan II as a launch vehicle for a lunar landing program. Although skeptical, Seamans nevertheless arranged for a more formal presentation. Abe Silverstein, NASA Director, Office of Space Flight Programs, was sufficiently impressed by the Martin briefing to ask Director Robert R. Gilruth and Space Task Group to study possible Titan II uses. Silverstein shortly informed Seamans of the possibility of using the Titan II to launch a scaled-up Mercury spacecraft.

• Martin proposal for a Titan-boosted Mercury vehicle. Nation: USA. Spacecraft: Mercury Mark I. James L. Decker of Martin Company submitted a proposal for a Titan-boosted Mercury vehicle. A Mercury-Titan program, expected to span an 18-month flight schedule, would benefit from the Air Force's booster development and test of the ballistic missile system and the considerable design and test that the Air Force had expended in the Dyna-Soar program to adapt the vehicle to manned spaceflight. The Titan, with its sea-level rating of 430,000 pounds of thrust in the first stage and 100,000 pounds in the second stage, was capable of lifting significantly heavier spacecraft payloads than the Mercury-Atlas. Its hypergolic propulsion system, using storable liquid propellants, was a much simpler system than the cryogenic propellant system in Atlas. A highly reliable booster could be provided, employing complete redundancy in the flight control systems in the form of a three-axis reference system, autopilot, servo, electrical, and hydraulic systems. The short time he proposed would depend on the availability of pad 19 at Cape Canaveral, planned for conversion to the Titan II configuration. Pad 19, unlike the other three Titan I pads, had been intended for space applications and was better designed for required prelaunch test programs.

• Martin briefed Space Task Group on Titan II technical characteristics and performance. Nation: USA. Representatives of Martin Company briefed Director Robert R. Gilruth and some of the senior staff of Space Task Group on Titan II technical characteristics and expected performance. At a senior staff meeting four days later, August 7, Gilruth commented on the Titan II's promise for manned spaceflight, particularly its potential ability to place larger payloads in orbit than could Atlas, which would make it 'a desirable booster for a two-man spacecraft.' Martin had estimated the cost of procuring and launching nine Titan II boosters, with cost of ancillary equipment, at $47.889 million spread over fiscal years 1962 through 1964.

• Titan II to be selected as the launch vehicle for NASA's advanced Mercury. Nation: USA. Spacecraft: Gemini. Martin Company received informal indications from the Air Force that Titan II would be selected as the launch vehicle for NASA's advanced Mercury. Martin, Air Force, and NASA studied the feasibility of modifying complex 19 at Cape Canaveral from the Titan weapon system configuration to the Mercury Mark II launch vehicle configuration.

• Program of manned spaceflight for 1963-1965. Nation: USA. Spacecraft: Gemini. Space Task Group (STG), assisted by George M. Low, NASA Assistant Director for Space Flight Operations, and Warren J. North of Low's office, prepared a project summary presenting a program of manned spaceflight for 1963-1965. This was the final version of the Project Development Plan, work on which had been initiated August 14.Additional Details: Program of manned spaceflight for 1963-1965.(21219).

• Recommendation that the weapon system of the Titan II, with minimal modifications, be approved for the Mercury Mark II rendezvous mission. Spacecraft: Gemini. On the basis of a report of the Large Launch Vehicle Planning Group, Robert C. Seamans, Jr., NASA Associate Administrator, and John H. Rubel, Department of Defense Deputy Director for Defense Research and Engineering, recommended to Secretary of Defense Robert S. McNamara that the weapon system of the Titan II, with minimal modifications, be approved for the Mercury Mark II rendezvous mission. The planning group had first met in August 1961 to survey the Nation's launch vehicle program and was recalled in November to consider Titan II, Titan II-1/2, and Titan III. On November 16, McNamara and NASA Administrator James E. Webb had also begun discussing the use of Titan II.

• Two-man Mercury Mark II spacecraft announced Nation: USA. Program: Gemini. Spacecraft: Gemini. Plans for the development of a two-man Mercury spacecraft were announced by Robert R. Gilruth, MSC Director. The two-man spacecraft, to be built by McDonnell Aircraft Corporation, would be similar in shape to the Mercury spacecraft but slightly larger and two to three times heavier. Its booster rocket would be a modified Air Force Titan II, scheduled for flight test in early 1962. One of the major objectives in the program would be a test of orbital rendezvous, in which the two-man spacecraft would be launched into orbit by the Titan II and attempt to rendezvous with an Agena stage launched by an Atlas rocket. The total cost for a dozen two-man spacecraft plus boosters and other equipment was estimated at $500 million.References: 16.

• DOD/NASA coordination for Mercury Mark II Nation: USA. Program: Gemini. Spacecraft: Gemini. NASA Associate Administrator Robert C. Seamans, Jr., and DOD Deputy Director of Defense Research and Engineering John H. Rubel recommended to Secretary of Defense Robert S. McNamara and NASA Administrator James E. Webb that detailed arrangements for support of the Mercury Mark II spacecraft and the Atlas-Agena vehicle used in rendezvous experiments be planned directly between NASA's Office of Manned Space Flight and the Air Force and other DOD organizations. NASA's primary responsibilities would be the overall management and direction for the Mercury Mark II/ Agena rendezvous development and experiments. The Air Force responsibilities would include acting as NASA contractor for the Titan II launch vehicle and for the Atlas-Agena vehicle to be used in rendezvous experiments. DOD's responsibilities would include assistance in the provision and selection of astronauts and the provision of launch, range, and recovery support, as required by NASA.References: 16.

• NASA announced plans to develop a two-man Mercury capsule. Nation: USA. Program: Gemini. Spacecraft: Gemini. In Houston, Director Robert R. Gilruth of Manned Spacecraft Center announced plans to develop a two-man Mercury capsule. Built by McDonnell, it would be similar in shape to the Mercury capsule but slightly larger and from two to three times heavier. Its booster would be a modified Titan II. A major program objective would be orbital rendezvous. The two-man spacecraft would be launched into orbit and would attempt to rendezvous with an Agena stage put into orbit by an Atlas. Total cost of 12 capsules plus boosters and other equipment was estimated at $500 million. The two-man flight program would begin in the 1963-1964 period with several unmanned ballistic flights to test overall booster-spacecraft compatibility and system engineering. Several manned orbital flights would follow. Besides rendezvous flybys of the target vehicle, actual docking missions would be attempted in final flights. The spacecraft would be capable of missions of a week or more to train pilots for future long-duration circumlunar and lunar landing flights. The Mercury astronauts would serve as pilots for the program, but additional crew members might be phased in during the latter portions of the program.

• Recommendations to Secretary of Defense Robert S. McNamara on the division of effort between NASA and DOD in the Mark II program. Spacecraft: Gemini. NASA Associate Administrator Robert C. Seamans, Jr., and John H. Rubel, Department of Defense (DOD) Deputy Director for Defense Research and Engineering, offered recommendations to Secretary of Defense Robert S. McNamara on the division of effort between NASA and DOD in the Mark II program. They stressed NASA's primary responsibility for managing and directing the program, although attaining the program objectives would be facilitated by using DOD (especially Air Force) resources in a contractor relation to NASA. In addition, DOD personnel would aquire useful experience in manned spaceflight design, development, and operations. Space Systems Division of Air Force Systems Command became NASA's contractor for developing, procuring, and launching Titan II and Atlas-Agena vehicles for the Mark II program.

• Dynasoar suborbital tests deleted from program. Nation: USA. Class: Manned. Type: Spaceplane. Spacecraft: Dynasoar. Development time schedule for Dyna-Soar was reduced when DOD authorized the USAF to move directly from B-52 drop tests to unmanned and then manned orbital flights. This eliminated the previous interim stage of suborbital flights to be powered by the Titan II. This required renegotiation of the development contract held by the Martin Co. and negotiating of a new contract for a larger booster.References: 18.

• Manned Spacecraft Center directed Air Force Space Systems Division to authorize contractors to begin the work necessary to use the Titan II in the Mercury Mark II program. Nation: USA. On December 27, Martin-Baltimore received a go-ahead on the launch vehicle from the Air Force. A letter contract for 15 Gemini launch vehicles and associated aerospace ground equipment followed on January 19, 1962.

• Titan 2 first ground test. Nation: USA. Program: Gemini. Class: Manned. Type: Spacecraft. Spacecraft: Gemini. Titan II, an advanced ICBM and the booster designated for NASA's two-man orbital flights, was successfully captive-fired for the first time at the Martin Co.'s Denver facilities. The test not only tested the flight vehicle but the checkout and launch equipment intended for operational use.References: 18.

• Titan 2 first static ground test. Titan 2 was successfully captive-fired for the first time at the Martin Co.'s Denver facilities.

• NASA issued the Gemini Operational and Management Plan, which outlined the roles and responsibilities of NASA and Department of Defense in the Gemini (Mercury Mark II) program. Spacecraft: Gemini. NASA would be responsible for overall program planning, direction, systems engineering, and operation-including Gemini spacecraft development; Gemini/Agena rendezvous and docking equipment development; Titan II/Gemini spacecraft systems integration; launch, flight, and recovery operations; command, tracking, and telemetry during orbital operations; and reciprocal support of Department of Defense space projects and programs within the scope of the Gemini program. Department of Defense would be responsible for: Titan II development and procurement, Atlas procurement, Agena procurement, Atlas-Agena systems integration, launch of Titan II and Atlas-Agena vehicles, range support, and recovery support. A slightly revised version of the plan was signed in approval on March 27 by General Bernard A. Schriever, Commander, Air Force Systems Command, for the Air Force, and D. Brainerd Holmes, Director of Manned Space Flight, for NASA.

• Titan 2 390th SMW and 570th SMS (9 missiles) activated at Davis-Monthan AFB, Arizona.

• Statement of Work for the procurement of Titan II launch vehicles for the Gemini program. Nation: USA. Manned Spacecraft Center prepared a Statement of Work to be accomplished by Air Force Space Systems Division (SSD) in its role as contractor to NASA for the procurement of Titan II launch vehicles for the Gemini program. The launch vehicle would retain the general aerodynamic shape, basic systems, and propulsion concepts of the missile. Modifications, primarily for crew safety, were to be kept to a minimum. The Statement of Work accompanied a purchase request for $27 million, dated January 5, 1962, for 15 Titan launch vehicles. Pending ratification of the Gemini Operational and Management Plan, however, funding was limited to $3 million. To oversee this work, SSD established a Gemini Launch Vehicle Directorate, headed by Colonel Richard C. Dineen, on January 11. Initial budgeting and planning were completed by the end of March, and a final Statement of Work was issued May 14; although amended, it remained in effect throughout the program.

• Titan II plans to ensure flight safety and enhance reliability. Nation: USA. After investigating potential malfunction problems of the modified Titan II/Gemini launch vehicle, Martin-Baltimore prepared a study report with plans to provide the components necessary to ensure flight safety and enhance reliability. Martin defined the malfunction problem quantitatively in terms of the probability of each cause and its characteristic effect on the system and vehicle. Martin intended to keep the launch vehicle as much like the weapon system as possible; thus the data obtained from the Air Force's weapon system development program would be applicable to the launch vehicle. Only minimal modifications to enhance probability of mission success, to increase pilot safety, and to accommodate the Gemini spacecraft as the payload were to be made. These included a malfunction detection system; backup guidance, control, and hydraulic systems; and selective electrical redundancies.

• Aerospace Corporation to support of the Gemini Launch Vehicle Program. Nation: USA. Air Force Space Systems Division issued a Technical Operating Plan to Aerospace Corporation, El Segundo, California, for support of the Gemini Launch Vehicle Program; a contract followed on March 15. Aerospace was to assume responsibility for general systems engineering and technical direction of the development of the launch vehicle and its associated subsystems. Aerospace had already established a Gemini Launch Vehicle Program Office in January.

• Proposal for redundant subsystems for the Gemini launch vehicle. Nation: USA. Spacecraft: Gemini. Martin-Baltimore submitted its initial proposal for the redundant flight control and hydraulic subsystems for the Gemini launch vehicle; on March 1, Martin was authorized to proceed with study and design work. The major change in the flight control system from Titan II missile to Gemini launch vehicle was substitution of the General Electric Mod IIIG radio guidance system (RGS) and Titan I three-axis reference system for the Titan II inertial guidance system. Air Force Space Systems Division issued a letter contract to General Electric Company, Syracuse, New York, for the RGS on June 27. Technical liaison, computer programs, and ground-based computer operation and maintenance were contracted to Burroughs Corporation, Paoli, Pennsylvania, on July 3.

• Titan 2 381st SMW and 532nd SMS (9 missiles) activated at McConnell AFB, Kansas.

• Mk 6 re-entry vehicle test launch Nation: USA. Agency: USAF. Apogee: 1,300 km (800 mi). The Air Force successfully launched a Titan II intercontinental ballistic missile. This was the first full-scale test of the vehicle; it flew 8000 km out over the Atlantic Ocean. References: 867.

• Contract to Aerojet-General for 15 propulsion systems for the Gemini launch vehicle. Nation: USA. Air Force Space Systems Division awarded a letter contract to Aerojet-General Corporation, Azusa, California, for the research, development, and procurement of 15 propulsion systems for the Gemini launch vehicle. It also included the design and development of the related aerospace ground equipment. Aerojet had been authorized to go ahead with work on the engines on February 14, 1962, and the final engine was scheduled for delivery by April 1965.

• Air Force Space Systems Division published the "Development Plan for the Gemini Launch Vehicle System". Nation: USA. From experience in Titan II and Mercury programs, the planners estimated a budget of $164.4 million, including a 50 percent contingency for cost increases and unforeseen changes.

• Martin-Baltimore submitted a "Description of the Launch Vehicle for the Gemini Spacecraft" to Air Force Space Systems Division. Nation: USA. This document laid the foundation for the design of the Gemini launch vehicle by defining the concept and philosophy of each proposed subsystem.

• Titan 2 308th SMW and 373rd SMS (9 missiles) activated at Little Rock AFB, Arkansas

• Titan 2 571st SMS (9 missiles) activated within the 390th SMW at Davis-Monthan AFB, Arizona.

• Project Gemini cost estimates had tripled from the original estimate of $250 million. Nation: USA. Program: Gemini. Spacecraft: Gemini. James E. Webb, NASA's new Administrator, reviewed the Gemini program. Project Gemini cost estimates at this point ($744.3 million) had increased substantially over the original estimate of $250 million. Estimated spacecraft cost had risen from $240.5 to $391.6 million; Titan II cost, from $113.0 to $161.8 million; Atlas-Agena, from $88.0 to $106.3 million; and supporting development (including the paraglider program), from $29.0 to $36.8 million. Estimated operations costs had declined from $59.0 to $47.8 million.

• A Launch Vehicle-Spacecraft Interface Working Group was established. Nation: USA. Gemini Project Office (GPO) and Aerospace had agreed on the need for such a group at a Gemini-Titan coordination meeting on May 11. The main function of the group, composed of Martin and McDonnell personnel with a McDonnell representative as chairman, was to provide mutual exchange of design and physical data on mechanical, electrical, and structural details between the spacecraft contractor and the booster contractor. The group would make no policy decisions; its actions were to be reviewed at regularly scheduled coordination meetings held by GPO.

• Amendment No. 6 to the Gemini launch vehicle procurement contract assigned $2.609 million to fund the construction necessary to convert pad 19 at Cape Canaveral for Gemini flights. Nation: USA. The Air Force had originally constructed pad 19 for the Titan I development program. Following the final Titan I development flight (January 29) from the Cape, design of the required modifications had begun in February. In April, Gemini Project Office decided that Pad 19 would have an erector rather than a gantry, the upper third of which would be designed as a white room. The final design review of pad 19 modifications took place July 9-10, and the Army Corps of Engineers awarded the construction contract to Consolidated Steel, Cocoa Beach, Florida. Construction began in September. Work was completed and pad 19 was activated on October 17, 1963.

• Avco proposal for a space station. Nation: USA. Spacecraft: MOL. Representatives from Avco Manufacturing Corporation made a presentation to MSC on a proposal for a space station. Prime purpose of the station, company spokesmen said, was to determine the effects of zero-g on the crew's ability to stand reentry and thus fix the limit that man could safely remain in orbit. Avco's proposed station design comprised three separate tubes about 3 m in diameter and 6 m long, launched separately aboard Titan IIs and joined in a triangular shape in orbit. A standard Gemini spacecraft was to serve as ferry vehicle.

• Avco proposal for Titan-launched space station. Avco's proposed station design comprised three separate tubes about 3 m in diameter and 6 m long, launched separately aboard Titan 2s and joined in a triangular shape in orbit. A standard Gemini spacecraft was to serve as ferry vehicle.

• Mk 6 re-entry vehicle test launch Nation: USA. Agency: USAF AFSC. Apogee: 1,300 km (800 mi). References: 867.

• Martin-Baltimore's airborne systems functional test stand went into operation at Baltimore. Nation: USA. In this 3000-square-foot facility, all airborne systems in the Gemini launch vehicle - including flight control, hydraulic, electrical, instrumentation, and malfunction detection - were assembled on tables and benches; actual engines, but simulated propellant tanks and guidance, were used. In addition to individual and combined systems tests, the facility was used to check system design changes and trouble-shoot problems encountered in other test programs.

• Martin prepared a plan for flight testing the malfunction detection system (MDS) for the Gemini launch vehicle on development flights of the Titan II weapon system. Nation: USA. Gemini Project Office (GPO) had requested Martin to prepare Systems Division and Aerospace approved the plan and won GPO concurrence early in August. This so-call 'piggyback plan' required installing the Gemini MDS in Titan II engines on six Titan II flights to demonstrate its reliability before it was flown on Gemini.

• Mk 6 re-entry vehicle test launch Nation: USA. Agency: USAF AFSC. Apogee: 1,300 km (800 mi). References: 1804.

• Gemini-Titan Launch Operations Committee. Nation: USA. A technical team at Air Force Missile Test Center, Cape Canaveral, Florida - responsible for detailed launch planning, consistency of arrangements with objectives, and coordination - met for the first time with official status and a new name. The group of representatives from all organizations supplying major support to the Gemini-Titan launch operations, formerly called the Gemini Operations Support Committee, was now called the Gemini-Titan Launch Operations Committee.

• A reliability review of the Titan II launch vehicle engine system was held in Sacramento, California, at Aerojet-General's Liquid Rocket Plant, the site where the engines were being developed. Nation: USA. Gemini engines had to be more reliable than did intercontinental ballistic missile (ICBM) engines. This requirement meant supplementing the ICBM engine reliability program, a task being performed by Aerojet under Air Force Space Systems Division direction.

• Mk 6 re-entry vehicle test launch Nation: USA. Agency: USAF AFSC. Apogee: 1,300 km (800 mi). References: 1804.

• Titan 2 533rd SMS (9 missiles) activated within the 381st SMW at McConnell AFB, Kansas.

• Titan 2 374th SMS (9 missiles) activated within the 308th SMW at Little Rock AFB, Arkansas

• Mk 6 re-entry vehicle test launch Nation: USA. Agency: USAF AFSC. Apogee: 1,300 km (800 mi). References: 1804.

• Air Force Space Systems Division revised the Development Plan for the Gemini launch vehicle. Nation: USA. The budget was raised to $181.3 million. Cost increases in work on the vertical test facility at Martin's Baltimore plant, on the conversion of pad 19 at Cape Canaveral, and on aerospace ground equipment had already generated a budget increase to $172.6 million during September. The new Development Plan also indicated that the first launch date had slipped to December 1963.

• Mk 6 re-entry vehicle test launch Nation: USA. Agency: USAF AFSC. Apogee: 1,300 km (800 mi). References: 1804.

• Mk 6 re-entry vehicle test launch Nation: USA. Agency: USAF AFSC. Apogee: 1,300 km (800 mi). References: 1804.

• During the first three weeks of the month, Air Force Space Systems Division and Martin-Baltimore negotiated the terms of the contract for Phase I of the Gemini launch vehicle program. Nation: USA. The resulting cost-plus-fixed-fee contract included an estimated cost of $52.5 million and a fixed fee of $3.465 million. This contract covered the development and procurement of the first launch vehicle and preparations for manufacturing and procuring the remaining 14 vehicles required by the Gemini program.

• Aerojet-General contract for the first phase of the Gemini launch vehicle engine program. Nation: USA. Air Force Space Systems Division and Aerojet-General negotiated a cost-plus-fixed-fee contract for the first phase of the Gemini launch vehicle engine program, February 14, 1962, through June 30, 1963. The contract required delivery of one set of engines, with the remaining 14 sets included for planning purposes. Estimated cost of the contract was $13.9 million, with a fixed fee of $917,400 for a total of $14,817,400.

• Mk 4 re-entry vehicle test mission Nation: USA. Agency: USAF AFSC. Apogee: 1,300 km (800 mi). Titan II flight N-11, the eighth in a series being conducted by the Air Force to develop the weapon system, was launched from Cape Canaveral. It carried a design change intended to reduce the amplitude of longitudinal oscillations which had appeared during first stage operation on all seven previous Titan II flights. This phenomenon, which subsequently became known as POGO, generated g-forces as high as nine in the first stage and over three at the position on the missile corresponding to the location of the spacecraft on the Gemini launch vehicle. Fearing the potentially adverse effect on astronaut performance of such superimposed g-forces, NASA established 0.25g at 11 cycles per second as the maximum level tolerable for Gemini flights. As a first try at solving the POGO problem, Titan II N-11 carried standpipes in each leg of the stage I oxidizer feed lines to interrupt the coupling between the missile's structure and its propulsion system. This coupling was presumed to be the cause of the instability. Postflight analysis, however, revealed that the POGO fix was unsuccessful; longitudinal oscillation had actually been multiplied by a factor of two.References: 1804.

• Mk 6 re-entry vehicle test launch Nation: USA. Agency: USAF AFSC. Apogee: 1,300 km (800 mi). References: 1804.

• Gemini Launch Vehicle Configuration Control Board. Nation: USA. Air Force Space Systems Division established the Gemini Launch Vehicle Configuration Control Board to draw up and put into effect procedures for approving and disapproving specifications and engineering change proposals for the Gemini launch vehicle. It formally convened for the first time on March 5, 1963.

• Mk 6 re-entry vehicle test launch Nation: USA. Agency: USAF AFSC. Apogee: 500 km (310 mi). References: 867.

• James E Webb, Administrator of NASA, and Robert S McNamara, Secretary of Defense, concluded a major policy agreement defining the roles of NASA and Department of Defense (DOD) in Project Gemini. The agreement provided for the establishment of a joint NASA-DOD Gemini Program Planning Board. The board would plan experiments, conduct flight tests, and analyze and disseminate results. NASA would continue to manage Project Gemini, while DOD would take part in Gemini development, pilot training, preflight checkout, launch, and flight operations, and would be specifically responsible for the Titan II launch vehicle and the Atlas-Agena target vehicle. DOD would also contribute funds toward the attainment of Gemini objectives.

• Titan II development flight failures caused by problems in the airborne radio guidance system. Nation: USA. At a launch guidance and control coordination meeting, Aerospace described three Titan II development flight failures that had been caused by problems in the General Electrical Mod III airborne radio guidance system. Although these failures did not appear to be the result of inherent design faults that might react on the Gemini program, Aerospace felt that a tighter quality assurance program was needed: 'GE has a poor MOD III (G) quality control program, basically poor workmanship.'

• Mk 6 re-entry vehicle test launch Nation: USA. Agency: USAF AFSC. Apogee: 1,300 km (800 mi). References: 867.

• Awful Tired Nation: USA. Program: Gemini. Agency: USAF AFSC. Apogee: 5.00 km (3.10 mi). Research and development launch - Mk 6 re-entry vehicle References: 88, 867.

• Pilot safety philosophy and procedures would be carried over from Mercury-Atlas to Gemini-Titan. Nation: USA. In a letter transmitting copies of the Gemini Launch Vehicle Pilot Safety Program to Gemini contractors and other organizations engaged in Gemini development and operations, Air Force Space Systems Division explained that pilot safety philosophy and procedures would be carried over from Mercury-Atlas to Gemini-Titan.

• The stage II oxidizer tank from Gemini launch vehicle (GLV) 2 was airlifted from Martin-Denver to Martin-Baltimore to be used in GLV-1. Nation: USA. GLV propellant tank and skirt assemblies were manufactured, pressure-tested, and calibrated at Martin-Denver, then shipped to Baltimore where the GLV was assembled. Additional Details: The stage II oxidizer tank from Gemini launch vehicle (GLV) 2 was airlifted from Martin-Denver to Martin-Baltimore to be used in GLV-1.(21367).

• Study group to recommend DOD experiments for inclusion in the Gemini flight program. Nation: USA. The Gemini Program Planning Board, meeting in Washington, agreed to the establishment of an ad hoc study group to compare NASA and Department of Defense (DOD) objectives for the Gemini program and to recommend DOD experiments for inclusion in the Gemini flight program. The group met in continuous session March 25 to April 26, presenting its final report to the board on May 6. The board then recommended that a program of inflight military experiments be immediately approved, that the Air Force establish a field office at Manned Spacecraft Center to manage DOD participation in the Gemini program in general and integration of experiments in particular, and that work on preventing longitudinal oscillations in stage I and combustion instability in stage II of the Gemini launch vehicle to be urgently pursued. The board declined to recommend additional flights in the Gemini program, as suggested by the study group, to encompass experiments that would not fit into the framework of the planned Gemini program. The Secretary of Defense and NASA Administrator concurred in the Board's recommendations.

• Mk 6 re-entry vehicle test launch Nation: USA. Agency: USAF AFSC. Apogee: 1,300 km (800 mi). References: 867.

• POGO problems in the Titan II. Nation: USA. The Titan II-Gemini Coordination Committee was established to direct efforts to reduce longitudinal vibration (POGO) in the Titan II and to improve engine reliability. Air Force Space Systems Division (SSD) and Aerospace had presented to NASA and the Air Force a series of briefings on the POGO problem that culminated in a briefing to the Gemini Program Planning Board. The main problem was that POGO level satisfactory in the weapon system was too high to meet NASA standards for the Gemini program, and further reduction in the POGO level required a much more elaborate and extensive analytic and experimental program than had so far been considered necessary. The board approved the SSD/Aerospace proposals and established a committee to oversee work toward a POGO remedy. The high-level committee was composed of officials from Air Force Ballistic Systems Division, SSD, Space Technology Laboratories, and Aerospace.

• Research and development launch Nation: USA. Agency: USAF AFSC. Apogee: 500 km (310 mi). Mk 6 re-entry vehicle References: 867.

• The Gemini Abort Panel met. Martin-Baltimore's analysis of the last three Titan II flight tests tended to show that successful crew escape would have been possible. Nation: USA. McDonnell presented data on spacecraft structural capabilities, but lack of data on what to expect from Titan II catastrophic failure meant that spacecraft structural capabilities remained a problem. Also some questions had existed as to what could happen to the adapter retrosection during and after an abort. A study had been made of this problem, assuming a 70,000 foot altitude condition, and there appeared to be no separation difficulties. This study investigated the period of up to 10 seconds after separation, and there was no evidence that recontact would occur.

• Dinner Party Nation: USA. Agency: USAF AFSC. Apogee: 1,300 km (800 mi). Research and development launch. Mk 6 re-entry vehicle. References: 867.

• Charles W Mathews, new Acting Manager of Project Gemini, reviewed the current status of the spacecraft, launch vehicles, and ground facilities for the Gemini Management Panel. Modifications of launch complexes 19 and 14, of the tracking network, and of Atlantic Missile Range checkout facilities were all on schedule, although no margin remained for complex 19 work. The Atlas and Agena presented no problems, but the Gemini launch vehicle schedule was tight; technical problems, notably stage I longitudinal oscillations and stage II engine instability, were compounded by funding difficulties. The Gemini spacecraft, suffering from late deliveries by subcontractors, was being reprogrammed.

• The Gemini Program Planning Board approved the Air Force Systems Command development plan for the Gemini/Titan II improvement program. Nation: USA. The plan covered the development work required to man-rate the Titan II beyond the requirements of the Titan II weapon system and included three major areas: (1) reducing longitudinal oscillation levels to NASA requirements, (2) reducing the incidence of stage II engine combustion instability, and (3) cleaning up the design of stage I and II engines and augmenting the continuing engine improvement program to enhance engine reliability. The work was to be funded by the Titan Program Office of Air Force Ballistics Systems Division and managed by the Titan II/Gemini Coordination Committee, which had been established April 1. NASA found the plan satisfactory.

• Aerojet-General delivered the first flight engines for Gemini launch vehicle No. 1 to Martin-Baltimore. Nation: USA. Aerojet-General had provided a set of Type 'E' dummy engines March 18. These were installed and used to lay out tubing and wiring while the launch vehicle was being assembled. Additional Details: Aerojet-General delivered the first flight engines for Gemini launch vehicle No. 1 to Martin-Baltimore.(21391).

• Research and development launch Nation: USA. Agency: USAF AFSC. Apogee: 1,000 km (600 mi). Mk 6 re-entry vehicle. References: 867.

• Flying Frog Nation: USA. Agency: USAF AFSC. Apogee: 1,300 km (800 mi). Research and development launch. Mk 6 re-entry vehicle. References: 867.

• Research and development launch Nation: USA. Agency: USAF AFSC. Apogee: 1,300 km (800 mi). Mk 6 re-entry vehicle References: 867.

• The vertical test facility (VTF) at Martin-Baltimore was activated. Nation: USA. The VTF comprised a 165-foot tower and an adjacent three-story blockhouse with ground equipment similar to that used at complex 19. In it, the completely assembled Gemini launch vehicle was tested to provide a basis for comparison with subsequent tests conducted at complex 19. Each subsystem was tested separately, then combined systems tests were performed, concluding with the Combined Systems Acceptance Test, the final step before the launch vehicle was presented for Air Force acceptance.

• Research and development launch Nation: USA. Agency: USAF AFSC. Apogee: 2.00 km (1.20 mi). Titan II flight N-20, the 19th in the series of Air Force research and development flights, was launched from Cape Canaveral. It carried oxidizer standpipes and fuel accumulators to suppress longitudinal oscillations (POGO). During the spring of 1963, static firings of this configuration had been successful enough to confirm the hypothesis that POGO was caused by coupling between the missile structure and its propulsion system, resulting in an unstable closed loop system. Standpipes and accumulators, by interrupting the coupling reduced the source of instability. Flight N-20 failed 55 seconds after launch and yielded no POGO data. Although the failure was not attributed to the installed POGO fix, Air Force Ballistics Systems Division decided officially that no further Titan II development flights would carry the POGO fix because so few test flights remained to qualify the weapon system operationally. This decision did not stand, however, and the POGO fix was flown again on N-25 (November 1), as well as on two later flights.References: 867.

• Stage I of Gemini launch vehicle 1 was erected in Martin-Baltimore's vertical test facility. Nation: USA. Stage II was erected on June 9, and posterection inspection was completed June 12. Subsystem Functional Verification Tests began June 10.

• Manned Spacecraft Center - Atlantic Missile Range Operations Office reported that the malfunction detection system would be flown on Titan II launches N-24, N-25, N-29, N-31, and N-32. Nation: USA. The first launch in this so-called 'piggyback program' was scheduled for June 21. All preparations for this flight, including installation and checkout of all malfunction detection system components, were reported complete at a Titan II coordination meeting on June 14.

• Thread Needle Nation: USA. Agency: USAF AFSC. Apogee: 1,300 km (800 mi). Research and development launch. Mk 6 re-entry vehicle. References: 867.

• Martin-Baltimore received the stage II fuel tank for Gemini launch vehicle 2 from Martin-Denver. Nation: USA. This was a new tank, replacing a tank rejected for heat treatment cracks. Stage II oxidizer tank and stage I fuel and oxidizer tanks were received July 12 after a roll-out inspection at Martin-Denver July 1-3.

• Gemini Project Office exploring the possibility of backing up the first Gemini flight with a payload consisting of a boilerplate reentry module and a production adapter. Nation: USA. Acting Manager Charles W Mathews informed Manned Spacecraft Center (MSC) senior staff that Gemini Project Office was exploring the possibility of backing up the first Gemini flight with a payload consisting of a boilerplate reentry module and a production adapter. Additional Details: Gemini Project Office exploring the possibility of backing up the first Gemini flight with a payload consisting of a boilerplate reentry module and a production adapter.(21420).

• Effects on pilot performance of longitudinal oscillations (POGO) of the Gemini launch vehicle. Nation: USA. Gemini Project Office (GPO) completed a test program on the centrifuge at Ames Research Center to evaluate the effects on pilot performance of longitudinal oscillations (POGO) of the Gemini launch vehicle. When subjected to oscillatory g-loads ranging from 0 to ± 3g superimposed on a steady-state load of 3.5g, pilot perception and performance decreased markedly above ± 0.25g. Primary effects were impaired pilot vision, reduced eye scan rate, masked sensory perception and kinesthetic cues, and degraded speech. GPO reconfirmed the need to reduce POGO to a maximum of 0.25g.

• Electronic-Electrical Interference (EEI) Tests of Gemini launch vehicle (GLV) 1. Nation: USA. Electronic-Electrical Interference (EEI) Tests of Gemini launch vehicle (GLV) 1 began in the vertical test facility at Martin-Baltimore, following a review by Air Force Space Systems Division and Aerospace of data from Sub-system Verification Tests. Additional Details: Electronic-Electrical Interference (EEI) Tests of Gemini launch vehicle (GLV) 1.(21424).

• Research and development launch Nation: USA. Agency: USAF AFSC. Apogee: 1,300 km (800 mi). Titan II development flight N-24 was launched from the Atlantic Missile Range. This was the first of five flight tests in the Gemini malfunction detection system (MDS) piggyback series. All MDS parameters were lost 81 seconds after liftoff because of a short circuit in the MDS. Operation in the second flight (N-25 on November 1) was normal except for two minor instrumentation problems. Three more test flights (N-29 on December 12, 1963; N-31 on January 15, 1964; and N-33 on March 23, 1964) verified the performance of the Gemini MDS under actual conditions of flight environment and engine operation. References: 781.

• A Mission Planning Coordination Group was established. Nation: USA. Flight: Gemini 3. A Mission Planning Coordination Group was established at the request of the Gemini Project Office to review monthly activities in operations, network guidance and control, and trajectories and orbits; and to ensure the coordination of various Manned Spacecraft Center elements actively concerned with Gemini mission planning. Additional Details: A Mission Planning Coordination Group was established.(21437).

• Department of Defense approved the Titan II Augmented Engine Improvement Program. Nation: USA. On November 15, Aerojet-General received an Air Force contract to develop and test new engine components to correct weak and potentially dangerous problem areas of engine design. Aerojet-General had already initiated the development effort on September 30. The goal was to enhance engine reliability by a complete redesign rather than resort to piecemeal fixes as problems came up. While the primary goal was not achieved, the program did yield several side benefits, including the correction of several minor design deficiencies, the improvement of welding techniques, and the development of better assembly procedures.

• The formal Combined Systems Acceptance Test (CSAT) of Gemini launch vehicle No. 1 was conducted in the vertical test facility at Martin-Baltimore. Nation: USA. Two preliminary CSAT dry runs had been conducted on August 2 and 17, in conjunction with Electronic-Electrical Interference (EEI) Tests. Additional Details: The formal Combined Systems Acceptance Test (CSAT) of Gemini launch vehicle No. 1 was conducted in the vertical test facility at Martin-Baltimore.(21441).

• Vehicle acceptance team for Gemini launch vehicle (GLV) 1. Nation: USA. The vehicle acceptance team for Gemini launch vehicle (GLV) 1 inspected the vehicle and reviewed its manufacturing and testing history, focusing on the results of the Combined Systems Acceptance Test (CSAT) of September 6. Additional Details: Vehicle acceptance team for Gemini launch vehicle (GLV) 1.(21444).

• Gemini Project Office reported a delay of about three weeks in the battery qualification program. Nation: USA. McDonnell had sent a team to investigate the problem of high porosity welds in titanium battery cases. Another problem had turned up with the batteries in prequalification vibration test. The batteries vibrated excessively, although they did not fail electrically; the vibration's amplification factor was apparently low enough to be remedied by potting.

• Tar Top Nation: USA. Agency: USAF AFSC. Apogee: 1,300 km (800 mi). Research and development launch. Mk 6 re-entry vehicle. References: 867.

• Manned Spacecraft Center awarded its first incentive-type contract to Ling-Temco-Vought, Inc., Dallas, Texas for the fabrication of a trainer to be used in the Gemini launch vehicle training program. Nation: USA. The fixed-price-incentive-fee contract had a target cost of $90,000, a target profit of $9,000, and a ceiling of $105,000. The incentive was based on cost only and provided for an 80/20 sharing arrangement; that is, the contractor would pay from his profit 20 percent of all savings under the target cost, or, alternatively, would receive 20 percent of all savings under the target cost. This meant that the contractor's profit would be zero after $97,500 was spent, and would be minus if costs exceeded $105,000.

• Air Force Space Systems Division contracted with Aerojet-General for a program to develop a backup for the injectors of the second stage engine of the Gemini launch vehicle. Nation: USA. Titan II development flights had shown the stage II engine tended toward incipient combustion instability. The Gemini Stability Improvement Program, begun as a backup, became a program aimed at maximum probability of success on December 24, 1963. The 18-month program produced a completely redesigned stage II engine injector.

• Evaluation of data from the second Combined Systems Acceptance Test of Gemini launch vehicle (GLV) 1. Nation: USA. Martin-Baltimore completed its evaluation of data from the second Combined Systems Acceptance Test of Gemini launch vehicle (GLV) 1, found it acceptable, and presented it to the GLV-1 vehicle acceptance team (VAT). Additional Details: Evaluation of data from the second Combined Systems Acceptance Test of Gemini launch vehicle (GLV) 1.(21454).

• Reconsideration of flying Gemini fixes on Titan II development flights. Nation: USA. Personnel from Air Force Space Systems Division (SSD), Air Force Ballistic Systems Division (BSD), and Titan II contractors met in Los Angeles to reconsider flying Gemini launch vehicle (GLV) fixes on Titan II development flights. BSD, which was responsible for the weapon system development program, had halted the installation of GLV fixes on the Titan II flights because of the limited number of flights remaining to qualify the missile. General Bernard A Schriever, Commander of Air Force Systems Command (of which BSD and SSD were subordinate division), intervened in support of an active program to clean up launch vehicle problem areas. The incorporation of GLV fixes on Titan II flights resumed on November 1 with the flight of Titan II N-25.

• Gemini launch vehicle 1 arrived at Atlantic Missile Range and was transferred to complex 19. Nation: USA. Stage I was erected in the complete vehicle erector October 28, stage II in the second stage erector October 29. The two stages were cabled together in the side-by-side configuration required for the Sequence Compatibility Firing scheduled for mid-December. A limited Electronic-Electrical Interference Test was completed November 7, and power was applied to the vehicle November 13.

• Research and development launch Nation: USA. Agency: USAF AFSC. Apogee: 1,300 km (800 mi). Titan II development flight N-25 was launched from the Atlantic Missile Range. It carried the oxidizer surge chamber and fuel accumulator kit intended to reduce the amplitude of longitudinal vibration which had characterized earlier flights. NASA regarded 0.25g as the maximum level tolerable in manned space flight; this flight achieved a level of 0.22g, the first to fall within acceptable limits. Although the kit had been tested on only one flight, Gemini Project Office had sufficient confidence in it to decide, on November 6, to procure several more such kits for subsequent installation in Gemini launch vehicles. Two later Titan II development flights (N-29 on December 12, 1963, and N-31 on January 15, 1964) and the flight of Gemini-Titan 1 confirmed the validity of this decision. The required kits for the remaining Gemini launch vehicles were then procured. References: 781.

• Fire Truck Nation: USA. Agency: USAF AFSC. Apogee: 1,300 km (800 mi). Research and development launch References: 867.

• Gemini launch schedules reexamined. Nation: USA. Flight: Gemini 3. The Gemini Management Panel, after reviewing the status of spacecraft and launch vehicle, decided that Gemini launch schedules need reexamination, especially the amount of testing at Cape Canaveral necessary to establish confidence in mission success. Additional Details: Gemini launch schedules reexamined.(21465).

• Flight Crew Support Division reported an agreement with Flight Operations Division on a flight profile and rendezvous evaluation experiment for the Gemini-Titan 4 mission. Nation: USA. Flight: Gemini 4. Objective of the experiment was to stimulate normal Agena/Gemini rendezvous and to repeat part of the maneuver using loss of signal/manual technique. Basically, the mission would use circular phasing and catch-up orbit as proposed by the Flight Crew Support Division. Exact fuel requirements and ground tracking requirement were under study by Flight Operations Division.

• The Gemini Program Planning Board issued a memorandum of understanding of the correction of the Titan II deficiencies for the Gemini program. Nation: USA. This agreement formalized NASA specifications and Air Force plans to clean up problems related to longitudinal oscillations (POGO), combustion instability, and engine improvement. The program to alleviate the POGO effect included ground proof tests of all subsystems modified to control oscillations. Flight tests of the solutions would be flown on Titan II missiles before application to the Gemini launch vehicle. For the combustion stability program, dynamic stability would be demonstrated through the use of artificially produced disturbances, with the engines being flight tested on unmanned vehicles as final proof of man-rating. Engine improvement was a program to correct all design deficiencies that had cropped up during the Titan II development flights.

• Aerojet-General delivered the stage II engine for Gemini launch vehicle (GLV) 2 to Martin-Baltimore. Nation: USA. The engine was installed December 31. An interim stage I engine was received December 29 and installed January 9, 1964. Additional Details: Aerojet-General delivered the stage II engine for Gemini launch vehicle (GLV) 2 to Martin-Baltimore.(21474).

• Research and development launch Nation: USA. Agency: USAF AFSC. Apogee: 1,300 km (800 mi). References: 781.

• Martin-Baltimore received the propellant tanks for Gemini launch vehicle (GLV) 3 from Martin-Denver, which had begun fabricating them in June. Nation: USA. Flight: Gemini 3. Splicing the oxidizer and fuel tanks for each stage was completed April 17, 1964. Flight engines arrived from Aerojet-General on May 10, and installation was completed June 6. Final horizontal tests of the assembled launch vehicle began June 1 and were concluded on June 17 with an Air Force inspection of GLV-3 before the vehicle was erected in the vertical test facility.

• Useful Task Nation: USA. Agency: USAF AFSC. Apogee: 1,300 km (800 mi). Research and development launch References: 867.

• Gemini launch vehicle 1 completed the Combined Systems Test (CST). Nation: USA. The two stages of Gemini launch vehicle 1, standing side by side on complex 19, completed the Combined Systems Test (CST) in preparation for Sequence Compatibility Firing (SCF). CST had been scheduled for December 13 but was delayed by late completion of the complex support systems for operational compatibility with the launch vehicle.Additional Details: Gemini launch vehicle 1 completed the Combined Systems Test (CST).(21481).

• The program plan for Gemini extravehicular operations was published. Nation: USA. Flight: Gemini 5, Gemini 6, Gemini 7, Gemini 8, Gemini 9, Gemini 10, Gemini 11, Gemini 12. Objectives of the operations were to evaluate man's capabilities to perform useful tasks in a space environment, to employ extravehicular operations to augment the basic capability of the spacecraft, and to provide the capability to evaluate advanced extravehicular equipment in support of manned space flight and other national space programs. Additional Details: The program plan for Gemini extravehicular operations was published.(21482).

• NASA Headquarters directed Gemini Project Office to take the radar and rendezvous evaluation pod out of Gemini-Titan (GT) missions 3 and 4. Spacecraft: Gemini. Flight: Gemini 4, Gemini 5. GT-4 would be a battery-powered long-duration flight. The pod would go on GT-5, and thus the first planned Agena flight would probably slip in the schedule.

• Research and development launch Nation: USA. Agency: USAF AFSC. Apogee: 1,300 km (800 mi). References: 867.

• Martin-Baltimore conducted a static test-to-failure of the spacecraft/launch vehicle interface structure. Nation: USA. Test results demonstrated a very satisfactory minimum structural margin of 23 percent above ultimate conditions expected to be met in the transonic buffet conditions of launch. Plans were made to hold a structures meeting in Houston on March 17-19, 1964, for final review of all load conditions, stress distribution, and margins, in readiness for the Gemini-Titan 1 mission.

• Red Sails. Nation: USA. Agency: USAF AFSC. Apogee: 1,300 km (800 mi). Research and development launch References: 867.

• Gemini launch vehicle 2 stage I and interstage were erected in the vertical test facility at Martin-Baltimore. Nation: USA. Stage II was erected February 7. Subsystems Functional Verification Tests began February 21.

• Safe Conduct Nation: USA. Agency: USAF AFSC. Apogee: 1,300 km (800 mi). Research and development launch References: 867.

• Gemini launch vehicle 1 Subsystem Functional Verification Tests (SSFVT) began on complex 19. Nation: USA. These repeated the SSFVT performed at Martin-Baltimore in the vertical test facility. Their purpose was to verify the vehicle's readiness to begin systems tests. SSFVT were completed on March 3.

• Research and development launch Nation: USA. Agency: USAF AFSC. Apogee: 1,300 km (800 mi). References: 867.

• Gemini launch vehicle (GLV) 1 and spacecraft No. 1 were mechanically mated at complex 19. Nation: USA. Before GLV and spacecraft were electrically mated, the launch vehicle's status was reverified with a Combined Systems Test (CST) performed on March 10. A special series of Electronic-Electrical Interference (EEI) Tests began March 12 and ended March 25. Evaluation of test results confirmed that the intent of EEI testing had been accomplished, despite some persistent anomalies. A successful post-EEI systems reverification CST was performed March 27.

• Martin-Baltimore received the propellant tanks for Gemini launch vehicle 4 from Martin-Denver, which had begun fabricating them in November 1963. Nation: USA. Flight: Gemini 4. Tank splicing was completed July 21. Aerojet-General delivered the stage II flight engine June 26, the stage I engine July 28. Engine installation was completed September 4. Final horizontal tests were completed and reviewed October 26, with Martin authorized to erect the vehicle in the vertical test facility.

• Apple Pie Nation: USA. Agency: USAF AFSC. Apogee: 1,300 km (800 mi). Research and development launch References: 867.

• The Air Force Systems Command weekly report (inaugurated in September 1963) summarizing actions taken to resolve Titan II development problems would no longer be issued. Nation: USA. George E. Mueller, NASA Associate Administrator for Manned Space Flight, informed Associate Administrator Robert C. Seamans, Jr., that the launch vehicle 'no longer appears to be the pacing item in the Gemini program.'

• Research and development launch Nation: USA. Agency: USAF AFSC. Apogee: 1,300 km (800 mi). References: 780.

• Electrical and mechanical modification of Gemini launch vehicle (GLV) 1 airborne components was completed. Nation: USA. GLV-1 had been shipped to the Cape equipped with several items to be used only for ground tests. These were replaced with flight units, beginning January 31. The GLV-1 Wet Mock Simulated Launch, a complete countdown exercise including propellant loading, was successfully completed April 2. Testing concluded on April 5 with a Simulated Flight Test.

• Gemini 1 Nation: USA. Program: Gemini. Payload: Gemini SC1. Mass: 3,187 kg (7,026 lb). Class: Manned. Type: Spacecraft. Spacecraft: Gemini. Agency: NASA MSC. Perigee: 154 km (95 mi). Apogee: 299 km (185 mi). Inclination: 32.60 deg. Period: 89.00 min. COSPAR: 1964-018A. USAF Sat Cat: 782. Decay Date: 1964-04-12. The first Gemini mission, Gemini-Titan I, was launched from Complex 19 at Cape Kennedy at 11:00 a.m., e.s.t. This was an unmanned flight, using the first production Gemini spacecraft and a modified Titan II Gemini launch vehicle (GLV). The mission's primary purpose was to verify the structural integrity of the GLV and spacecraft, as well as to demonstrate the GLV's ability to place the spacecraft into a prescribed earth orbit. Mission plans did not include separation of the spacecraft from the second stage of the vehicle, and both were inserted into orbit as a unit six minutes after launch. The planned mission encompassed only the first three orbits and ended about four hours and 50 minutes after liftoff. No recovery was planned for this mission, but Goddard continued to track the spacecraft until it reentered the atmosphere on the 64th orbital pass over the southern Atlantic Ocean (April 12) and disintegrated. The flight qualified the GLV and its systems and the structure of the spacecraft.References: 1, 2, 5, 6, 16, 26.

• Research and development launch Nation: USA. Agency: USAF AFSC. Apogee: 1,300 km (800 mi). This Air Force conducted test program contributed significantly to the development of the Gemini launch vehicle; the Gemini malfunction detection system was tested on five flights, Gemini guidance components on three, and the longitudinal oscillation fix on four. In addition to flight testing these (and other) critical components, these flights also enhanced confidence in the use of the Titan II as a launch vehicle. Thirty-two Titan II test flights were analyzed to determine whether any characteristic of the flight would have demanded a Gemini abort; 22 were adjudged successful from the standpoint of a Gemini mission, nine would have required Gemini to abort, and one resulted in a prelaunch shutdown.References: 867.

• Electrical-Electronic Interference Tests began on Gemini launch vehicle (GLV) 2 in the vertical test facility at Martin-Baltimore. Nation: USA. Oscillograph recorders monitored 20 GLV and aerospace ground equipment (AGE) circuits, five of which displayed anomalies. Two hydraulic switchover cicuits showed voltage transients exceeding failure criteria, but a special test fixed this anomaly in the AGE rather than the GLV.

• After reviewing the results of Gemini-Titan (GT) 1, the Gemini Management Panel remained optimistic that manned flight could be accomplished in 1964. Nation: USA. Flight: Gemini 3. According to the work schedule, GT-2 could fly on August 24 and GT-3 on November 16, with comfortable allowances for four-week slips for each mission. Some special attention was devoted to GT-2, where the spacecraft had become the pacing item, a position held by the launch vehicle on GT-1. Spacecraft No. 2 systems tests had started one month late but were proceeding well. In addition, the schedule looked tight for starting spacecraft No. 3 systems tests on June 1.

• The formal Combined Systems Acceptance Test (CSAT) of Gemini launch vehicle (GLV) 2 was satisfactorily completed in the vertical test facility at Martin-Baltimore. Nation: USA. Three preliminary CSATs (April 17-20) had been completed and all anomalies resolved. Additional Details: The formal Combined Systems Acceptance Test (CSAT) of Gemini launch vehicle (GLV) 2 was satisfactorily completed in the vertical test facility at Martin-Baltimore.(21522).

• The vehicle acceptance team (VAT) for Gemini launch vehicle (GLV) 2 convened at Martin-Baltimore. Nation: USA. The VAT inspection was completed May 1 with GLV-2 found acceptable. Additional Details: The vehicle acceptance team (VAT) for Gemini launch vehicle (GLV) 2 convened at Martin-Baltimore.(21523).

• Langley Research Center completed tests on a model of the Gemini launch vehicle to determine the static and dynamic loads imposed on the vehicle and the launch vehicle erector by ground winds. Nation: USA. Simulated wind velocities of 5 to 52 miles per hour did not produce loads great enough to be of concern. Tests had begun on April 15.

• Primary and backup crews for Gemini-Titan 3 inspected a spacecraft No.3 crew station mock-up at McDonnell. Nation: USA. Flight: Gemini 3. They found all major aspects of the crew station acceptable. A few items remained to be corrected but would not affect the launch schedule.

• The entire complement of astronauts began launch abort training on the Ling-Temco-Vought simulator. Nation: USA. Flight: Gemini 3. Group 1 (selected April 1959) and Group 2 (September 1962) astronauts averaged approximately 100 runs each whereas Group 3 (October 1963) astronauts completed 32 runs apiece. The Gemini-Titan 3 launch profile was simulated in detail, including such cues as noise, vibration, pitch and roll programming, and other motion cues which results from various launch anomalies. The training was completed July 30.

• Contract with Martin for 15 Gemini launch vehicles (GLV) converted. Nation: USA. Air Force Space Systems Division's cost-plus-fixed-fee contract with Martin for 15 Gemini launch vehicles (GLV) and associated aerospace ground equipment was replaced by a cost-plus-incentive-fee contract. Contract negotiations had been conducted between March 15 and April 30, 1964. The final contract contained cost, performance, and schedule incentives. Target cost was $111 million and target fee was $8.88 million. The maximum fee possible under the contract was $16.65 million as against a minimum of $3.33 million. The period of performance under the contract was July 1, 1963, through December 31, 1967, and covered the delivery of 14 GLVs (one GLV had already been delivered) and associated equipment and services, including checkout and launch.

• Christopher C. Kraft, Jr., Assistant Director for Flight Operations, Manned Spacecraft Center, reported that three basic plans were under study for rendezvous missions. Nation: USA. Flight: Gemini 6. Rendezvous at first apogee would probably be rejected because of possible dispersions which might necessitate plane changes. Rendezvous from concentric orbits seemed to be desirable because of the freedom in selection of the geographic position of rendezvous. Major work thus far, however, had been expended on the tangential rendezvous. Subsequently, the concentric orbit plan was chosen for Gemini-Titan 6, the first rendezvous mission.

• Contract with Aerojet-General for engines and related aerospace ground equipment revised. Nation: USA. Air Force Space Systems Division's cost-plus-fixed-fee contract with Aerojet-General for engines and related aerospace ground equipment for the Gemini launch vehicle was replaced by a cost-plus-incentive-fee contract. Contract negotiations had been conducted between May 25 and June 17, 1964. The final contract covered the procurement of 14 sets of engines (one set had already been delivered) and associated equipment during the period from July 1, 1963, through December 31, 1967. Cost, performance, and schedule incentives made possible a maximum fee of $5,885,250 versus a minimum fee of $1,177,050. The initial target cost was $39,235,000 with a target fee of $3,138,800.

• Stage I of Gemini launch vehicle 3 was erected in the vertical test facility at Martin-Baltimore. Nation: USA. Flight: Gemini 3. Stage II was erected June 22. Power was first applied June 29, and subsystems functional verification testing concluded July 31.

• Martin-Baltimore received the propellant tanks for Gemini launch vehicle (GLV) 5 from Martin-Denver, which had begun fabrication in October 1963. Nation: USA. Flight: Gemini 5. Aerojet-General delivered the flight engines for GLV-5 November 5. Tank splicing was completed December 5; engine installation December 9. Final horizontal tests were completed January 7, 1965.

• Gemini spacecraft 2 began the second phase of Spacecraft Systems Tests. Nation: USA. Following the successful mating of its modules, Gemini spacecraft No. 2 began the second phase of Spacecraft Systems Tests (SST) at McDonnell. SST continued through September. During August and September, test operations alternated with the receipt and installation of a number of flight items in the spacecraft.Additional Details: Gemini spacecraft 2 began the second phase of Spacecraft Systems Tests.(21547).

• Manager Charles W. Mathews reported that the Gemini Program Office had been reviewing and evaluating plans for Gemini-Titan (GT) missions 4 through 7. Nation: USA. Spacecraft: Gemini. Flight: Gemini 4, Gemini 5, Gemini 6. GT-4 would be a four-day mission using battery power. Additional Details: Manager Charles W. Mathews reported that the Gemini Program Office had been reviewing and evaluating plans for Gemini-Titan (GT) missions 4 through 7.(21548).

• Gemini launch vehicle 2 arrived at Eastern Test Range. Nation: USA. Stage I was erected at complex 19 on July 13, stage II on July 14. Electrical power was applied to the vehicle on July 20 in preparation for Subsystems Functional Verification Tests, which began July 21.

• Gemini Program Office reported that tests had been conducted on section I of the fuel cells planned for the long-duration Gemini-Titan 5 mission. Nation: USA. Spacecraft: Gemini. Flight: Gemini 5. These tests had resulted in a failure characterized by output decay. A complete investigation was in process to determine the cause of the failure.

• McDivitt and White II named for the Gemini-Titan 4 mission. Nation: USA. Flight: Gemini 4. Astronauts James A. McDivitt and Edward H. White II were named as command pilot and pilot, respectively, for the Gemini-Titan (GT) 4 mission scheduled for the first quarter of 1965. The backup crew for the mission would be Frank Borman, command pilot, and James A. Lovell, Jr., pilot.Additional Details: McDivitt and White II named for the Gemini-Titan 4 mission.(21552).

• Gemini missions beyond the 12 originally planned considered. Nation: USA. In response to a request from NASA Headquarters, Gemini Program Office (GPO) provided a study for Gemini missions beyond the 12 originally planned. 'The Advanced Gemini Missions Conceptual Study' described 16 further missions, including a space station experiment, a satellite chaser mission, a lifeboat rescue mission, and both a circumlunar and lunar orbiting mission. On February 28, 1965, GPO reported that a preliminary proposal for Gemini follow-on missions to test the land landing system had not been approved. Spare Gemini launch vehicles 13, 14, and 15 were canceled, and there were no current plans for Gemini missions beyond the approved 12-flight program.

• Cobra Skin Nation: USA. Agency: USAF SAC. Apogee: 1,300 km (800 mi). Demonstration and shakedown operations launch References: 867.

• The formal Combined Systems Acceptance Test (CSAT) of Gemini launch vehicle (GLV) 3 was successfully performed. Nation: USA. Flight: Gemini 3. The vehicle acceptance team (VAT) met August 17 to review CSAT and other test and manufacturing data. Additional Details: The formal Combined Systems Acceptance Test (CSAT) of Gemini launch vehicle (GLV) 3 was successfully performed.(21556).

• Double Talley Nation: USA. Agency: USAF SAC. Apogee: 1,300 km (800 mi). Demonstration and shakedown operations launch References: 867.

• Gentle Annie Nation: USA. Agency: USAF SAC. Apogee: 1,300 km (800 mi). Demonstration and shakedown operations launch References: 867.

• Martin-Baltimore received the propellant tanks for Gemini launch vehicle 6 from Martin-Denver, which had begun fabricating them in April. Nation: USA. Flight: Gemini 6. After being inspected, the tanks were placed in storage where they remained until December 18.

• A severe electrical storm in the vicinity of complex 19 interrupted testing of Gemini launch vehicle (GLV) 2. Nation: USA. Several observers reported a lightning strike at or near complex 19. Additional Details: A severe electrical storm in the vicinity of complex 19 interrupted testing of Gemini launch vehicle (GLV) 2.(21559).

• Hurricane Cleo struck the Cape Kennedy area. Nation: USA. Stage II of Gemini launch vehicle (GLV) 2 was deerected and stored; the erector was lowered to horizontal, and stage I was lashed in its vertical position. Stage II was reerected September 1. Power was applied to the launch vehicle September 2, and Subsystem Functional Verification Tests (SSFVT) began September 3. When forecasts indicated that Hurricane Dora would strike Cape Kennedy, both stages of GLV-2 were deerected on September 8 and secured in the Missile Assembly Building. Hurricane Ethel subsequently threatened the area, and both stages remained in the hanger until September 14, when they were returned to complex 19 and reerected. SSFVT, begun again on September 18, ended successfully October 5.

• Air Force Space Systems Division (SSD), supported by launch vehicle contractors, recommended that Gemini launch vehicle (GLV) 2 be flown as scheduled. Nation: USA. Manned Spacecraft Center had proposed dropping GLV-2 from the Gemini program because of possible ill effects resulting from the electromagnetic incident of August 17 and from Hurricane Cleo. GLV-3 would then be substituted for the second Gemini mission, and the program would be shortened by one flight. After reviewing the incidents, their effects, corrective action, and retesting, SSD, Martin, Aerospace, and Aerojet-General all felt GLV-2 should fly, and NASA accepted their recommendation.