PART III (B)

Flight Tests

January 1966 through February 1967

January 5

Atlas 5302, target launch vehicle for Gemini VIII, was erected at complex 14. Air Force Space Systems Division and General Dynamics/Convair had begun intensive efforts to ensure the vehicle's flight readiness immediately after the Agena failure on October 25, 1965. The effort resulted in procedural and design changes intended to improve vehicle reliability. Of the 20 engineering change proposal differences between Atlas 5301 (launched October 25) and Atlas 5302, all but one were proven in other Atlas flights before Atlas 5302 was launched. The exception was a new destruct unit which flew for the first time in Atlas 5302. Booster subsystems tests continued until February 23.

Mission Report for GT-VIII, p. 12-13; Quarterly Status Report No. 16, p. 18.

January 8

McDonnell delivered spacecraft No. 8 to Cape Kennedy. Fuel cell installation, heater resistance checks, and pyrotechnics buildup lasted two weeks. The spacecraft was then transferred to Merritt Island Launch Area for integrated (Plan X) test with the target vehicle, January 26-28, and extravehicular equipment compatibility test, January 29.

Mission Report for GT-VIII, p. 12-4.

January 8

Gemini Agena target vehicle (GATV) 5003 completed its final acceptance tests at Sunnyvale, after an elusive command system problem had made it necessary to rerun the final systems test (January 4). No vehicle discrepancy marred the rerun. Air Force Space Systems Division formally accepted GATV 5003 on January 18, after the vehicle acceptance team inspection. It was shipped to Eastern Test Range the same day, but bad weather delayed delivery until January 21. GATV 5003 was to be the target vehicle for Gemini VIII.

GATV Progress Report, January 1966, pp. 2-2, 2-4.

January 13

Gemini launch vehicle (GLV) 8 was erected at complex 19. After the vehicle was inspected and umbilicals connected, power was applied January 19. Subsystems Reverification Tests began the following day and lasted until January 31. The Prespacecraft Mate Verification of GLV-8 was run February 1. A launch test-procedure review was held February 2-3. During leak checks of the stage II engine on February 7, small cracks were found in the thrust chamber manifold. X-rays revealed the cracks to be confined to the weld; rewelding eliminated the problem. Systems rework and validation were completed February 9.

Mission Report for GT-VIII, p. 12-7; Aerospace Final Report, p. II.G-5; Kuras and Albert, "Gemini-Titan Technical Summary," p. 146.

January 16

Project Surefire verification testing began at Bell Aerosystems. Bell's part in the test program was to demonstrate the sea-level flightworthiness of the modified Agena main engine. Bell completed testing on March 4 with a full 180-second mission simulation firing. The successful completion of this phase of the test program gave the green light for the launch of Gemini Agena target vehicle 5003, scheduled for March 15.

GATV Progress Reports: January, pp. 2-1, 2-2; March 1966, pp. 2-3, 2-4.

January 17

At a NASA-McDonnell Management Panel meeting, W. B. Evans of Gemini Program Office reviewed possible future mission activities. Gemini VIII would have three periods of extravehicular activity (EVA) - two in daylight, one in darkness - and would undock during EVA with the right hatch snubbed against the umbilical guide and the astronaut strapped into the adapter section. A redocking would be performed with one orbit of stationkeeping performed before each docking. EVA would include retrieval of the emulsion pack from the adapter, the starting of the S-10 (Micrometeorite Collection) experiment on the Agena, and the use of a power tool. The astronaut would don the extravehicular support pack, use the hand-held maneuvering unit, and check different lenghts of tether. The spacecraft would maneuver to the astronaut and the astronaut to the Agena. It would incorporate a secondary propulsion system burn with the Agena and would be a three-day mission. Gemini IX would also be a three-day mission and would include a simulated lunar module (LM) rendezvous (third apogee rendezvous), a primary propulsion system (PPS) burn with the docked Agena, a rendezvous from above, a simulated LM abort, a phantom rendezvous with three PPS burns (double rendezvous), EVA with the modular maneuvering unit, and the parking of the Gemini VIII and Gemini IX Agenas. Gemini X would include a dual rendezvous with a parked Agena and the retrieval of the S-10 experiment after undocking with the new Agena, using EVA.

Minutes of NASA-MAC Management Panel Meeting held at MSC, Jan. 17, 1966.

January 20

Martin-Denver delivered propellant tanks for Gemini launch vehicle (GLV) 12 to Martin-Baltimore by air. The GLV-12 stage II fuel tank had been reallocated to GLV-11, and GLV-12 used the stage II fuel tank originally assigned to GLV-10, which had been reworked to eliminate the damaged dome that had caused the tank reshuffling. The reworked tank arrived March 12. Aerojet-General had delivered the stage I engine on December 13, 1965, the stage II engine on January 20. Stage I tank splicing was completed April 25, stage II on May 4. Engine installations were completed May 19. Stage I horizontal testing ended June 1, and stage II, June 22.

Gemini Program Mission Report, Gemini XII, January 1967, p. 12-7; Aerospace Final Report, p. II.G-7; Gemini-Titan Air Force Launch Vehicle, pp. D-19, D-20.

January 21

McDonnell completed final assembly of the augmented target docking adapter (ATDA). Voltage Standing Wave Ratio Tests were conducted January 21 and 22. Systems Assurance Tests were completed January 25, vibration tests January 27. Simulated flight and phasing tests were conducted January 30-February 1. The ATDA was shipped to Cape Kennedy February 4.

Mission Report for GT-IXA, p. 12-8.

January 21

Qualification testing of the freon-14 extravehicular propulsion system for the Gemini VIII mission had been successfully completed. During earlier tests some freezing problems had resulted; however, with particular attention given to drying procedures used in loading the gas, the freezing problem was eliminated, and later tests were successful. Oxygen had been used for propulsion fuel during extravehicular activities by Astronaut Edward H. White II on Gemini IV.

Quarterly Activity Report, Jan. 31, 1966, p. 44.

January 22

Gemini Agena target vehicle (GATV) 5003 was mated to target docking adapter (TDA) 3. McDonnell had delivered TDA-3 to Cape Kennedy on January 8. The GATV/TDA interface functional test was completed January 24, and the vehicle was transferred to Merritt Island Launch Area for integrated tests with spacecraft No. 8 and extravehicular equipment, which were completed January 28.

Mission Report for GT-VIII, p. 12-10; GATV Progress Report, January 1966, p. 2-5.

January 25

Astronaut John W. Young had been selected as the command pilot for Gemini X. The pilot would be Astronaut Michael Collins. The backup crew would be James A. Lovell, Jr., command pilot, and Edwin E. Aldrin, Jr., pilot.

Astronautics and Aeronautics, 1966: Chronology of Science, Technology, and Policy, NASA SP-4007, p. 27; MSC Space News Roundup, Feb. 4, 1966, p. 2.

January 26

Gemini Agena target vehicle (GATV) 5004 was transferred to the vehicle systems test area at Sunnyvale. Its modified main engine had been received on schedule from Bell Aerosystems January 12 and installed by January 20. Because of GATV 5003 priority, however, several main electronic assemblies, including the command system, had been removed from GATV 5004 and used in GATV 5003 final acceptance tests. As a result, GATV 5004 had fallen eight days behind its scheduled transfer date, January 18.

GATV Progress Report, January 1966, pp. 2-5, 2-6.

January 28

Gemini Agena target vehicle (GATV) 5003 was returned to Hanger E after completing Plan X tests at Merritt Island Launch Area. Systems Verification and Combined Interface Tests were conducted through February 18, followed by functional checks of the primary and secondary propulsion systems. Hanger E testing ended February 28, and the GATV was transferred to complex 14.

Mission Report for GT-VIII, p. 12-10; GATV Progress Report, January 1966, p. 2-5.

January 31

Gemini spacecraft No. 8 was transferred to complex 19 and hoisted to its position atop the launch vehicle. Cables were connected for test February 1-2, and Prespacecraft Mate Verification Tests were conducted February 3-8. Fuel cells were activated February 8 and deactivated the following day. Spacecraft / launch vehicle integrated tests began February 10.

Mission Report for GT-VIII, p. 12-4.

February 2

A mission planning meeting for Gemini flights IX through XII, held at McDonnell, was attended by members of the Gemini Program Office and Flight Operations Division. The last item on the agenda was a reminder from McDonnell that the Gemini spacecraft was capable of flying to a relatively high elliptic orbit from which it could safely reenter under certain circumstances. The type of orbit McDonnell suggested had an apogee of 500-700 nautical miles. This would involve using the Agena primary propulsion system both to get into this orbit and to return to a 161-mile circular orbit for nominal reentry.

Memo, Asst. Chief, MPAD, to Distribution, Subj: Mission Planning Meeting at MAC, Feb. 8, 1966.

February 2

Agena D (AD-129) was accepted by the Air Force for delivery to the Gemini program. It was transferred to the final assembly area at Sunnyvale for modification to Gemini Agena target vehicle 5005.

Aerospace Final Report, p. III.G-3.

February 4

The augmented target docking adapter (ATDA) arrived at Cape Kennedy. Modifications, testing, and troubleshooting were completed March 4. The ATDA, which was intended to back up the Gemini Agena target vehicle (GATV), was then placed in storage (March 8) where it remained until May 17, when the failure of target launch vehicle 5303 prevented GATV 5004 from achieving orbit. The ATDA became the target for Gemini IX-A.

Mission Report for GT-IXA, p. 12-9; Quarterly Status Report No. 17 for Period Ending May 31, 1966, p. 2.

February 9

The Combined Systems Acceptance Test of Gemini launch vehicle (GLV) 9 was successfully conducted in the vertical test facility at Martin-Baltimore. The vehicle acceptance team convened February 14 and concluded its review on February 17 by accepting the vehicle. Deerection of GLV-9 was completed February 25, and the vehicle was formally accepted by the Air Force March 8. Stage I arrived at Cape Kennedy on March 9, stage II on March 10.

Mission Report for GT-IXA, pp. 12-6, 12-7; Aerospace Final Report, p. II.G-7; Gemini-Titan II Air Force Launch Vehicle, p. D-15.

February 10

Gemini launch vehicle 8 and spacecraft 8 were electrically mated; the Electrical Interface Integrated Validation and Joint Guidance and Control Test was completed February 14. After data from this test were reviewed (February 15), the Joint Combined Systems Test was run February 16.

Mission Report for GT-VIII, p. 12-7.

February 17

The tanking test of Gemini launch vehicle (GLV) 8 was conducted. While the launch vehicle was being cleaned up after the test, spacecraft No. 8 Final Systems Test was completed February 23. On February 25, GLV and spacecraft were temporarily mated for an erector-cycling test. The extravehicular support package and life support system were checked out and installed in the spacecraft between February 26 and March 5, while GLV systems were modified and revalidated February 28 to March 3.

Mission Report for GT-VIII, pp. 12-4, 12-7; Aerospace Final Report, p. II.G-5.

February 23

A successful Booster Flight Acceptance Composite Test (B-FACT) completed subsystems testing of target launch vehicle 5302. Component problems had delayed completion of some of the vehicle pad tests, including B-FACT, which had first been run on February 4. Difficulties were also encountered in completing the propellant tanking tests.

Mission Report for GT-VIII, p. 12-13; Quarterly Status Report No. 16, p. 18.

February 23

The astronaut maneuvering unit (AMU) scheduled to be tested on the Gemini IX mission was delivered to Cape Kennedy. The receiving inspection revealed nitrogen leaks in the propulsion system and oxygen leaks in the oxygen supply system. Reworking these systems to eliminate the leakage was completed on March 11. Following systems tests, the AMU was installed in spacecraft No. 9 (March 14-18).

Mission Report for GT-IXA, p. 12-12.

Figure 119. Method of donning the astronaut maneuvering unit, carried in the adapter section. (NASA Photo S-66-24197, Mar. 16, 1966.)

February 23-24

Over 600 representatives of Government agencies and industrial firms participating in Project Gemini attended a Gemini Midprogram Conference at Manned Spacecraft Center. They heard some 44 papers describing the development of spacecraft and launch vehicle, flight operations, and the results of the first seven Gemini missions, including the findings of experiments performed during these missions.

Gemini Midprogram Conference, passim.

February 27

Gemini Agena target vehicle (GATV) 5004 completed systems testing at Sunnyvale. It was formally accepted by the Air Force on March 11, following the vehicle acceptance team inspection. The next day (March 12), GATV 5004 was shipped by air to Eastern Test Range, arriving March 14.

Aerospace Final Report, p. III.G-3; GATV Progress Report, March 1966, pp. 2-5, 2-6.

February 28

Gemini IX Astronauts Elliot M. See, Jr., and Charles A. Bassett II were killed when their T-38 jet training plane crashed in rain and fog short of the St. Louis Municipal Airport. The jet, which had been cleared for an instrument landing, was left of center in its approach to the runway when it turned toward the McDonnell complex, 1000 feet from the landing strip. It hit the roof of the building where spacecraft nos. 9 and 10 were being housed, bounced into an adjacent courtyard, and exploded. Several McDonnell employees were slightly injured. Minutes later the Gemini IX backup crew, Thomas P. Stafford and Eugene A. Cernan, landed safely. The four astronauts were en route to McDonnell for two weeks' training in the simulator. NASA Headquarters announced that Stafford and Cernan would fly the Gemini IX mission on schedule and appointed Alan B. Shepard, Jr., to head a seven-man investigating team.

MSC Space News Roundup, Mar. 4, 1966, p. 1; Washington Post, Mar. 1 and 2, 1966; interview, John H. Bickers, St. Louis, Apr. 13 1966.

February 28

Stage I of Gemini launch vehicle 10 was erected in the east cell of the vertical test facility at Martin-Baltimore. After completing horizontal testing March 3, stage II was erected March 7. Power was applied to the vehicle for the first time on March 14. Subsystems Functional Verification Tests were completed April 13.

Mission Report for GT-X, p. 12-7; Gemini-Titan II Air Force Launch Vehicle, pp. D-16, D-17.

March 1

Gemini Agena target vehicle 5003 was mated to targate launch vehicle 5302 at complex 14. After ground equipment compatibility tests, the Joint Flight Acceptance Composite Test was successfully performed on March 7. Simultaneous Launch Demonstration March 8-9 completed Gemini Atlas-Agena target vehicle systems testing in preparation for launch on March 15 as part of the Gemini VIII mission.

Mission Report for GT-VIII, p. 12-10; GATV Progress Report, March 1966, p. 2-4.

March 2

Spacecraft No. 9 and target docking adapter No. 5 arrived at Cape Kennedy from McDonnell. Spacecraft fuel cells were installed March 3-4. Pyrotechnics buildup, further installations, and preparations for test lasted until March 18. The spacecraft was then transferred to Merritt Island Launch Area for Plan X integrated tests with the target vehicle and extravehicular systems March 22-24.

Mission Report for GT-IXA, p. 12-4.

March 6

Gemini launch vehicle 8 and spacecraft No. 8 were mated for flight at complex 19. The Simultaneous Launch Demonstration with the Gemini Atlas-Agena target vehicle on complex 14 was completed March 9. The Final Simulated Flight Test concluded prelaunch tests on March 10.

Mission Report for GT-VIII, p. 12-7.

March 13

The fuel tank of target launch vehicle 5302 was overfilled during propellant loading. The necessary replacement of the fuel-tank regulator and fuel relief valve was completed the next day. The launch, which had been scheduled for March 15, was postponed to March 16.

Mission Report for GT-VIII, p. 12-13; Kuras and Albert, "Gemini-Titan Technical Summary," p. 147.

March 16

The Gemini VIII mission began with the launch of the Gemini Atlas-Agena target vehicle from complex 14 at 9:00 a.m., e.s.t. The Gemini space vehicle, with command pilot Astronaut Neil A. Armstrong and pilot Astronaut David R. Scott, was launched from complex 19 at 10:41 a.m. Primary objectives of the scheduled three-day mission were to rendezvous and dock with the Gemini Agena target vehicle (GATV) and to conduct extravehicular activities. Secondary objectives included rendezvous and docking during the fourth revolution, performing docked maneuvers using the GATV primary propulsion system, executing 10 experiments, conducting docking practice, performing a rerendezvous, evaluating the auxiliary tape memory unit, demonstrating controlled reentry, and parking the GATV in a 220-nautical mile circular orbit. The GATV was inserted into a nominal 161-nautical mile circular orbit, the spacecraft into a nominal 86 by 147-nautical mile elliptical orbit. During the six hours following insertion, the spacecraft completed nine maneuvers to rendezvous with the GATV. Rendezvous phase ended at 5 hours 58 minutes ground elapsed time, with the spacecraft 150 feet from the GATV and no relative motion between the two vehicles. Stationkeeping maneuvers preceded docking, which was accomplished at 6 hours 33 minutes ground elapsed time. A major problem developed 27 minutes after docking, when a spacecraft orbit attitude and maneuver system (OAMS) thruster malfunctioned. The crew undocked from the GATV and managed to bring the spacecraft under control by deactivating the OAMS and using the reentry control system (RCS) to reduce the spacecraft's rapid rotation. Premature use of the RCS, however, required the mission to be terminated early. The retrofire sequence was initiated in the seventh revolution, followed by nominal reentry and landing in a secondary recovery area in the western Pacific Ocean. The spacecraft touched down less than seven miles from the planned landing point at 10:22 p.m. The recovery ship, the destroyer Leonard Mason, picked up both crew and spacecraft some three hours later. Early termination of the mission precluded achieving all mission objectives, but one primary objective - rendezvous and docking - was accomplished. Several secondary objectives were also achieved: rendezvous and docking during the fourth revolution, evaluating the auxiliary tape memory unit, demonstrating controlled reentry, and parking the GATV. Two experiments were partially performed.

Mission Report for GT-VIII, pp. 1-1 to 1-4, 2-1, 2-2, 4-1 to 4-5; Fact Sheet 291-E, Gemini VIII, Rendezvous and Docking Mission, April 1966; McDonnell Final Report, pp. 73-75.

Figure 120. The launch of the Gemini Atlas-Agena target vehicle for the Gemini VIII mission from complex 14. (NASA Photo No. 66-H-296, released Mar. 16, 1966.)


Figure 121A. The Gemini VIII spacecraft approaching the Gemini Agena target vehicle in the final stage of rendezvous (the distance between the two craft is approximately two feet). (NASA Photo No. 66-H-225 [66-HC-191], released Mar. 16, 1966.)	Figure 121B. The docked Gemini and Agena. (NASA Photo No. 66-H-226 [66-HC-192], released Mar. 16, 1966.)

March 16

Following the early termination of Gemini VIII, Gemini Agena target vehicle (GATV) 5003 remained in orbit, where its various systems were extensively exercised. The main engine was fired nine times, four more than required by contract, and 5000 commands were received and executed by the command and communications system, as against a contractural requirement of 1000. GATV 5003 electrical power was exhausted during the 10th day of orbit and the vehicle could no longer be controlled. Before that, however, all attitude control gas was vented overboard to preclude errant thruster malfunction, and the vehicle was placed into a 220-nautical mile circular decay orbit, one of the secondary objectives of the Gemini VIII mission. This would put GATV 5003 low enough during the Gemini X mission to be inspected by the astronauts.

MSC Minutes of Senior Staff Meeting, Mar. 18, 1966, p. 2; Mission Report for GT-VIII, pp. 1-3, 1-4, 2-2; GATV Progress Reports: March pp. 2-1, 2-2; April 1966, pp. 2-7, 2-8, 2-9.

March 17

The extravehicular life support system (ELSS) for Gemini spacecraft No. 9 was delivered to Cape Kennedy. Compatibility tests involving the ELSS, the astronaut maneuvering unit, and the spacecraft were completed March 24. The ELSS was returned to the contractor on April 6 for modification.

Mission Report for GT-IXA, p. 12-12.

March 19

NASA announced the astronaut assignments for Gemini XI. The prime crew would be command pilot Charles Conrad, Jr., and pilot Richard F. Gordon, Jr.; backup crew would be Neil A. Armstrong, command pilot, and William A. Andres, pilot. James A. Lovell, Jr., and Edwin E. Aldrin, Jr., backup crew for the Gemini X mission, were reassigned as backup crew for Gemini IX. Alan L. Bean and Clifton C. Williams, Jr., were named as the new backup crew for Gemini X.

MSC News Release 66-20, Mar. 21, 1966.

March 21

Gemini Agena target vehicle 5004 and spacecraft No. 9 began Plan X compatibility tests at Merritt Island Launch Area Radar Range.

GATV Progress Report, March 1966, p. 2-6.

March 22

Agena D (AD-130) was formally accepted by the Air Force for the Gemini program and moved to Building 104 at Sunnyvale for modification and final assembly as Gemini Agena target vehicle 5006.

GATV Progress Report, March 1966, p. 2-10.

March 24

Gemini launch vehicle 9 was removed from storage and erected at complex 19. The vehicle was inspected and umbilicals connected by March 28. Power was applied March 29, and the Subsystems Reverification Test (SSRT) began March 30. SSRT concluded April 11. The Prespacecraft Mate Verification Combined Systems Test was completed April 12.

Mission Report for GT-IXA, p. 12-7.

March 24

Air Force Space Systems Division and Lockheed agreed not to curtail the Project Surefire test program despite the excellent performance of Gemini Agena target vehicle (GATV) 5003 during the Gemini VIII mission. The final test phase of Project Surefire began March 28 with two firings at Arnold Engineering Development Center. This phase of testing included low temperature starts and planned malfunctions. Testing culminated on April 4 with a planned fuel lead test. As predicted, an engine hard start occurred. Data from analysis of engine damage correlated well with data from the GATV 5002 failure, tending to confirm the hypothesis that failure resulted from a hard start caused by fuel preceding oxidizer into the thrust chamber during ignition.

MSC Minutes of Senior Staff Meeting, Apr. 8, 1966, p. 4; Quarterly Status Report No. 17, pp. 18-19; GATV Progress Reports: March, p. 2-3; April 1966, pp. 2-9, 2-10.

March 28

Gemini spacecraft No. 9 was transferred to complex 19 and hoisted to its position atop the launch vehicle. During the next two days the spacecraft was cabled for testing, and premate verification began March 31, ending April 6. After activation and deactivation of the fuel cells, preparations for spacecraft/launch vehicle integrated tests began April 11.

Mission Report for GT-IXA, p. 12-4.

March 31

Atlas target launch vehicle (TLV) 5304 was not accepted immediately for the Gemini program at the San Diego acceptance meeting because of an unfulfilled contractural requirement. The vehicle had completed systems test on March 23. After the technicalities were ironed out, the Air Force formally accepted TLV-5304 on April 14, and the vehicle was then shipped to Cape Kennedy by truck. En route an accident damaged the skirt on booster engine No. 1. After inspection and analysis, the contractor determined that the dented tubes resulting from the accident could be used without repair. TLV-5304 arrived at its destination on May 8 after a nine-day road trip. Following a receiving inspection, it was placed in storage May 11.

Mission Report for GT-IXA, pp. 12-10, 12-11; Quarterly Status Report No. 17, p. 17.

April 4

Atlas 5303, target launch vehicle for Gemini IX, was erected at launch complex 14. Electrical power was applied on April 11, and the Booster Flight Acceptance Composite Test was completed April 27.

Quarterly Status Report No. 17, p. 16.

April 12

Gemini Agena target vehicle 5005 completed modification and final assembly with the installation of a number of electrical and electronic components for which it had been waiting - including the guidance module, flight control junction box, and flight electronics package. The vehicle was transferred to test complex C-10 at Sunnyvale to begin Vehicle Systems Tests. Preliminary test tasks were completed by April 23, with preliminary inspection on April 26-27.

GATV Progress Report, April 1966, pp. 2-2, 2-4.

April 12

Gemini Agena target vehicle 5004 began the Combined Interface Test (CIT) at Hanger E, Eastern Test Range, after completing Plan X tests March 24. CIT ended April 22 and engine functional tests of both the primary and secondary propulsion systems followed. Hanger E testing was completed May 1.

GATV Progress Report, April 1966, pp. 2-2.

April 13

The Electrical Interface Integrated Validation and Joint Guidance and Control Test began after Gemini launch vehicle 9 and spacecraft No. 9 were electrically mated. These activities were completed April 15. The Joint Combined Systems Test was run April 19.

Mission Report for GT-IXA, p. 12-7.

April 14

The Combined Systems Acceptance Test (CSAT) of Gemini launch vehicle (GLV) 10 was conducted at Martin-Baltimore. The CSAT was followed by a performance data review, completed April 19. The vehicle acceptance team convened April 26 and accepted GLV-10 on April 29. The vehicle was deerected May 2-4 and formally accepted by the Air Force May 18. Stage I was flown to Cape Kennedy the same day, with stage II following May 20. Both stages were transferred to Hanger L where they were purged and pressurized with dry nitrogen and placed in controlled access storage.

Mission Report for GT-X, pp. 12-7, 12-8; Aerospace Final Report, p. II.G-7; Gemini-Titan II Air Force Launch Vehicle, p. D-17.

April 18

Stage I of Gemini launch vehicle 11 was erected in the west cell of the vertical test facility at Martin-Baltimore. After completing horizontal tests April 25, stage II was erected April 29. Power was applied to the vehicle for the first time on May 9, and Subsystems Functional Verification Tests were completed June 8.

Mission Report for GT-XI, p. 12-7; Gemini-Titan II Air Force Launch Vehicle, p. D-18.

April 18

The extravehicular life support system (ELSS) for Gemini spacecraft No. 9 was returned to Cape Kennedy and underwent an electrical compatibility test with the astronaut maneuvering unit (AMU). An ELSS/AMU Joint Combined System Test was run the following day and rerun April 21. The ELSS was then delivered to Manned Spacecraft Center for tests (April 22) while the AMU was prepared for installation in the adapter. The ELSS was returned to the Cape April 26. AMU Final Systems Test and installation for flight were accomplished May 7. The ELSS was serviced and installed for flight May 16.

Mission Report for GT-IXA, p. 12-12.

Figure 122. Demonstration of the astronaut maneuvering unit. (NASA Photo S-66-32550, May 12, 1966.)

April 20

The tanking test of Gemini launch vehicle (GLV) 9 was conducted. While the GLV was undergoing post-tanking cleanup, the spacecraft computer and extravehicular systems were retested (April 21-22), pyrotechnics were installed in the spacecraft (April 25), spacecraft final systems tests were run (April 27-28), spacecraft crew stowage was reviewed (April 29), and the astronaut maneuvering unit was reverified (April 30-May 2). On May 3 the spacecraft and launch vehicle were temporarily mated for an erector-cycling test. GLV systems were then revalidated in preparation for Simultaneous Launch Demonstration (SLD), while spacecraft extravehicular equipment was reworked and revalidated. Spacecraft and GLV were mated for flight May 8. The SLD was conducted May 10, the Final Simulated Flight Test on May 11.

Mission Report for GT-IXA, pp. 12-4, 12-7; Gemini-Titan II Air Force Launch Vehicle, p. D-15.

April 22

Gemini Program Manager Charles W. Mathews reported the launch dates tentatively scheduled for Gemini X as July 18, for Gemini XI as September 7, and for Gemini XII as October 31, 1966.

MSC Minutes of Senior Staff Meeting, Apr. 22, 1966, p. 3.

May 2

Gemini Agena target vehicle 5004 was transferred to complex 14 and mated to Atlas target launch vehicle 5303. Joint Flight Acceptance Composite Test was completed May 6, and Simultaneous Launch Demonstration followed on May 10.

GATV Progress Report, May 1966, p. 2-1.

May 3

Lockheed completed Combined Systems Acceptance Test on Gemini Agena target vehicle 5005 in test complex C-10 at Sunnyvale. The vehicle was formally accepted by the Air Force on May 14 and delivered to Eastern Test Range on May 16.

Aerospace Final Report, p. III.G-3; GATV Progress Report, May 1966, pp. 2-2, 2-3, 3-2.

May 8

Lockheed established a task force to handle the refurbishing of Gemini Agena target vehicle (GATV) 5001 and announced a GATV 5001 Reassembly Plan. The task force's function was to see that GATV 5001 reached a flightworthy condition on time and as economically as possible. The reassembly plan provided an operational base line as well as guidelines for reassembling the vehicle, which was completely disassembled down to the level of riveted or welded parts. GATV 5001 was scheduled for acceptance on September 20 and would be the target vehicle for Gemini XII.

Aerospace Final Report, p. III.G-5; GATV Progress Report, May 1966, p. 2-8.

May 13

McDonnell delivered Gemini spacecraft No. 10 to Cape Kennedy. Installation of fuel cells was completed May 18, and that of the pyrotechnics, May 25. Preparations for Plan X testing were completed June 1, and the spacecraft was moved to Merritt Island Launch Area June 3.

Mission Report for GT-X, p. 12-5.

May 17

The scheduled launch of Gemini IX was postponed when target launch vehicle 5303 malfunctioned and, as a result, Gemini Agena target vehicle 5004 failed to achieve orbit. Launch and flight were normal until about 120 seconds after liftoff, 10 seconds before booster engine cutoff. At that point, booster engine No. 2 gimbaled to full pitchdown position. Automatic correction was ineffective. Stabilization was achieved after booster separation, but in the meantime the vehicle had executed a 216-degree pitchdown maneuver and was pointing toward Cape Kennedy at a climbing angle of about 13 degrees above the horizontal. Ground guidance was also lost, and the vehicle continued on the new trajectory with normal sequencing through vernier engine cutoff. The Agena separated normally but could not attain orbit. It fell into the Atlantic Ocean some 90 miles off the Florida coast about seven and one-half minutes after launch. Subsequent investigation indicated that the failure had been caused by a short in the sevo control circuit.

Quarterly Status Report No. 17, pp. 16, 22; Aerospace Final Report, p. IV-8; GATV Progress Report, May 1966, p. 2-2; General Dynamics / Convair Test Evaluation Group, "Space Launch Vehicle Flight Evaluation Report, SLV-3 5303," June 27, 1966 (GDC/BKF 66-029).

May 17

Recycling operations began immediately after the cancellation of the Gemini IX mission. Propellants were unloaded, and ordnance and pyrotechnics were removed from the launch vehicle and the spacecraft. Spacecraft and launch vehicle were demated May 18. Both were checked and serviced, then remated May 24 and subjected to Electrical Interface Integrated Validation. The Simulated Flight Test on May 26 completed retesting in preparation for launch on June 1. The mission was redesignated Gemini IX-A.

Mission Report for GT-IXA, pp. 12-4, 12-7.

May 18

NASA decided to launch the augmented target docking adapter (ATDA) because of the failure on the previous day of Atlas target launch vehicle (TLV) 5303 and the loss of Gemini Agena target vehicle 5004. TLV-5304 was removed from storage and began modification to serve as the launch vehicle for the ATDA. The standard mission of the Atlas standard launch vehicle (SLV-3) was to place an Agena into a specified coast ellipse. The ATDA mission, however, required the SLV-3 to place the target into a direct-ascent Earth orbit. This called for numerous modifications. The necessity for such modifications had been anticipated when the ATDA program was initiated after the Agena failure on October 25, 1965. By March 1, 1966, there were ATDA kits ready at the Cape to modify any SLV-3 for an ATDA mission to be launched within 18 days from go-ahead. In fact, it took only 14 days. Modification was complete May 20, TLV-5304 was erected at complex 14 on May 21, TLV and ATDA were mated May 25, and all launch preparations were completed by May 30. The launch took place on June 1, the 15th day following the TLV-5303 failure.

Mission Report for GT-IXA, p. 12-11; Quarterly Status Report No. 17, p. 17; Aerospace Final Report, pp. IV-8, IV-9.

May 25

Gemini Agena target vehicle 5005 was mated to the target docking adapter (TDA) in Hanger E at Cape Kennedy. McDonnell had delivered the TDA on May 4. After mating, interface functional tests were performed, May 25-27. Preparations then began for Plan X testing with spacecraft No. 10 at Merritt Island Launch Area.

Mission Report for GT-X, p. 12-10; GATV Progress Report, May 1966, p. 2-3.

June 1

The augmented target docking adapter (ATDA) was launched from complex 14 at 10:00 a.m., e.s.t. The ATDA achieved a near-circular orbit (apogee 161.5, perigee 158.5 nautical miles). One hour and 40 minutes later, the scheduled launch of Gemini IX-A was postponed by a ground equipment failure which prevented the transfer of updating information from Cape Kennedy mission control center to the spacecraft computer. The mission was recycled for launch on June 3, following a prepared 48-hour recycle plan.

Mission Report for GT-IXA, pp. 1-1, 1-2, 5-143; Gemini-Titan II Air Force Launch Vehicle, p. D-16; Kuras and Albert, "Gemini-Titan Technical Summary," pp. 147-148.

June 1

Gemini Agena target vehicle 5005 completed preliminary testing at Hanger E, Eastern Test Range, and was moved to Merritt Island Launch Area for Plan X tests with spacecraft No. 10. Plan X tests had first been scheduled for May 23 but were rescheduled for June 2-3. To avoid an impact on the schedule, the delay was absorbed by conducting several activities normally performed after Plan X: secondary propulsion system (SPS) modules fit check and alignment, SPS heatshield fit check, and booster adapter fit check. But the vehicle work plan was again rescheduled, and Plan X did not begin until June 7. Following the successful completion of Plan X on June 8, the vehicle was returned to Hanger E for systems verification tests, which began on June 9. Cause of rescheduling was the Gemini IX-A launch.

Mission Report for GT-X, p. 12-10; GATV Progress Reports: May, p. 2-3; June 1966, p. 2-1.

June 3

Gemini IX-A, the seventh manned and third rendezvous mission of the Gemini program, was launched from complex 19 at 8:39 a.m., e.s.t. Major objectives of the mission, crewed by command pilot Astronaut Thomas P. Stafford and pilot Astronaut Eugene A. Cernan, were to rendezvous and dock with the augmented target docking adapter (ATDA) and to conduct extravehicular activities (EVA). These objectives were only partially met. After successfully achieving rendezvous during the third revolution - a secondary objective - the crew discovered that the ATDA shroud had failed to separate, precluding docking - a primary objective - as well as docking practice - another secondary objective. The crew was able, however, to achieve other secondary objectives: an equi-period rendezvous, using onboard optical techniques and completed at 6 hours 36 minutes ground elapsed time; and a rendezvous from above, simulating the rendezvous of an Apollo command module with a lunar module in a lower orbit (completed at 21 hours 42 minutes ground elapsed time). Final separation maneuver was performed at 22 hours 59 minutes after liftoff. EVA was postponed because of crew fatigue, and the second day was given over to experiments. The hatch was opened for EVA at 49 hours 23 minutes ground elapsed time. EVA was successful, but one secondary objective - evaluation of the astronaut maneuvering unit (AMU) - was not achieved because Cernan's visor began fogging. The extravehicular life support system apparently became overloaded with moisture when Cernan had to work harder than anticipated to prepare the AMU for donning. Cernan reentered the spacecraft, and the hatch was closed at 51 hours 28 minutes into the flight. The rest of the third day was spent on experiments. Following the third sleep period, the crew prepared for retrofire, which was initiated during the 45th revolution. The spacecraft landed within a mile of the primary recovery ship, the aircraft carrier Wasp. The crew remained with the spacecraft, which was hoisted aboard 53 minutes after landing.

Mission Report for GT-IXA, pp. 1-1 to 1-3, 2-1, 2-2, 4-1 to 4-3; Fact Sheet 291-F, Gemini IX-A, Rendezvous Mission, August 1966; McDonnell Final Report, pp. 76-77.

Figure 123. The augmented target docking adapter with shroud partly open and still attached, as seen from the Gemini IX-A spacecraft in orbit. Shroud's failure to separate precluded docking. (NASA Photo No. 66-H-725, released June 7, 1966.)

June 6

Gemini Agena target vehicle 5006 completed modification and final assembly and was transferred to Vehicle Systems Test (VST) at Sunnyvale. Although the vehicle lacked the flight control electronics package and guidance module, testing began immediately. The guidance module was received June 7 and the flight control electronics package June 9. Preliminary VST was completed June 17. The Air Force Plant Representative Office at Sunnyvale authorized final acceptance test to begin on June 20.

GATV Progress Report, June 1966, pp. 2-2, 2-3.

June 7

The acceptance meeting for target launch vehicle (TLV) 5305 was held at General Dynamics/Convair in San Diego. TLV systems test had originally been completed March 25. During the next two months, TLV components were reworked to the latest flight configuration. Systems tests were then rerun, May 26-June 1, followed by composite test June 2-3. Following acceptance, the vehicle was shipped by air on June 9 to Cape Kennedy; this was the first TLV to be transported by air to the Cape, and it arrived the same day.

Mission Report for GT-X, p. 12-11; Quarterly Status Report No. 18 for Period Ending Aug. 31, 1966, p. 15.

June 7

Gemini launch vehicle 10 was removed from storage and erected at complex 19. Umbilicals were connected and power applied June 9. Subsystems Reverification Tests (SSRT) began immediately. SSRT ended June 16, and the Prespacecraft Mate Verification Combined Systems Test was conducted June 17.

Mission Report for GT-X, p. 12-8; Gemini-Titan II Air Force Launch Vehicle, p. D-17.

June 9

Gemini spacecraft No. 10 was moved to complex 19 and hoisted to the top of its launch vehicle. Cabling for test was completed June 13. Premate verification, as well as fuel cell activation and deactivation, were completed June 16. Preparation for integrated tests with the launch vehicle was accomplished the following day.

Mission Report for GT-X, p. 12-5.

June 9

The launch vehicle acceptance test of Gemini launch vehicle (GLV) 11 was conducted. The vehicle acceptance team convened June 20 and accepted GLV-11 June 24. The vehicle was deerected June 29 and formally accepted by the Air Force on July 11. Stage I was delivered by air to Cape Kennedy the same day and stage II on July 13. Both stages were transferred to Hanger U where the tanks were purged and pressurized. The stages remained in controlled access storage until the launch pad was revalidated after the launch of Gemini X; revalidation was completed July 21.

Mission Report for GT-XI, pp. 12-7, 12-8; Aerospace Final Report, p. II.G-7; Gemini-Titan II Air Force Launch Vehicle, pp. D-18, D-19.

Figure 124. The first and second stages of Gemini launch vehicle 11 arriving at complex 19. (NASA Photo No. 66-H-1045, released July 23, 1966.)

June 13

Combined Interface Tests(CIT) of Gemini Agena target vehicle (GATV) 5005 began. CIT was completed June 22, with no significant anomalies detected. Primary and secondary propulsion system functional checks were completed June 30. The GATV was then moved to complex 14.

GATV Progress Report, June 1966, p. 2-1.

June 15

Atlas 5305, target launch vehicle for Gemini X, was erected at launch complex 14. Electrical power was applied June 17, and subsystem testing was completed June 28. During propellant system checks, a leak was discovered in the fuel start tank. Access to repair the leak required removing the sustainer engine and the fuel tank apex cone.

Mission Report for GT-X, p. 12-12; Quarterly Status Report No. 18, p. 15.

June 17

During the Gemini IX-A postlaunch press conference with Astronauts Thomas P. Stafford and Eugene A. Cernan, Director Robert R. Gilruth of Manned Spacecraft Center announced that James A. Lovell, Jr., and Edwin E. Aldrin, Jr., would be the prime crew for the last Gemini flight, Gemini XII. The backup crew would be L. Gordon Cooper, Jr., and Eugene A. Cernan. The mission was scheduled for late October or early November.

MSC Space News Roundup, June 24, 1966, p. 8.

June 19

NASA announced that the Gemini X mission had been scheduled for no earlier than July 18, with John W. Young, command pilot, and Michael Collins, pilot, as the prime crew. Alan L. Bean, command pilot, and Clifton C. Williams, pilot, would be the backup crew. Mission plans would include rendezvous, docking, and extravehicular activity. The spacecraft was scheduled to rendezvous and dock with an Agena target vehicle which was to be launched the same day. If possible, Gemini X would also rendezvous with the Agena launched in the March 16 Gemini VIII mission.

NASA News Release 66-155, June 19, 1966.

June 20

Gemini launch vehicle 10 and spacecraft No. 10 were electrically mated at complex 19. The Electrical Interface Integrated Validation and Joint Guidance and Control Test was conducted June 20-21. Following a data review, the Joint Combined Systems Test was run June 23.

Mission Report for GT-X, p. 12-8.

June 24

The tanking test of Gemini launch vehicle (GLV) 10 was conducted. During the post-tanking cleanup and systems testing of the GLV, spacecraft No. 10 hypergolics were serviced (June 27-28), spacecraft Final Systems Tests were conducted (June 28-July 1), crew stowage was evaluated, and the extravehicular life support system was checked (July 1). On July 5, spacecraft and GLV were mechanically mated and the erector was cycled. The electrical interface was retested July 6. The Simultaneous Launch Demonstration on July 12 and Simulated Flight Test on July 13 completed prelaunch testing.

Mission Report for GT-X, p. 12-8.

June 27

Final acceptance test of Gemini Agena target vehicle 5006 was completed at Sunnyvale. The vehicle was disconnected from the test complex July 6 and formally accepted by the Air Force on July 13, two days ahead of schedule. Shipment of the vehicle to Eastern Test Range (ETR), planned for July 13, was delayed until July 14 by wind conditions. It arrived at ETR in the early morning of July 15.

Mission Report for GT-XI, p. 12-10; GATV Progress Reports: June, p. 2-3; July 1966, p. 2-4.

July 1

Gemini Agena target vehicle 5005 was transferred to complex 14 and mated to target launch vehicle 5305. Joint Flight Acceptance Composite Test was completed July 8. Complex 14 systems tests were completed July 12 with the Simultaneous Launch Demonstration.

Mission Report for GT-X, p. 12-10; GATV Progress Report, July 1966, pp. 2-3, 2-4.

Figure 125. The Gemini Atlas-Agena target vehicle undergoing systems tests at complex 14 prior to the Gemini X mission. (NASA Photo No. 66-H-989, released July 18, 1966.)

July 7

McDonnell delivered Gemini spacecraft No. 11 to Cape Kennedy. After fuel and pyrotechnic installation and preliminary checks, the spacecraft was moved to the Merritt Island Launch Area for Plan X integrated tests with the target vehicle on July 25.

Mission Report for GT-XI, p. 12-5.

Figure 126. McDonnell personnel bolting the Gemini XI spacecraft to a support ring for boresighting in the Pyrotechnic Installation Building, Merritt Island. (NASA Photo S-66-47635, July 2, 1966.)

July 15

The acceptance meeting for Atlas 5306, the target launch vehicle for Gemini XI, was held at San Diego. Final acceptance was completed July 18. The vehicle was shipped the same day by air to Cape Kennedy, arriving July 19.

Quarterly Status Report No. 18, p. 15.

July 18

Gemini Agena target vehicle (GATV) 5006 was mated to target docking adapter (TDA) 6. McDonnell had delivered TDA-6 to Cape Kennedy July 7. The interface functional test was completed July 21. The next day GATV 5006 was moved to the Merritt Island Launch Area for integrated tests with spacecraft No. 11 and extravehicular equipment.

Mission Report for GT-XI, p. 12-10; GATV Progress Report, July 1966, p. 2-4.

July 18

The Gemini X mission began with the launch of the Gemini Atlas-Agena target vehicle from complex 14 at 3:40 p.m., e.s.t. The Gemini space vehicle, manned by command pilot Astronaut John W. Young and pilot Astronaut Michael Collins, was launched from complex 19 at 5:20 p.m. The Gemini Agena target vehicle (GATV) attained a near-circular, 162- by 157-nautical-mile orbit. Spacecraft No. 10 was inserted into a 145- by 86-nautical-mile elliptical orbit. Slant range between the two vehicles was very close to the nominal 1000 miles. Major objective of the mission was achieved during the fourth revolution when the spacecraft rendezvoused with the GATV at 5 hours 23 minutes ground elapsed time and docked with it about 30 minutes later. More spacecraft propellant was used to achieve rendezvous than had been predicted, imposing constraints on the remainder of the mission and requiring the development of an alternate flight plan. As a result, several experiments were not completed, and another secondary objective - docking practice - was not attempted. To conserve fuel and permit remaining objectives to be met, the spacecraft remained docked with the GATV for about 39 hours. During this period, a bending mode test was conducted to determine the dynamics of the docked vehicles, standup extravehicular activties (EVA) were conducted, and several experiments were performed. The GATV primary and secondary propulsion systems were used for six maneuvers to put the docked spacecraft into position for rendezvous with the Gemini VIII GATV as a passive target. The spacecraft undocked at 44 hours 40 minutes ground elapsed time, separated from the GATV, and used its own thrusters to complete the second rendezvous some three hours later. At 48 hours and 42 minutes into the flight, a 39-minute period of umbilical EVA began, which included the retrieval of a micrometorite collection package from the Gemini VIII Agena. The hatch was opened a third time about an hour later to jettison extraneous equipment before reentry. After about three hours of stationkeeping, the spacecraft separated from the GATV. At 51 hours 39 minutes ground elapsed time, the crew performed a true anomaly-adjust maneuver to minimize reentry dispersions resulting from the retrofire maneuver. The retrofire maneuver was initiated at 70 hours 10 minutes after liftoff, during the 43rd revolution. The spacecraft landed within sight of the prime recovery ship, the aircraft carrier Guadalcanal, some three miles from the planned landing point, at 4:07 p.m., July 21.

Mission Report for GT-X, pp. 1-1 to 1-3, 2-1, 2-2, 4-1, 4-2, 4-35; Fact Sheet 291-G, Gemini X, Multiple Rendezvous, EVA Mission, September 1966.

July 21

Following the reentry of spacecraft No. 10, Gemini Agena target vehicle (GATV) 5005 made three orbital maneuvers under ground control. Its primary propulsion system (PPS) fired to put the vehicle in a 750.5 by 208.6 nautical mile orbit in order to determine the temperature effects of such an orbit on the vehicle. Temperature data showed no appreciable difference from that obtained at lower orbits. The PPS fired again to circularize the orbit and a secondary propulsion system Unit II maneuver placed the GATV in a 190 nautical mile circular orbit for possible use as a Gemini XI rendezvous target. During its time in orbit, the GATV received and executed 1700 commands, 1350 by ground controllers and 350 from spacecraft 10.

Mission Report for GT-X, pp. 1-3, 4-35, 5-140; Fact Sheet 291-G.

July 21

Gemini Agena target vehicle 5001 was transferred to systems test complex C-10 at Sunnyvale, after the long process of refurbishing it had been completed; however, it was still short several pieces of equipment.

GATV Progress Report, July 1966, p. 2-6.

July 22

Gemini launch vehicle 11 was removed from storage and erected at complex 19. After the vehicle was inspected and umbilicals connected, power was applied July 27, and Subsystems Reverification Tests (SSRT) began. SSRT ended August 4, and the Prespacecraft Mate Verification Combined Systems Test was run the following day.

Mission Report for GT-XI, p. 12-8; Gemini-Titan II Air Force Launch Vehicle, p. D-19.

July 26

After completing Plan X tests at Merritt Island Launch Area, Gemini target vehicle (GATV) 5006 returned to Hanger E to begin systems verification tests. Combined Interface Tests began August 4 and ended August 12. Primary and secondary propulsion system (PPS and SPS) functional tests began August 13. SPS functionals were completed August 18, and the SPS modules were installed August 19. PPS functionals were completed August 21. GATV 5006 was then transferred to complex 14 for mating with the Atlas.

Mission Report for GT-XI, p. 12-10; GATV Progress Report, August 1966, p. 2-1.

July 28

Atlas 5306, the target launch vehicle (TLV) for Gemini XI, was erected at launch complex 14. Electrical power was applied the following day. The dual propellant loading (DPL) was run August 18, after a number of liquid oxygen leaks had been eliminated. A discrepancy noted in the vernier engine liquid oxygen bleed system during the first loading required a second DPL, successfully completed on August 22. The Booster Flight Acceptance Composite Test was successfully completed on August 19, and the TLV and Gemini Agena target vehicle were mated on August 22.

Mission Report for GT-XI, p. 12-12; Quarterly Status Report No. 18, pp. 15-16.

July 28

Gemini spacecraft No. 11 was moved to complex 19 and hoisted atop its launch vehicle. Cabling was completed August 1, and the Premate Systems Test was conducted August 1-3. Some fuel cell sections were replaced August 4, when checks revealed high leakage rates. Fuel cell activation and deactivation were completed August 6.

Mission Report for GT-XI, pp. 12-5, 12-6.

July 29

The launch vehicle acceptance test of Gemini launch vehicle (GLV) 12 was conducted. The vehicle acceptance team convened August 9 and accepted the vehicle August 12. GLV-12 was deerected August 17 and formally accepted by the Air Force August 30. Stage I was airlifted to Cape Kennedy the same day. Stage II arrived September 3. Both stages were placed in controlled access storage in Hanger T pending the launch of Gemini XI and the revalidation of the launch pad, completed September 16.

Mission Report for GT-XII, pp. 12-7, 12-8; Aerospace Final Report, p. II.G-7; Gemini-Titan II Air Force Launch Vehicle, p. D-20.

August 8

Gemini launch vehicle 11 and spacecraft No. 11 were electrically mated at complex 19. Elecrical Interface Integrated Validation and Joint Guidance and Control Test was conducted August 8-9. The Joint Combined Systems Test followed August 11-12.

Mission Report for GT-XI, p. 12-8.

August 15

The tanking test of Gemini launch vehicle (GLV) 11 was conducted. While GLV post-tanking operations were being performed, the Final Systems Tests of spacecraft No. 11 were conducted August 22-23. Spacecraft and GLV were mechanically mated August 24 and erector cycling was tested. The electrical interface was revalidated August 25-29. The Simultaneous Launch Demonstration on August 31 and the Simulated Flight Test on September 1 completed prelaunch testing.

Mission Report for GT-XI, p. 12-8.

August 16

Gemini Agena target vehicle 5001 completed final acceptance testing. Analysis of test data was completed by August 24 and the vehicle was disconnected from the test complex.

GATV Progress Report, August 1966, pp. 2-3, 2-4.

August 22

Gemini Agena target vehicle 5006 was mated to target launch vehicle 5306. Joint Flight Acceptance Composite Test was performed August 26, Simultaneous Launch Demonstration on August 31.

Mission Report for GT-XI, p. 12-10; GATV Progress Report, August 1966, pp. 2-1, 2-2.

September 2

Gemini Agena target vehicle 5001 was formally accepted by the Air Force after vehicle acceptance team inspection. It was shipped from Sunnyvale on September 3 and arrived at Eastern Test Range on September 4.

Mission Report for GT-XII, p. 12-10; GATV Progress Report, September 1966, pp. 2-1, 5-1.

September 6

McDonnell delivered Gemini spacecraft No. 12 to Cape Kennedy. After preliminary installations were completed, the spacecraft was moved to the Merritt Island Launch Area for integrated tests with the target vehicle (September 19-20).

Mission Report for GT-XII, p. 12-5.

September 9

The scheduled launch of Gemini XI was postponed when a pinhole leak was discovered in the stage I oxidizer tank of the launch vehicle shortly after propellants had been loaded. The decision to repair the leak required rescheduling the launch for September 10. After propellants were unloaded, the leak was plugged with a sodium silicate solution and covered with an aluminium patch.

Mission Report for GT-XI, pp. 5-106, 5-107; Gemini-Titan II Air Force Launch Vehicle, p. D-19; Kuras and Albert, "Gemini-Titan Technical Summary," p. 149.

September 10

The scheduled Atlas-Agena launch was postponed because of apparent problems with the target launch vehicle autopilot. It was later determined that the problems were caused by a combination of propellant sloshing, wind loading, and autopilot recorder sensitivity. The circumstances were determined to be normal and hardware replacement was not required. Launch was rescheduled for September 12.

Mission Report for GT-XI, pp. 5-107, 6-2; Quarterly Status Report No. 19 for Period Ending Nov. 30, 1966, p. 11.

September 12

The Gemini XI mission began with the launch of the Gemini Atlas-Agena target vehicle from complex 14 at 8:05 a.m., e.s.t. The Gemini space vehicle, carrying command pilot Astronaut Charles Conrad, Jr., and pilot Astronaut Richard F. Gordon, Jr., was launched from complex 19 at 9:42 a.m. The primary objective of the Gemini XI mission was to rendezvous with the Gemini Agena target vehicle (GATV) during the first revolution and dock. Five maneuvers completed the spacecraft/GATV rendezvous at 1 hour 25 minutes ground elapsed time, and the two vehicles docked nine minutes later. Secondary objectives included docking practice, extravehicular activity (EVA), 11 experiments, docked maneuvers, a tethered vehicle test, demonstrating automatic reentry, and parking the GATV. All objectives were achieved except one experiment - evaluation of the minimum reaction power tool - which was not performed because umbilical EVA was terminated prematurely. Umbilical EVA began at 24 hours 2 minutes ground elapsed time and ended 33 minutes later. Gordon became fatigued while attaching the tether from the GATV to the spacecraft docking bar. An hour later the hatch was opened to jettison equipment no longer required. At 40 hours 30 minutes after liftoff, the GATV primary propulsion system (PPS) was fired to raise the apogee of the docked vehicles to 741 nautical miles for two revolutions. The PPS was fired again, 3 hours 23 minutes later, to reduce apogee to 164 nautical miles. The crew then prepared for standup EVA, which began at 47 hours 7 minutes into the flight and lasted 2 hours 8 minutes. The spacecraft was then undocked to begin the tether evaluation. At 50 hours 13 minutes ground elapsed time, the crew initiated rotation. Initial oscillations damped out and the combination became very stable after about 20 minutes; the rotational rate was then increased. Again, initial oscillations gradually damped out and the combination stabilized. At about 53 hours into the mission, the crew released the tether, separated from the GATV, and maneuvered the spacecraft to an identical orbit with the target vehicle. A fuel cell stack failed at 54 hours 31 minutes, but the remaining five stacks shared the load and operated satisfactorily. A rerendezvous was accomplished at 66 hours 40 minutes ground elapsed time, and the crew then prepared for reentry. The spacecraft landed less than three miles from the planned landing point at 71 hours 17 minutes after liftoff. The crew was retrieved by helicopter, and the spacecraft was brought aboard the prime recovery ship, the aircraft carrier Guam, about an hour after landing.

Mission Report for GT-XI, pp. 1-1 to 1-4, 2-1, 4-1 to 4-3; Fact Sheet 291-H, Gemini XI Mission, High Altitude, Tethered Flight, October 1966.


Figure 127. Astronaut Richard F. Gordon, Jr., returning to the hatch of Gemini XI after extravehicular activity. (NASA Photo No. 66-H-1249, released Sept. 13, 1966.)	Figure 128. View of India and Ceylon from Gemini XI at 540 nautical miles looking north, with the Bay of Bengal to the right and the Arabian Sea to the left. (NASA Photo No. 66-H-1246 [66-HC-1608], released Sept. 17, 1966.)

Figure 129. The Gemini XI spacecraft landing approach in the western Atlantic. (NASA Photo No. 66-H-1214, released Sept. 15, 1966.)

September 12

Gemini Agena target vehicle 5001 was mated to target docking adapter (TDA) 7A at Cape Kennedy. McDonnell had delivered TDA 7A to the Cape August 19. After functional verification tests (September 13-15), the vehicle was moved (September 19-20) to the Merritt Island Launch Area for Plan X integrated tests with spacecraft No. 12.

Mission Report for GT-XII, p. 12-10.

September 16

The acceptance meeting for target launch vehicle (TLV) 5307 was conducted at San Diego. The vehicle was shipped to Cape Kennedy following acceptance, arriving September 20. This vehicle had originally been assigned to the Lunar Orbiter program. The Atlas 5305 failure on May 17, however, followed by the decision to use Atlas 5304 to launch the augmented target docking adapter, made it necessary to procure an additional TLV for the Gemini Program. In May, Gemini Program Office (GPO) completed negotiations to aquire Atlas 7127 from Vandenberg Air Force Base, California. This vehicle was so different from the Gemini TLV, however, that GPO decided to use the Lunar Orbiter vehicle, Atlas 5803, redesignating it TLV 5307. This vehicle had only nine minor engineering change proposal (ECP) differences from earlier TLVs, all of which analysis showed to be acceptable. Modification for the Gemini program was completed August 22 and factory testing on September 12.

Mission Report for GT-XII, pp. 12-11, 12-12; Quarterly Status Reports: No. 17, p. 18; No. 18, p. 16; No. 19, p. 11.

September 19

Gemini launch vehicle (GLV) 12 was removed from storage and erected at complex 19. Umbilicals were connected after GLV inspection September 21. Power was applied the next day and Subsystems Reverification Tests (SSRT) began September 23. SSRT ended October 2 and Prespacecraft Mate Verification Combined Systems Test was run October 4.

Mission Report for GT-XII, p. 12-8; Gemini-Titan II Air Force Launch Vehicle, p. D-20.

September 21

Gemini Agena target vehicle (GATV) 5001 was returned to Hanger E and began systems test after completing Plan X tests at the Merritt Island Launch Area. Systems testing was completed September 29. The Combined Interface Test (September 29-October 13) was followed by functional tests of the primary and secondary propulsion systems, completed October 22. GATV 5001 was then moved to complex 14.

Mission Report for GT-XII, p. 12-10; GATV Progress Report, October 1966, p. 2-1.

September 23

The astronaut maneuvering unit (AMU), which had been installed in Gemini spacecraft No. 12 on September 17, was removed as the spacecraft was undergoing final preparations for movement to complex 19. NASA Headquarters deleted the AMU experiment from the extravehicular activities (EVA) planned for the Gemini XII mission. Persistent problems in performing EVA on earlier flights had slowed the originally planned step-by-step increase in the complexity of EVA. With only one flight left, George E. Mueller, NASA Associate Administrator for Manned Space Flight, felt that more work was required on EVA fundamentals - the performance of easily monitored and calibrated basic tasks. On this flight, the pilot would remove, install, and tighten bolts, operate connectors and hooks, strip velcro, and cut cables.

Mission Report for GT-XII, p. 12-5; letter, Mueller to Gen. James R. Ferguson, Sept. 30, 1966.

September 23

Gemini spacecraft No. 12 was moved to complex 19 and hoisted to the top of the launch vehicle. Premate verification was completed October 3.

Mission Report for GT-XII, p. 12-5.

September 26

Target launch vehicle 5307 was erected at complex 14. Systems tests began the next day and lasted until October 18. The Booster Flight Acceptance Composite Test was conducted October 24.

Mission Report for GT-XII, p. 12-12.

October 5

Gemini launch vehicle 12 and spacecraft No. 12 were electrically mated at complex 19. The Electrical Interface Integrated Validation and Joint Guidance and Control Test was conducted October 5-6, and data was reviewed the following day. The Joint Combined Systems Test was run on October 10.

Mission Report for GT-XII, p. 12-8; Kuras and Albert, "Gemini-Titan Technical Summary," p. 150.

October 11

The tanking test of Gemini launch vehicle (GLV) 12 was conducted. While the GLV was being cleaned up after the tanking test, the Final Systems Test of spacecraft No. 12 was conducted October 17-19. Spacecraft and GLV were mechanically mated October 25 and the erector was cycled. The spacecraft guidance system was retested October 26-27, and the spacecraft/GLV electrical interface was revalidated October 28. The Simultaneous Launch Demonstration on November 1 and the Simulated Flight Test on November 2 completed prelaunch testing and checkout.

Mission Report for GT-XII, pp. 12-5, 12-8; Gemini-Titan II Air Force Launch Vehicle, p. D-20.

October 23

Gemini Agena target vehicle 5001 was mated to target launch vehicle 5307 on complex 14. Joint Flight Acceptance Composite Test was completed October 28, Simultaneous Launch Demonstration on November 1.

GATV Progress Report, October 1966, p. 2-2.

November 8

The scheduled launch of Gemini XII was postponed by a malfunctioning power supply in the launch vehicle secondary autopilot, discovered before the countdown for the November 9 launch began. The secondary autopilot package and the secondary stage I rate gyro package were replaced, and the mission was rescheduled for November 10. During tests of the replacement autopilot on November 9, another malfunction occurred, which was resolved by again replacing the secondary autopilot package. The launch was rescheduled for November 11.

Mission Report for GT-XII, pp. 5-111, 5-112, 12-22, 12-23; Gemini-Titan II Air Force Launch Vehicle, p. D-21; Kuras and Albert, "Gemini-Titan Technical Summary," p. 150.

November 11

The Gemini Atlas-Agena target vehicle for the Gemini XII mission was launched from complex 14 at 2:08 p.m., e.s.t. The Gemini space vehicle, manned by command pilot Astronaut James A. Lovell, Jr., and pilot Astronaut Edwin E. Aldrin, Jr., was launched from complex 19 at 3:47 p.m. Major objectives of the mission were to rendezvous and dock and to evaluate extravehicular activities (EVA). Among the secondary objectives were tethered vehicle evaluation, experiments, third revolution rendezvous and docking, automatic reentry demonstration, docked maneuvering for a high-apogee excursion, docking practice, systems tests, and Gemini Agena target vehicle (GATV) parking. The high-apogee excursion was not attempted because an anomaly was noted in the GATV primary propulsion system during insertion, and parking was not attempted because the GATV's attitude control gas was depleted. All other objectives were achieved. Nine spacecraft maneuvers effected rendezvous with the GATV. The onboard radar malfunctioned before the terminal phase initiate maneuver, but the crew used onboard backup procedures to calculate the maneuvers. Rendezvous was achieved at 3 hours 46 minutes ground elapsed time, docking 28 minutes later. Two phasing maneuvers, using the GATV secondary propulsion system, were accomplished, but the primary propulsion system was not used. The first of two periods of standup EVA began at 19 hours 29 minutes into the flight and lasted for 2 hours 29 minutes. During a more than two-hour umbilical EVA which began at 42 hours 48 minutes, Aldrin attached a 100-foot tether from the GATV to the spacecraft docking bar. He spent part of the period at the spacecraft adapter, evaluating various restraint systems and performing various basic tasks. The second standup EVA lasted 55 minutes, ending at 67 hours 1 minute ground elapsed time. The tether evaluation began at 47 hours 23 minutes after liftoff, with the crew undocking from the GATV. The tether tended to remain slack, although the crew believed that the two vehicles did slowly attain gravity-gradient stabilization. The crew jettisoned the docking bar and released the tether at 51 hours 51 minutes. Several spacecraft systems suffered problems during the flight. Two fuel cell stacks failed and had to be shut down, while two others experienced significant loss of power. At 39 hours 30 minutes ground elapsed time, the crew reported that little or no thrust was available from two orbit attitude and maneuver thrusters. Retrofire occurred 94 hours after liftoff. Reentry was automatically controlled. The spacecraft landed less than three miles from the planned landing point at 2:21 p.m., November 15. The crew was picked up by helicopter and deposited 28 minutes later on the deck of the prime recovery ship, the aircraft carrier Wasp. The spacecraft was recovered 67 minutes after landing.

Mission Report for GT-XII, pp. 1-1 to 1-4, 2-1, 2-2, 4-1 to 4-7; Fact Sheet 291-I, Gemini XII Flight and Gemini Program Summary, December 1966; McDonnell Final Report, pp. 84-85.


Figure 130. Astronaut Edwin E. Aldrin, Jr., carrying a micrometeoroid package to the spacecraft from the adapter section during extravehicular activity on Gemini XII. (NASA Photo No. 66-H-753 [66-HC-1546], released Nov. 16, 1966.)	Figure 131. The Gemini Agena target vehicle tethered to the spacecraft during the Gemini XII mission. (NASA Photo No. 66-H-751, released Nov. 16, 1966.)

1967

February 1

Manned Spacecraft Center's (MSC) Gemini Program Office was abolished. The responsibility and authority for final Gemini actvities, such as disposing of equipment and settling contract costs, were assigned to George F. MacDougall, Jr., the newly appointed Special Assistant for Gemini in MSC's Office of the Director of Administration. Wrapping up the program would require several years of gradually decreasing effort.

MSC Announcement No. 67-15, Feb. 1, 1967; MacDougall interview.

February 1-2

A Gemini Summary Conference was held at Manned Spacecraft Center. Major focus of the 22 papers which followed the welcoming address by Director Robert R. Gilruth was on the results of the final Gemini missions. Sessions were devoted to orbital rendezvous and docking operations, extravehicular activities, operational experience, and the results of experiments carried aboard the Gemini missions.

Program, Gemini Summary Conference, MSC Auditorium, Houston, Tex., February 1967; Gemini Summary Conference, NASA SP-138, Feb. 1-2, 1967, passim.