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Atlas SLV-3 Agena D

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SLV-3 Atlas/Agena D SLV-3 Atlas / Agena D - COSPAR 1966-012

AKA: Atlas Agena D SLV-3;SLV-3. Status: Retired 1967. First Launch: 1964-08-14. Last Launch: 1967-11-05. Number: 48 . Payload: 2,000 kg (4,400 lb). Thrust: 1,629.00 kN (366,213 lbf). Gross mass: 140,000 kg (300,000 lb). Height: 32.10 m (105.30 ft). Diameter: 3.05 m (10.00 ft). Apogee: 180 km (110 mi).

LEO Payload: 1,000 kg (2,200 lb). Payload: 700 kg (1,540 lb) to a GEO.

• Westinghouse Electric Corporation, Baltimore, Maryland, received a $6.8 million subcontract from McDonnell to provide the rendezvous radar and transponder system for the Gemini spacecraft. - . Nation: USA. Spacecraft: Gemini, Gemini Radar.

  Purpose of the rendezvous radar, sited in the recovery section of the spacecraft, was to locate and track the target vehicle during rendezvous maneuvers. The transponder, a combined receiver and transmitter designed to transmit signals automatically when triggered by an interrogating signal, was located in the Agena target vehicle.

• Small working group to discuss the feasibility of making the Gemini telemetry system a full PCM system. - . Nation: USA.

  Following a Lockheed briefing on pulse-code-modulation (PCM) instrumentation systems, representatives of Goddard Space Flight Center and Manned Spacecraft Center (MSC) formed a small working group to discuss the feasibility of making the Gemini telemetry system a full PCM system. PCM was a digital telemetry system which could provide more channels of information, faster data rates, improved accuracy, and less weight of equipment per data channel. Goddard had already reviewed several PCM ground station proposals and had concluded that such a system could handle future NASA programs. All who attended the meeting agreed that a full PCM telemetry system, airborne and ground, could be implemented in time to support the Gemini program. Gemini Project Office approved the formation of an MSC-Gemini PCM Instrumentation Working Group to be responsible for the implementation and compatibility of the airborne and ground PCM system for Gemini. On June 27, Walter C. Williams, MSC Associated Director, notified Goddard of NASA's decision 'to utilize a PCM telemetry system for Gemini and Agena real time data.' Ten sites were selected for the installation of PCM equipment; each of these also received dual acquisition equipment, dual digital command system, and pulse coders for distinguishing between the manned Gemini spacecraft and the Agena target when both were in orbit.

• A preliminary design criteria review conference for complex 14, held in Los Angeles, resulted in ground rules for all contractors. - . Nation: USA.

  Target dates established were (1) stand availability, July 1, 1963; (2) estimated beneficial occupancy date, November 1, 1963; and (3) vehicle on-stand date, February 1, 1964. Complex 14 would be used for launching the Gemini-Agena target vehicle and Mariner spacecraft, but basic modifications would be primarily for the Gemini program. On November 15, 1962, Air Force Space Systems Division reviewed the criteria summary report for complex 14 modifications and suggested only minor engineering changes.

• NASA Headquarters' recent decision to cut the MSC budget for fiscal year 1963 from $687 million to $660 million. - . Nation: USA. Related Persons: Chamberlin. Spacecraft: Gemini, Gemini Paraglide.

  Wesley L. Hjornevik, Manned Spacecraft Center (MSC) Assistant Director for Administration, described to members of MSC's senior staff the implications of NASA Headquarters' recent decision to cut the MSC budget for fiscal year 1963 from $687 million to $660 million, the entire reduction to be borne by the Gemini program. Hjornevik feared that the Gemini budget, already tight, could absorb so large a cut only by dropping the paraglider, Agena, and all rendezvous equipment from the program. Gemini Project Office (GPO) reported that funding limitations had already forced Martin and McDonnell to reduce their level of activity. The first Gemini flight (unmanned) was rescheduled for December 1963, with the second (manned) to follow three months later, and subsequent flights at two-month intervals, with the first Agena (fifth mission) in August or September 1964. This four-month delay imposed by budget limitations required a large-scale reprogramming of Gemini development work, reflected chiefly in drastic reduction in the scale of planned test programs. Details of the necessary reprogramming had been worked out by December 20, when GPO Manager James A. Chamberlin reported that December 1963 was a realistic date for the first Gemini flight. Gemini funding for fiscal year 1963 totaled $232.8 million.

• Manned Spacecraft Center informed Lockheed that Gemini program budget readjustments required reprogramming the Gemini-Agena program. - . Nation: USA.

  Subsequent meetings on November 2 and November 20 worked out the changes necessary to implement the Agena program at minimum cost. The overall test program for the Agena and its propulsion systems was significantly reduced, but in general neither the scope nor the requirements of the Agena program were altered. The major result of the reprogramming was a four-month slip in the scheduled launch date of the first Agena (to September 1964); this delay was about a month and a half less than had been anticipated when reprogramming began. In addition, Lockheed was to continue its program at a reduced level through the rest of 1962, a period of about six weeks, and to resume its normal level of activity on January 1, 1963.

• "T-back" pod proposed as the Gemini rendezvous target instead of the Agena. - . Nation: USA.

  Andre J. Meyer, Jr., of Gemini Project Office reported that Space Technology Laboratories was conducting a study for NASA Headquarters on a 'T-back' pod to be used in the spacecraft adapter as the rendezvous target instead of the Agena. The pod would be stabilized but would have no translation capabilities. Although it would be almost as expensive as the Agena, it would avoid separate launch problems.

• Flight Operations Division outlined detailed requirements for the remote stations of the worldwide tracking network. - . Nation: USA. Each station would need five consoles: Gemini system, Agena system, command, aeromedical, and maintenance and operations. The Gemini and Agena consoles would have 42 analog display meters and 40 on/off indicators..

• MSC assumed complete responsibility for the Gemini target vehicle program. - . Nation: USA.

  Manned Spacecraft Center (MSC) assumed complete responsibility for the Gemini target vehicle program from Marshall Space Flight Center following a meeting between MSC and Marshall on January 11 establishing procedures for the transfer. Marshall was to continue to participate actively in an advisory capacity until March 1 and thereafter as technical consultant to MSC upon request. All other NASA Atlas-Agena programs were transferred to Lewis Research Center in a move aimed at freeing Marshall to concentrate on Saturn launch vehicle development and consolidating Atlas launch vehicle technology at Lewis. NASA Headquarters had decided to effect the transfer on October 12, 1962.

• Gemini Rendezvous and Reentry Panel meeting. - . Nation: USA. At a Gemini Rendezvous and Reentry Panel meeting, it was reported that attempts to obtain information on flight controller procedures to command the Agena in orbit had been delayed by the Air Force Agena security program. .

• Agena target vehicle checkout plans were presented at a meeting of the Gemini Management Panel. - . Nation: USA. Spacecraft: Gemini, Gemini Radar.

  Upon receipt at Cape Canaveral, the target vehicle would be inspected and certified. After this action, mechanical mate and interface checks with the target docking adapter would be accomplished. Agena-Gemini spacecraft compatibilty tests would then be conducted, and the Agena would undergo validation and weight checks. Subsequently, a joint checkout of the spacecraft and Agena would be conducted with tests on the Merritt Island radar tower.

• Gemini Project Office discussed with contractors the establishment of a philosophy for the final phase of the rendezvous mission. - . Nation: USA. Spacecraft: Gemini, Gemini Radar.

  They agreed on the following general rules: (1) when the launch was on time, the terminal maneuver would be initiated when the Agena came within range of the spacecraft's sensors, which would occur between spacecraft insertion and first apogee; (2) automatic and optical terminal guidance techniques would always back each other up, one method being selected as an objective for each mission and the other serving as a standby; (3) during early rendezvous missions, the terminal phase would be initiated by the third spacecraft apogee or delayed until the twelfth because of range radar tracking limitations; (4) for the same reason, no midcourse corrections should be made during orbits 4 through 11; (5) in case of extreme plane or phase errors, the Agena would be maneuvered to bring it within the spacecraft's maneuver capability; and (6) after such gross Agena maneuvers, the Agena orbit would be recircularized and two orbits of spacecraft catchup would precede the initiation of terminal rendezvous plan.

• Bell Aerosystems successfully completed initial firing of the Gemini Agena Model 8247 engine at its Buffalo plant early in the month. - . Nation: USA.

  The Model 8247 engine for the Gemini Agena's primary propulsion system was developed from the Model 8096 currently being flown in satellite and probe programs for NASA and the Air Force. Unlike the operational engine, the new engine was capable of being restarted several times in orbit, a Gemini program requirement. The principle change in the new engine was the substitution of liquid propellants for solid pyrotechnic 'starter cans' to start the gas generator. The unit tested was the development engine that had been assembled in March. In mid-April, the test engine was shipped to Arnold Engineering Development Center (AEDC), Tullahoma, Tennessee, for further development tests. At AEDC, test cell arrangements were completed April 12, with testing scheduled to begin in May.

• Representatives of Air Force Space Systems Division (SSD), Manned Spacecraft Center, and Lockheed met in Sunnyvale for the first management review of the Gemini Agena target vehicle (GATV). - . Nation: USA.

  Patterned after similar meetings regularly held between SSD, Lewis Research Center, and Lockheed on medium space vehicle satellite and probe programs, the Gemini Target Management Review Meetings encompassed a comprehensive monthly review of the status of the GATV program.

• NASA Headquarters approved rescheduling of the Gemini flight program as proposed by Gemini Project Office (GPO). - . Nation: USA. Spacecraft: Gemini, Gemini Parachute, Gemini Paraglide.

  Late delivery of the spacecraft systems coupled with the unexpectedly small number of Mercury systems incorporated in the Gemini spacecraft had forced GPO to review the flight program critically. In the revised program, the first flight was still set for December 1963 and was still to be unmanned, but it was now to be orbital rather than suborbital to flight-qualify launch vehicle subsystems and demonstrate the compatibility of the launch vehicle and spacecraft; no separation or recovery was planned. The second mission, originally a manned orbital flight, now became an unmanned suborbital ballistic flight schedule for July 1964. Its primary objection was to test spacecraft reentry under maximum heating-rate reentry conditions; it would also qualify the launch vehicle and all spacecraft systems required for manned orbital flight. The third flight, formerly planned as a manned orbital rendezvous mission, became the first manned flight, a short-duration (probably three-orbit) systems evaluation flight scheduled for October 1964. Subsequent flights were to follow at three-month intervals, ending in January 1967. Rendezvous terminal maneuvers were planned for missions 3 (if flight duration permitted) and 4, a seven-day mission using a rendezvous pod. The sixth flight was to be a 14-day long-duration mission identical to 4 except that no rendezvous maneuver missions with the Atlas-launched Agena D target vehicle. Water landing by parachute was planned for the first six flights and land landing by paraglider from flight 7 on.

• The Cape Gemini/Agena Test Integration Working Group met to define "Plan X" test procedures and responsibilities. - . Nation: USA. Spacecraft: Gemini, Gemini Radar.

  The purpose of Plan X was to verify the Gemini spacecraft's ability to command the Agena target vehicle both by radio and hardline; to exercise all command, data, and communication links between the spacecraft, target vehicle, and mission control in all practical combinations, first with the two vehicles about six feet apart, then with the vehicles docked and latched but not rigidized; and to familiarize the astronauts with operating the spacecraft/target vehicle combination in a simulated rendezvous mission. Site of the test was to be the Merritt Island Launch Area Radar Range Boresight Tower ('Timber Tower'), a 65 x 25 x 50-foot wooden structure.

• Development tests of the Agena 8247 engine ended in an emergency shutdown. - . Nation: USA.

  Development tests of the Agena Model 8247 main engine at Arnold Engineering Development Center ended when the latch-type gas generator valve failed in testing, making an emergency shutdown of the engine necessary. The wrong choice of emergency shutdown procedures caused turbine overspeed and total failure of the engine's turbine pump assembly. As a result of this failure, the valve was redesigned. Because success of the new design was doubtful, a parallel program was initiated to design and develop an alternative valve configuration, solenoid-operated rather than latch-type. Intensive development testing followed; and in a meeting at Bell Aerosystems on November 15, the solenoid type was selected for use in the first flight system of the Agena target vehicle. The new valve allowed significant reductions in engine complexity and increased reliability, but the development effort imposed a serious delay in Preliminary Flight Rating Tests, which had been scheduled to begin in September 1963.

• Lockheed's contract for the Gemini Agena target vehicle (GATV) was amended. - . Nation: USA.

  As a result of the seven-and-one-half-month relaxation of the required launch date for the first GATV, Lockheed was directed to use the improved version of the standard Agena, the AD-62 block of vehicles, instead of AD-13. The AD-62 block originally included the multistart engine, subsequently slipped to the AD-71 block. Lockheed accordingly was directed in January 1964 to substitute the AD-71 for AD-62. The combined effect of these changes was to use up much of the seven-and-one-half-month leeway. The change to AD-62 caused a two-month slip, and changing to AD-71 added a five-week slip. With much of the contingency time gone, the Agena schedule was now tight, and further slippage threatened to cause launch delays.

• Electro-Mechanical Research successfully tested the compatibility of airborne and ground station PCM (pulse code modulated) telemetry equipment. - . Nation: USA. The tests demonstrated that Gemini spacecraft and Agena telemeter and recorder formats were compatible with NASA ground stations..

• Lockheed included a milestone schedule for the Gemini Agena target vehicle (GATV) in its monthly progress report for the first time since January 1963. - . Nation: USA.

  The new schedule reflected the revised Gemini flight program of April 29 and the corresponding revision of the Agena program which followed. It displayed key events in the progress of the first GATV taking place between five and six months later than the January schedule. Engineering development was now scheduled to be completed by May 15, 1964, rather than by December 11, 1963. Completion of modification and final assembly was now planned for June 12 rather than January 10, 1964; preliminary vehicle systems testing was rescheduled from April 10 to September 11, 1964. Special tests, including a Radio frequency Interference Test in the later schedule in addition to the hot-firing scheduled earlier, were to end November 20 instead of May 22, 1964. Final Vehicle Systems Tests were to be completed December 18 instead of June 19, 1964, with shipment to follow on January 6, 1965, rather than June 30, 1964. Launch was now expected on April 15, 1965, seven and one-half months later than the September 1, 1964, date that had been planned in January 1963.

• Douglas Aircraft Corporation, Tulsa, Oklahoma, began a series of tests to demonstrate the structural integrity of the Gemini target docking adapter (TDA) during shroud separation. - . Nation: USA.

  The shroud, which protected the TDA during the launch and ascent of the Agena target vehicle, was tested under simulated altitude conditions to show proper operation of pyrotechnic devices and adequate clearance between shroud and TDA during separation. Successfully concluded on November 21, and tests demonstrated the compatibility of the TDA with the shroud system during operational performance, with no indication of damage or failure of the TDA structure.

• Bell Aerosystems began Preliminary Flight Rating Tests (PFRT) of the Agena primary propulsion system (PPS). - . Nation: USA.

  Tests were expected to be completed April 24 but were not actually concluded until late June. Testing proceeded with only minor problems through the first week of April. But in the following week PPS testing encountered what proved to be a six-week delay when the test unit's fuel and oxidizer start tanks failed. The two start tanks, stainless steel canisters with an internal bellows arrangement, supplied the propellants required to initiate the main engine start sequence. Visible longitudinal cracks in the outer shell allowed the gas which forced the propellants out of the tank to escape. Investigation revealed that the cracks had resulted from intergranular corrosion of the stainless steel tanks. The defective tanks were replaced by start tanks with a new heat-treated shell (delivered April 24), and PFRT resumed early in May.

• Bell Aerosystems delivered the first Gemini Agena Model 8247 main engine to Lockheed. - . Nation: USA.

  This engine was installed in the propulsion test vehicle assembly (PTVA), a unit to be used for a series of tests on the Agena primary and secondary propulsion systems at Lockheed's Santa Cruz Test Base. Bell delivered the two secondary propulsion system modules for the PTVA on March 6 and 14. Installation was completed and the PTVA delivered to Santa Cruz Test Base on March 26.

• Bell Aerosystems began Preliminary Flight Rating Tests (PFRT) of the Agena secondary propulsion system (SPS). - . Nation: USA.

  After proceeding through the acceleration and vibration test phases of PFRT without incident, the SPS began calibration firings early in April. The failure of a propellant valve in Unit I (the 16-pound thrust chamber fired prior to starting the main engine in order to orient propellant) of the SPS imposed a minor delay, but a more serious problem emerged late in April during high-temperature firings. The wall of the Unit II 200-pound thrust chamber burned through near the injector face after an accumulated PFRT firing time of 354 seconds, below the specification limit of 400 seconds although well in excess of the maximum orbital useful time of 200 seconds. The thrust chamber was replaced and testing continued, but PFRT, originally scheduled to end June 19, was first slipped to July 8, and finally completed in mid-August. To resolve the burn-through problem, Bell began a test program in September to determine the cause of failure.

• Gemini Project Manager Charles W. Mathews informed Manned Spacecraft Center senior staff of efforts to control Gemini spacecraft weight and configuration more tightly. - . Nation: USA.

  Mathews had assigned Lewis R. Fisher of his office to head a Systems Integration Office within Gemini Project Office to oversee these efforts by keeping very precise accounts of spacecraft weight, interface actions between the spacecraft and launch vehicle, and interface actions between the spacecraft and the Agena target vehicle.

• Test program to increase confidence in critical components of the Gemini Agena target vehicle. - . Nation: USA.

  Manned Spacecraft Center (MSC) approved Air Force Space Systems Division's (SSD) recommendations for a test program to increase confidence in 16 critical electronic and electrical components of the Gemini Agena target vehicle. The program included complete electromagnetic interference (EMI) testing of all components peculiar to the Gemini mission, as well as elevated stress tests and extended life tests. SSD had also recommended subsystem-level, as well as component-level, EMI testing, but this part of the program MSC disapproved. SSD directed Lockheed to proceed with the program on March 23. EMI tests were scheduled to be completed by July 1, stress and life tests by September 1, 1964.

• Gemini mission plans for the first Agena rendezvous flight. - . Nation: USA. Related Persons: Aldrin. Spacecraft: Gemini, Gemini Radar.

  At a meeting of the Gemini Project Office's Trajectories and Orbits Panel, members of Flight Operations Division described two mission plans currently under consideration for the first Agena rendezvous flight. One was based on the concept of tangential Agena and spacecraft orbits, as proposed by Howard W. Tindall, Jr., and James T. Rose when they were members of Space Task Group. The second plan, based on a proposal by Edwin E. Aldrin, Jr., then of Air Force Space Systems Division, involved orbits which were concentric rather than tangential. The most significant advantage of the second plan was that it provided the greatest utilization of onboard backup techniques; that is, it was specifically designed to make optimum use of remaining onboard systems in the event of failure in the inertial guidance system platform, computer, or radar.

• The propulsion test vehicle assembly (PTVA) arrived at Santa Cruz Test Base. - . Nation: USA.

  It consisted of a basic Agena structure with propellant pressurization, feed-and-load system, the primary propulsion system (PPS), and two secondary propulsion system (SPS) modules attached to the aft rack. The test program called for loading operations and hot firings of both propulsion systems to establish the adequacy of PPS and SPS propellant loading systems and associated ground equipment, to demonstrate proper overall system operation, and to provide engineering data on systems operation and the resulting environment. Start of testing was delayed by the PPS start tank problems which showed up during Preliminary Flight Rating Tests at Bell Aerosystems during April. Lockheed returned the PTVA main engine start tanks to Bell, where they were inspected and found to be defective. New tanks were ready by mid-May, but additional minor problems delayed the initiation of hot-firing until June 16.

• Air Force Space Systems Division (SSD) recommended a Gemini Agena launch on a nonrendezvous mission to improve confidence in target vehicle performance before undertaking a rendezvous mission. - . Nation: USA. Flight: Gemini 12. Gemini Project Office (GPO) rejected this plan, regarding it as impractical within current schedule, launch sequence, and cost restraints. . Additional Details: here....

• First Agena D for the Gemini program. - . Nation: USA. Program: Gemini. Flight: Gemini 12. Spacecraft: Gemini, Gemini Radar.

  Air Force Space Systems Division (SSD) accepted the first Agena D (AD-71) for the Gemini program. The Agena D was a production-line vehicle procured from Lockheed by SSD for NASA through routine procedures. Following minor retrofit operations, the vehicle, now designated Gemini Agena target vehicle 5001, entered the manufacturing final assembly area at the Lockheed plant on May 14. There began the conversion of the Agena D into a target vehicle for Gemini rendezvous missions. Major modifications were installation of a target docking adapter (supplied by McDonnell), an auxiliary equipment rack, external status displays, a secondary propulsion system, and an L-band tracking radar.

• Sea trials of the tracking ship, Rose Knot, were begun on Chesapeake Bay to study the effects of shock vibrations on Gemini equipment. - . Nation: USA. A few vibration problems with the pulse-code-modulation system were reported. Gemini-Agena systems were simulated by an instrumented Lockheed Super Constellation aircraft..

• Flight Operations Division presented the Gemini Program Office's proposed mission plan No. 3 for the first Agena rendezvous flight to the Trajectories and Orbits Panel. - . Nation: USA. Plan No. 3, as yet incomplete, provided for rendezvous at first apogee on a perfectly nominal mission..

• Lockheed inaugurated the Gemini Extra Care Program to reduce the incidence of equipment failures and discrepancies. - . Nation: USA.

  In cooperation with Air Force and NASA, Lockheed inaugurated the Gemini Extra Care Program to reduce the incidence of equipment failures and discrepancies resulting from poor or careless workmanship during the modification and assembly of the Agena target vehicle. The program included increased inspection, exhortation, morale boosters, special awards, and other activities aimed at fostering and maintaining a strong team spirit at all levels. Results of the program were evidenced in a drastic decline in the number of FEDRs (Failed Equipment and Discrepancy Reports) recorded in the Gemini final manufacturing area on successive vehicles.

• Lockheed began test-firing the propulsion test vehicle assembly at its Santa Cruz Test Base, after a delay caused primarily by problems with the Agena main engine start tanks. - . Nation: USA.

  The program, undertaken because of extensive changes in the propulsion system required to adapt the standard Agena D for use in Gemini missions, comprised three series of static-firing tests. The first series, in addition to providing base line performance for both primary and secondary propulsion systems (PPS and SPS), also subjected one SPS module to the dynamic and acoustic environment created by 55 seconds of PPS firing. The second series, successfully completed July 16, simulated a possible Gemini mission profile, including multiple firings and various coast and burn times on both PPS and SPS units. The third series, which concluded the test program on August 7, involved a maximum number of starts and minimum-impulse firings on both PPS and SPS. All firings were successful, and review of test data revealed only minor anomalies. The entire test program comprised 27 PPS firings for a run time totaling 545 seconds, 30 SPS Unit I firings totaling 286 seconds, and 11 SPS Unit II firings totaling 268 seconds. Post-test disassembly revealed no physical damage to any equipment.

• Construction of Gemini-Agena facilities at complex 14 was completed. - . Nation: USA. General Dynamics finished the installation and checkout of equipment in the Launch Operations Building on July 20. Lockheed equipment in the Launch Operations Building was installed and checked out by July 31..

• KH 7-10 - . Payload: KH-7 no. 10 / OPS 3802. Mass: 2,000 kg (4,400 lb). Nation: USA. Agency: NRO, USAF. Class: Surveillance. Type: Military surveillance satellite. Spacecraft Bus: WS-117. Spacecraft: KH-7. Decay Date: 1964-08-23 . USAF Sat Cat: 850 . COSPAR: 1964-045A. Apogee: 300 km (180 mi). Perigee: 165 km (102 mi). Inclination: 95.4000 deg. Period: 89.10 min.

  The first Atlas/Agena D standard launch vehicle (SLV-3, 7100 Series) was successfully launched from Vandenberg AFB. This vehicle, Number 7101, was the first Atlas booster to be designed and produced to fully standardized specifications. KH-7 type satellite. Space craft engaged in investigation of spaceflight techniques and technology (US Cat A).

• OPS 3316 - . Payload: P-11 s/n 4202. Mass: 79 kg (174 lb). Nation: USA. Agency: USAF. Class: Surveillance. Type: Naval signals intelligence satellite. Spacecraft Bus: P 11. Spacecraft: SSF. Decay Date: 1979-03-08 . USAF Sat Cat: 851 . COSPAR: 1964-045B. Apogee: 3,751 km (2,330 mi). Perigee: 272 km (169 mi). Inclination: 95.7000 deg. Period: 127.40 min. The first Atlas/Agena D standard launch vehicle (SLV-3, 7100 Series) was successfully launched from Vandenberg AFB. This vehicle, Number 7101, was the first Atlas booster to be designed and produced to fully standardized specifications. .

• KH 7-11 - . Payload: KH-7 no. 11 / OPS 4262. Mass: 2,000 kg (4,400 lb). Nation: USA. Agency: NRO, USAF. Class: Surveillance. Type: Military surveillance satellite. Spacecraft Bus: WS-117. Spacecraft: KH-7. Decay Date: 1964-09-28 . USAF Sat Cat: 884 . COSPAR: 1964-058A. Apogee: 303 km (188 mi). Perigee: 143 km (88 mi). Inclination: 92.9000 deg. Period: 88.90 min. KH-7 type satellite. Space craft engaged in investigation of spaceflight techniques and technology (US Cat A). .

• Lockheed completed the modification and final assembly of Gemini Agena target vehicle 5001 and transferred it to systems test complex C-10 at the Lockheed plant. - . Nation: USA. Flight: Gemini 12. Lockheed began the task of hooking the vehicle up for systems testing the next day, September 25..

• KH-7 12 - . Payload: KH-7 no. 12. Mass: 2,000 kg (4,400 lb). Nation: USA. Agency: USAF. Class: Surveillance. Type: Military surveillance satellite. Spacecraft Bus: WS-117. Spacecraft: KH-7. Decay Date: 1964-10-08 . KH-7 type satellite..

• SRV - . Mass: 2,000 kg (4,400 lb). Nation: USA. Agency: USAF AFSC. Spacecraft Bus: WS-117. Spacecraft: KH-7.

• Bell Aerosystems successfully fired the Agena secondary propulsion system (SPS) in a test of the system's ability to survive a launch hold. - . Nation: USA. The SPS had first gone through a 20-day dry (unloaded) period, followed by a 20-day wet (loaded) period. The system reverted to hold condition and was successfully refired November 2..

• Gemini Agena target vehicle (GATV) 5001 competed a simulated flight (ascent and orbit) at Lockheed test complex C-10. - . Nation: USA. Flight: Gemini 12. Minor anomalies required portions of the test to be rerun. This concluded GATV 5001 systems tests in preparation for captive-firing tests to be conducted at Lockheed's Santa Cruz Test Base. The vehicle was shipped November 30..

• Lockheed shipped Gemini Agena target vehicle (GATV) 5001 to its Santa Cruz Test Base for captive-firing tests. - . Nation: USA. Flight: Gemini 12. Primary test objective was verifying the operational capabilities of the GATV during actual firing of the primary and secondary propulsion systems. . Additional Details: here....

• KH 7-14 - . Payload: KH-7 no. 14 / OPS 4439. Mass: 2,000 kg (4,400 lb). Nation: USA. Agency: NRO, USAF. Class: Surveillance. Type: Military surveillance satellite. Spacecraft Bus: WS-117. Spacecraft: KH-7. Decay Date: 1964-12-05 . USAF Sat Cat: 946 . COSPAR: 1964-079A. Apogee: 357 km (221 mi). Perigee: 158 km (98 mi). Inclination: 97.0000 deg. Period: 89.70 min. KH-7 type satellite. Space craft engaged in investigation of spaceflight techniques and technology (US Cat A). .

• Gemini Program Office (GPO) reported that it had initiated contractual action to delete the eighth Agena from the Gemini Agena target vehicle program. - . Nation: USA. On March 6, 1965, GPO reported its decision to eliminate the seventh Agena as well..

• Air Force Space Systems Division officially accepted Agena D (AD-82) for the Gemini program. - . Nation: USA. Flight: Gemini 6. Lockheed then transferred it to the vehicle final assembly area for modification to Gemini Agena target vehicle 5002. Work was scheduled to begin in mid-January 1965..

• Gemini Agena target vehicle 5001 underwent a successful hot-firing test at Lockheed's Santa Cruz Test Base. - . Nation: USA. Flight: Gemini 12.

  The test simulated a full 20,000-second mission, including multiple firings of both the primary and secondary propulsion systems and transmission of operational data in real time to two PCM (pulse-code-modulated) telemetry ground stations, one at the test site and one in Sunnyvale. Major test anomaly was a series of command programmer time-accumulator jumps, seven of which totaled 77,899 seconds. The vehicle was removed from the test stand on February 1 and returned to Sunnyvale.

• KH 7-15 - . Payload: KH-7 no. 15 / OPS 4703. Mass: 2,000 kg (4,400 lb). Nation: USA. Agency: NRO, USAF. Class: Surveillance. Type: Military surveillance satellite. Spacecraft Bus: WS-117. Spacecraft: KH-7. Decay Date: 1965-01-29 . USAF Sat Cat: 980 . COSPAR: 1965-005A. Apogee: 291 km (180 mi). Perigee: 146 km (90 mi). Inclination: 102.5000 deg. Period: 88.90 min. KH-7 type satellite. Space craft engaged in investigation of spaceflight techniques and technology (US Cat A). .

• Lockheed initiated a "Ten-point Plan for C&C; Equipment." - . Nation: USA.

  The Agena command and communication (C and C) system comprised the electronic systems for tracking the vehicle, for monitoring the performance of its various subsystems, and for verifying operating commands for orbital operations. Because of the unique requirements of the Gemini mission, in particular rendezvous and docking, Lockheed had had to design and develop a new C and C system for the Gemini target vehicle. Numerous failures and problems calling for rework during the initial manufacturing stages of the C and C system suggested the existence of mechanical and electronic design deficiencies. Aerospace, which had assumed technical surveillance functions for the Gemini Agena in the fall of 1964, was instrumental in bringing these problems to the attention of Air Force and Lockheed top management. Among the results of the 10-point plan were several redesigned programmer circuits and packaging changes, closer monitoring of vendor work, expedited failure analysis, and improved quality control.

• Gemini Agena target vehicle (GATV) 5001 was removed from the test stand at Santa Cruz Test Base and returned to Sunnyvale. - . Nation: USA. Flight: Gemini 12. After a brief stopover in systems test complex C-10, the vehicle was transferred to the anechoic chamber for elecromagnetic interference and radio-frequency-interference tests. . Additional Details: here....

• Gemini Agena target vehicle 5001 completed electromagnetic compatibility tests in the anechoic chamber at Sunnyvale. - . Nation: USA. Flight: Gemini 12.

  It remained in the chamber, however, until March 17 while Lockheed verified the corrective action that had been taken to eliminate programmer time-accumulator jumps and telemetry synchronization problems. The vehicle was then transferred to systems test complex C-10 for final Vehicle Systems Tests on March 18.

• KH 7-16 - . Payload: KH-7 no. 16 / OPS 4920. Mass: 2,000 kg (4,400 lb). Nation: USA. Agency: NRO, USAF. Class: Surveillance. Type: Military surveillance satellite. Spacecraft Bus: WS-117. Spacecraft: KH-7. Decay Date: 1965-03-17 . USAF Sat Cat: 1247 . COSPAR: 1965-019A. Apogee: 358 km (222 mi). Perigee: 223 km (138 mi). Inclination: 107.5000 deg. Period: 90.30 min. KH-7 type satellite. Space craft engaged in investigation of spaceflight techniques and technology (US Cat A). .

• Gemini Agena target vehicle (GATV) 5001 was transferred from the anechoic chamber to systems test complex C-10. - . Nation: USA. Flight: Gemini 12. Six days were scheduled for vehicle modifications before beginning final systems tests. . Additional Details: here....

• Snapshot - . Payload: SNAP 10A / Agena D / OPS 4682. Mass: 440 kg (970 lb). Nation: USA. Agency: AEC, USAF. Class: Technology. Type: Ion engine technology satellite. Spacecraft: Snapshot. USAF Sat Cat: 1314 . COSPAR: 1965-027A. Apogee: 1,314 km (816 mi). Perigee: 1,270 km (780 mi). Inclination: 90.3000 deg. Period: 111.40 min.

  The 6595th Aerospace Test Wing launched an Atlas/Agena which boosted the Atomic Energy Commission (AEC) Snapshot spacecraft into orbit carrying the SNAP-10A satellite nuclear power supply experiment. The onboard nuclear reactor was used to provide electric power for an ion engine, marking the first attempt to test a reactor-ion system in orbit. Only nuclear reactor ever orbited by the United States. The SNAP-10A reactor provided electrical power for an 8.5 mN ion engine using cesium propellant. The engine was shut off after one hour of operation when high-voltage spikes created electromagnetic interference with the satellite's attitude control system sensors. The reactor continued in operation, generating 39 kWt and more than 500 watts of electrical power for 43 days before the spacecraft telemetry failed.

• SECOR 4 - . Payload: EGRS 4. Mass: 40 kg (88 lb). Nation: USA. Agency: USA ACE. Class: Earth. Type: Geodetic satellite. Spacecraft: SECOR. USAF Sat Cat: 1315 . COSPAR: 1965-027B. Apogee: 1,316 km (817 mi). Perigee: 1,267 km (787 mi). Inclination: 90.2000 deg. Period: 111.40 min. Failed. Space craft engaged in investigation of spaceflight techniques and technology (US Cat A)..

• KH 7-17 - . Payload: KH-7 no. 17 / OPS 4983. Mass: 2,000 kg (4,400 lb). Nation: USA. Agency: NRO, USAF. Class: Surveillance. Type: Military surveillance satellite. Spacecraft Bus: WS-117. Spacecraft: KH-7. Decay Date: 1965-05-03 . USAF Sat Cat: 1327 . COSPAR: 1965-031A. Apogee: 259 km (160 mi). Perigee: 180 km (110 mi). Inclination: 95.6000 deg. Period: 89.00 min. KH-7 type satellite. Space craft engaged in investigation of spaceflight techniques and technology (US Cat A). .

• OPS 6717 - . Payload: EHH B1. Mass: 60 kg (132 lb). Nation: USA. Agency: NRO, USAF. Class: Surveillance. Type: Naval signals intelligence satellite. Spacecraft Bus: P 11. Spacecraft: SSF. Decay Date: 1969-10-31 . USAF Sat Cat: 1329 . COSPAR: 1965-031B. Apogee: 547 km (339 mi). Perigee: 506 km (314 mi). Inclination: 95.2000 deg. Period: 95.10 min. Radar monitoring..

• Gemini Agena target vehicle (GATV) 5001 completed vehicle systems testing with a final simulated flight. - . Nation: USA. Flight: Gemini 12. The vehicle was disconnected from the test complex on May 14, and data analysis was completed May 19. Meanwhile, the First Article Configuration Inspection on GATV 5001 began on May 10..

• First Article Configuration Inspection (FACI) of Gemini Agena target vehicle (GATV) 5001 at Sunnyvale. - . Nation: USA. Flight: Gemini 12, Gemini 6. A team of representatives from NASA, Air Force Space Systems Division, Aerospace, and Lockheed began the First Article Configuration Inspection (FACI) of Gemini Agena target vehicle (GATV) 5001 at Sunnyvale. . Additional Details: here....

• Gemini Agena target vehicle (GATV) 5002 completed final assembly and was transferred to systems test complex C-10 at Sunnyvale to begin Vehicle Systems Tests. - . Nation: USA. Flight: Gemini 6.

  The transfer had been scheduled for May 5 but was delayed by parts shortages, engineering problems, and considerable work backlog. The major source of delay was correcting a gap between the forward auxiliary rack and the vehicle; machining and aligning the rack and refinishing the scraped surfaces proved time-consuming. GATV 5002 was still short several items of command equipment. Systems testing began May 21.

• KH 7-18 - . Payload: KH-7 no. 18 / OPS 5236. Mass: 2,000 kg (4,400 lb). Nation: USA. Agency: NRO, USAF. Class: Surveillance. Type: Military surveillance satellite. Spacecraft Bus: WS-117. Spacecraft: KH-7. Decay Date: 1965-06-01 . USAF Sat Cat: 1386 . COSPAR: 1965-041A. Apogee: 267 km (165 mi). Perigee: 149 km (92 mi). Inclination: 95.6000 deg. Period: 88.70 min. KH-7 type satellite. Space craft engaged in investigation of spaceflight techniques and technology (US Cat A). .

• Gemini Agena target vehicle 5001 arrived at Cape Kennedy following its conditional acceptance by the Air Force on May 27. - . Nation: USA. Flight: Gemini 6.

  It was moved to the Missile Assembly Building (Hanger E) for testing. The target vehicle was mated with target docking adapter No. 1 on June 18, and Combined Interface Tests began June 19. Testing was completed July 8 with secondary propulsion system (SPS) functional and static leak checks, SPS installation and postinstallation checks, and thermal control surface preparation. Target vehicle 5001 was then transferred to complex 14 to be mated to target launch vehicle 5301.

• OPS 6749 - . Payload: EHH B2. Mass: 60 kg (132 lb). Nation: USA. Agency: NRO, USAF. Class: Surveillance. Type: Naval signals intelligence satellite. Spacecraft Bus: P 11. Spacecraft: SSF. Decay Date: 1968-08-22 . USAF Sat Cat: 1422 . COSPAR: 1965-050A. Apogee: 510 km (310 mi). Perigee: 496 km (308 mi). Inclination: 107.6000 deg. Period: 94.70 min. Radar monitoring..

• KH 7-19 - . Payload: KH-7 no. 19 / OPS 5501. Mass: 2,000 kg (4,400 lb). Nation: USA. Agency: NRO, USAF. Class: Surveillance. Type: Military surveillance satellite. Spacecraft Bus: WS-117. Spacecraft: KH-7. Decay Date: 1965-06-30 . USAF Sat Cat: 1424 . COSPAR: 1965-050B. Apogee: 349 km (216 mi). Perigee: 254 km (157 mi). Inclination: 107.6000 deg. Period: 90.50 min. KH-7 type satellite. Space craft engaged in investigation of spaceflight techniques and technology (US Cat A). .

• Gemini Agena target vehicle 5002 completed Vehicle Systems Tests at Sunnyvale, and the final acceptance test was conducted. - . Nation: USA. Flight: Gemini 6. The vehicle was disconnected from the test complex on July 13, after NASA, Air Force Space Systems Division, Aerospace, and Lockheed representatives agreed that all data discrepancies from the final systems tests had been resolved..

• KH-7-20 - . Payload: KH-7 no. 20. Mass: 2,000 kg (4,400 lb). Nation: USA. Agency: USAF. Class: Surveillance. Type: Military surveillance satellite. Spacecraft Bus: WS-117. Spacecraft: KH-7. Decay Date: 1965-07-12 . KH-7 type satellite..

• SRV - . Mass: 2,000 kg (4,400 lb). Nation: USA. Agency: USAF AFSC. Spacecraft Bus: WS-117. Spacecraft: KH-7.

• Standard Agena D (AD-108), which had been completed in June and held in storage, was transferred to Building 104 at Sunnyvale for modifications and final assembly as Gemini Agena target vehicle 5003. - . Nation: USA. Flight: Gemini 8. While in storage, several pieces of AD-108 equipment had been removed for modification to the Gemini configuration. Final assembly began August 8..

• Air Force Space Systems Division formally accepted delivery of Gemini Agena target vehicle (GATV) 5002 after the vehicle acceptance team inspection had been completed. - . Nation: USA. Flight: Gemini 6.

  The vehicle was then shipped by air to Eastern Test Range on July 24, arriving July 25. Although GATV 5002 was accepted, several items of equipment remained in 'not qualified' status, including the shroud, secondary and primary propulsion systems, and components of both the electrical power and command systems.

• KH 7-21 - . Payload: KH-7 no. 21 / OPS 5698. Mass: 2,000 kg (4,400 lb). Nation: USA. Agency: NRO, USAF. Class: Surveillance. Type: Military surveillance satellite. Spacecraft Bus: WS-117. Spacecraft: KH-7. Decay Date: 1965-08-07 . USAF Sat Cat: 1471 . COSPAR: 1965-062A. Apogee: 352 km (218 mi). Perigee: 278 km (172 mi). Inclination: 107.4000 deg. Period: 90.80 min. KH-7 type satellite. Space craft engaged in investigation of spaceflight techniques and technology (US Cat A). .

• OPS 6761 - . Payload: EHH B3. Mass: 60 kg (132 lb). Nation: USA. Agency: NRO, USAF. Class: Surveillance. Type: Naval signals intelligence satellite. Spacecraft Bus: P 11. Spacecraft: SSF. Decay Date: 1968-06-17 . USAF Sat Cat: 1472 . COSPAR: 1965-062B. Apogee: 515 km (320 mi). Perigee: 501 km (311 mi). Inclination: 107.4000 deg. Period: 94.80 min. Radar monitoring..

• Gemini Agena target vehicle 5002 completed preliminary systems testing at Hanger E. - . Nation: USA. Flight: Gemini 6.

  Gemini Agena target vehicle 5002 completed preliminary systems testing at Hanger E and was transferred to Merritt Island Launch Area, where it was joined by spacecraft No. 6 for Plan X testing. After ground equipment checks, Plan X tests proceeded on August 25. No significant interference problems were found, and testing ended on August 31.

• Final troubleshooting on Gemini Agena target vehicle (GATV) 5002 after Plan X testing at Merritt Island Launch Area (MILA) was completed. - . Nation: USA. Flight: Gemini 6. The next day GATV 5002 was returned to Hanger E from MILA, where it began a series of tests to verify the operational readiness of all vehicle systems prior to erection and mating with the launch vehicle..

• Representatives of Air Force Space Systems Division, Aerospace, and Lockheed attended a technical review of the flight verification test program for the oxidizer gas generator solenoid valve. - . Nation: USA.

  This was the last remaining component of the Agena primary propulsion system needing test qualification. Testing had been completed August 26; disassembly, inspection, and evaluation were concluded September 3. The consensus of those attending was that the successful test program had demonstrated flightworthiness of this configuration. This concluded qualification of all propulsion system components.

• KH 7-22 - . Payload: KH-7 no. 22 / OPS 7208. Mass: 2,000 kg (4,400 lb). Nation: USA. Agency: NRO, USAF. Class: Surveillance. Type: Military surveillance satellite. Spacecraft Bus: WS-117. Spacecraft: KH-7. Decay Date: 1965-10-05 . USAF Sat Cat: 1609 . COSPAR: 1965-076A. Apogee: 361 km (224 mi). Perigee: 237 km (147 mi). Inclination: 95.6000 deg. Period: 90.50 min. KH-7 type satellite. Space craft engaged in investigation of spaceflight techniques and technology (US Cat A). .

• Gemini Agena target vehicle 5002 was transported to complex 14 and mated to target launch vehicle 5301. - . Nation: USA. Flight: Gemini 6.

  Preliminary checks were followed, on October 4, by the Joint Flight Acceptance Composite Test (J-FACT). J-FACT was a combined check of all contractors, the range, the vehicles, and aerospace ground equipment in a simulated countdown and flight; propellants and high pressure gases were not loaded, nor was the gantry removed. Simultaneous Launch Demonstration was successfully completed October 7.

• Gemini Agena target vehicle 5003 was transferred to Vehicle Systems Test after completing final assembly on October 9. - . Nation: USA. Flight: Gemini 8. Testing began October 18..

• Gemini 6 Agena Target - . Payload: TDA-2. Mass: 3,261 kg (7,189 lb). Nation: USA. Agency: NASA. Program: Gemini. Class: Manned. Type: Manned logistics spacecraft. Flight: Gemini 6, Gemini 7. Spacecraft Bus: Agena. Spacecraft: Gemini Agena Target Vehicle. Decay Date: 1965-10-25 . The Agena target vehicle failed to reach orbit. Gemini 6, awaiting launch, was cancelled. In the ashes of this setback, the idea of launching Gemini 6 to rendezvous with Gemini 7 was born..

• Catastrophic anomaly of Gemini Agena target vehicle (GATV) 5002 on October 25 defined as a mission failure. - . Nation: USA. Flight: Gemini 6.

  NASA Associate Administrator Robert C. Seamans, Jr., informed George E. Mueller, Associate Administrator for Manned Space Flight, that the catastrophic anomaly of Gemini Agena target vehicle (GATV) 5002 on October 25 had been defined as a mission failure. Additional Details: here....

• Discrepancies remaining on Gemini Agena target vehicle 5001 cleared. - . Nation: USA. Flight: Gemini 12.

  The major portion of 819 discrepancies remaining from the First Article Configuration Inspection (FACI) of Gemini Agena target vehicle 5001 in June were cleared; 128 that had not been applied against the acceptance document (DD-250) remained. All subsystem FACI discrepancies were also closed out during October.

• The subpanel for Gemini VI of the Agena Flight Safety Review Board met at Lockheed. - . Nation: USA. Flight: Gemini 6. The subpanel, chaired by Colonel John B. Hudson, Deputy Commander for Launch Vehicles, Air Force Space Systems Division, reviewed Lockheed's flight safety analysis of the failure of Gemini Agena target vehicle (GATV) 5002 on October 25. . Additional Details: here....

• The Agena Flight Safety Review Board met at Lockheed to continue its investigation of the failure of Gemini Agena target vehicle 5002 on October 25. - . Nation: USA. Flight: Gemini 6. The board, chaired by George E. Mueller, NASA Associate Administrator of Manned Space Flight, reviewed the findings of the subpanel for Gemini VI and reached the same conclusion: the failure resulted from a hard start probably caused by the fuel lead. . Additional Details: here....

• KH 7-23 - . Payload: KH-7 no. 23 / OPS 8293. Mass: 2,000 kg (4,400 lb). Nation: USA. Agency: NRO, USAF. Class: Surveillance. Type: Military surveillance satellite. Spacecraft Bus: WS-117. Spacecraft: KH-7. Decay Date: 1965-11-11 . USAF Sat Cat: 1727 . COSPAR: 1965-090A. Apogee: 352 km (218 mi). Perigee: 280 km (170 mi). Inclination: 93.9000 deg. Period: 90.80 min. Space craft engaged in investigation of spaceflight techniques and technology (US Cat A). .

• OPS 6232/Agena D - . Payload: Agena Pickaback / OPS 6232. Mass: 60 kg (132 lb). Nation: USA. Agency: USAF. Class: Surveillance. Type: Naval signals intelligence satellite. Spacecraft Bus: P 11. Spacecraft: SSF. Decay Date: 1965-11-09 . USAF Sat Cat: 1728 . COSPAR: 1965-090B. Apogee: 284 km (176 mi). Perigee: 155 km (96 mi). Inclination: 93.9000 deg. Period: 88.90 min. Not identified as a subsatellite ferret by McDowell..

• A symposium on hypergolic rocket ignition at altitude was held at Lockheed. - . Nation: USA. Flight: Gemini 6.

  Because too little diagnostic information had been obtained from the flight of Gemini Agena target vehicle (GATV) 5002 to determine the exact nature of the probable hard start, it was not certain that the proposed modification - a return to oxidizer lead - would definitely prevent a recurrence of the malfunctions. Additional Details: here....

• Gemini Agena target vehicle (GATV) engine modification and test program. - . Nation: USA. Related Persons: Hohmann, Bernhard.

  Lockheed presented its proposed Gemini Agena target vehicle (GATV) engine modification and test program to Colonel A. J. Gardner, Gemini Target Vehicle Program Director, Air Force Space Systems Division (SSD). The proposal was immediately turned over to a three-man team comprising B. A. Hohmann (Aerospace), Colonel J. B. Hudson (Deputy Commander for Launch Vehicles, SSD), and L. E. Root (Lockheed) for consideration. On November 18, the group decided on a final version of the proposal that called for: (1) modifying the Agena engine to provide oxidizer lead during the start sequence, (2) demonstrating sea-level engine flightworthiness in tests at Bell Aerosystems, and (3) conducting an altitude test program at Arnold Engineering Development Center. The final proposal was presented to the GATV Review Board at Manned Spacecraft Center on November 20.

• Air Force Space Systems Division (SSD) directed Lockheed to return Gemini Agena target vehicle (GATV) 5001 to Sunnyvale. - . Nation: USA. Flight: Gemini 12. The GATV was still being stored in Hanger E, Eastern Test Range, minus its main engine which SSD had directed Lockheed to ship to Bell Aerosystems on November 9 for modification. . Additional Details: here....

• Lockheed submitted an engineering change proposal to Air Force Space Systems Division (SSD) for Project Surefire. - . Nation: USA. Flight: Gemini 8, Gemini 9. Surefire was the code name for the Gemini Agena Target Vehicle (GATV) Modification and Test Program designed to correct the malfunction which had caused the failure of GATV 5002 on October 25. . Additional Details: here....

• McDonnell proposed building a backup target vehicle for Gemini rendezvous missions. - . Nation: USA. Flight: Gemini 8. Spacecraft: Gemini, Gemini Radar.

  The augmented target docking adapter (ATDA) would serve as an alternative to the Gemini Agena target vehicle (GATV) if efforts to remedy the GATV problem responsible for the October 25 mission abort did not meet the date scheduled for launching Gemini VIII. Additional Details: here....

• Air Force Space Systems Division authorized Lockheed to begin the disassembly and inspection of Gemini Agena target vehicle 5001 to determine the extent of refurbishment needed. - . Nation: USA. Flight: Gemini 12. The vehicle was stripped down to its major structural components to expose all areas of possible contamination..

• The Air Force accepted the main rocket engine for Gemini Agena target vehicle (GATV) 5003 after Bell Aerosystems had completed Project Surefire modifications. - . Nation: USA. Flight: Gemini 8. The engine was shipped immediately and arrived at Lockheed December 18. Lockheed completed reinstalling the engine on December 20. GATV 5003 systems retesting began December 27 after other equipment modifications had been installed..

• 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). - . Nation: USA. Flight: Gemini 8.

  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.

• Project Surefire verification testing began at Bell Aerosystems. - . Nation: USA. Flight: Gemini 8.

  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.

• Gemini Program Office review of possible future mission activities. - . Nation: USA. Flight: Gemini 10, Gemini 8, Gemini 9.

  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. Additional Details: here....

• KH 7-24 - . Payload: KH-7 no. 24 / OPS 7253. Mass: 2,000 kg (4,400 lb). Nation: USA. Agency: NRO, USAF. Class: Surveillance. Type: Military surveillance satellite. Spacecraft Bus: WS-117. Spacecraft: KH-7. Decay Date: 1966-01-25 . USAF Sat Cat: 1939 . COSPAR: 1966-002A. Apogee: 259 km (160 mi). Perigee: 138 km (85 mi). Inclination: 93.8000 deg. Period: 88.40 min. KH-7 type satellite. Space craft engaged in investigation of spaceflight techniques and technology (US Cat A). .

• OPS 3179/Agena D - . Payload: Agena Pickaback / OPS 3179. Mass: 60 kg (132 lb). Nation: USA. Agency: USAF. Class: Surveillance. Type: Naval signals intelligence satellite. Spacecraft Bus: P 11. Spacecraft: SSF. Decay Date: 1966-01-23 . USAF Sat Cat: 1940 . COSPAR: 1966-002B. Apogee: 149 km (92 mi). Perigee: 120 km (70 mi). Inclination: 93.8000 deg. Period: 87.20 min. Not identified as a subsatellite ferret by McDowell..

• Gemini Agena target vehicle (GATV) 5003 was mated to target docking adapter (TDA) 3. - . Nation: USA. Flight: Gemini 8.

  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.

• Gemini Agena target vehicle (GATV) 5004 was transferred to the vehicle systems test area at Sunnyvale. - . Nation: USA. Flight: Gemini 9.

  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.

• Gemini Agena target vehicle (GATV) 5003 was returned to Hanger E after completing Plan X tests at Merritt Island Launch Area. - . Nation: USA. Flight: Gemini 8. 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..

• Agena D (AD-129) was accepted by the Air Force for delivery to the Gemini program. - . Nation: USA. Flight: Gemini 10. It was transferred to the final assembly area at Sunnyvale for modification to Gemini Agena target vehicle 5005..

• 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. - . Nation: USA.

  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.

• The augmented target docking adapter (ATDA) arrived at Cape Kennedy. Modifications, testing, and troubleshooting were completed March 4. - . Nation: USA. Flight: Gemini 9.

  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.

• KH 7-25 - . Payload: KH-7 no. 25 / OPS 1184. Mass: 2,000 kg (4,400 lb). Nation: USA. Agency: NRO, USAF. Class: Surveillance. Type: Military surveillance satellite. Spacecraft Bus: WS-117. Spacecraft: KH-7. Decay Date: 1966-02-22 . USAF Sat Cat: 2012 . COSPAR: 1966-012A. Apogee: 290 km (180 mi). Perigee: 142 km (88 mi). Inclination: 96.5000 deg. Period: 88.90 min. KH-7 type satellite. Space craft engaged in investigation of spaceflight techniques and technology (US Cat A). .

• Bluebell 2C (Cylinder) - . Payload: OPS 3011. Mass: 9.00 kg (19.80 lb). Nation: USA. Agency: USAF. Class: Surveillance. Type: Radar calibration target. Spacecraft: Bluebell. Decay Date: 1966-02-16 . USAF Sat Cat: 2014 . COSPAR: 1966-012B. Apogee: 253 km (157 mi). Perigee: 115 km (71 mi). Inclination: 96.5000 deg. Period: 88.10 min. Space craft engaged in investigation of spaceflight techniques and technology (US Cat A). .

• Bluebell 2S (Sphere) - . Payload: OPS 3031. Mass: 4.00 kg (8.80 lb). Nation: USA. Agency: USAF. Class: Surveillance. Type: Radar calibration target. Spacecraft: Bluebell. Decay Date: 1966-02-22 . USAF Sat Cat: 2015 . COSPAR: 1966-012C. Apogee: 268 km (166 mi). Perigee: 147 km (91 mi). Inclination: 96.5000 deg. Period: 88.60 min. Space craft engaged in investigation of spaceflight techniques and technology (US Cat A). .

• Gemini Agena target vehicle (GATV) 5004 completed systems testing at Sunnyvale. - . Nation: USA. Flight: Gemini 9. 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..

• Gemini Agena target vehicle 5003 systems exercised. - . Nation: USA. Flight: Gemini 10, Gemini 8.

  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. Additional Details: here....

• Gemini 8 Agena Target - . Payload: TDA 3/Agena D 5003 GATV. Mass: 3,175 kg (6,999 lb). Nation: USA. Agency: NASA Houston. Program: Gemini. Class: Manned. Type: Manned logistics spacecraft. Flight: Gemini 8. Spacecraft Bus: Agena. Spacecraft: Gemini Agena Target Vehicle. Decay Date: 1967-09-15 . USAF Sat Cat: 2104 . COSPAR: 1966-019A. Apogee: 299 km (185 mi). Perigee: 285 km (177 mi). Inclination: 28.9000 deg. Period: 90.40 min. Target vehicle for Gemini 8..

• KH 7-26 - . Payload: KH-7 no. 26 / OPS 0879. Mass: 60 kg (132 lb). Nation: USA. Agency: NRO, USAF. Class: Surveillance. Type: Military surveillance satellite. Spacecraft Bus: WS-117. Spacecraft: KH-7. Decay Date: 1966-03-24 . USAF Sat Cat: 2109 . COSPAR: 1966-022A. Apogee: 308 km (191 mi). Perigee: 162 km (100 mi). Inclination: 101.0000 deg. Period: 89.30 min. Not identified as a subsatellite ferret by McDowell..

• OPS 0974/Agena D - . Payload: NRL PL137 / OPS 0974. Mass: 2,000 kg (4,400 lb). Nation: USA. Agency: USAF. Class: Surveillance. Type: Naval signals intelligence satellite. Spacecraft Bus: P 11. Spacecraft: SSF. Decay Date: 1966-03-23 . USAF Sat Cat: 2112 . COSPAR: 1966-022B. Apogee: 285 km (177 mi). Perigee: 149 km (92 mi). Inclination: 101.0000 deg. Period: 88.80 min. Space craft engaged in investigation of spaceflight techniques and technology (US Cat A). .

• Gemini Agena target vehicle 5004 and spacecraft No. 9 began Plan X compatibility tests at Merritt Island Launch Area Radar Range. - . Nation: USA. Flight: Gemini 9. Spacecraft: Gemini, Gemini Radar.

• 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. - . Nation: USA. Flight: Gemini 11.

• Project Surefire test program not to be curtailed. - . Nation: USA. Flight: Gemini 8. 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. . Additional Details: here....

• OAO 1 - . Payload: OAO A1. Mass: 1,774 kg (3,911 lb). Nation: USA. Agency: NASA Greenbelt. Class: Astronomy. Type: X-ray astronomy satellite. Spacecraft: OAO. USAF Sat Cat: 2142 . COSPAR: 1966-031A. Apogee: 793 km (492 mi). Perigee: 783 km (486 mi). Inclination: 35.0000 deg. Period: 100.60 min. Orbiting Astronomical Observatory. Spacecraft engaged in research and exploration of the upper atmosphere or outer space (US Cat B). .

• Gemini Agena target vehicle 5004 began the Combined Interface Test (CIT) at Hanger E, Eastern Test Range, after completing Plan X tests March 24. - . Nation: USA. Flight: Gemini 9. CIT ended April 22 and engine functional tests of both the primary and secondary propulsion systems followed. Hanger E testing was completed May 1..

• Evaluation of a Lockheed proposal to launch space probes from orbit using Agena rockets launched from AAP stations in space. - . Nation: USA. Related Persons: Mueller, Seamans. Spacecraft Bus: Skylab. Spacecraft: Orbital Workshop.

  Associate Administrator for Manned Space Fight George E. Mueller informed Deputy Administrator Robert C. Seamans, Jr., of the Saturn/Apollo Applications Program Office's evaluation of a Lockheed proposal to launch space probes from orbit using Agena rockets launched from AAP stations in space. The proposal was feasible, Mueller advised, but did not seem a desirable mission for inclusion in the AAP. Additional Details: here....

• KH 7-27 - . Payload: KH-7 no. 27 / OPS 0910. Mass: 2,000 kg (4,400 lb). Nation: USA. Agency: NRO, USAF. Class: Surveillance. Type: Military surveillance satellite. Spacecraft Bus: WS-117. Spacecraft: KH-7. Decay Date: 1966-04-26 . USAF Sat Cat: 2146 . COSPAR: 1966-032A. Apogee: 375 km (233 mi). Perigee: 139 km (86 mi). Inclination: 116.9000 deg. Period: 89.60 min. KH-7 type satellite. Space craft engaged in investigation of spaceflight techniques and technology (US Cat A). .

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

• Lockheed established a task force to handle the refurbishing of Gemini Agena target vehicle (GATV) 5001 and announced a GATV 5001 Reassembly Plan. - . Nation: USA. Flight: Gemini 12.

  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.

• KH 7-28 - . Payload: KH-7 no. 28 / OPS 1950. Mass: 2,000 kg (4,400 lb). Nation: USA. Agency: NRO, USAF. Class: Surveillance. Type: Military surveillance satellite. Spacecraft Bus: WS-117. Spacecraft: KH-7. Decay Date: 1966-05-21 . USAF Sat Cat: 2171 . COSPAR: 1966-039A. Apogee: 319 km (198 mi). Perigee: 130 km (80 mi). Inclination: 110.5000 deg. Period: 89.00 min. KH-7 type satellite. Space craft engaged in investigation of spaceflight techniques and technology (US Cat A). .

• OPS 6785 - . Payload: EHH B4. Mass: 60 kg (132 lb). Nation: USA. Agency: NRO, USAF. Class: Surveillance. Type: Naval signals intelligence satellite. Spacecraft Bus: P 11. Spacecraft: SSF. Decay Date: 1970-10-27 . USAF Sat Cat: 2172 . COSPAR: 1966-039B. Apogee: 555 km (344 mi). Perigee: 519 km (322 mi). Inclination: 110.0000 deg. Period: 95.40 min. Radar monitoring..

• Launch of Gemini IX was postponed when Agena target vehicle failed to achieve orbit. - . Nation: USA. Flight: Gemini 9.

  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. Additional Details: here....

• Gemini 9 Agena Target - . Payload: TDA 5. Mass: 3,248 kg (7,160 lb). Nation: USA. Agency: NASA. Program: Gemini. Class: Manned. Type: Manned logistics spacecraft. Flight: Gemini 9. Spacecraft Bus: Agena. Spacecraft: Gemini Agena Target Vehicle. Decay Date: 1966-05-17 .

  The Gemini 9 mission was scrubbed when the Atlas booster launched from Cape Canaveral failed to place the Gemini Agena Target Vehicle (GATV) in its planned circular orbit. A malfunction of the number 2 booster engine of the Atlas caused both the Atlas and Agena to fall into the ocean. The Gemini 9-Atlas/Agena mission was later rescheduled to 1 June using the Augmented Target Docking Adapter (ATDA).

• Gemini Agena target vehicle 5005 was mated to the target docking adapter (TDA) in Hanger E at Cape Kennedy. - . Nation: USA. Flight: Gemini 10. 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..

• Gemini Agena target vehicle 5005 completed preliminary testing. - . Nation: USA. Flight: Gemini 10, Gemini 9.

  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. Additional Details: here....

• KH 7-29 - . Payload: KH-7 no. 29 / OPS 1577. Mass: 2,000 kg (4,400 lb). Nation: USA. Agency: NRO, USAF. Class: Surveillance. Type: Military surveillance satellite. Spacecraft Bus: WS-117. Spacecraft: KH-7. Decay Date: 1966-06-09 . USAF Sat Cat: 2192 . COSPAR: 1966-048A. Apogee: 288 km (178 mi). Perigee: 143 km (88 mi). Inclination: 87.0000 deg. Period: 88.90 min. KH-7 type satellite. Space craft engaged in investigation of spaceflight techniques and technology (US Cat A). .

• OPS 1856/Agena D - . Payload: [AAS 6] / OPS 1856. Mass: 60 kg (132 lb). Nation: USA. Agency: USAF. Class: Surveillance. Type: Naval signals intelligence satellite. Spacecraft Bus: P 11. Spacecraft: SSF. Decay Date: 1966-06-09 . USAF Sat Cat: 2194 . COSPAR: 1966-048B. Apogee: 230 km (140 mi). Perigee: 148 km (91 mi). Inclination: 86.9000 deg. Period: 88.20 min. Not identified as a subsatellite ferret by McDowell..

• Gemini Agena target vehicle 5006 completed modification and final assembly and was transferred to Vehicle Systems Test (VST) at Sunnyvale. - . Nation: USA. Flight: Gemini 11.

  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.

• Midas 10 - . Payload: Midas RTS 1 / Agena TV 1351 / Agena D 1351 / OPS 1. Mass: 2,000 kg (4,400 lb). Nation: USA. Agency: USAF. Class: Surveillance. Type: Early warning satellite. Spacecraft Bus: WS-117. Spacecraft: Midas. Decay Date: 1966-12-03 . USAF Sat Cat: 2200 . COSPAR: 1966-051A. Apogee: 3,678 km (2,285 mi). Perigee: 154 km (95 mi). Inclination: 90.0000 deg. Period: 125.20 min. The first Atlas SLV-3/Agena D (7200 Series, Vehicle #7201) standard booster was successfully launched from Vandenberg. Missile Defense Alarm System. Left in transfer orbit..

• ORS 2 - . Payload: ERS 16. Mass: 15 kg (33 lb). Nation: USA. Agency: USAF. Class: Earth. Type: Magnetosphere satellite. Spacecraft: ERS. Decay Date: 1967-03-12 . USAF Sat Cat: 2202 . COSPAR: 1966-051C. Apogee: 3,641 km (2,262 mi). Perigee: 178 km (110 mi). Inclination: 90.0000 deg. Period: 125.10 min. The first Atlas SLV-3/Agena D (7200 Series, Vehicle #7201) standard booster was successfully launched from Vandenberg. Metal-to-metal bonding experiments. Space craft engaged in investigation of spaceflight techniques and technology (US Cat A). .

• SECOR 6 - . Payload: EGRS 6. Mass: 17 kg (37 lb). Nation: USA. Agency: USA ACE. Class: Earth. Type: Geodetic satellite. Spacecraft: SECOR. Decay Date: 1967-07-06 . USAF Sat Cat: 2205 . COSPAR: 1966-051B. Apogee: 3,646 km (2,265 mi). Perigee: 168 km (104 mi). Inclination: 90.0000 deg. Period: 125.00 min. Space craft engaged in investigation of spaceflight techniques and technology (US Cat A). .

• Combined Interface Tests(CIT) of Gemini Agena target vehicle (GATV) 5005 began. - . Nation: USA. Flight: Gemini 10. 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..

• 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. - . Nation: USA. Flight: Gemini 10, Gemini 8.

  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.

• Final acceptance test of Gemini Agena target vehicle 5006 was completed at Sunnyvale. - . Nation: USA. Flight: Gemini 11.

  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.

• Gemini Agena target vehicle 5005 was transferred to complex 14 and mated to target launch vehicle 5305. - . Nation: USA. Flight: Gemini 10. Joint Flight Acceptance Composite Test was completed July 8. Complex 14 systems tests were completed July 12 with the Simultaneous Launch Demonstration..

• KH 7-30 - . Payload: KH-7 no. 30 / OPS 1850. Mass: 2,000 kg (4,400 lb). Nation: USA. Agency: NRO, USAF. Class: Surveillance. Type: Military surveillance satellite. Spacecraft Bus: WS-117. Spacecraft: KH-7. Decay Date: 1966-07-20 . USAF Sat Cat: 2322 . COSPAR: 1966-062A. Apogee: 261 km (162 mi). Perigee: 150 km (90 mi). Inclination: 95.5000 deg. Period: 88.70 min. KH-7 type satellite. Space craft engaged in investigation of spaceflight techniques and technology (US Cat A). .

• Gemini Agena target vehicle (GATV) 5006 was mated to target docking adapter (TDA) 6. - . Nation: USA. Flight: Gemini 10, Gemini 11, Gemini 8. 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..

• Gemini 10 Agena Target - . Payload: TDA 1A/Agena D 5005 GATV. Mass: 3,175 kg (6,999 lb). Nation: USA. Agency: NASA Houston. Program: Gemini. Class: Manned. Type: Manned logistics spacecraft. Flight: Gemini 10. Spacecraft Bus: Agena. Spacecraft: Gemini Agena Target Vehicle. Decay Date: 1966-12-29 . USAF Sat Cat: 2348 . COSPAR: 1966-065A. Apogee: 296 km (183 mi). Perigee: 290 km (180 mi). Inclination: 28.9000 deg. Period: 90.40 min.

  An Air Force Titan Gemini Launch Vehicle placed the Gemini 10 (GT-10) spacecraft into orbit for the three-day mission of Astronauts John Young and Michael Collins. Rendezvous and docking were accomplished with the Gemini Agena Target Vehicle (GATV) that had been launched from Cape Kennedy aboard an Atlas Booster just ahead of GT-10. Using the GATV-10 Primary Propulsion System (PPS), the docked vehicles achieved a manned-flight altitude record of 476 miles. Reentry was accomplished on 21 July and recovery was made 544 miles east of Cape Canaveral. Space craft engaged in investigation of spaceflight techniques and technology (US Cat A).

• Gemini Agena target vehicle 5001 was transferred to systems test complex. - . Nation: USA. Flight: Gemini 12. 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. .

• Gemini Agena target vehicle made three orbital maneuvers under ground control. - . Nation: USA. Flight: Gemini 10, Gemini 11.

  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. Additional Details: here....

• Lunar Orbiter 1 - . Payload: Lunar Orbiter A. Mass: 386 kg (850 lb). Nation: USA. Agency: NASA Langley. Class: Moon. Type: Lunar probe. Spacecraft: Lunar Orbiter. Decay Date: 1966-10-29 . USAF Sat Cat: 2394 . COSPAR: 1966-073A.

  Lunar Orbiter I was launched from Cape Kennedy Launch Complex 13 at 3:26 p.m. EDT August 10 to photograph possible Apollo landing sites from lunar orbit. The Atlas-Agena D launch vehicle injected the spacecraft into its planned 90-hour trajectory to the moon. A midcourse correction maneuver was made at 8 p.m. the next day; a planned second midcourse maneuver was not necessary. A faultless deboost maneuver on August 14 achieved the desired initial elliptic orbit around the moon, and one week later the spacecraft was commanded to make a transfer maneuver to place it in a final close-in elliptic orbit of the moon.

  During the spacecraft's stay in the final close-in orbit, the gravitational fields of the earth and the moon were expected to influence the orbital elements. The influence was verified by spacecraft tracking data, which showed that the perilune altitude varied with time. From an initial perilune altitude of 58 kilometers, the perilune decreased to 49 kilometers. At this time an orbit adjustment maneuver began an increase in the altitude, which was expected to reach a maximum after three months and then begin to decrease again. The spacecraft was expected to impact on the lunar surface about six months after the orbit adjustment.

  During the photo-acquisition phase of the flight, August 18 to 29, Lunar Orbiter I photographed the 9 selected primary potential Apollo landing sites, including the one in which Surveyor I landed; 7 other potential Apollo landing sites; the east limb of the moon; and 11 areas on the far side of the moon. Lunar Orbiter I also took photos of the earth, giving man the first view of the earth from the vicinity of the moon (this particular view has been widely publicized). A total of 207 frames (sets of medium- and high-resolution pictures) were taken, 38 while the spacecraft was in initial orbit, the remainder while it was in the final close-in orbit. Lunar Orbiter I achieved its mission objectives, and, with the exception of the high-resolution camera, the performance of the photo subsystem and other spacecraft subsystems was outstanding. At the completion of the photo readouts, the spacecraft had responded to about 5,000 discrete commands from the earth and had made about 700 maneuvers.

  Photographs obtained during the mission were assessed and screened by representatives of the Lunar Orbiter Project Office, U.S. Geological Survey, DOD mapping agencies, MSC, and Jet Propulsion Laboratory. The spacecraft was deliberately crashed into moon after the mission was completed.

• Gemini Agena target vehicle 5001 completed final acceptance testing. - . Nation: USA. Flight: Gemini 12. Analysis of test data was completed by August 24 and the vehicle was disconnected from the test complex..

• KH 7-31 - . Payload: KH-7 no. 31 / OPS 1832. Mass: 2,000 kg (4,400 lb). Nation: USA. Agency: NRO, USAF. Class: Surveillance. Type: Military surveillance satellite. Spacecraft Bus: WS-117. Spacecraft: KH-7. Decay Date: 1966-08-24 . USAF Sat Cat: 2396 . COSPAR: 1966-074A. Apogee: 330 km (200 mi). Perigee: 143 km (88 mi). Inclination: 93.2000 deg. Period: 89.20 min. KH-7 type satellite. Space craft engaged in investigation of spaceflight techniques and technology (US Cat A). .

• OPS 6810 - . Payload: SSF-B No. 5. Mass: 60 kg (132 lb). Nation: USA. Agency: NRO, USAF. Class: Surveillance. Type: Naval signals intelligence satellite. Spacecraft Bus: P 11. Spacecraft: SSF. Decay Date: 1970-03-05 . USAF Sat Cat: 2397 . COSPAR: 1966-074B. Apogee: 522 km (324 mi). Perigee: 511 km (317 mi). Inclination: 93.2000 deg. Period: 94.90 min. Radar monitoring..

• Midas 11 - . Payload: Midas RTS 2 / Agena TV 1352 / Agena D / OPS 0856. Mass: 2,000 kg (4,400 lb). Nation: USA. Agency: USAF. Class: Surveillance. Type: Early warning satellite. Spacecraft Bus: WS-117. Spacecraft: Midas. USAF Sat Cat: 2403 . COSPAR: 1966-077A. Apogee: 3,708 km (2,304 mi). Perigee: 3,658 km (2,272 mi). Inclination: 89.7000 deg. Period: 167.40 min. Missile Defense Alarm System..

• SECOR 7 - . Payload: EGRS 7. Mass: 17 kg (37 lb). Nation: USA. Agency: USA ACE. Class: Earth. Type: Geodetic satellite. Spacecraft: SECOR. USAF Sat Cat: 2411 . COSPAR: 1966-077B. Apogee: 3,700 km (2,200 mi). Perigee: 3,671 km (2,281 mi). Inclination: 89.7000 deg. Period: 167.50 min. Space craft engaged in investigation of spaceflight techniques and technology (US Cat A). .

• ORS 1 - . Payload: ERS 15. Mass: 5.00 kg (11.00 lb). Nation: USA. Agency: USAF. Class: Earth. Type: Magnetosphere satellite. Spacecraft: ERS. USAF Sat Cat: 2412 . COSPAR: 1966-077C. Apogee: 3,700 km (2,200 mi). Perigee: 3,680 km (2,280 mi). Inclination: 89.7000 deg. Period: 167.60 min. Cold welding experiments. Space craft engaged in investigation of spaceflight techniques and technology (US Cat A). .

• Gemini Agena target vehicle 5006 was mated to target launch vehicle 5306. - . Nation: USA. Flight: Gemini 11. Joint Flight Acceptance Composite Test was performed August 26, Simultaneous Launch Demonstration on August 31..

• Gemini Agena target vehicle 5001 was formally accepted by the Air Force after vehicle acceptance team inspection. - . Nation: USA. Flight: Gemini 12. It was shipped from Sunnyvale on September 3 and arrived at Eastern Test Range on September 4..

• Gemini Agena target vehicle 5001 was mated to target docking adapter (TDA) 7A at Cape Kennedy. - . Nation: USA. Flight: Gemini 11, Gemini 12. 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..

• Gemini 11 Agena Target - . Payload: TDA 6/Agena D 5006 GATV. Mass: 3,175 kg (6,999 lb). Nation: USA. Agency: NASA Houston. Program: Gemini. Class: Manned. Type: Manned logistics spacecraft. Flight: Gemini 11. Spacecraft Bus: Agena. Spacecraft: Gemini Agena Target Vehicle. Decay Date: 1966-12-30 . USAF Sat Cat: 2414 . COSPAR: 1966-080A. Apogee: 298 km (185 mi). Perigee: 298 km (185 mi). Inclination: 28.8000 deg. Period: 90.40 min. Docking target for Gemini 11..

• KH 7-32 - . Payload: KH-7 no. 32 / OPS 1686. Mass: 2,000 kg (4,400 lb). Nation: USA. Agency: NRO, USAF. Class: Surveillance. Type: Military surveillance satellite. Spacecraft Bus: WS-117. Spacecraft: KH-7. Decay Date: 1966-09-23 . USAF Sat Cat: 2419 . COSPAR: 1966-083A. Apogee: 328 km (203 mi). Perigee: 146 km (90 mi). Inclination: 93.9000 deg. Period: 89.20 min. KH-7 type satellite. Space craft engaged in investigation of spaceflight techniques and technology (US Cat A). .

• OPS 6874 - . Payload: EHH B5. Mass: 60 kg (132 lb). Nation: USA. Agency: NRO, USAF. Class: Surveillance. Type: Naval signals intelligence satellite. Spacecraft Bus: P 11. Spacecraft: SSF. Decay Date: 1968-05-09 . USAF Sat Cat: 2420 . COSPAR: 1966-083B. Apogee: 501 km (311 mi). Perigee: 461 km (286 mi). Inclination: 94.1000 deg. Period: 94.20 min. Radar monitoring..

• 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. - . Nation: USA. Flight: Gemini 12. 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..

• Midas 12 - . Payload: Midas RTS 3 / Agena TV 1353 / Agena D / OPS 1920. Mass: 2,000 kg (4,400 lb). Nation: USA. Agency: USAF. Class: Surveillance. Type: Early warning satellite. Spacecraft Bus: WS-117. Spacecraft: Midas. USAF Sat Cat: 2481 . COSPAR: 1966-089A. Apogee: 3,724 km (2,313 mi). Perigee: 3,657 km (2,272 mi). Inclination: 89.8000 deg. Period: 167.60 min. Missile Defense Alarm System..

• SECOR 8 - . Payload: EGRS 8. Mass: 17 kg (37 lb). Nation: USA. Agency: USA ACE. Class: Earth. Type: Geodetic satellite. Spacecraft: SECOR. USAF Sat Cat: 2520 . COSPAR: 1966-089B. Apogee: 3,707 km (2,303 mi). Perigee: 3,674 km (2,282 mi). Inclination: 90.0000 deg. Period: 167.60 min. Space craft engaged in investigation of spaceflight techniques and technology (US Cat A). .

• KH 7-33 - . Payload: KH-7 no. 33 / OPS 2055. Mass: 2,000 kg (4,400 lb). Nation: USA. Agency: NRO, USAF. Class: Surveillance. Type: Military surveillance satellite. Spacecraft Bus: WS-117. Spacecraft: KH-7. Decay Date: 1966-10-20 . USAF Sat Cat: 2489 . COSPAR: 1966-090A. Apogee: 287 km (178 mi). Perigee: 155 km (96 mi). Inclination: 91.0000 deg. Period: 89.00 min. KH-7 type satellite. Space craft engaged in investigation of spaceflight techniques and technology (US Cat A). .

• OPS 5345/Agena D - . Payload: SGLS 1 / OPS 5345. Mass: 60 kg (132 lb). Nation: USA. Agency: USAF. Class: Surveillance. Type: Naval signals intelligence satellite. Spacecraft Bus: P 11. Spacecraft: SSF. Decay Date: 1966-10-21 . USAF Sat Cat: 2490 . COSPAR: 1966-090B. Apogee: 258 km (160 mi). Perigee: 181 km (112 mi). Inclination: 90.9000 deg. Period: 89.00 min. Not identified as a subsatellite ferret by McDowell..

• Gemini Agena target vehicle 5001 was mated to target launch vehicle 5307 on complex 14. - . Nation: USA. Flight: Gemini 12. Joint Flight Acceptance Composite Test was completed October 28, Simultaneous Launch Demonstration on November 1..

• KH 7-34 - . Payload: KH-7 no. 34 / OPS 2070. Mass: 2,000 kg (4,400 lb). Nation: USA. Agency: NRO, USAF. Class: Surveillance. Type: Military surveillance satellite. Spacecraft Bus: WS-117. Spacecraft: KH-7. Decay Date: 1966-11-10 . USAF Sat Cat: 2523 . COSPAR: 1966-098A. Apogee: 305 km (189 mi). Perigee: 159 km (98 mi). Inclination: 91.0000 deg. Period: 89.20 min. KH-7 type satellite. Space craft engaged in investigation of spaceflight techniques and technology (US Cat A). .

• OPS 5424/Agena D - . Payload: Agena Pickaback / OPS 5424. Mass: 60 kg (132 lb). Nation: USA. Agency: USAF. Class: Surveillance. Type: Naval signals intelligence satellite. Spacecraft Bus: P 11. Spacecraft: SSF. Decay Date: 1966-11-16 . USAF Sat Cat: 2525 . COSPAR: 1966-098B. Apogee: 324 km (201 mi). Perigee: 208 km (129 mi). Inclination: 91.0000 deg. Period: 89.90 min. Not identified as a subsatellite ferret by McDowell..

• Lunar Orbiter 2 - . Payload: Lunar Orbiter B. Mass: 390 kg (850 lb). Nation: USA. Agency: NASA Langley. Class: Moon. Type: Lunar probe. Spacecraft: Lunar Orbiter. Decay Date: 1967-10-11 . USAF Sat Cat: 2534 . COSPAR: 1966-100A.

  Lunar Orbiter II was launched at 6:21 p.m. EST from Launch Complex 13 at Cape Kennedy, to photograph possible landing sites on the moon for the Apollo program. The Atlas-Agena D booster placed the spacecraft in an earth-parking orbit and, after a 14-minute coast, injected it into its 94-hour trajectory toward the moon. A midcourse correction maneuver on November 8 increased the velocity from 3,051 to 3,133 kilometers per hour. At that time the spacecraft was 265,485 kilometers from the earth.

  The spacecraft executed a deboost maneuver at 3:26 p.m., November 10, while 352,370 kilometers from the earth and 1,260 kilometers from the moon and traveling at a speed of 5,028 kilometers per hour. The maneuver permitted the lunar gravitational field to pull the spacecraft into the planned initial orbit around the moon. On November 15, a micrometeoroid hit was detected by one of the 20 thin-walled pressurized sensors.

  The spacecraft was transferred into its final close-in orbit around the moon at 5:58 p.m. November 15 and the photo-acquisition phase of Lunar Orbiter II's mission began November 18. Thirteen selected primary potential landing sites and a number of secondary sites were to be photographed. By the morning of November 25, the spacecraft had taken 208 of the 211 photographs planned and pictures of all 13 selected potential landing sites. It also made 205 attitude change maneuvers and responded to 2,421 commands.

  The status report of the Lunar Orbiter II mission as of November 28 indicated that the first phase of the photographic mission was completed when the final photo was taken on the afternoon of November 25. On November 26, the developing web was cut with a hot wire in response to a command from the earth. Failure to achieve the cut would have prevented the final readout of all 211 photos. Readout began immediately after the cut was made. One day early, December 6, the readout terminated when a transmitter failed, and three medium-resolution and two high-resolution photos of primary site 1 were lost. Full low-resolution coverage of the site had been provided, however, and other data continued to be transmitted. Three meteoroid hits had been detected.

• Gemini 12 Agena Target - . Payload: TDA 7A/Agena D 5001R GATV. Mass: 3,175 kg (6,999 lb). Nation: USA. Agency: NASA Houston. Program: Gemini. Class: Manned. Type: Manned logistics spacecraft. Flight: Gemini 12. Spacecraft Bus: Agena. Spacecraft: Gemini Agena Target Vehicle. Decay Date: 1966-12-23 . USAF Sat Cat: 2565 . COSPAR: 1966-103A. Apogee: 310 km (190 mi). Perigee: 243 km (150 mi). Inclination: 28.8000 deg. Period: 89.90 min. Docking target for Gemini 12..

• KH 7-35 - . Payload: KH-7 no. 35 / OPS 1890. Mass: 2,000 kg (4,400 lb). Nation: USA. Agency: NRO, USAF. Class: Surveillance. Type: Military surveillance satellite. Spacecraft Bus: WS-117. Spacecraft: KH-7. Decay Date: 1966-12-14 . USAF Sat Cat: 2606 . COSPAR: 1966-109A. Apogee: 341 km (211 mi). Perigee: 137 km (85 mi). Inclination: 104.6000 deg. Period: 89.20 min. KH-7 type satellite. Space craft engaged in investigation of spaceflight techniques and technology (US Cat A). .

• ATS 1 - . Payload: ATS B. Mass: 352 kg (776 lb). Nation: USA. Agency: NASA Greenbelt. Program: ATS. Class: Technology. Type: Communications technology satellite. Spacecraft Bus: HS 306. Spacecraft: ATS-1. Completed Operations Date: 1985-04-01 . USAF Sat Cat: 2608 . COSPAR: 1966-110A. Apogee: 35,783 km (22,234 mi). Perigee: 35,728 km (22,200 mi). Inclination: 12.5000 deg. Period: 1,434.50 min.

  Applications Technology Satellite; communications and meteorological experiments. Positioned in geosynchronous orbit over the Americas at 151 deg W in 1966-1968?; over the Americas at 149 deg W in 1968-1982; over the Pacific Ocean 170 deg E in 1982-1985 As of 3 September 2001 located at 167.30 deg E drifting at 0.065 deg E per day. As of 2007 Mar 9 located at 59.28W drifting at 0.332E degrees per day.

• Agena D - . Mass: 2,000 kg (4,400 lb). Nation: USA. Agency: USAF. Spacecraft Bus: WS-117. Spacecraft: KH-7. Decay Date: 1967-02-15 . USAF Sat Cat: 2665 . COSPAR: 1967-007B. Apogee: 285 km (177 mi). Perigee: 126 km (78 mi). Inclination: 102.7000 deg. Period: 88.61 min.

• KH 7-36 - . Payload: KH-7 no. 36 / OPS 4399. Mass: 2,000 kg (4,400 lb). Nation: USA. Agency: NRO, USAF. Class: Surveillance. Type: Military surveillance satellite. Spacecraft Bus: WS-117. Spacecraft: KH-7. Decay Date: 1967-02-12 . USAF Sat Cat: 2664 . COSPAR: 1967-007A. Apogee: 357 km (221 mi). Perigee: 136 km (84 mi). Inclination: 103.0000 deg. Period: 89.50 min. KH-7 type satellite. Space craft engaged in investigation of spaceflight techniques and technology (US Cat A). .

• Lunar Orbiter 3 - . Payload: Lunar Orbiter C. Mass: 385 kg (848 lb). Nation: USA. Agency: NASA Langley. Class: Moon. Type: Lunar probe. Spacecraft: Lunar Orbiter. Decay Date: 1967-10-09 . USAF Sat Cat: 2666 . COSPAR: 1967-008A. Crashed into Moon; returned 182 photos of lunar surface. Selenocentric orbit. Spacecraft engaged in research and exploration of the upper atmosphere or outer space (US Cat B)..

• ATS 2 - . Payload: ATS A. Mass: 370 kg (810 lb). Nation: USA. Agency: NASA Greenbelt. Program: ATS. Class: Technology. Type: Communications technology satellite. Spacecraft Bus: ATS. Spacecraft: ATS-2. Decay Date: 1969-09-02 . USAF Sat Cat: 2743 . COSPAR: 1967-031A. Apogee: 11,119 km (6,909 mi). Perigee: 177 km (109 mi). Inclination: 28.4000 deg. Period: 218.80 min. Launch vehicle failure left in useless orbit; communications tests..

• Research Payload Module 481 - . Payload: Module 481. Nation: USA. Agency: NASA Cleveland. Program: ATS. Spacecraft Bus: Shuttle Attached Payloads. Spacecraft: Research Payload Module 481. Decay Date: 1968-06-29 . USAF Sat Cat: 2744 . COSPAR: 1967-031B. Apogee: 10,732 km (6,668 mi). Perigee: 160 km (90 mi). Inclination: 28.4000 deg. Period: 213.28 min.

• Lunar Orbiter 4 - . Payload: Lunar Orbiter D. Mass: 390 kg (850 lb). Nation: USA. Agency: NASA Langley. Class: Moon. Type: Lunar probe. Spacecraft: Lunar Orbiter. Decay Date: 1967-10-06 . USAF Sat Cat: 2772 . COSPAR: 1967-041A. Returned 163 photos of lunar surface before impacting Moon. Selenocentric orbit. Spacecraft engaged in research and exploration of the upper atmosphere or outer space (US Cat B)..

• KH 7-37 - . Payload: KH-7 no. 37 / OPS 4321. Mass: 2,000 kg (4,400 lb). Nation: USA. Agency: NRO, USAF. Class: Surveillance. Type: Military surveillance satellite. Spacecraft Bus: WS-117. Spacecraft: KH-7. Decay Date: 1967-05-30 . USAF Sat Cat: 2813 . COSPAR: 1967-050A. Apogee: 293 km (182 mi). Perigee: 135 km (83 mi). Inclination: 91.5000 deg. Period: 88.80 min. KH-7 type satellite. Space craft engaged in investigation of spaceflight techniques and technology (US Cat A). .

• OPS 5557/Agena D - . Payload: LOGACS / OPS 5557. Mass: 700 kg (1,540 lb). Nation: USA. Agency: USAF. Class: Surveillance. Type: Naval signals intelligence satellite. Spacecraft Bus: P 11. Spacecraft: SSF. Decay Date: 1967-05-27 . USAF Sat Cat: 2816 . COSPAR: 1967-050B. Apogee: 240 km (140 mi). Perigee: 148 km (91 mi). Inclination: 91.5000 deg. Period: 88.40 min. Not identified as a subsatellite ferret by McDowell..

• KH 7-38 - . Payload: KH-7 no. 38 / OPS 4360. Mass: 2,000 kg (4,400 lb). Nation: USA. Agency: NRO, USAF. Class: Surveillance. Type: Military surveillance satellite. Spacecraft Bus: WS-117. Spacecraft: KH-7. Decay Date: 1967-06-12 . USAF Sat Cat: 2831 . COSPAR: 1967-055A. Apogee: 456 km (283 mi). Perigee: 149 km (92 mi). Inclination: 104.9000 deg. Period: 90.60 min. The final Air Force Atlas/Agena D (SLV-3 #7128/SS-01B #4837) was successfully launched from Vandenberg AFB. KH-7 type satellite. Space craft engaged in investigation of spaceflight techniques and technology (US Cat A). .

• Mariner 5 - . Payload: Mariner 67-2. Mass: 244 kg (537 lb). Nation: USA. Agency: JPL, NASA. Program: Mariner. Class: Venus. Type: Venus probe. Spacecraft Bus: Mariner. Spacecraft: Mariner 5. USAF Sat Cat: 2845 . COSPAR: 1967-060A.

  Mariner 5 flew by Venus on October 19, 1967 at an altitude of 3,990 kilometres. With more sensitive instruments than its predecessor Mariner 2, Mariner 5 was able to shed new light on the hot, cloud-covered planet and on conditions in interplanetary space. Operations of Mariner 5 ended in November 1967. The spacecraft instruments measured both interplanetary and Venusian magnetic fields, charged particles, and plasmas, as well as the radio refractivity and UV emissions of the Venusian atmosphere.

• Lunar Orbiter 5 - . Payload: Lunar Orbiter E. Mass: 389 kg (857 lb). Nation: USA. Agency: NASA Langley. Class: Moon. Type: Lunar probe. Spacecraft: Lunar Orbiter. Decay Date: 1968-01-31 . USAF Sat Cat: 2907 . COSPAR: 1967-075A.

  Lunar Orbiter V was launched from the Eastern Test Range at 6:33 p.m. EDT August 1. The Deep Space Net Tracking Station at Woomera, Australia, acquired the spacecraft about 50 minutes after liftoff. Signals indicated that all systems were performing normally and that temperatures were within acceptable limits. At 12:48 p.m. EDT August 5, Lunar Orbiter V executed a deboost maneuver that placed it in orbit around the moon. The spacecraft took its first photograph of the moon at 7:22 a.m. EDT August 6. Before it landed on the lunar surface on January 31, 1968, Lunar Orbiter V had photographed 23 previously unphotographed areas of the moon's far side, the first photo of the full earth, 36 sites of scientific interest, and 5 Apollo sites for a total of 425 photos.

• ATS 3 - . Payload: ATS C. Mass: 365 kg (804 lb). Nation: USA. Agency: NASA Greenbelt. Program: ATS. Class: Technology. Type: Communications technology satellite. Spacecraft Bus: ATS. Spacecraft: ATS-3. USAF Sat Cat: 3029 . COSPAR: 1967-111A. Apogee: 35,837 km (22,268 mi). Perigee: 35,736 km (22,205 mi). Inclination: 14.5000 deg. Period: 1,436.10 min.

  Communications tests. Positioned in geosynchronous orbit over the Atlantic Ocean at 45 deg W in-100 deg W in 1968-1970; over the Americas at 69 deg W in 1971-1976; over the Americas at 105 deg W in 1977-1998 As of 4 September 2001 located at 105.90 deg W drifting at 0.003 deg W per day. As of 2007 Mar 10 located at 105.23W drifting at 0.006W degrees per day.

• HQ SAMSO formally transferred management responsibility for Standard Launch Vehicle-3 (SLV-3) vehicle to National Aeronautics and Space Administration (NASA) - .