1965 July 1 - -
Apollo Site Selection Board Nation: USA. Program: Apollo. Within its Office of Manned Space Flight, NASA organized an Apollo Site Selection Board. As an advisory body to the Associate Administrator for Manned Space Flight, George E. Mueller, the group would recommend landing sites for Apollo. References: 16.
1965 July 1 - Launch Site: Kwajalein. Launch Complex: -. Launch Pad: -. Launch Vehicle: Nike Zeus. Model: Nike Zeus. LV Configuration: Nike Zeus-3. -
Interceptor mission Nation: USA. Agency: USA. Apogee: 200 km (120 mi). References: 2.
1965 July 1 - Launch Site: Barbados. Launch Complex: HARP. Launch Pad: -. Launch Vehicle: Martlet. Model: Martlet 2. -
Ionosphere mission Nation: Canada. Agency: HARP. Apogee: 150 km (90 mi). References: 2.
1965 July - Launch Vehicle: Spiral 50-50. -
Spiral cosmonaut team formed Nation: USSR. Spacecraft: Spiral OS. In 1965 the advanced project of the Mikoyan Spiral aerospace system was approved. The ambitious work plan indicted operation of a regular earth-orbit-earth reusable transportation system by the mid-1970's. With Gherman Titov as its head, a Spiral cosmonaut training group was formed (Titov, Dobrovolskiy, Filipchenko, Kuklin, Matinchenko) to train to fly the spaceplane.
1965 July 1 - 01:45 GMT - Launch Site: Woomera. Launch Complex: LA2. Launch Pad: LA2 SL. Launch Vehicle: Skylark. Model: Skylark 7C. LV Configuration: Skylark-7C SL106. -
Solar X-rays / Ionosphere Ionosphere / solar x-rays mission Nation: Australia. Agency: WRE/RAE. Apogee: 130 km (80 mi). References: 2.
1965 July 1 - 09:54 GMT - Launch Site: Vandenberg. Launch Complex: 576B1. Launch Pad: -. Launch Vehicle: Atlas. Model: Atlas D. LV Configuration: Atlas D 59D. -
NTMP KX-32 re-entry vehicle test flight Nation: USA. Agency: USAF AFSC. Apogee: 1,800 km (1,100 mi). References: 2.
1965 July 2 - Launch Site: Vandenberg. Launch Complex: LF03. Launch Pad: -. Launch Vehicle: Minuteman 1. Model: Minuteman 1B. LV Configuration: Minuteman 1B 799. -
Operational missile test Nation: USA. Agency: SAC 1STRAD. Apogee: 1,300 km (800 mi). References: 2.
1965 July 2 - 04:07 GMT - Launch Site: Cape Canaveral. Launch Complex: LC17B. Launch Pad: -. Launch Vehicle: Delta. Model: Thor Delta C. LV Configuration: Thor Delta C 415/D32. -
Tiros 10 Nation: USA. Program: Tiros. Payload: Tiros OT1. Mass: 127 kg (279 lb). Class: Earth. Type: Weather. Spacecraft: Tiros. Agency: ESSA. Perigee: 722 km (448 mi). Apogee: 807 km (501 mi). Inclination: 98.80 deg. Period: 100.10 min. COSPAR: 1965-051A. USAF Sat Cat: 1430. Spacecraft engaged in practical applications and uses of space technology such as weather or communication (US Cat C). References: 2, 6.
1965 July 2 - 06:30 GMT - Launch Site: Kapustin Yar. Launch Complex: LC86/1. Launch Pad: -. Launch Vehicle: Kosmos 2. Model: Kosmos 63S1. -
Cosmos 70 Nation: USSR. Program: DS. Payload: DS-A1 s/n 7. Mass: 250 kg (550 lb). Class: Technology. Type: Navigation. Spacecraft: DS-A1. Agency: MO SSSR. Perigee: 223 km (138 mi). Apogee: 1,176 km (730 mi). Inclination: 48.80 deg. Period: 98.80 min. COSPAR: 1965-052A. USAF Sat Cat: 1431. Completed Operations Date: 1965-07-12. Decay Date: 1966-12-18. Carried military experiments to test communications and navigation equipment needed for command and control of Soviet nuclear forces (later used on the Uragan navigation satellites). Also conducted operational monitoring of cosmic rays, radiation from nuclear tests, and natural and artifically-produced radiation belts.
References: 2, 6, 99.
1965 July 5 - Launch Site: Hammaguira. Launch Complex: Brigitte. Launch Pad: -. Launch Vehicle: Diamant. Model: Saphir. LV Configuration: Saphir VE231 P1. -
Re-entry Vehicle test Nation: France. Agency: ONERA. Apogee: 1,000 km (600 mi). References: 2.
1965 July 6 - -
Soyuz hot mock-up Nation: USSR. Program: Soyuz. Spacecraft: Soyuz 7K-LOK. Chertok argues for the necessity of adding one Soyuz to production and using it as an iron bird - a hot mock-up on which avionics and electrical systems can be integrated and tested. Gherman Semenov and Turkov convince Korolev that this cannot be done within the existing schedules.
References: 367.
1965 July 6 - Launch Site: Vandenberg. Launch Complex: LF07. Launch Pad: -. Launch Vehicle: Minuteman 1. Model: Minuteman 1B. LV Configuration: Minuteman 1B 1069. -
Operational missile test Nation: USA. Agency: SAC 1STRAD. Apogee: 1,300 km (800 mi). References: 2.
1965 July 7 - Launch Vehicle: Titan. Model: Titan 2. -
Gemini launch vehicle (GLV) 5 and spacecraft No. 5 were mechanically mated at complex 19. Nation: USA. Flight: Gemini 5. The Electrical Interface Integrated Validation and Joint Guidance and Control Test began immediately and was completed July 9. The spacecraft/GLV Joint Combined Systems Test followed on July 12. The Flight Configuration Mode Test completed systems testing on July 16.
1965 July 7 - 07:25 GMT - Launch Site: Fort Churchill. Launch Complex: -. Launch Pad: -. Launch Vehicle: Aerobee. Model: Aerobee 150. LV Configuration: Aerobee 150 AE3.117/VFT65-S-1. -
Noctilucent clouds Aeronomy mission Nation: USA. Agency: USAF. Apogee: 166 km (103 mi). References: 2.
1965 July 7 - 08:37 GMT - Launch Site: Woomera. Launch Complex: LA2. Launch Pad: -. Launch Vehicle: HAD. LV Configuration: HAD 174. -
Aeronomy mission Nation: Australia. Agency: WRE. Apogee: 105 km (65 mi). References: 2.
1965 July 8 - Launch Site: Kwajalein. Launch Complex: -. Launch Pad: -. Launch Vehicle: Nike Zeus. Model: Nike Zeus. LV Configuration: Nike Zeus-3. -
DM-15S Qual-2 Nation: USA. Agency: USA. Apogee: 200 km (120 mi). References: 2.
1965 July 8 - 17:16 GMT - Launch Site: Delamar Dry Lake DZ. Launch Complex: -. Launch Pad: 37.3 N x 114.9 W. Launch Vehicle: X-15. LV Configuration: X-15 2-40-72. -
X-15A-2 ST,Landing,Alt test Nation: USA. Agency: NASA/USAF. Apogee: 64 km (39 mi). Maximum Speed - 5887 kph. Maximum Altitude - 64800 m. Star tracker mission to photograph Gamma Cassiopeia. References: 2.
1965 July 9 - Launch Site: Baikonur. Launch Complex: PU33. Launch Pad: -. Launch Vehicle: Tsiklon. Model: R-36 8K67. -
State trials missile test Nation: USSR. Agency: RVSN. Apogee: 1,000 km (600 mi). References: 2.
1965 July 10 - Launch Site: Baikonur. Launch Complex: -. Launch Pad: -. Launch Vehicle: UR-100. FAILURE: Failure. -
State trials missile test Nation: USSR. Agency: RVSN. Apogee: 0 km ( mi). References: 2.
1965 July 11 - -
Apollo RCS oxidizer tank failed during test Nation: USA. Program: Apollo. Spacecraft: Apollo CSM. An RCS oxidizer tank failed during a test to demonstrate propellant compatibility with titanium tanks. This was the first of seven tanks to fail from a group of ten tanks put into test to investigate a failure that occurred during February 1965. These results caused an intensive investigation to be undertaken.
References: 16.
1965 July 12 - -
Extravehicular activity deleted from Gemini missions 5, 6, and 7. Nation: USA. Flight: Gemini 5, Gemini 6, Gemini 7. NASA Headquarters Gemini Program Office informed Manned Spacecraft Center that it had decided to delete extravehicular activity from Gemini missions 5, 6, and 7.
1965 July 12 - 19:00 GMT - Launch Site: Vandenberg. Launch Complex: SLC4E. Launch Pad: -. Launch Vehicle: Atlas. Model: SLV-3 Agena D. LV Configuration: SLV-3 Agena D 7112. FAILURE: Failure. -
KH-7-20 Nation: USA. Payload: KH-7 no. 20. Mass: 2,000 kg (4,400 lb). Class: Surveillance. Type: Military. Spacecraft: KH-7. Agency: U.S. Air Force. COSPAR: F650712A. Decay Date: 1965-07-12. KH-7 type satellite. References: 126, 278.
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SRV Nation: USA. Spacecraft: KH-7. Agency: USAF AFSC. COSPAR: F650712B. References: 279.
1965 July 13 - Launch Site: Baikonur. Launch Complex: LC31. Launch Pad: -. Launch Vehicle: Soyuz. Model: Vostok 8A92. LV Configuration: Vostok 8A92 R15002-05. FAILURE: Second stage guidance failure. -
Zenit-2 11F61 s/n 28 Nation: USSR. Payload: Zenit-2 11F61 s/n 28. Mass: 4,720 kg (10,400 lb). Class: Surveillance. Type: Military. Spacecraft: Zenit-2. Agency: RVSN. COSPAR: F650713A. Decay Date: 1965-07-13. Area survey photo reconnaissance satellite. References: 93.
1965 July 14 -
1965 July 14 - 11:08 GMT - Launch Site: Woomera. Launch Complex: LA2. Launch Pad: LA2 SL. Launch Vehicle: Skylark. Model: Skylark 7C. LV Configuration: Skylark-7C SL48. -
Stellar ultraviolet / Attitude Ultraviolet astronomy mission Nation: Australia. Agency: WRE/RAE. Apogee: 182 km (113 mi). References: 2.
1965 July 15 - -
Redesign of the side hatch in the Block II Apollo CM Nation: USA. Program: Apollo. Spacecraft: Apollo CSM. North American began redesigning the side hatch mechanism in the CM to satisfy the requirement for extravehicular transfer from Block II spacecraft. Two basic modifications to the Block I mechanism were required: (1) enlarging it to overcome thermal warpage; and (2) adding some hinge retention device to secure the hatch once it was opened.
References: 16.
1965 July 15 - 20:50 GMT - Launch Site: White Sands. Launch Complex: LC35. Launch Pad: -. Launch Vehicle: Aerobee. Model: Aerobee 150. LV Configuration: Aerobee 150 NASA 04.128UA. -
Thermosphere comparison Aeronomy mission Nation: USA. Agency: NASA. Apogee: 196 km (121 mi). References: 2.
1965 July 16 - -
Passive water landing for Apollo Nation: USA. Program: Apollo. Spacecraft: Apollo CSM. North American recommended to MSC that, for the time being, the present method for landing the CM (i.e., a passive water landing) be maintained. However, on the basis of a recent feasibility study, the contractor urged that a rocket landing system be developed for possible use later on. North American said that such a system would improve mission reliability through the increase in impact capability on both land and water.
References: 16.
1965 July 16 - Launch Site: Green River. Launch Complex: Pad 1. Launch Pad: -. Launch Vehicle: Athena RTV. LV Configuration: Athena B003. -
USN B003 re-entry vehicle test flight Nation: USA. Agency: USAF. Apogee: 200 km (120 mi). References: 2.
1965 July 16-August 15 - -
Apollo LEM as backup for the service propulsion system Nation: USA. Program: Apollo. Spacecraft: Apollo LM. In order to use the LEM as a backup for the service propulsion system (SPS) to abort the mission during the 15-hour period following translunar injection, Grumman informed North American that some redesign of the spacecraft's helium system would likely be required. This information prompted North American designers to undertake their own analysis of the situation. On the basis of their own findings, this latter group disagreed with the LEM manufacturer.
Additional Details: Apollo LEM as backup for the service propulsion system. References: 16.
1965 July 16 - 03:31 GMT - Launch Site: Baikonur. Launch Complex: LC41/15. Launch Pad: -. Launch Vehicle: Kosmos 3. Model: Kosmos 65S3. LV Configuration: Kosmos 65S3 05L. -
Cosmos 71 Nation: USSR. Program: Strela. Mass: 50 kg (110 lb). Class: Communications. Type: Military Store-dump. Spacecraft: Strela-1. Agency: MO SSSR. Perigee: 522 km (324 mi). Apogee: 542 km (336 mi). Inclination: 56.00 deg. Period: 95.20 min. COSPAR: 1965-053A. USAF Sat Cat: 1441. Decay Date: 1970-08-11. References: 2, 6.
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Cosmos 72 Nation: USSR. Program: Strela. Mass: 50 kg (110 lb). Class: Communications. Type: Military Store-dump. Spacecraft: Strela-1. Agency: MO SSSR. Perigee: 538 km (334 mi). Apogee: 588 km (365 mi). Inclination: 56.10 deg. Period: 95.90 min. COSPAR: 1965-053B. USAF Sat Cat: 1442. Decay Date: 1979-08-24. References: 2, 6.
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Cosmos 73 Nation: USSR. Program: Strela. Mass: 50 kg (110 lb). Class: Communications. Type: Military Store-dump. Spacecraft: Strela-1. Agency: MO SSSR. Perigee: 538 km (334 mi). Apogee: 556 km (345 mi). Inclination: 56.10 deg. Period: 95.50 min. COSPAR: 1965-053C. USAF Sat Cat: 1443. Decay Date: 1974-03-20. References: 2, 6.
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Cosmos 74 Nation: USSR. Program: Strela. Mass: 50 kg (110 lb). Class: Communications. Type: Military Store-dump. Spacecraft: Strela-1. Agency: MO SSSR. Perigee: 539 km (334 mi). Apogee: 616 km (382 mi). Inclination: 56.00 deg. Period: 96.20 min. COSPAR: 1965-053D. USAF Sat Cat: 1444. Decay Date: 1979-12-13. References: 2, 6.
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Cosmos 75 Nation: USSR. Program: Strela. Mass: 50 kg (110 lb). Class: Communications. Type: Military Store-dump. Spacecraft: Strela-1. Agency: MO SSSR. Perigee: 540 km (330 mi). Apogee: 644 km (400 mi). Inclination: 56.00 deg. Period: 96.50 min. COSPAR: 1965-053E. USAF Sat Cat: 1445. Decay Date: 1979-09-28. References: 2, 6.
1965 July 16 - 10:50 GMT - Launch Site: Kagoshima. Launch Complex: -. Launch Pad: -. Launch Vehicle: Kappa. Model: Kappa 8. LV Configuration: Kappa 8 K-8-12. -
Aeronomy / ionosphere mission Nation: Japan. Agency: ISAS. Apogee: 160 km (90 mi). References: 2.
1965 July 16 - 11:16 GMT - Launch Site: Baikonur. Launch Complex: LC81/23. Launch Pad: -. Launch Vehicle: Proton. Model: UR-500. LV Configuration: UR-500 107207-01 (207). -
Proton 1 Nation: USSR. Program: Proton. Payload: N-4 s/n 1. Mass: 8,300 kg (18,200 lb). Class: Astronomy. Spacecraft: N-4 . Agency: MOM. Perigee: 181 km (112 mi). Apogee: 578 km (359 mi). Inclination: 63.40 deg. Period: 92.20 min. COSPAR: 1965-054A. USAF Sat Cat: 1466. Decay Date: 1965-10-11. The first launch of the Proton launch vehicle was not without problems. A leak in the oxidiser pipeline resulted in nitrogen tetroxide spilling on electrical wires. The question was: proceed with the launch or abort? Chelomei decided to go ahead, and on 16 July 1965 the first UR-500 successfully launched the Proton 1 satellite. In the first hours after launch specialists from OKB-52 could only receive signals in the first hours that indicated the satellite was ‘alive’. However it later functioned normally and provided physics data on ultra-high-energy cosmic particles for 45 days.At the first launch the rocket was called ‘Gerkules’ (other sources say ‘Atlantis’), as indicated by the large symbol on the second stage skin. This name was however was not taken up.
References: 2, 6, 67, 273, 274.
1965 July 17 - Launch Site: Baikonur. Launch Complex: LC131. Launch Pad: -. Launch Vehicle: UR-100. LV Configuration: UR-100 229420-01. FAILURE: Failure. -
State trials missile test Nation: USSR. Agency: RVSN. Apogee: 0 km ( mi). References: 2.
1965 July 17 - 05:55 GMT - Launch Site: Vandenberg. Launch Complex: SLC2W. Launch Pad: -. Launch Vehicle: Delta. Model: Thor SLV-2A Agena D. LV Configuration: Thor SLV-2A Agena D 422 / Agena D SS-01B 2702. -
OPS 8411 Nation: USA. Payload: Ferret 8 / Agena D 2702. Mass: 1,500 kg (3,300 lb). Class: Sigint. Spacecraft: Ferret. Agency: NRO/USAF. Perigee: 471 km (292 mi). Apogee: 512 km (318 mi). Inclination: 70.20 deg. Period: 94.50 min. COSPAR: 1965-055A. USAF Sat Cat: 1447. Decay Date: 1968-12-18. References: 2, 6.
1965 July 18 - 14:38 GMT - Launch Site: Baikonur. Launch Complex: LC1. Launch Pad: -. Launch Vehicle: Soyuz. Model: Molniya 8K78. -
Zond 3 Nation: USSR. Program: Mars. Payload: 3MV-4A s/n 3. Mass: 959 kg (2,114 lb). Class: Planetary. Type: Mars. Spacecraft: Mars 3MV-4A. Agency: MOM. COSPAR: 1965-056A. USAF Sat Cat: 1454. Zond 3 was towards the moon and interplanetary space. The spacecraft was equipped with a TV system that provided automatic inflight film processing. On July 20, during lunar flyby, 25 pictures of very good quality were taken of the lunar farside from distances of 11,570 to 9960 km. The photos covered 19,000,000 km square of the lunar surface. Photo transmissions by facsimile were returned to earth from a distance of 2,200,000 km on July 29 and were retransmitted later from a distance of 31,500,000 km, thus proving the ability of the communications system. After the lunar flyby, Zond 3 continued space exploration in a heliocentric orbit. Those pictures showed clearly the heavily cratered nature of the surface. This mission dramatized the advances in space photography that the U.S.S.R. had made since its first far-side effort six years earlier.
References: 2, 6, 16, 64, 296.
1965 July 19 - -
Apollo Block II CSM fuel cells from Pratt and Whitney Nation: USA. Program: Apollo. Spacecraft: Apollo CSM. NASA Headquarters authorized North American to subcontract the Block II CSM fuel cells to Pratt and Whitney. Estimates placed the cost at $30 million. References: 16.
1965 July 19 - -
Eight KC-135 aircraft and three ships for communications during Apollo flights Nation: USA. Program: Apollo. NASA was acquiring eight KC-135 aircraft and three ships to help maintain communications during Apollo moon flights. In addition, two ships of the existing DOD instrumentation fleet were being remodeled for support of the Apollo lunar mission's reentry phase. The KC-135 jet transports would be used during reentry to combat the effects of the plasma sheath blackout which had drowned out communications on previous manned launchings. In addition, three primary ground stations were being prepared at Goldstone, Calif.; Canberra, Australia; and Madrid, Spain.
References: 16.
1965 July 19 - -
Total Apollo LEM weight 14,515 kg Nation: USA. Program: Apollo. Spacecraft: Apollo LM. MSC directed Grumman to implement changes in weights of the LEM:| Total LEM | 14,515 kg (32,000 lbs) | | Ascent stage inert | 2,193 kg (4,835 lbs) | | Descent stage inert | 2,166 kg (4,775 lbs) | Memorandum, James L. Neal, MSC, to GAEC, Attn: John C. Snedeker,
References: 16.
1965 July 19 - 22:01 GMT - Launch Site: Vandenberg. Launch Complex: SLC3W. Launch Pad: -. Launch Vehicle: Delta. Model: Thor SLV-2A Agena D. LV Configuration: Thor SLV-2A Agena D 446 / Agena D SS-01B 1617. -
KH-4A 1022 Nation: USA. Payload: KH-4A s/n 1022 / Agena D 1617. Mass: 1,500 kg (3,300 lb). Class: Surveillance. Type: Military. Spacecraft: KH-4A. Agency: NRO/CIA. Perigee: 189 km (117 mi). Apogee: 461 km (286 mi). Inclination: 85.10 deg. Period: 91.00 min. COSPAR: 1965-057A. USAF Sat Cat: 1457. Decay Date: 1965-08-18. KH-4A. All cameras operated satisfactorily. References: 2, 6.
1965 July 20 - Launch Site: Green River. Launch Complex: Pad 3. Launch Pad: -. Launch Vehicle: Athena RTV. LV Configuration: Athena C007. FAILURE: Failure. -
USAF C007 re-entry vehicle test flight Nation: USA. Agency: USAF. Apogee: 0 km ( mi). References: 2.
1965 July 20 - 08:27 GMT - Launch Site: Cape Canaveral. Launch Complex: LC13. Launch Pad: -. Launch Vehicle: Atlas. Model: Atlas Agena D. LV Configuration: Atlas Agena D 225D / Agena D 1803. -
Vela 5 Nation: USA. Payload: Vela 3A. Mass: 235 kg (518 lb). Class: Surveillance. Type: Nuclear Detection. Spacecraft: Vela. Agency: USAF. Perigee: 106,367 km (66,093 mi). Apogee: 115,839 km (71,978 mi). Inclination: 35.20 deg. Period: 6,679.00 min. COSPAR: 1965-058A. USAF Sat Cat: 1458. Space craft engaged in investigation of spaceflight techniques and technology (US Cat A). References: 2, 6, 278.
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Vela 6 Nation: USA. Payload: Vela 3B. Mass: 235 kg (518 lb). Class: Surveillance. Type: Nuclear Detection. Spacecraft: Vela. Agency: USAF. Perigee: 101,715 km (63,202 mi). Apogee: 121,281 km (75,360 mi). Inclination: 34.20 deg. Period: 6,712.70 min. COSPAR: 1965-058B. USAF Sat Cat: 1459. Space craft engaged in investigation of spaceflight techniques and technology (US Cat A). References: 2, 6, 278.
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ORS 3 Nation: USA. Payload: ERS 17. Mass: 5.00 kg (11.00 lb). Class: Earth. Type: Magnetosphere. Spacecraft: ERS. Agency: USAF. Perigee: 566 km (351 mi). Apogee: 111,793 km (69,464 mi). Inclination: 36.90 deg. Period: 2,595.40 min. COSPAR: 1965-058C. USAF Sat Cat: 1460. Decay Date: 1968-07-01. Radiation data. Space craft engaged in investigation of spaceflight techniques and technology (US Cat A). References: 2, 6, 278.
1965 July 20 - 17:59 GMT - Launch Site: Delamar Dry Lake DZ. Launch Complex: -. Launch Pad: 37.3 N x 114.9 W. Launch Vehicle: X-15. LV Configuration: X-15 3-45-69. -
X-15A Bound.Layer Noise test Nation: USA. Agency: NASA/USAF. Apogee: 32 km (19 mi). Maximum Speed - 6050 kph. Maximum Altitude - 32126 m. References: 2.
1965 July 21 - -
Surveyor small rover cancelled Nation: USA. Program: Apollo. Spacecraft: Surveyor Lunar Rover. Several lunar surface vehicles received national attention: - NASA announced that it had dropped plans for developing a small rover to be carried to the moon aboard soft-landing Surveyor spacecraft. This action, the space agency said, stemmed from a desire to concentrate on the development of the spacecraft per se and on its scientific instrumentation.
References: 16.
1965 July 21 - -
Apollo Manned Flying System Nation: USA. Program: Apollo. Spacecraft: MFS. Bell Aerosystems Company announced that it had received additional funds from NASA (almost a half million dollars) to continue work on another lunar vehicle, the so-called Manned Flying System. This latter craft, also primarily a tool for exploration, would be able to transport an astronaut and about 136 kg (300 lbs) of equipment (or two astronauts) for distances up to 24 km (15 mi) from the original landing site.
References: 16.
1965 July 21 - -
Apollo Lunar Flying Vehicle (LFV) Nation: USA. Program: Apollo. Spacecraft: LFV Bell. Bell Aerosystems Company announced that it had designed a rocket-propelled Lunar Flying Vehicle (LFV) to aid Apollo astronauts in their exploration of the moon. This work was the result of a year-long study that the company had conducted for MSFC. The LFV, nicknamed "Hopper," would be able to travel about 80 km (50 mi) without stopping. Bell announced also that it had received additional funds from NASA (almost a half million dollars) to continue work on another lunar vehicle, the so-called Manned Flying System. This latter craft, also primarily a tool for exploration, would be able to transport an astronaut and about 136 kg (300 lbs) of equipment (or two astronauts) for distances up to 24 km (15 mi) from the original landing site.
References: 16.
1965 July 21 - Launch Vehicle: R-9. -
R-9A ICBM accepted into military service. Nation: USSR. Decree 'On adoption of the R-9A in shaft and surface variants into armaments' was issued. References: 474.
1965 July 21 - Launch Site: Baikonur. Launch Complex: LC60/6. Launch Pad: -. Launch Vehicle: R-16. Model: R-16U. -
Military training launch Nation: USSR. Agency: RVSN. Apogee: 1,210 km (750 mi). References: 2.
1965 July 21 - 10:33 GMT - Launch Site: Eglin. Launch Complex: -. Launch Pad: -. Launch Vehicle: Nike. Model: Nike Iroquois. LV Configuration: Nike Iroquois AE07.347. -
Sphere / Vehicle test / aeronomy mission Nation: USA. Agency: USAF. Apogee: 178 km (110 mi). References: 2.
1965 July 21 - 18:18 GMT - Launch Site: Vandenberg. Launch Complex: 395-B. Launch Pad: -. Launch Vehicle: Titan. Model: Titan 2. LV Configuration: Titan II B-62. -
Long Ball operational test Nation: USA. Agency: USAF SAC. Apogee: 1,300 km (800 mi). References: 2.
1965 July 21 - 20:00 GMT - Launch Site: White Sands. Launch Complex: LC35. Launch Pad: -. Launch Vehicle: Aerobee. Model: Aerobee 150. LV Configuration: Aerobee 150 CRL AD3.375. -
Mass spectrometer / Impulse probe Ionosphere mission Nation: USA. Agency: USAF. Apogee: 193 km (119 mi). References: 2.
1965 July 22 - -
Apollo AES program decisions. Nation: USA. Spacecraft: Apollo X. Edward Z. Gray, Director, Advanced Manned Missions Program at NASA Hq, informed the Center Directors at MSC, MSFC, and KSC of significant recent program decisions on the approach to be followed during Fiscal Year 1966 in defining payload integration for the AES to the extent necessary for awarding major project contracts approximately a wear later. In defining AES activity, Gray said, the Centers must follow the phased approach, with definition phase contracts to be awarded competitively to industry about the first of 1966.
Additional Details: Apollo AES program decisions..
1965 July 23 - Launch Vehicle: Titan. Model: Titan 2. -
Gemini-Titan (GT) 5 was demated following completion of the Wet Mock Simulated Launch to allow the spacecraft fuel cells to be replaced and the coolant bypass to be modified. Nation: USA. Flight: Gemini 5. Spacecraft and launch vehicle were remated August 5. Modified Electrical Interface Integrated Validation and the Joint Guidance and Control Tests were run on August 6. Spacecraft Final Systems Test on August 9-10 and the Simulated Flight Test on August 13 completed prelaunch testing of GT-5, scheduled for launch August 19.
1965 July 23 - 04:33 GMT - Launch Site: Kapustin Yar. Launch Complex: LC86/1. Launch Pad: -. Launch Vehicle: Kosmos 2. Model: Kosmos 63S1. -
Cosmos 76 Nation: USSR. Program: DS. Payload: DS-P1-Yu s/n 3. Mass: 325 kg (716 lb). Class: Military. Type: Target. Spacecraft: DS-P1-Yu. Agency: MO SSSR. Perigee: 256 km (159 mi). Apogee: 513 km (318 mi). Inclination: 48.80 deg. Period: 92.20 min. COSPAR: 1965-059A. USAF Sat Cat: 1464. Completed Operations Date: 1965-10-28. Decay Date: 1966-03-16. Development of systems for air defence and the control of outer space. References: 2, 6, 99.
1965 July 23 - 17:05 GMT - Launch Site: Wallops Island. Launch Complex: -. Launch Pad: -. Launch Vehicle: Cajun. Model: Nike Cajun. LV Configuration: Nike Cajun NASA 10.128GM. -
Grenades Aeronomy mission Nation: USA. Agency: NASA. Apogee: 116 km (72 mi). References: 2.
1965 July 24 - 08:36 GMT - Launch Site: Fort Churchill. Launch Complex: -. Launch Pad: -. Launch Vehicle: Aerobee. Model: Aerobee 150. LV Configuration: Aerobee 150 AF3.266/VFT65-S-3. -
Noctilucent clouds Aeronomy mission Nation: USA. Agency: USAF. Apogee: 179 km (111 mi). References: 2.
1965 July 26 - Launch Vehicle: Titan. Model: Titan 2. -
Circumlunar flight using Gemini seriously studied Nation: USA. Program: Apollo. Spacecraft: Gemini. During a news conference, Kenneth S. Kleinknecht, Deputy Manager of the Gemini Project Office at MSC, affirmed that, although no firm decisions had yet been made, the concept of a circumlunar flight using a Gemini spacecraft was being seriously studied. The mission would use Titan II and III-C launch vehicles and would require rendezvousing in earth orbit. NASA, Martin-Marietta Corporation (builder of the Titan), and Aerojet-General Corporation (which manufactured upper stages for the III-C) all were studying the feasibility of such a flight. Later in the year, NASA Administrator James E. Webb eliminated the possibility of a Gemini circumlunar mission, ". . . our main reliance for operating at lunar distances . . . is the large Saturn V/Apollo system."
References: 16.
1965 July 26 - -
Malfunction caused Apollo boilerplate 1 to impact on land Nation: USA. Program: Apollo. Spacecraft: Apollo CSM. At North American's drop facility, a malfunction in the release mechanism caused boilerplate 1 to impact on land rather than water. After a recurrence of this accident on August 6, a team of investigators began looking into the problem. Drops were suspended pending their findings. These incidents aggravated delays in the test program, which already was seven weeks behind schedule.
References: 16.
1965 July 26 - Launch Site: Green River. Launch Complex: Pad 2. Launch Pad: -. Launch Vehicle: Athena RTV. LV Configuration: Athena C011. -
USAF C011 re-entry vehicle test flight Nation: USA. Agency: USAF. Apogee: 200 km (120 mi). References: 2.
1965 July 26 - 12:01 GMT - Launch Site: Kagoshima. Launch Complex: -. Launch Pad: -. Launch Vehicle: Kappa. Model: Kappa 9M. LV Configuration: Kappa 9M K-9M-12. -
Optical astronomy / x-ray astronomy mission Nation: Japan. Agency: ISAS. Apogee: 350 km (210 mi). References: 2.
1965 July 26 - 17:00 GMT - Launch Site: Woomera. Launch Complex: LA5B. Launch Pad: LA5B?. Launch Vehicle: Black Knight. Model: Black Knight 301/C2. LV Configuration: Black Knight-301/C2 BK.23. -
Dazzle re-entry vehicle test Nation: UK. Agency: RAE. Apogee: 492 km (305 mi). References: 2.
1965 July 27 - Launch Site: Green River. Launch Complex: Pad 1. Launch Pad: -. Launch Vehicle: Athena RTV. LV Configuration: Athena D005. FAILURE: Failure. -
USAF D005 re-entry vehicle test flight Nation: USA. Agency: USAF. Apogee: 0 km ( mi). References: 2.
1965 July 27 - 03:10 GMT - Launch Site: Kagoshima. Launch Complex: -. Launch Pad: -. Launch Vehicle: Kappa. Model: Kappa 9M. LV Configuration: Kappa 9M K-9M-13. -
Ionosphere mission Nation: Japan. Agency: ISAS. Apogee: 317 km (196 mi). References: 2.
1965 July 28 - -
Five further Voskhod spacecraft authorised. Nation: USSR. Spacecraft: Voskhod. Military-Industrial Commission (VPK) Decree 156 'On the Manufacture of 'Voskhod' Space Ship-Satellites-manufacture of five more Voskhod spacecraft' was issued. References: 474.
1965 July 28 - -
Voskhod production Nation: USSR. Program: Voskhod. Flight: Voskhod 3, Voskhod 4, Voskhod 5, Voskhod 6. The All-Soviet national economic commission on Military-Industrial Matters issues resolution 145, "On completion of the Voskhod spacecraft". Voskhod s/n 5, 6, and 7 are to be completed in October, November, and December 1965; and s/n 8 and 9 in February and March 1966. The new-design spacecraft will be designed for flight of two cosmonauts up to 15 days, with provisions for multiple spacewalks outside of the capsule over periods of 3 to 6 days, provisions for artificial gravity tests, and equipment for medical, biological, physics, technical, and military experiments. All concerned ministries are instructed to complete development and deliver all needed subsystem and experimental equipment 45 days before the completion dates of the spacecraft. The trainer for the 3KV Voskhod is to be delivered by October 1965, and the 3KD trainer in the first quarter of 1966.
References: 376.
1965 July 30 - -
Final report on Lockheed modular multipurpose space station. Nation: USA. Spacecraft: LORL. The final report on a modular multipurpose space station was delivered to MSC by the Spacecraft Organization of Lockheed-California Company. The concept provided for a sequential evolution of space vehicles ranging from small Apollo-dependent laboratories, through larger, more versatile laboratories, to a semipermanent space station. Initial objectives of the study were to refine and optimize the design of the large orbital research laboratory.
Additional Details: Final report on Lockheed modular multipurpose space station..
1965 July 30 - 13:00 GMT - Launch Site: Cape Canaveral. Launch Complex: LC37B. Launch Pad: -. Launch Vehicle: Saturn I. Model: Saturn I. LV Configuration: Saturn I-Blk2 SA-10. -
Pegasus 3 Nation: USA. Program: Apollo. Payload: Pegasus 3. Mass: 10,500 kg (23,100 lb). Class: Earth. Type: Micrometeoroid. Spacecraft: Pegasus. Agency: NASA MSF. Perigee: 441 km (274 mi). Apogee: 449 km (278 mi). Inclination: 28.90 deg. Period: 93.40 min. COSPAR: 1965-060A. USAF Sat Cat: 1467. Decay Date: 1969-08-04. NASA launched Pegasus 3, third of the meteoroid detection satellites, as scheduled at 8:00 a.m. EST, from Cape Kennedy. As earlier, an Apollo spacecraft (boilerplate 9) served as the payload's shroud. This flight (SA-10) marked the end of the Saturn I program, which during its seven-year lifetime had achieved 10 straight successful launches and had contributed immeasurably to American rocket technology.
References: 2, 6, 16, 26, 27.
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Apollo-Model 5 Nation: USA. Program: Apollo. Payload: Apollo CSM Boilerplate 9A. Class: Manned. Type: Lunar spacecraft. Spacecraft: Apollo CSM. Agency: NASA MSC. Perigee: 521 km (323 mi). Apogee: 536 km (333 mi). Inclination: 28.80 deg. Period: 95.21 min. COSPAR: 1965-060B. USAF Sat Cat: 1468. Decay Date: 1975-11-22. References: 2, 279.
1965 July 31 - -
NASA / Public Health Service agreements on Apollo back contamination Nation: USA. Program: Apollo. At a meeting between representatives of NASA and Public Health Service representatives, it was agreed: - That the PHS had responsibility for the health of the nation and for any potential threat to that health from extraterrestrial life, particularly from back contamination.
- That the Office of the Surgeon General, PHS, would submit to the NASA Administrator a proposal for action deemed necessary.
- That the Department of Agriculture had a similar responsibility for the nation's crops and animals of economic importance and that the Department of Agriculture would probably accept arrangements made by PHS, and be brought into the matter at the point they considered action to be necessary.
Additional Details: NASA / Public Health Service agreements on Apollo back contamination. References: 16.
1965 July 31 - Launch Site: Baikonur. Launch Complex: LC131. Launch Pad: LC131?. Launch Vehicle: UR-100. FAILURE: Failure. -
State trials missile test Nation: USSR. Agency: RVSN. Apogee: 0 km ( mi). References: 2.
1965 July 31 - Launch Site: Green River. Launch Complex: Pad 2. Launch Pad: -. Launch Vehicle: Athena RTV. LV Configuration: Athena D004. -
USAF D004 re-entry vehicle test flight Nation: USA. Agency: USAF. Apogee: 200 km (120 mi). References: 2.
1965 July -
1965 August 1 - -
Development of military versions of Voskhod and Soyuz approved. Nation: USSR. Program: Voskhod. Spacecraft: Voskhod, Soyuz VI. Flight: Voskhod 3, Voskhod 4, Voskhod 5, Voskhod 6, Soyuz VI Flight 1. Military-Industrial Commission (VPK) Decree 'On creation of military Voskhod and Soyuz spacecraft' was issued. Eight days later, Kamanin receives the resolution, signed by Marshal Zharkov, countersigned by Smirnov. Krylov, Vershinin, Sudts, and Gorshkov are ordered to immediately begin military space research aboard Voskhod and also develop a special version of the Soyuz spacecraft for visual and photographic military reconnaissance, satellite inspection, interception in orbit, as well as development of nuclear missile early warning systems. This is old hat to Kamanin. Krylov has no interest in military spacecraft, and will not implement the order.
References: 376, 474.
1965 August -
1965 August 2 - -
Marquardt to build Apollo Block II SM reaction control system engines Nation: USA. Program: Apollo. Spacecraft: Apollo CSM. NASA's office at Downey, Calif., approved the contract with the Marquardt Corporation for the procurement of Block II SM reaction control system engines. Estimated cost of the fixed price contract would be $6.5 million. Marquardt was supplying the Block I SM engines.
References: 16.
1965 August 2 - -
First prototype Apollo portable life support system Nation: USA. Program: Apollo. Spacecraft: A7L. Hamilton Standard shipped the first prototype portable life support system to Houston, where it would undergo testing by the Crew Systems Division. References: 16.
1965 August 3 - -
ALSEP Prototypes to be built by three firms. Nation: USA. Program: Apollo. Spacecraft: Apollo ALSEP. NASA named three firms, Bendix Systems Division, TRW Systems Group, and Space-General Corporation to design prototypes of the Apollo Lunar Surface Experiments Package (ALSEP). Each company received a $500,000, six-month contract. After delivery of the prototypes, MSC would select one of the three to develop the ALSEP flight hardware.
References: 16.
1965 August 3 - Launch Site: Baikonur. Launch Complex: PU32. Launch Pad: -. Launch Vehicle: Tsiklon. Model: R-36 8K67. FAILURE: Failure. -
State trials missile test Nation: USSR. Agency: RVSN. Apogee: 0 km ( mi). References: 2.
1965 August 3 - 04:30 GMT - Launch Site: Green River. Launch Complex: Pad 3. Launch Pad: -. Launch Vehicle: Athena RTV. LV Configuration: Athena C014. -
USAF C014 re-entry vehicle test flight Nation: USA. Agency: USAF. Apogee: 200 km (120 mi). References: 2.
1965 August 3 - 08:52 GMT - Launch Site: Woomera. Launch Complex: LA2. Launch Pad: -. Launch Vehicle: HAD. LV Configuration: HAD 177. -
Aeronomy mission Nation: Australia. Agency: WRE. Apogee: 115 km (71 mi). References: 2.
1965 August 3 - 11:02 GMT - Launch Site: Baikonur. Launch Complex: LC31. Launch Pad: -. Launch Vehicle: Soyuz. Model: Voskhod 11A57. LV Configuration: Voskhod 11A57 U15001-01. -
Cosmos 77 Nation: USSR. Payload: Zenit-4. Mass: 6,300 kg (13,800 lb). Class: Surveillance. Type: Military. Spacecraft: Zenit-4. Agency: MOM. Perigee: 200 km (120 mi). Apogee: 281 km (174 mi). Inclination: 51.80 deg. Period: 89.30 min. COSPAR: 1965-061A. USAF Sat Cat: 1469. Duration: 8.00 days. Decay Date: 1965-08-11. High resolution photo reconnaissance satellite; returned film capsule References: 2, 6.
1965 August 3 - 19:12 GMT - Launch Site: Vandenberg. Launch Complex: SLC4E. Launch Pad: -. Launch Vehicle: Atlas. Model: SLV-3 Agena D. LV Configuration: SLV-3 Agena D 7111 / Agena D 7111. -
KH 7-21 Nation: USA. Payload: KH-7 no. 21. Mass: 2,000 kg (4,400 lb). Class: Surveillance. Type: Military. Spacecraft: KH-7. Agency: NRO/USAF. Perigee: 278 km (172 mi). Apogee: 352 km (218 mi). Inclination: 107.40 deg. Period: 90.80 min. COSPAR: 1965-062A. USAF Sat Cat: 1471. Decay Date: 1965-08-07. KH-7 type satellite. Space craft engaged in investigation of spaceflight techniques and technology (US Cat A). References: 2, 6, 278.
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OPS 6761 Nation: USA. Payload: EHH B3. Mass: 60 kg (132 lb). Class: Sigint. Spacecraft: SSF. Agency: NRO/USAF. Perigee: 501 km (311 mi). Apogee: 515 km (320 mi). Inclination: 107.40 deg. Period: 94.80 min. COSPAR: 1965-062B. USAF Sat Cat: 1472. Decay Date: 1968-06-17. Radar monitoring. References: 2, 6, 172, 278.
1965 August 3 - 20:40 GMT - Launch Site: Delamar Dry Lake DZ. Launch Complex: -. Launch Pad: 37.3 N x 114.9 W. Launch Vehicle: X-15. LV Configuration: X-15 2-41-73. -
X-15A-2 RAS,ST,Landing test Nation: USA. Agency: NASA/USAF. Apogee: 63 km (39 mi). Maximum Speed - 5796 kph. Maximum Altitude - 63612 m. References: 2.
1965 August 4 - Launch Site: Cape Canaveral. Launch Complex: LC32B. Launch Pad: -. Launch Vehicle: Minuteman 2. LV Configuration: Minuteman 2 457. -
Research and development launch Nation: USA. Agency: USAF AFSC. Apogee: 1,300 km (800 mi). References: 2.
1965 August 4 - 12:43 GMT - Launch Site: Vandenberg. Launch Complex: 576B1. Launch Pad: -. Launch Vehicle: Atlas. Model: Atlas D. LV Configuration: Atlas D 183D. -
ABRES WAC-5 re-entry vehicle test flight Nation: USA. Agency: USAF AFSC. Apogee: 1,800 km (1,100 mi). References: 2.
1965 August 5 - -
Apollo boilerplate (BP) 6A sustained considerable damage Nation: USA. Program: Apollo. Spacecraft: Apollo CSM. During tests of the Apollo earth landing system (ELS) at El Centro, Calif., boilerplate (BP) 6A sustained considerable damage in a drop that was to have demonstrated ELS performance during a simulated apex-forward pad abort. Oscillating severely at the time the auxiliary brake parachute was opened, the spacecraft severed two of the electrical lines that were to have released that device. Although the ELS sequence took place as planned, the still-attached brake prevented proper operation of the drogues and full inflation of the mains. As a result, BP-6A landed at a speed of about 50 fps.
References: 16.
1965 August 5 - Launch Vehicle: Saturn V. -
First ground test firing of Saturn S-IC stage Nation: USA. Program: Apollo. The Saturn V's booster, the S-IC stage, made a "perfect" full-duration static firing by burning for the programmed 2.5 minutes at its full 33,360-kilonewton (7.5-million-lbs) thrust in a test conducted at MSFC. The test model demonstrated its steering capability on command from the blockhouse after 100 sec had elapsed; the firing consumed 2.133-million liters (537,000 gallons) of kerosene and liquid oxygen.
References: 16.
1965 August 5 - 13:21 GMT - Launch Site: Vandenberg. Launch Complex: 576A2. Launch Pad: -. Launch Vehicle: Atlas. Model: Atlas F. LV Configuration: Atlas F 147F. -
ABRES LORV-2A re-entry vehicle test flight Nation: USA. Agency: USAF AFSC. Apogee: 1,400 km (800 mi). References: 2.
1965 August 6 - 17:41 GMT - Launch Site: Delamar Dry Lake DZ. Launch Complex: -. Launch Pad: 37.3 N x 114.9 W. Launch Vehicle: X-15. LV Configuration: X-15 1-56-93. -
X-15A IR Scan,Stability test Nation: USA. Agency: NASA/USAF. Apogee: 31 km (19 mi). Maximum Speed - 5686 kph. Maximum Altitude - 31455 m. References: 2.
1965 August 7 - Launch Site: Pameungpeuk. Launch Complex: -. Launch Pad: -. Launch Vehicle: Kappa. Model: Kappa 8. LV Configuration: Kappa 8 K-8(L). -
Aeronomy mission Nation: Japan. Agency: ISAS. Apogee: 100 km (60 mi). References: 2.
1965 August 7 - Launch Site: Green River. Launch Complex: Pad 2. Launch Pad: -. Launch Vehicle: Athena RTV. LV Configuration: Athena C005. -
USAF C005 re-entry vehicle test flight Nation: USA. Agency: USAF. Apogee: 200 km (120 mi). References: 2.
1965 August 7 - Launch Site: Green River. Launch Complex: Pad 1. Launch Pad: -. Launch Vehicle: Athena RTV. LV Configuration: Athena C009. FAILURE: Failure. -
USAF C009 re-entry vehicle test flight Nation: USA. Agency: USAF. Apogee: 200 km (120 mi). References: 2.
1965 August 7 - 11:13 GMT - Launch Site: Point Barrow. Launch Complex: -. Launch Pad: -. Launch Vehicle: Cajun. Model: Nike Cajun. LV Configuration: Nike Cajun NASA 10.151GM. -
Grenades Aeronomy mission Nation: USA. Agency: NASA. Apogee: 120 km (70 mi). References: 2.
1965 August 7 - 12:00 GMT - Launch Site: Fort Churchill. Launch Complex: -. Launch Pad: -. Launch Vehicle: Cajun. Model: Nike Cajun. LV Configuration: Nike Cajun NASA 10.96GM. -
Grenades Aeronomy mission Nation: USA. Agency: NASA. Apogee: 127 km (78 mi). References: 2.
1965 August 7 - 18:30 GMT - Launch Site: Wallops Island. Launch Complex: -. Launch Pad: -. Launch Vehicle: Cajun. Model: Nike Cajun. LV Configuration: Nike Cajun NASA 10.154UA. -
Falling sphere Aeronomy mission Nation: USA. Agency: NASA. Apogee: 167 km (103 mi). References: 2.
1965 August 7 - 19:39 GMT - Launch Site: Point Barrow. Launch Complex: -. Launch Pad: -. Launch Vehicle: Cajun. Model: Nike Cajun. LV Configuration: Nike Cajun NASA 10.162GM. -
Grenades Aeronomy mission Nation: USA. Agency: NASA. Apogee: 127 km (78 mi). References: 2.
1965 August 7 - 19:45 GMT - Launch Site: Fort Churchill. Launch Complex: -. Launch Pad: -. Launch Vehicle: Cajun. Model: Nike Cajun. LV Configuration: Nike Cajun NASA 10.165GM. -
Grenades Aeronomy mission Nation: USA. Agency: NASA. Apogee: 118 km (73 mi). References: 2.
1965 August 7 - 20:06 GMT - Launch Site: Wallops Island. Launch Complex: -. Launch Pad: -. Launch Vehicle: Cajun. Model: Nike Cajun. LV Configuration: Nike Cajun NASA 10.168GM. -
Grenades / UM Sphere Aeronomy mission Nation: USA. Agency: NASA. Apogee: 120 km (70 mi). References: 2.
1965 August 8 - 03:40 GMT - Launch Site: Wallops Island. Launch Complex: -. Launch Pad: -. Launch Vehicle: Cajun. Model: Nike Cajun. LV Configuration: Nike Cajun NASA 10.169GM. -
Grenades / UM Sphere Aeronomy mission Nation: USA. Agency: NASA. Apogee: 122 km (75 mi). References: 2.
1965 August 8 - 04:00 GMT - Launch Site: Fort Churchill. Launch Complex: -. Launch Pad: -. Launch Vehicle: Cajun. Model: Nike Cajun. LV Configuration: Nike Cajun NASA 10.166GM. -
Grenades Aeronomy mission Nation: USA. Agency: NASA. Apogee: 116 km (72 mi). References: 2.
1965 August 8 - 04:15 GMT - Launch Site: Point Barrow. Launch Complex: -. Launch Pad: -. Launch Vehicle: Cajun. Model: Nike Cajun. LV Configuration: Nike Cajun NASA 10.163GM. -
Grenades Aeronomy mission Nation: USA. Agency: NASA. Apogee: 124 km (77 mi). References: 2.
1965 August 8 - 08:40 GMT - Launch Site: Wallops Island. Launch Complex: -. Launch Pad: -. Launch Vehicle: Cajun. Model: Nike Cajun. LV Configuration: Nike Cajun NASA 10.157UA. -
Sphere Aeronomy mission Nation: USA. Agency: NASA. Apogee: 165 km (102 mi). References: 2.
1965 August 8 - 10:02 GMT - Launch Site: Fort Churchill. Launch Complex: -. Launch Pad: -. Launch Vehicle: Cajun. Model: Nike Cajun. LV Configuration: Nike Cajun NASA 10.167GM. -
Grenades Aeronomy mission Nation: USA. Agency: NASA. Apogee: 125 km (77 mi). References: 2.
1965 August 8 - 10:15 GMT - Launch Site: Wallops Island. Launch Complex: -. Launch Pad: -. Launch Vehicle: Cajun. Model: Nike Cajun. LV Configuration: Nike Cajun NASA 10.170GM. -
Grenades / UM Sphere Aeronomy mission Nation: USA. Agency: NASA. Apogee: 120 km (70 mi). References: 2.
1965 August 9 - Launch Vehicle: Saturn I, Saturn V. -
Saturn V stages tested Nation: USA. Program: Apollo. Two Saturn milestones occurred on the same day. At Santa Susana, Calif., North American conducted the first full-duration captive firing of an S-II, second stage of the Saturn V. And at Sacramento, Douglas static-tested the first flight-model S-IVB, second stage for the Saturn IB. This latter marked the first time that a complete static test (encompassing vehicle checkout, loading, and firing) had been controlled entirely by computers.
References: 16.
1965 August 9 - Launch Site: Little Rock AFB. Launch Complex: -. Launch Pad: -. Launch Vehicle: Titan. Model: Titan 2. -
Accident at Titan 2 Silo 373-4, Little Rock AFB, kills 53. Nation: USA. A fire started in the silo during construction work. Two workers survived. The Titan 2 missile was fueled and in the silo but did not explode. The warhead had been removed from the site prior to the start of construction. The complex wass off alert status for the next 13 months during the accident investigation and repairs.
1965 August 9 - 10:10 GMT - Launch Site: Point Barrow. Launch Complex: -. Launch Pad: -. Launch Vehicle: Cajun. Model: Nike Cajun. LV Configuration: Nike Cajun NASA 10.164GM. -
Grenades Aeronomy mission Nation: USA. Agency: NASA. Apogee: 124 km (77 mi). References: 2.
1965 August 10 - Launch Vehicle: CZ-1. -
Project 651 Nation: China. Spacecraft: DFH-1. Zhou En Lai approves the plan for the construction and launch of China's first satellite.
1965 August 10 - 17:54 GMT - Launch Site: Wallops Island. Launch Complex: LA3A. Launch Pad: -. Launch Vehicle: Scout. Model: Scout B. LV Configuration: Scout B S131R. -
SECOR 5 (EGRS 5) Nation: USA. Payload: SEV / FW4S. Mass: 24 kg (52 lb). Class: Earth. Type: Geodetic. Spacecraft: SECOR. Agency: NASA LaR. Perigee: 1,134 km (704 mi). Apogee: 2,419 km (1,503 mi). Inclination: 69.20 deg. Period: 122.20 min. COSPAR: 1965-063A. USAF Sat Cat: 1506. Spacecraft engaged in research and exploration of the upper atmosphere or outer space (US Cat B). References: 2, 6.
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Secor 5 Nation: USA. Payload: Secor 5. Spacecraft: SECOR. Agency: USA. Perigee: 1,136 km (705 mi). Apogee: 2,424 km (1,506 mi). Inclination: 69.20 deg. Period: 122.22 min. COSPAR: 1965-063B. USAF Sat Cat: 1502. References: 2, 279.
1965 August 10 - 19:24 GMT - Launch Site: Delamar Dry Lake DZ. Launch Complex: -. Launch Pad: 37.3 N x 114.9 W. Launch Vehicle: X-15. LV Configuration: X-15 3-46-70. -
X-15A Northrop Scan,BLN test Nation: USA. Agency: NASA/USAF. Apogee: 82 km (50 mi). Maximum Speed - 5712 kph. Maximum Altitude - 82601 m. Astronaut wings flight (USAF definition). References: 2.
1965 August 10 - 23:13 GMT - Launch Site: Salto di Quirra. Launch Complex: -. Launch Pad: -. Launch Vehicle: Skylark. Model: Skylark 7C. LV Configuration: Skylark-7C ESRO S05/1. -
Ultraviolet photometer Ultraviolet astronomy mission Nation: Europe. Agency: ESRO. Apogee: 215 km (133 mi). References: 2.
1965 August 11 - Launch Site: Cape Canaveral. Launch Complex: LC29A. Launch Pad: -. Launch Vehicle: Polaris. Model: Polaris A1. LV Configuration: Polaris A1 C2X-3. -
STAFF 3 test Nation: USA. Agency: USN. Apogee: 500 km (310 mi). References: 2.
1965 August 11 - 01:35 GMT - Launch Site: Pameungpeuk. Launch Complex: -. Launch Pad: -. Launch Vehicle: Kappa. Model: Kappa 8. LV Configuration: Kappa 8 K-8(L)-4. -
SK-8-4 Aeronomy / ionosphere / Fields mission Nation: Japan. Agency: ISAS. Apogee: 191 km (118 mi). References: 2.
1965 August 11 - 11:49 GMT - Launch Site: White Sands. Launch Complex: -. Launch Pad: -. Launch Vehicle: Cajun. Model: Nike Cajun. LV Configuration: Nike Cajun NASA 10.144GM. -
Meteoroids Aeronomy / meteorites mission Nation: USA. Agency: NASA. Apogee: 129 km (80 mi). References: 2.
1965 August 11 - 14:31 GMT - Launch Site: Cape Canaveral. Launch Complex: LC36B. Launch Pad: -. Launch Vehicle: Atlas. Model: Atlas Centaur D. LV Configuration: Atlas Centaur D AC-6 / Centaur D 151D. -
Surveyor; Atlas Centaur 6 Nation: USA. Payload: Surveyor-SD-2. Mass: 950 kg (2,090 lb). Class: Planetary. Type: Lunar. Spacecraft: Surveyor. Agency: NASA/JPL. COSPAR: 1965-064A. USAF Sat Cat: 1503. Centaur AC-6 launched dummy Surveyor payload into a barycentric / translunar orbit. References: 2, 6, 278.
1965 August 12 - -
Six key checkpoints in development of Apollo hardware listed Nation: USA. Program: Apollo. Spacecraft: Apollo CSM. Samuel C. Phillips, Apollo Program Director, listed the six key checkpoints in the development of Apollo hardware: - Preliminary Design Review (PDR)
- Critical Design Review (CDR)
- Flight Article Configuration Inspection (FACI)
- Certification of Flight Worthiness (COFR)
- Design Certification Review (DCR)
- Flight Readiness Review (FRR)
Additional Details: Six key checkpoints in development of Apollo hardware listed. References: 16.
1965 August 12 - 17:15 GMT - Launch Site: White Sands. Launch Complex: LC35. Launch Pad: -. Launch Vehicle: Aerobee. Model: Aerobee 150. LV Configuration: Aerobee 150 CRL AE3.519. -
Extreme ultraviolet Mon Solar extreme ultraviolet mission Nation: USA. Agency: USAF. Apogee: 241 km (149 mi). References: 2.
1965 August 13 - Launch Site: Vandenberg. Launch Complex: -. Launch Pad: -. -
Last launch of Thor/Able-Star from Vandenberg AFB. Nation: USA. Last launch of Thor/Able-Star from Vandenberg AFB. (first launch on 28 September 1963). References: 88.
1965 August 13 - Launch Site: Baikonur. Launch Complex: PU33. Launch Pad: -. Launch Vehicle: Tsiklon. Model: R-36 8K67. -
State trials missile test Nation: USSR. Agency: RVSN. Apogee: 1,000 km (600 mi). References: 2.
1965 August 13 - 22:11 GMT - Launch Site: Vandenberg. Launch Complex: SLC2E. Launch Pad: -. Launch Vehicle: Delta. Model: Thor Ablestar. LV Configuration: Thor Ablestar-2 455 AB020. -
Dodecapole 2 Nation: USA. Payload: PORCUPINE 2. Mass: 4.00 kg (8.80 lb). Class: Calibration. Spacecraft: DODECAPOLE. Agency: USN. Perigee: 979 km (608 mi). Apogee: 1,051 km (653 mi). Inclination: 90.00 deg. Period: 105.40 min. COSPAR: 1965-065C. USAF Sat Cat: 1510. Surveillance Calibration; dodecahedron; extended 12 25 ft. antennas. Space craft engaged in investigation of spaceflight techniques and technology (US Cat A). References: 2, 6.
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Tempsat 1 Nation: USA. Mass: 9.00 kg (19.80 lb). Class: Calibration. Spacecraft: Tempsat. Agency: USN. Perigee: 1,082 km (672 mi). Apogee: 1,188 km (738 mi). Inclination: 89.90 deg. Period: 108.00 min. COSPAR: 1965-065E. USAF Sat Cat: 1512. Surveillance Calibration; black 14 inch dia. sphere. Space craft engaged in investigation of spaceflight techniques and technology (US Cat A). References: 2, 6.
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Transit O-5 Nation: USA. Program: Transit. Payload: NNS 30050. Mass: 61 kg (134 lb). Class: Navigation. Spacecraft: Transit. Agency: USN. Perigee: 1,078 km (669 mi). Apogee: 1,183 km (735 mi). Inclination: 89.90 deg. Period: 107.90 min. COSPAR: 1965-065F. USAF Sat Cat: 1514. Naval Avionics Facility-assembled production spacecraft. Failed after a few weeks operation. References: 2, 6.
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Long Rod Nation: USA. Payload: Navspasur Rod. Class: Calibration. Spacecraft: Surcal. Agency: USN. Perigee: 1,090 km (670 mi). Apogee: 1,194 km (741 mi). Inclination: 90.00 deg. Period: 108.10 min. COSPAR: 1965-065G. USAF Sat Cat: 1515. Space craft engaged in investigation of spaceflight techniques and technology (US Cat A). References: 2, 6.
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Calsphere 4A Nation: USA. Payload: NRL PL 158?. Mass: 2.00 kg (4.40 lb). Class: Calibration. Spacecraft: Calsphere. Agency: USN. Perigee: 1,077 km (669 mi). Apogee: 1,179 km (732 mi). Inclination: 90.10 deg. Period: 107.90 min. COSPAR: 1965-065H. USAF Sat Cat: 1520. Surveillance Calibration; white 14 inch dia. sphere. References: 2, 6.
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SURCAL 5 Nation: USA. Payload: NRL PL150C?. Class: Calibration. Spacecraft: SURCAL. Agency: USN. Perigee: 1,083 km (672 mi). Apogee: 1,196 km (743 mi). Inclination: 90.00 deg. Period: 108.11 min. COSPAR: 1965-065K. USAF Sat Cat: 1521. References: 2, 279.
1965 August 14 - 11:16 GMT - Launch Site: Baikonur. Launch Complex: LC31. Launch Pad: -. Launch Vehicle: Soyuz. Model: Vostok 8A92. LV Configuration: Vostok 8A92 U15001-02. -
Cosmos 78 Nation: USSR. Payload: Zenit-2 11F61 s/n 30. Mass: 4,720 kg (10,400 lb). Class: Surveillance. Type: Military. Spacecraft: Zenit-2. Agency: MOM. Perigee: 330 km (200 mi). Apogee: 379 km (235 mi). Inclination: 69.00 deg. Period: 91.60 min. COSPAR: 1965-066A. USAF Sat Cat: 1505. Duration: 8.00 days. Decay Date: 1965-08-22. Area survey photo reconnaissance satellite. References: 2, 6,93.
1965 August 15 - Launch Vehicle: Saturn V. -
First ground test firing of S-IVB stage Nation: USA. Program: Apollo. Class: manned. References: 26, 27.
1965 August 16 - Launch Vehicle: Titan. Model: Titan 2. -
Martin-Baltimore received propellant tanks for Gemini launch vehicle (GLV) 9 from Martin-Denver, which had begun fabricating them February 25. Nation: USA. Flight: Gemini 9. These were the first GLV tanks to be carried by rail from Denver to Baltimore. All previous tanks had traveled by air, but shortage of suitable aircraft made the change necessary. The tanks were shipped August 9. Aerojet-General delivered the stage I engine for GLV-9 August 20 and the stage II engine September 22. Tank splicing was completed October 21, engine installation November 10. Horizontal testing concluded November 23.
1965 August 16 - -
Chelomei's lunar spacecraft attacked Nation: USSR. Program: Lunar L1. Spacecraft: LK-1. Korolev discusses Chelomei's manned lunar flyby spacecraft with Kamanin. The Party ordered Chelomei to have 12 manned circumlunar spacecraft completed during 1966 and the first quarter of 1967. Chelomei has worked on the he project for many years, but his bureau has not yet decided on a single firm design for the spacecraft, let alone start construction.
References: 376.
1965 August 16 - 20:04 GMT - Launch Site: Vandenberg. Launch Complex: 395-C. Launch Pad: -. Launch Vehicle: Titan. Model: Titan 2. LV Configuration: Titan II B-6. -
Magic Lamp operational test Nation: USA. Agency: USAF SAC. Apogee: 1,300 km (800 mi). References: 2.
1965 August 17 - 00:05 GMT - Launch Site: Pameungpeuk. Launch Complex: -. Launch Pad: -. Launch Vehicle: Kappa. Model: Kappa 8. LV Configuration: Kappa 8 K-8(L). -
SK-8-3 (Grenades) Aeronomy mission Nation: Japan. Agency: ISAS. Apogee: 100 km (60 mi). References: 2.
1965 August 17 - 20:59 GMT - Launch Site: Vandenberg. Launch Complex: SLC3W. Launch Pad: -. Launch Vehicle: Delta. Model: Thor SLV-2A Agena D. LV Configuration: Thor SLV-2A Agena D 449 / Agena D SS-01B 1618. -
KH-4A 1023 Nation: USA. Payload: KH-4A s/n 1023 / Agena D 1618. Mass: 1,500 kg (3,300 lb). Class: Surveillance. Type: Military. Spacecraft: KH-4A. Agency: NRO/CIA. Perigee: 179 km (111 mi). Apogee: 399 km (247 mi). Inclination: 70.00 deg. Period: 90.30 min. COSPAR: 1965-067A. USAF Sat Cat: 1513. Decay Date: 1965-10-11. KH-4A. Program anomaly caused the fore camera to cease operation during revolutions 103-132. References: 2, 6.
1965 August 18 - -
Operation Scrape to lighten the Apollo LEM Nation: USA. Program: Apollo. Spacecraft: Apollo LM. At a third status meeting on LEM-1, Grumman put into effect "Operation Scrape," an effort to lighten that spacecraft by about 57 kg (125 lbs). "Scrape" involved an exchange of parts between LEM-1 and LTA-3. The former vehicle thus would be heavier than the latter; LTA-3, on the other hand, would have the same structural weight as LEMs 2 and forthcoming.
References: 16.
1965 August 18 - -
Soyuz development program reoriented; Soyuz 7K-OK earth orbit version to be built in lieu of Soyuz A. Nation: USSR. Program: Soyuz, Lunar L1. Spacecraft: Soyuz A, Soyuz 7K-OK, Soyuz B, Soyuz V, LK-1. Flight: Soyuz A-1, Soyuz A-2, Soyuz A-3, Soyuz A-4, Soyuz A-5, Soyuz 1, Soyuz 2A, Soyuz 3A, Soyuz 4A. Military-Industrial Commission (VPK) Decree 180 'On the Order of Work on the Soyuz Complex--approval of the schedule of work for Soyuz spacecraft' was issued. It set the following schedule for the new Soyuz 7K-OK version: two spacecraft to be completed in fourth quarter 1965, two in first quarter 1966, and three in second quarter 1966. Air-drop and sea trails of the 7K-OK spacecraft are to be completed in the third and fourth quarters 1965, and first automated docking of two unmanned Soyuz spacecraft in space in the first quarter of 1966. Korolev insists the automated docking system will be completely reliable, but Kamanin wishes that the potential of the cosmonauts to accomplish a manual rendezvous and docking had been considered in the design. With this decree the mission of the first Soyuz missions has been changed from a docking with unmanned Soyuz B and V tanker spacecraft, to docking of two Soyuz A-type spacecraft. It is also evident that although nothing is official, Korolev is confident he has killed off Chelomei's LK-1 circumlunar spacecraft, and that a Soyuz variant will be launched in its place.
References: 376, 474.
1965 August 18 - -
American surge in space Nation: USSR. Kamanin spends several hours reviewing new films of the American Gemini 4 flight, Apollo program, and unmanned lunar probes. He realises the scope of the American program is "colossal", and that the USA is set to quickly surpass the Soviet Union in space. References: 376.
1965 August 18 - 11:30 GMT - Launch Site: Vandenberg. Launch Complex: LF21. Launch Pad: -. Launch Vehicle: Minuteman 2. LV Configuration: Minuteman 2 2001. -
Research and development launch Nation: USA. Agency: USAF AFSC. Apogee: 1,300 km (800 mi). References: 2.
1965 August 19 - Launch Vehicle: Titan. Model: Titan 2. -
A spacecraft computer malfunction caused a hold of the countdown 10 minutes before the scheduled launch of Gemini-Titan 5. Nation: USA. Spacecraft: Gemini. Flight: Gemini 5. While the problem was being investigated, thunderstorms approached the Cape Kennedy area. With the computer problem unresolved and the weather deteriorating rapidly, the mission was scrubbed and rescheduled for August 21. Recycling began with unloading propellants.
1965 August 19-26 - -
Two Apollo LEM test articles to be used Nation: USA. Program: Apollo. Spacecraft: Apollo LM. MSC assigned two LEM test articles (numbers 10 and 2, respectively) to the SA-501 and SA-502 missions. Prior to flight, the spacecraft would be refurbished by Grumman, which would require four to five months' work on each vehicle. References: 16.
1965 August 19 - 01:40 GMT - Launch Site: Wallops Island. Launch Complex: -. Launch Pad: -. Launch Vehicle: Apache. Model: Nike Apache. LV Configuration: Nike Apache NASA 14.133NA. -
Airglow Aeronomy mission Nation: USA. Agency: NASA. Apogee: 144 km (89 mi). References: 2.
1965 August 20 - Launch Vehicle: Saturn V. -
Apollo S-IVB static-fired simulating a lunar mission Nation: USA. Program: Apollo. Douglas Aircraft Company static-fired the S-IVB in a test at Sacramento, Calif., simulating the workload of a lunar mission. The stage was run for three minutes, shut down for half an hour, then reignited for almost six minutes. References: 16.
1965 August 20 - -
NASA MSFC began serious investigation of the concept of an S-IVB Orbital Workshop (OWS). Nation: USA. Spacecraft: Orbital Workshop. As part of MSFC's activities related to the AES program, designers at the Center began serious investigation of the concept of an S-IVB Orbital Workshop (OWS). This concept, which involved 'in- orbit' conversion of a spent S-IVB stage to a shelter suitable for extended stay and utilization by man, showed great potential for experiment work during the Earth-orbital phase of the AES program. Accordingly, MSFC officials planned a four-month conceptual design effort, to begin immediately, with help and participation from both MSC and the S-IVB stage builder, Douglas Aircraft Company.
Additional Details: NASA MSFC began serious investigation of the concept of an S-IVB Orbital Workshop (OWS)..
1965 August 20 - Launch Site: Green River. Launch Complex: Pad 1. Launch Pad: -. Launch Vehicle: Athena RTV. LV Configuration: Athena D009. FAILURE: Failure. -
USAF D009 re-entry vehicle test flight Nation: USA. Agency: USAF. Apogee: 0 km ( mi). References: 2.
1965 August 20 - Launch Site: Green River. Launch Complex: Pad 3. Launch Pad: -. Launch Vehicle: Athena RTV. LV Configuration: Athena C008. -
USAF C008 re-entry vehicle test flight Nation: USA. Agency: USAF. Apogee: 200 km (120 mi). References: 2.
1965 August 21 - Launch Site: Baikonur. Launch Complex: PU32. Launch Pad: -. Launch Vehicle: Tsiklon. Model: R-36 8K67. FAILURE: Failure. -
State trials missile test Nation: USSR. Agency: RVSN. Apogee: 0 km ( mi). References: 2.
1965 August 21 - 14:00 GMT - Launch Site: Cape Canaveral. Launch Complex: LC19. Launch Pad: -. Launch Vehicle: Titan. Model: Titan II GLV. LV Configuration: Titan II GLV GT-5 / 62-12560. -
Gemini 5 Nation: USA. Program: Gemini. Payload: Gemini SC5/Rendezvous Evaluation Pod. Mass: 3,605 kg (7,947 lb). Class: Manned. Type: Spacecraft. Spacecraft: Gemini. Location of Spacecraft: Space Center Houston (NASA Johnson Space Center's Visitor Center), Houston, TX. Agency: NASA MSC. Perigee: 304 km (188 mi). Apogee: 395 km (245 mi). Inclination: 32.60 deg. Period: 91.50 min. COSPAR: 1965-068A. USAF Sat Cat: 1516. Duration: 7.96 days. Decay Date: 1965-08-29. Crew: Conrad, Cooper. Flight: Gemini 5. Major objectives of the eight-day mission were evaluating the performance of the rendezvous guidance and navigation system, using a rendezvous evaluation pod (REP), and evaluating the effects of prolonged exposure to the space environment on the flight crew. Secondary objectives included demonstrating controlled reentry guidance, evaluating fuel cell performance, demonstrating all phases of guidance and control system operation needed for a rendezvous mission, evaluating the capability of either pilot to maneuver the spacecraft in orbit to rendezvous, evaluating the performance of rendezvous radar, and executing 17 experiments. The mission proceeded without incident through the first two orbits and the ejection of the REP. About 36 minutes after beginning evaluation of the rendezvous guidance and navigation system, the crew noted that the pressure in the oxygen supply tank of the fuel cell system was falling. Pressure dropped from 850 pounds per square inch absolute (psia) at 26 minutes into the flight until it stabilized at 70 psia at 4 hours 22 minutes, and gradually increased through the remainder of the mission. The spacecraft was powered down and the REP exercise was abandoned. By the seventh revolution, experts on the ground had analyzed the problem and a powering-up procedure was started. During the remainder of the mission the flight plan was continuously scheduled in real time. Four rendezvous radar tests were conducted during the mission, the first in revolution 14 on the second day; the spacecraft rendezvous radar successfully tracked a transponder on the ground at Cape Kennedy. During the third day, a simulated Agena rendezvous was conducted at full electrical load. The simulation comprised four maneuvers - apogee adjust, phase adjust, plane change, and coelliptical maneuver - using the orbit attitude and maneuver system (OAMS). Main activities through the fourth day of the mission concerned operations and experiments. During the fifth day, OAMS operation became sluggish and thruster No. 7 inoperative. Thruster No. 8 went out the next day, and the rest of the system was gradually becoming more erratic. Limited experimental and operational activities continued through the remainder of the mission. Retrofire was initiated in the 121st revolution during the eighth day of the mission, one revolution early because of threatening weather in the planned recovery area. Reentry and landing were satisfactory, but the landing point was 145 km short, the result of incorrect navigation coordinates transmitted to the spacecraft computer from the ground network. Landing occurred August 29, 190 hours 55 minutes after the mission had begun. The astronauts arrived on board the prime recovery ship, the aircraft carrier Lake Champlain, at 9:25. The spacecraft was recovered at 11:51 a.m.With this flight, the US finally took the manned spaceflight endurance record from Russia, while demonstrating that the crew could survive in zero gravity for the length of time required for a lunar mission. However the mission was incredibly boring, the spacecraft just drifting to conserve fuel most of the time, and was 'just about the hardest thing I've ever done' according to a hyperactive Pete Conrad. An accident with freeze dried shrimp resulted in the cabin being filled with little pink subsatellites.
References: 2, 6, 16, 26, 33,60.
1965 August 23 - 20:00 GMT - Launch Site: Cape Canaveral. Launch Complex: LC31B. Launch Pad: -. Launch Vehicle: Minuteman 2. LV Configuration: Minuteman 2 454. -
Research and development launch Nation: USA. Agency: USAF AFSC. Apogee: 1,300 km (800 mi). References: 2.
1965 August 24 - -
Soyuz-VI program started.. Nation: USSR. Spacecraft: Soyuz VI. Flight: Gemini 4, Soyuz VI Flight 1. Central Committee of the Communist Party and Council of Soviet Ministers Decree 'On expansion of military space research and on 7K-VI Zvezda' was issued. In June 1965 Gemini 4 began the first American experiments in military space. At the same time the large military Manned Orbital Laboratory space station was on the verge of being given its final go-ahead. These events caused a bit of a panic among the Soviet military, where the Soyuz-R and Almaz projects were in the very earliest stages of design and would not fly until 1968 at the earliest. VPK head Leonid Smirnov ordered that urgent measures be taken to test manned military techniques in orbit at the earliest possible date. Modifications were to be made to the Voskhod and Soyuz 7K-OK spacecraft to assess the military utility of manned visual and photographic reconnaissance; of inspection of enemy satellites from orbit; attacking enemy spacecraft; and obtaining early warning of nuclear attack. The decree instructed Kozlov to fly by 1967 a military research variant of the Soyuz 7K-OK 11F615.
References: 474.
1965 August 24 - Launch Vehicle: Tsiklon, UR-200. -
Development of R-36-O and Tsyklon launch vehicles authorised Nation: USSR. Spacecraft: IS-A, US-A, OGCh. Decree 'On Creation of an R-36 Based Carrier Rocket for Launching the IS and US KA--start of work on an R-36-based launch vehicle for the IS and US programs' was issued. After Khrushchev was ousted from power, Chelomei's projects were examined by an expert commission under M V Keldysh. It was found that Yangel’s R-36 rocket was superior to Chelomei’s UR-200. The UR-200 was cancelled; the IS and US satellites would be launched by the R-36 11K67. The Tsyklon 2 definitive operational version replaced the 11K67 launch vehicle from 1969.
References: 474.
1965 August 24 - Launch Site: Vik. Launch Complex: -. Launch Pad: -. Launch Vehicle: Belier. Model: Dragon 1. LV Configuration: Dragon D-17. -
FU-146 / VLF Aeronomy /ionosphere mission Nation: France. Agency: CNES. Apogee: 440 km (270 mi). References: 2.
1965 August 24 - 16:37 GMT - Launch Site: Vandenberg. Launch Complex: LF06. Launch Pad: -. Launch Vehicle: Minuteman 1. Model: Minuteman 1A. LV Configuration: Minuteman 1A 677. -
Follow-on operational missile test Nation: USA. Agency: SAC 1STRAD. Apogee: 1,000 km (600 mi). References: 2.
1965 August 24 - 21:59 GMT - Launch Site: Wallops Island. Launch Complex: -. Launch Pad: -. Launch Vehicle: Apache. Model: Nike Apache. LV Configuration: Nike Apache NASA 14.210GI. -
Ionosphere mission Nation: USA. Agency: NASA. Apogee: 162 km (100 mi). References: 2.
1965 August 25 - Launch Site: Vandenberg. Launch Complex: -. Launch Pad: -. Launch Vehicle: Titan. Model: Titan 3M. -
MOL to be launched from Canaveral and Vandenberg Nation: USA. Class: Manned. Type: Space station. Spacecraft: MOL. DoD revealed that newly-authorized Manned Orbiting Laboratory (MOL) program (announced by President Lyndon Johnson the same day) would be launched from both the Air Force Eastern and Western Test Ranges. References: 88.
1965 August 25 - -
President Johnson announced approval for the Department of Defense's $1.5-billion Manned Orbiting Laboratory (MOL). Nation: USA. Spacecraft: MOL. At a White House news conference, President Lyndon B. Johnson announced approval for the Department of Defense's development of the $1.5-billion Manned Orbiting Laboratory (MOL). Such a program, the President said, would bring 'new knowledge about what man is able to do in space.' Further, MOL 'will enable us to relate that ability to the defense of America.'
1965 August 25 - 10:19 GMT - Launch Site: Baikonur. Launch Complex: LC1. Launch Pad: -. Launch Vehicle: Soyuz. Model: Voskhod 11A57. LV Configuration: Voskhod 11A57 R15001-06. -
Cosmos 79 Nation: USSR. Mass: 6,300 kg (13,800 lb). Class: Surveillance. Type: Military. Spacecraft: Zenit-4. Agency: MOM. Perigee: 206 km (128 mi). Apogee: 338 km (210 mi). Inclination: 64.90 deg. Period: 89.90 min. COSPAR: 1965-069A. USAF Sat Cat: 1523. Duration: 8.00 days. Decay Date: 1965-09-02. High resolution photo reconnaissance satellite; returned film capsule References: 2, 6.
1965 August 25 - 15:17 GMT - Launch Site: Cape Canaveral. Launch Complex: LC17B. Launch Pad: -. Launch Vehicle: Delta. Model: Thor Delta C. LV Configuration: Thor Delta C 434/D33. FAILURE: Premature third stage ignition. -
OSO C Nation: USA. Payload: OSO C. Mass: 280 kg (610 lb). Class: Solar. Spacecraft: OSO. Agency: NASA. COSPAR: F650825A. Decay Date: 1965-08-25. References: 126.
1965 August 25 - 16:28 GMT - Launch Site: Vandenberg. Launch Complex: LF04. Launch Pad: -. Launch Vehicle: Minuteman 1. Model: Minuteman 1A. LV Configuration: Minuteman 1A 509. -
Follow-on operational missile test Nation: USA. Agency: SAC 1STRAD. Apogee: 1,300 km (800 mi). References: 2.
1965 August 25 - 17:54 GMT - Launch Site: Delamar Dry Lake DZ. Launch Complex: -. Launch Pad: 37.3 N x 114.9 W. Launch Vehicle: X-15. LV Configuration: X-15 1-57-96. -
X-15A MIT Scan,Stability test Nation: USA. Agency: NASA/USAF. Apogee: 65 km (40 mi). Maximum Speed - 5799 kph. Maximum Altitude - 65258 m. References: 2.
1965 August 25 - 18:31 GMT - Launch Site: Wallops Island. Launch Complex: -. Launch Pad: -. Launch Vehicle: Javelin. LV Configuration: Javelin NASA 8.11UA. -
Helium ionization Aeronomy mission Nation: USA. Agency: NASA. Apogee: 902 km (560 mi). References: 2.
1965 August 26 - 00:04 GMT - Launch Site: Vandenberg. Launch Complex: 395-D. Launch Pad: -. Launch Vehicle: Titan. Model: Titan 2. LV Configuration: Titan II B-19. -
New Role operational test Nation: USA. Agency: USAF SAC. Apogee: 1,300 km (800 mi). References: 2.
1965 August 26 - 11:20 GMT - Launch Site: Vandenberg. Launch Complex: 576B2. Launch Pad: -. Launch Vehicle: Atlas. Model: Atlas D. LV Configuration: Atlas D 61D. -
NTMP KX-41 re-entry vehicle test flight Nation: USA. Agency: USAF AFSC. Apogee: 1,800 km (1,100 mi). References: 2.
1965 August 26 - 17:52 GMT - Launch Site: Delamar Dry Lake DZ. Launch Complex: -. Launch Pad: 37.3 N x 114.9 W. Launch Vehicle: X-15. LV Configuration: X-15 3-47-71. -
X-15A Northrop Radiom,BLN Test/Aeronomy mission? Nation: USA. Agency: NASA/USAF. Apogee: 73 km (45 mi). Maximum Speed - 5426 kph. Maximum Altitude - 73030 m. References: 2.
1965 August 26 - 19:03 GMT - Launch Site: Eglin. Launch Complex: -. Launch Pad: -. Launch Vehicle: Aerobee. Model: Aerobee 150. LV Configuration: Aerobee 150 CRL AE3.614. -
Gyro Resonance Ionosphere mission Nation: USA. Agency: USAF. Apogee: 109 km (67 mi). References: 2.
1965 August 27 - Launch Site: Green River. Launch Complex: Pad 2. Launch Pad: -. Launch Vehicle: Athena RTV. LV Configuration: Athena D012. -
USAF D012 re-entry vehicle test flight Nation: USA. Agency: USAF. Apogee: 200 km (120 mi). References: 2.
1965 August 28 - -
Korolev secretly puts Voskhod production on back burner. Nation: USSR. Program: Voskhod, Soyuz. Spacecraft: Soyuz 7K-OK, Voskhod. Flight: Gemini 5, Voskhod 3, Voskhod 4, Voskhod 5, Voskhod 6, Voskhod 7, Soyuz 1, Soyuz 2A, . It is becoming clear that in order to ever get Soyuz into space it is necessary to clear all decks at OKB-1. After Voskhod-2 the Soviet manned space plans are in confusion. The Americans have flown Gemini 5, setting a new 8-day manned space endurance record - the first time the Americans are ahead in the space race. They rubbed salt into the Soviet wound by sending astronauts Cooper and Conrad on a triumphal world tour. This American success is very painful to Korolev, and contributes to his visibly deteriorat
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