Chronology - Quarter 1 1965 home
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1965 January 1 -
  • Almaz space station development authorised. Nation: USSR. Spacecraft: Almaz APOS. Central Committee of the Communist Party and Council of Soviet Ministers Decree 'On work on space stations at OKB-52' was issued. References: 474.
1965 January 1 - Launch Vehicle: Spiral 50-50.
  • Spiral development at MiG bureau authorised. Nation: USSR. Spacecraft: MiG 105-11. Decree 'On plan of work on Spiral at OKB-155' was issued. References: 474.
1965 January 1 -
  • Raketoplan canceled. Nation: USSR. Spacecraft: Raketoplan. Decree 'On end of work on the Raketoplan at OKB-52' was issued. This action was in accordance with the Five Year Military Space Plan approved on 18 June 1964. References: 474.
1965 January 1 -
  • Journalist Cosmonaut Training Group selected. Nation: USSR. The group was selected to provide trainees for a planned Voskhod spaceflight made with a journalist aboard.
1965 - Launch Site: Kapustin Yar. Launch Complex: V-2. Launch Pad: -. Launch Vehicle: RT-15.
  • Test mission Nation: USSR. Agency: RVSN. Apogee: 1,000 km (600 mi). References: 2.
1965 - Launch Site: Nenoksa. Launch Complex: -. Launch Pad: -. Launch Vehicle: R-27. Model: Zyb.
  • Test mission Nation: USSR. Agency: RVSN. Apogee: 500 km (310 mi). References: 2.
1965 During the Year -
  • DS-U5 cancelled. Nation: USSR. Spacecraft: DS-U5. Light satellite with propulsion for periodic correction of orbit; never flown.
1965 During the Year - Launch Vehicle: R-56.
  • Yangel proposes collaborative Soviet moon landing project using R-56 launch vehicle Nation: USSR. Yangel had decided that the bitter fight between Chelomei and Korolev over control of manned programs was damaging the Soviet space effort. In any case he could see that the size of the projects had reached such a scale that it was impossible for one design bureau to handle all of the required elements. He proposed a collaborative effort: Yangel would design and build the launch vehicle; Korolev the manned spacecraft; and Chelomei the unmanned spacecraft. However the leadership was loath to change course with funds already invested in development of boosters and spacecraft by Chelomei and Korolev.
During 1965 - Launch Vehicle: GR-1, N1, R-9, RT-1, RT-2.
  • N1 development issues Nation: USSR. Program: Lunar L3. Spacecraft: Luna E-6, LK, Soyuz 7K-LOK. There were two camps on the N1-L3 control systems. One group was within OKB-1, and had developed the systems for the Vostok and Zenit spacecraft, under the personal oversight of Korolev. They stressed the maximum quality and reliability in their systems. The second group had worked with Pilyugin, and had designed the systems for the Mars, Venus, Luna E-6 probes, the R-9, RT-1, RT-2, and GR-1 missiles; and piloted spacecraft. Their design emphasis was on maximum usability and output. Pilyugin had been named chief designer of the control system for the N1-L3. Additional Details: N1 development issues. References: 367.
January 1965 - Launch Vehicle: CZ-1.
  • Project 651 Nation: China. Spacecraft: DFH-1. Tsien presents his plan for a Chinese satellite to the Central Committee.
1965 January 3 -
  • Kosberg dies Nation: USSR. On the same day that rocket engine designer Kosberg is killed in an automobile crash, Lebedinskiy, Director of the IMBP, dies. The unexpected death of Kosberg, who's engines have reliably taken nine Soviet cosmonauts into orbit, is a particular blow. References: 376.
1965 January 5 -
  • Study of manual control of the Apollo LEM Nation: USA. Program: Apollo. Spacecraft: Apollo LM. MSC's Guidance and Control Division conducted a pilot simulation study to determine whether a pilot could take over manual control of the LEM between 4,572 and 3,048 m (15,000 and 10,000 ft) above the lunar surface and satisfactorily land the vehicle. Additional Details: Study of manual control of the Apollo LEM. References: 16.
1965 January 5 - Launch Vehicle: Titan. Model: Titan 2.
  • NASA Headquarters provided Flight Operations Division with preliminary data for revising the Gemini-Titan (GT) 3 flight plan to cover the possibility of retrorocket failure. Nation: USA. Flight: Gemini 3, Gemini 4. The problem was to ensure the safe reentry of the astronauts even should it become impossible to fire the retrorockets effectively. The Headquarters proposal incorporated three orbit attitude and maneuver system maneuvers to establish a fail-safe orbit from which the spacecraft would reenter the atmosphere whether the retrorockets fired or not. This proposal, as refined by Mission Planning and Analysis Division, became part of the flight plans for GT-3 and GT-4.
1965 January 6 - Launch Vehicle: Titan. Model: Titan 2.
  • Redesigned stage I tandem actuators were received and installed in Gemini launch vehicle (GLV) 2. Nation: USA. Although some retesting began shortly after the Gemini-Titan 2 mission was scrubbed on December 9, 1964, most activity in preparing GLV-2 for another launch attempt was curtailed until the new actuators arrived. Subsystems retesting then began. The final combined systems test - the Simulated Flight Test - was completed January 14, with launch scheduled for January 19.
1965 January 6-8 -
  • Preliminary Design Review of the Apollo Block II CM Nation: USA. Program: Apollo. Spacecraft: Apollo LM. The Preliminary Design Review of the Block II CM was held at North American's Downey, Calif., plant. Ten working groups evaluated the spacecraft design and resolved numerous minor details. They then reported to a review board of NASA and North American officials. Additional Details: Preliminary Design Review of the Apollo Block II CM. References: 16.
1965 January 7 -
  • Revised Apollo launch schedule Nation: USA. Program: Apollo. Spacecraft: Apollo CSM. William A. Lee, chief of ASPO's Operations Planning Division, announced a revised Apollo launch schedule for 1966 and 1967. In 1968, a week-long earth orbital flight would be a dress rehearsal for the lunar mission. "Then the moon," Lee predicted. "We have a fighting chance to make it by 1970," he said, "and also stay within the 20 billion price tag set . . . by former President Kennedy." References: 16.
1965 January 7 - Launch Site: Atlantic Ocean. Launch Complex: -. Launch Pad: 56.5 S x 27.4 W. Launch Vehicle: Iris. Model: Hydra-Iris. LV Configuration: Hydra-Iris SAP-1. FAILURE: Failure.
  • LRL SAP-1 Ionosphere/Magnesium release mission Nation: USA. Agency: USN NMC. Apogee: 2.00 km (1.20 mi). References: 2.
1965 January 7 - 03:50 GMT - Launch Site: Wallops Island. Launch Complex: -. Launch Pad: -. Launch Vehicle: Apache. Model: Nike Apache. LV Configuration: Nike Apache NASA 14.142NA.
  • Airglow Aeronomy mission Nation: USA. Agency: NASA. Apogee: 146 km (90 mi). References: 2.
1965 January 8 - 18:59 GMT - Launch Site: Vandenberg. Launch Complex: OSTF2. Launch Pad: -. Launch Vehicle: Atlas. Model: Atlas F. LV Configuration: Atlas F 106F.
  • ST Nation: USA. Agency: USAF SAC. Apogee: 1,400 km (800 mi). References: 2.
1965 January 9 -
  • Cosmonaut recruitment Nation: USSR. Program: Voskhod. Spacecraft: Voskhod. Flight: Voskhod 5. Kamanin would like to get going with the training of 40 additional cosmonauts from many disciplines in order to 'storm space'. Korolev is opposed. Kamanin is also trying to get new flights scheduled for his female cosmonauts. This is never mentioned in the planning of future flights. Korolev is opposed to sending any further women into space. Kamanin would like to see a two-woman Voskhod flight, or a woman making a spacewalk. Aside from Tereshkova, Ponomaryova and Solovyova are as qualified and talented as any of the male cosmonauts for such flights. Yerkina and Kuznetsova, although they have completed the course, are ruled out by weaknesses in technical areas or character, in Kamanin's opinion. References: 376.
1965 January 11 -
  • Dalmo-Victor to supply antennas for Apollo CSM's Nation: USA. Program: Apollo. Spacecraft: Apollo CSM. North American selected Dalmo-Victor to supply S-band high-gain antennas for Apollo CSM's. (The deployable antenna would be used beyond 14,816 km (8,000 nm) from the earth.) Dalmo-Victor would complete the antenna design and carry out the development work, and North American would procure production units under a supplemental contract. References: 16.
1965 January 11 -
  • LC 16 to be converted to test stands for Apollo Nation: USA. Program: Apollo. Spacecraft: Apollo CSM. NASA announced that Kennedy Space Center's Launch Complex 16, a Titan missile facility, would be converted into static test stands for Apollo spacecraft. This decision eliminated the need for such a facility originally planned on Merritt Island and, it was predicted, would cost little more than a fourth of the $7 million estimated for the new site. References: 16.
1965 January 11 - Launch Site: ETR Launch Area. Launch Complex: -. Launch Pad: -. Launch Vehicle: Polaris. Model: Polaris A3. LV Configuration: Polaris A3P-67.
  • Operational test Nation: USA. Agency: USN. Apogee: 1,000 km (600 mi). References: 2.
1965 January 11 - 09:36 GMT - Launch Site: Baikonur. Launch Complex: LC31. Launch Pad: -. Launch Vehicle: Soyuz. Model: Vostok 8A92. LV Configuration: Vostok 8A92 R15002-03.
  • Cosmos 52 Nation: USSR. Payload: Zenit-2 11F61 s/n 26. Mass: 4,720 kg (10,400 lb). Class: Surveillance. Type: Military. Spacecraft: Zenit-2. Agency: NII-88. Perigee: 203 km (126 mi). Apogee: 298 km (185 mi). Inclination: 65.00 deg. Period: 89.50 min. COSPAR: 1965-001A. USAF Sat Cat: 968. Duration: 8.00 days. Decay Date: 1965-01-19. Area survey photo reconnaissance satellite. References: 2, 6,93.
1965 January 12 -
  • Various designs for the extravehicular mobility unit Nation: USA. Program: Apollo. Spacecraft: Apollo LM. Grumman and Hamilton Standard were exploring various designs for the extravehicular mobility unit. On the basis of some early conclusions, the MSC Crew Systems Division (CSD) recommended that meteoroid and thermal protection be provided by a single garment. Preliminary hypervelocity tests placed the garment's reliability at 0.999. Each would weigh about 7.7 kg (17 lbs), about 2.3 kg (5 lbs) less than the two-garment design. CSD further recommended that the unit be stored either in the LEM's descent stage or in a jettisonable container in the ascent portion. References: 16.
1965 January 12 - Launch Vehicle: Titan. Model: Titan 2.
  • Flight tests of the zero-gravity mock-up of the Gemini spacecraft began. Nation: USA. Flight: Gemini 4. The mock-up was installed in a KC-135 aircraft to provide astronauts with the opportunity to practice extravehicular activities under weightless conditions. The Gemini-Titan (GT) 3 flight crew participated in the opening exercises, which were duplicated the next day by the GT-4 flight crew.
1965 January 12 - Launch Vehicle: Tsiklon.
  • R-36 'sealed round' version development authorised. Nation: USSR. State Committee for Defence Technology (GKOT) Decree 'On Detailed Work on Ampulized R-36 and R-36-O Missiles--design work on the R-36 and R-36-O missiles' was issued. References: 474.
1965 January 12 - 14:32 GMT - Launch Site: Vandenberg. Launch Complex: 576B1. Launch Pad: -. Launch Vehicle: Atlas. Model: Atlas D. LV Configuration: Atlas D 166D.
  • NTMP RMV-302 Target mission Nation: USA. Agency: USAF SAC. Apogee: 1,800 km (1,100 mi). References: 2.
1965 January 13 -
  • OKB-1 program review Nation: USSR. Program: Voskhod. Spacecraft: Voskhod, Berkut. Flight: Voskhod 2. All systems development is complete, and the two boosters for Vykhod are ready. The launch of the pathfinder spacecraft with mannequins aboard will take place at the end of January, with the manned mission scheduled for March. Leonov's spacesuit is complete, but Zaikin's will not be finished until 5 February, and there will exist only the metal detail parts for Gorbatko's suit. References: 376.
1965 January 13 - 05:02 GMT - Launch Site: Baikonur. Launch Complex: LC80/17. 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 January 13 - 15:49 GMT - Launch Site: White Sands. Launch Complex: LC35. Launch Pad: -. Launch Vehicle: Aerobee. Model: Aerobee 150. LV Configuration: Aerobee 150 KP3.9.
  • Dayglow Aeronomy mission Nation: USA. Agency: KPNO. Apogee: 228 km (141 mi). References: 2.
1965 January 13 - 17:12 GMT - Launch Site: Wallops Island. Launch Complex: -. Launch Pad: -. Launch Vehicle: Javelin. LV Configuration: Javelin NASA 8.28UI.
  • Ionosphere mission Nation: USA. Agency: NASA. Apogee: 1,006 km (625 mi). References: 2.
1965 January 13 - 18:51 GMT - Launch Site: Hidden Hills DZ. Launch Complex: -. Launch Pad: 36.1 N x 116.0 W. Launch Vehicle: X-15. LV Configuration: X-15 3-39-62. FAILURE: Control system problems.
  • X-15A 3D,HT,Fric,BLN test Nation: USA. Agency: NASA/USAF. Apogee: 30 km (18 mi). Maximum Speed - 5973 kph. Maximum Altitude - 30297 m. Immediately after burnout aircraft gyrated around all 3 axes for 7 seconds. References: 2.
1965 January 13 - 23:48 GMT - Launch Site: Wallops Island. Launch Complex: -. Launch Pad: -. Launch Vehicle: Aerobee. Model: Aerobee 150. LV Configuration: Aerobee 150 NASA 04.111NA.
  • Airglow Aeronomy mission Nation: USA. Agency: NASA. Apogee: 178 km (110 mi). References: 2.
1965 January 14 -
  • Apollo CM/SM umbilical cutter caused damage to the heatshield Nation: USA. Program: Apollo. Spacecraft: Apollo CSM. During testing, it was found that blast effects of the linear charge for the CM/SM umbilical cutter caused considerable damage to the heatshield. To circumvent this problem, North American designed a vastly improved pyrotechnic-driven, guillotine-type cutter. MSC readily approved the new' device for both Block I and II spacecraft. References: 16.
1965 January 14-21 -
  • Development firings of the Apollo parachute mortars completed Nation: USA. Program: Apollo. Spacecraft: Apollo CSM. Development firings of the launch escape system's drogue and pilot parachute mortars were completed, and the units were slated for qualification trials the following month. References: 16.
1965 January 14 - 12:00 GMT - Launch Site: Vandenberg. Launch Complex: 395-A3. Launch Pad: -. Launch Vehicle: Titan. Model: Titan 1. LV Configuration: Titan I SM-33.
  • ST West Wind III operational test launch Nation: USA. Agency: USAF SAC. Apogee: 1,000 km (600 mi). References: 2.
1965 January 15 - Launch Site: Green River. Launch Complex: Pad 2. Launch Pad: -. Launch Vehicle: Athena RTV. LV Configuration: Athena C006.
  • USAF C006 re-entry vehicle test flight Nation: USA. Agency: USAF. Apogee: 200 km (120 mi). References: 2.
1965 January 15 - 21:00 GMT - Launch Site: Vandenberg. Launch Complex: SLC1E. Launch Pad: -. Launch Vehicle: Delta. Model: Thor SLV-2A Agena D. LV Configuration: Thor SLV-2A Agena D 414 / Agena D SS-01A 1608.
  • KH-4A 1016 Nation: USA. Payload: KH-4A s/n 1016 / Agena D 1608. Mass: 1,500 kg (3,300 lb). Class: Surveillance. Type: Military. Spacecraft: KH-4A. Agency: NRO/CIA. Perigee: 180 km (110 mi). Apogee: 420 km (260 mi). Inclination: 75.00 deg. Period: 90.50 min. COSPAR: 1965-002A. USAF Sat Cat: 972. Decay Date: 1965-02-09. KH-4A. Smearing of highly reflective images due to reflections within camera. References: 2, 6.
1965 January 18 - Launch Site: Vandenberg. Launch Complex: -. Launch Pad: -.
  • Initial West Coast launch of a Thor/Altair. Nation: USA. References: 88.
1965 January 18 -
  • Qualification testing completed of the tanks for the Apollo service propulsion system Nation: USA. Program: Apollo. Spacecraft: Apollo CSM. General Motors' Allison Division completed qualification testing of the propellant tanks for the service propulsion system. References: 16.
1965 January 19 - Launch Vehicle: Titan. Model: Titan 2.
  • Built-in holds in the GLV/Gemini countdown. Nation: USA. The study of 325 missile countdowns, 205 missile launches, as well as all Titan scrubs and holds, indicated that GLV launching would be considerably improved and a great many scrubs precluded by the addition of such holds.
1965 January 19 - 05:03 GMT - Launch Site: Vandenberg. Launch Complex: SLC10W. Launch Pad: -. Launch Vehicle: Delta. Model: Thor MG-18. LV Configuration: Thor MG-18 224.
  • DMSP-Block-4A F1 Nation: USA. Program: DMSP. Payload: DAPP 10. Mass: 150 kg (330 lb). Class: Earth. Type: Weather. Spacecraft: DMSP Block 4A. Agency: USAF. Perigee: 462 km (287 mi). Apogee: 833 km (517 mi). Inclination: 98.80 deg. Period: 97.60 min. COSPAR: 1965-003A. USAF Sat Cat: 973. Decay Date: 1979-07-13. Defense Meteorological Satellite Program. Launch date was January 18, 1965. The launch was successful and correct orbit was achieved. However, the heat shield on the second stage did not deploy correctly and the mission objectives were not fully realized. This first Burner I bird is distinguishable in photos by its black second stage. References: 2, 6.
1965 January 19 - 14:04 GMT - Launch Site: Cape Canaveral. Launch Complex: LC19. Launch Pad: -. Launch Vehicle: Titan. Model: Titan II GLV. LV Configuration: Titan II GLV GT-2.
  • Gemini 2 Nation: USA. Agency: NASA. Apogee: 169 km (105 mi). During the countdown for Gemini-Titan (GT) 2, the fuel cell hydrogen inlet valve failed to open. Efforts to correct the problem continued until it was determined that freeing the valve would delay the countdown. Work on the fuel cell ceased, and it was not activated for the flight. The fuel cell installed in spacecraft No. 2 was not a current flight design. When fuel cell design was changed in January 1964, several cells of earlier design were available. Although these cells were known to have some defects, flight testing with the reactant supply system was felt to be extremely desirable. Accordingly, it was decided to fly the entire system on GT-2, but only on a "non-interference with flight" basis. When it became clear that correcting the problem that emerged during the GT-2 countdown would cause delay, fuel cell activation for the flight was called off. References: 2.
1965 January 20 - Launch Site: Tonopah. Launch Complex: -. Launch Pad: -. Launch Vehicle: Tomahawk Sandia. LV Configuration: Tomahawk Sandia 152-14.
  • Magnus Stovepipe Test / aeronomy mission Nation: USA. Agency: Sandia. Apogee: 106 km (65 mi). References: 2.
1965 January 20 - Launch Site: Vandenberg. Launch Complex: LF03. Launch Pad: -. Launch Vehicle: Minuteman 1. Model: Minuteman 1B. LV Configuration: Minuteman 1B 777.
  • Operational missile test Nation: USA. Agency: SAC 1STRAD. Apogee: 1,300 km (800 mi). References: 2.
1965 January 21 -
  • Apollo dual drogue parachutes in drop test Nation: USA. Program: Apollo. Spacecraft: Apollo CSM. Northrop-Ventura verified the strength of the dual drogue parachutes in a drop test at El Centro, Calif. This was also the first airborne test of the new mortar by which the drogues were deployed and of the new pilot parachute risers, made of steel cables. All planned objectives were met. Additional Details: Apollo dual drogue parachutes in drop test. References: 16.
1965 January 21 - Launch Vehicle: Saturn I. Model: Saturn IB.
  • Requirements for Apollo spacecraft launched by Saturn IB assessed Nation: USA. Program: Apollo. At the request of Maj. Gen. Samuel C. Phillips, Apollo Program Director, ASPO reexamined the performance requirements for spacecraft slated for launch with Saturn IBs. MSC currently assessed that the launch vehicle was able to put 16,102 kg (35,500 lbs) into a circular orbit 105 nm above the earth. Based on the spacecraft control weights, however, it appeared that the total injected weight of the modules would exceed this amount by some 395 kg (870 lbs). Additional Details: Requirements for Apollo spacecraft launched by Saturn IB assessed. References: 16.
1965 January 21 -
  • Cosmonaut examinations completed Nation: USSR. The 15 cosmonaut candidates have all 'graduated' from basic cosmonaut training. The highest scores were by Beregovoi, Shatalov, Gubarev, and Demin. Two days later they officially receive their cosmonaut rating, bringing the total contingent to 34, of which 9 have already been in space. With this contingent the Soviet Union will fly to the moon and man an orbital station. That is insufficient - Kamanin wants a 40-man second contingent. The new contingent will have to be absolutely healthy male specimens, no older than 32 years, under 175 cm in height and 75 kg in weight. Keldysh, Korolev, and Tyulin are against further female flights in space, despite Kamanin's insistence. References: 376.
1965 January 21-28 -
  • STL sole contractor for the Apollo LEM descent engine Nation: USA. Program: Apollo. Spacecraft: Apollo LM, Apollo Lunar Landing. Parallel development of the LEM descent engine was halted. Space Technology Laboratories was named the sole contractor; the Rocketdyne contract was canceled. Grumman estimated that the cost of Rocketdyne's program would be about $25 million at termination. References: 16.
1965 January 21 - 20:30 GMT - Launch Site: White Sands. Launch Complex: LC35. Launch Pad: -. Launch Vehicle: Aerobee. Model: Aerobee 150. LV Configuration: Aerobee 150 NA3.163.
  • Solar extreme ultraviolet / x-ray mission Nation: USA. Agency: NRL. Apogee: 235 km (146 mi). References: 2.
1965 January 21 - 21:34 GMT - Launch Site: Vandenberg. Launch Complex: 576B3. Launch Pad: -. Launch Vehicle: Atlas. Model: Atlas D. LV Configuration: Atlas D 172D. FAILURE: Failure.
  • OV1-01 Nation: USA. Payload: ABRES MTV-1. Mass: 85 kg (187 lb). Class: Earth. Type: Magnetosphere. Spacecraft: OV1. Agency: U.S. Air Force. COSPAR: F650121A. Decay Date: 1965-01-21. Failure. References: 126, 278.
  • OV1-1 Nation: USA. Payload: OV1-1. Spacecraft: OV1. Agency: USAF SAC?. COSPAR: F650121B. References: 279.
1965 January 22 - Launch Site: Beale AFB. Launch Complex: -. Launch Pad: -. Launch Vehicle: Titan. Model: Titan 1.
  • Last Titan I ICBM taken off alert status at Beale AFB Nation: USA.
1965 January 22 - 05:14 GMT - Launch Site: Kagoshima. Launch Complex: -. Launch Pad: -. Launch Vehicle: Kappa. Model: Kappa 9M. LV Configuration: Kappa 9M K-9M-3.
  • Ionosphere mission Nation: Japan. Agency: ISAS. Apogee: 350 km (210 mi). References: 2.
1965 January 22 - 07:52 GMT - Launch Site: Cape Canaveral. Launch Complex: LC17A. Launch Pad: -. Launch Vehicle: Delta. Model: Thor Delta C. LV Configuration: Thor Delta C 374/D28.
  • Tiros 9 Nation: USA. Program: Tiros. Payload: Tiros I (A-54). Mass: 138 kg (304 lb). Class: Earth. Type: Weather. Spacecraft: Tiros. Agency: NASA GSF. Perigee: 705 km (438 mi). Apogee: 2,563 km (1,592 mi). Inclination: 96.40 deg. Period: 119.00 min. COSPAR: 1965-004A. USAF Sat Cat: 978. Spacecraft engaged in practical applications and uses of space technology such as weather or communication (US Cat C). References: 2, 6.
1965 January 23 -
  • Department of Defense requesting proposals for design / development of the MOL. Nation: USA. Spacecraft: MOL. Defense Secretary Robert S. McNamara announced that the Department of Defense was requesting proposals from the aerospace industry for design studies to support development of the MOL (especially cost and technical data). Three contractors would be chosen to conduct the studies, a step preliminary to any DOD decision to proceed with full-scale development of the space laboratory.
1965 January 23 - Launch Site: ETR Launch Area. Launch Complex: -. Launch Pad: -. Launch Vehicle: Polaris. Model: Polaris A3. LV Configuration: Polaris A3P-157.
  • Operational test Nation: USA. Agency: USN. Apogee: 1,000 km (600 mi). References: 2.
1965 January 23 - 20:09 GMT - Launch Site: Vandenberg. Launch Complex: SLC4W. Launch Pad: -. Launch Vehicle: Atlas. Model: SLV-3 Agena D. LV Configuration: SLV-3 Agena D 7106 / Agena D 7106.
  • KH 7-15 Nation: USA. Payload: KH-7 no. 15. Mass: 2,000 kg (4,400 lb). Class: Surveillance. Type: Military. Spacecraft: KH-7. Agency: NRO/USAF. Perigee: 146 km (90 mi). Apogee: 291 km (180 mi). Inclination: 102.50 deg. Period: 88.90 min. COSPAR: 1965-005A. USAF Sat Cat: 980. Decay Date: 1965-01-29. KH-7 type satellite. Space craft engaged in investigation of spaceflight techniques and technology (US Cat A). References: 2, 6, 278.
1965 January 25 -
  • Optimism permeated Apollo program Nation: USA. Program: Apollo. The optimism that permeated the Apollo program was reflected in statements by NASA's Associate Administrator, Robert C. Seamans, Jr., during budget briefings for the forthcoming year. He was "greatly encouraged" by recent design freezes and "very reassured" by testing of propulsion systems and launch vehicle stages. "We really feel," Seamans said, ". . . that we can get off the (lunar landing) flight on an earlier mission than I would have said a year ago?' Certainly it was "conceivable" that the moon landing could come "in early 1970." References: 16.
1965 January 25 -
  • Backup Apollo Block II space suit development program Nation: USA. Program: Apollo. Spacecraft: Apollo CSM, A7L. MSC negotiated a backup Block II space suit development program with David Clark Company, which paralleled the Hamilton Standard program, at a cost of $176,000. Criteria for selecting the suit for ultimate development for Block II would be taken from the Extravehicular Mobility Unit Design and Performance Specification. A selection test program would be conducted at MSC using the CM mockup, the lunar simulation facility, and the LEM mockup. References: 16.
1965 January 25 - Launch Vehicle: Titan. Model: Titan 2.
  • Gemini launch vehicle 3 was erected at complex 19. Nation: USA. Flight: Gemini 3. Power was applied January 29 and Subsystems Functional Verification Tests (SSFVT) commenced. SSFVT were finished February 12. The Combined Systems Test before spacecraft mating was conducted February 15-16.
1965 January 25 - 16:00 GMT - Launch Site: Fort Churchill. Launch Complex: -. Launch Pad: -. Launch Vehicle: Black Brant. Model: Black Brant 2B. LV Configuration: Black Brant IIB CC-2B-48.
  • Test mission Nation: Canada. Agency: NRCC. Apogee: 230 km (140 mi). References: 2.
1965 January 25 - 20:53 GMT - Launch Site: Fort Churchill. Launch Complex: -. Launch Pad: -. Launch Vehicle: Black Brant. Model: Black Brant 2B. LV Configuration: Black Brant IIB CC-2B-56. FAILURE: Failure.
  • Test mission Nation: Canada. Agency: NRCC. Apogee: 20 km (12 mi). References: 2.
1965 January 26 -
  • Apollo Lunar Landing Research Vehicle results Nation: USA. Program: Apollo. Spacecraft: Apollo LLRV. Warren J. North, Chairman of the Lunar Landing Research Vehicle (LLRV) Coordination Panel, reported to MSC Director Robert R. Gilruth that the LLRV had been flown 10 times by Flight Research Center pilots - eight times by Joe Walker and twice by Don Mallick. Maximum altitude achieved was 91 m (300 ft) and maximum forward velocity was 12 m (40 ft) per sec. Additional Details: Apollo Lunar Landing Research Vehicle results. References: 16.
1965 January 26 - 09:40 GMT - Launch Site: Atlantic Ocean. Launch Complex: -. Launch Pad: 35.1 S x 35.5 W. Launch Vehicle: Iris. Model: Hydra-Iris. LV Configuration: Hydra-Iris SAP-2.
  • LRL SAP-2 (SAA) Ionosphere / magnetosphere mission Nation: USA. Agency: USN NMC. Apogee: 289 km (179 mi). References: 2.
1965 January 27 - Launch Site: Barking Sands. Launch Complex: -. Launch Pad: -. Launch Vehicle: Tomahawk Sandia. Model: Nike Tomahawk. LV Configuration: Nike Tomahawk-9a Sandia 152-23.
  • Ballistic (TTR?) test Nation: USA. Agency: Sandia. Apogee: 302 km (187 mi). References: 2.
1965 January 27 - 21:32 GMT - Launch Site: Wallops Island. Launch Complex: -. Launch Pad: -. Launch Vehicle: Cajun. Model: Nike Cajun. LV Configuration: Nike Cajun NASA 10.118GA.
  • Grenades Aeronomy mission Nation: USA. Agency: NASA. Apogee: 117 km (72 mi). References: 2.
1965 January 28 - Launch Vehicle: Saturn V.
  • First major Saturn V flight component delivered Nation: USA. Program: Apollo. The first major Saturn V flight component, a 10-m (33-ft) diameter, 27,215 kg (60,000 lb corrugated tail section which would support the booster's 6,672 kilonewtons (1.5-million-lb) thrust engines, arrived at MSFC from NASA's Michoud Operations near New Orleans. The section was one of five major structural units comprising Saturn V's first stage. References: 16.
1965 January 28 - 04:24 GMT - Launch Site: Fort Churchill. Launch Complex: -. Launch Pad: -. Launch Vehicle: Cajun. Model: Nike Cajun. LV Configuration: Nike Cajun NASA 10.121GA.
  • Grenades Aeronomy mission Nation: USA. Agency: NASA. Apogee: 125 km (77 mi). References: 2.
1965 January 28 - 12:51 GMT - Launch Site: Cape Canaveral. Launch Complex: LC18A. Launch Pad: LC18A. Launch Vehicle: Scout. Model: Blue Scout Jr. LV Configuration: Blue Scout Jr 22-3. FAILURE: Failure.
  • OAR 22-3 / AFCRL-309 Magnetosphere mission Nation: USA. Agency: USAF. Apogee: 200 km (120 mi). References: 2.
1965 January 29 -
  • Emergency defecation capability added to the Apollo LEM Nation: USA. Program: Apollo. Spacecraft: Gemini. ASPO concurred with the requirement to provide an emergency defecation capability aboard the LEM as established by MSC's Center Medical Programs Office. The addition of a Gemini-type defecation glove appeared to present a satisfactory solution. Crew Systems Division was directed to proceed with their recommendation and add the Gemini gloves to the LEM crew provisions. References: 16.
1965 January 29 -
  • Apollo boilerplate 28 second water impact test Nation: USA. Program: Apollo. Spacecraft: Apollo CSM. Apollo boilerplate 28 underwent its second water impact test. Despite its strengthened aft structure, in this and a subsequent drop on February 9 the vehicle again suffered damage to the aft heatshield and bulkhead, though far less severe than that experienced in its initial test. The impact problem, it was obvious, was not yet solved. References: 16.
1965 January 29 - Launch Vehicle: Titan. Model: Titan 2.
  • Qualification testing of the food, water, and waste management systems for the Gemini-Titan 3 mission was completed. Nation: USA. Flight: Gemini 3.
1965 January 29 -
  • Manned Vykhod airlock test fails. Nation: USSR. Program: Voskhod. Spacecraft: Voskhod, Berkut. Flight: Voskhod 2. The first manned test of the airlock fails before an audience of 60 government and industry leaders. A VVS pilot in a spacesuit was to demonstrate the entire sequence involved in exiting into space. (release of the forward ring, inflation of the airlock, opening of the hatch between the spacecraft and airlock, closing the hatch, evacuation of the air from the airlock, opening of the outer hatch of the airlock, then the sequence in reverse). Two attempts are made at 15 km equivalent altitude, but the hatch from the spacecraft to the airlock cannot be opened due to defects in its construction in the first try. This is fixed, but on the second try the Vega system that monitors the cosmonaut's condition fails. References: 376.
1965 January 29 - Launch Site: Cape Canaveral. Launch Complex: LC31B. Launch Pad: -. Launch Vehicle: Minuteman 2. LV Configuration: Minuteman 2 453.
  • Research and development launch Nation: USA. Agency: USAF AFSC. Apogee: 1,300 km (800 mi). References: 2.
1965 January 30 - 07:45 GMT - Launch Site: White Sands. Launch Complex: LC35. Launch Pad: -. Launch Vehicle: Aerobee. Model: Aerobee 150. LV Configuration: Aerobee 150 NF3.162.
  • Infrared astronomy mission Nation: USA. Agency: NRL. Apogee: 211 km (131 mi). References: 2.
1965 January 30 - 08:04 GMT - Launch Site: Baikonur. Launch Complex: LC67/22. Launch Pad: -. Launch Vehicle: Tsiklon. Model: R-36 8K67.
  • POR state trials missile launch Nation: USSR. Agency: RVSN. Apogee: 1,493 km (927 mi). References: 2.
1965 January 30 - 09:36 GMT - Launch Site: Kapustin Yar. Launch Complex: LC86/1. Launch Pad: -. Launch Vehicle: Kosmos 2. Model: Kosmos 63S1.
  • Cosmos 53 Nation: USSR. Program: DS. Payload: DS-A1 s/n 5. Mass: 310 kg (680 lb). Class: Technology. Type: Navigation. Spacecraft: DS-A1. Agency: MO SSSR. Perigee: 221 km (137 mi). Apogee: 1,172 km (728 mi). Inclination: 48.70 deg. Period: 98.70 min. COSPAR: 1965-006A. USAF Sat Cat: 983. Completed Operations Date: 1965-02-09. Decay Date: 1966-08-12. 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 January -
  • Grumman modified the Apollo LEM's forward hatch Nation: USA. Program: Apollo. Spacecraft: Apollo LM. To make it easier to get in and out of the spacecraft, Grumman modified the LEM's forward hatch. During mobility tests on the company's mockup, a hinged, trapezoidal-shaped door had proved superior to the original circular hatch, so the earlier design was dropped. References: 16.
1965 January 31 - 05:01 GMT - Launch Site: Kagoshima. Launch Complex: L. Launch Pad: -. Launch Vehicle: Lambda. Model: Lambda 3. LV Configuration: Lambda 3 L-3-2.
  • Ionosphere mission Nation: Japan. Agency: ISAS. Apogee: 1,040 km (640 mi). References: 2.
1965 February 1 - Launch Site: Vandenberg. Launch Complex: -. Launch Pad: -.
  • AFWTR replaces PMR. Nation: USA. Five months ahead of the original schedule, Air Force Western Test Range (AFWTR) assumed responsibilities for intercontinental ballistic missile and space vehicle support functions from the Navy's Pacific Missile Range. References: 88.
1965 February 1 - Launch Site: Ellsworth AFB. Launch Complex: -. Launch Pad: -. Launch Vehicle: Titan. Model: Titan 1.
  • Last Titan I ICBM taken off alert status at Ellsworth AFB Nation: USA.
1965 February 1 - Launch Site: Ile du Levant. Launch Complex: -. Launch Pad: CERES. Launch Vehicle: Jericho.
  • Tir 1 test Nation: Israel. Agency: Dassault. Apogee: 100 km (60 mi). First launch of prototype single-stage MD.620. References: 2.
1965 February 2 -
  • Cosmonaut organisation Nation: USSR. Program: Lunar L1, Lunar L3. Spacecraft: Soyuz A, Soyuz B, Soyuz V, LK-1, Soyuz PPK, Soyuz R. Kamanin will organise the cosmonauts into two groups: the first group will be commanded by Nikolayev, and the latest group by Beregovoi. They will be assigned to support and train seven missions: military space (reconnaissance, interceptor, and combat spacecraft); space navigation; life support and rescue systems; communications and telemetry systems; scientific orbital stations; lunar fly-by; and lunar landing expeditions. All of this may be for nought, since Marshall Malinovskiy has said that heavy launch vehicles and lunar flights have no military utility and should be funded and handled by the Academy of Science. References: 376.
1965 February 2 - Launch Site: Larson AFB. Launch Complex: -. Launch Pad: -. Launch Vehicle: Titan. Model: Titan 1.
  • Last Titan I ICBM taken off alert status at Larson AFB Nation: USA.
1965 February 2 - Launch Site: Tonopah. Launch Complex: -. Launch Pad: -. Launch Vehicle: Tomahawk Sandia. LV Configuration: Tomahawk Sandia 152-17.
  • Magnus Test / aeronomy mission Nation: USA. Agency: Sandia. Apogee: 106 km (65 mi). References: 2.
1965 February 2 - Launch Site: Vandenberg. Launch Complex: LF02. Launch Pad: -. Launch Vehicle: Minuteman 1. Model: Minuteman 1B. LV Configuration: Minuteman 1B 1041.
  • Operational missile test Nation: USA. Agency: SAC 1STRAD. Apogee: 1,300 km (800 mi). References: 2.
1965 February 2 - Launch Site: Vandenberg. Launch Complex: LF08. Launch Pad: -. Launch Vehicle: Minuteman 1. Model: Minuteman 1B. LV Configuration: Minuteman 1B 714.
  • Operational missile test Nation: USA. Agency: SAC 1STRAD. Apogee: 1,300 km (800 mi). References: 2.
1965 February 2 - 06:30 GMT - Launch Site: Green River. Launch Complex: Pad 2. Launch Pad: -. Launch Vehicle: Athena RTV. LV Configuration: Athena D003. FAILURE: Failure.
  • USAF D003 re-entry vehicle test flight Nation: USA. Agency: USAF. Apogee: 50 km (31 mi). References: 2.
1965 February 2 - 09:57 GMT - Launch Site: Woomera. Launch Complex: LA2. Launch Pad: -. Launch Vehicle: HAD. LV Configuration: HAD 152.
  • Aeronomy mission Nation: Australia. Agency: WRE. Apogee: 123 km (76 mi). References: 2.
1965 February 2 - 20:50 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 3-40-63.
  • X-15A MA-25S TPS,MH-96,BLN Test/Technology mission Nation: USA. Agency: NASA/USAF. Apogee: 29 km (18 mi). Maximum Speed - 6253 kph. Maximum Altitude - 29931 m. References: 2.
1965 February 3 -
  • Vykhod airlock experiments Nation: USSR. Program: Voskhod. Spacecraft: Voskhod. Flight: Voskhod 2. At Chkalovskiy Airfield, the Vykhod airlock experiments are repeated, this time to an altitude of 37 km. This time the tests, run at up to 37 km equivalent altitude, are successful. The cosmonaut's pulse reached 90-108 per minute during the effort to get into the lock and open it. In all the test took two hours, but Korolev was pleased with the results. But afterwards he differs with Kamanin in the need for a 16-m arm centrifuge to be used for cosmonaut training. It should mainly be used by industry, Korolev believes. References: 376.
1965 February 3 - Launch Site: Tonopah. Launch Complex: -. Launch Pad: -. Launch Vehicle: Tomahawk Sandia. LV Configuration: Tomahawk Sandia 152-47.
  • Magnus Test / aeronomy mission Nation: USA. Agency: Sandia. Apogee: 106 km (65 mi). References: 2.
1965 February 3 - 16:36 GMT - Launch Site: Cape Canaveral. Launch Complex: LC17B. Launch Pad: -. Launch Vehicle: Delta. Model: Thor Delta C. LV Configuration: Thor Delta C 411/D29.
  • OSO 2 Nation: USA. Payload: OSO B2 (S-17). Mass: 247 kg (544 lb). Class: Solar. Spacecraft: OSO. Agency: NASA GSF. Perigee: 294 km (182 mi). Apogee: 306 km (190 mi). Inclination: 32.80 deg. Period: 90.50 min. COSPAR: 1965-007A. USAF Sat Cat: 987. Decay Date: 1989-08-09. Orbiting Solar Observatory; returned solar X-ray, UV, gamma ray data. Spacecraft engaged in research and exploration of the upper atmosphere or outer space (US Cat B). References: 2, 6.
1965 February 3 - 18:08 GMT - Launch Site: Wallops Island. Launch Complex: -. Launch Pad: -. Launch Vehicle: Apache. Model: Nike Apache. LV Configuration: Nike Apache NASA 14.61UE.
  • UNH Particles Plasma mission Nation: USA. Agency: NASA. Apogee: 141 km (87 mi). References: 2.
1965 February 4 - 04:45 GMT - Launch Site: Point Barrow. Launch Complex: -. Launch Pad: -. Launch Vehicle: Cajun. Model: Nike Cajun. LV Configuration: Nike Cajun NASA 10.125GA.
  • Grenades Aeronomy mission Nation: USA. Agency: NASA. Apogee: 121 km (75 mi). References: 2.
1965 February 4 - 05:10 GMT - Launch Site: Wallops Island. Launch Complex: -. Launch Pad: -. Launch Vehicle: Cajun. Model: Nike Cajun. LV Configuration: Nike Cajun NASA 10.119GA.
  • Grenades Aeronomy mission Nation: USA. Agency: NASA. Apogee: 118 km (73 mi). References: 2.
1965 February 5 -
  • Apollo SM 001's service propulsion engine static-fired Nation: USA. Program: Apollo. Spacecraft: Apollo CSM. SM 001's service propulsion engine was static-fired for 10 sec at White Sands. The firing was the first in a program to verify the mission profiles for later flight tests of the module. (SM 001 was the first major piece of flight-weight Apollo hardware.) References: 16.
1965 February 5 - Launch Vehicle: Titan. Model: Titan 2.
  • Modifications to Gemini launch vehicle 5 were completed and stage I was erected in the vertical test facility at Martin-Baltimore. Nation: USA. Flight: Gemini 5. Stage II was erected February 8. Power was applied to the vehicle for the first time on February 15, and Subsystems Functional Verification Tests were completed March 8. Another modification period followed.
1965 February 5 -
  • Vykhod redesignated Voskhod 2 Nation: USSR. Program: Voskhod. Spacecraft: Voskhod. Flight: Voskhod 2. The 3KD spacecraft will be known as Voskhod-2 rather than Vykhod. It was felt that 'Vykhod' ('exit') would reveal the purpose of the flight, which should not be revealed unless the experiment succeeds. The cosmonauts are training very hard in the zero-G trainer and will use the airlock at 37 km equivalent vacuum in the TBK-60 on 8 February. The motto is "Train hard to make it easy to do". References: 376.
1965 February 6 - Launch Site: ETR Launch Area. Launch Complex: -. Launch Pad: -. Launch Vehicle: Polaris. Model: Polaris A2.
  • Operational test Nation: USA. Agency: USN. Apogee: 1,000 km (600 mi). References: 2.
1965 February 6 - Launch Site: ETR Launch Area. Launch Complex: -. Launch Pad: -. Launch Vehicle: Polaris. Model: Polaris A2.
  • Operational test Nation: USA. Agency: USN. Apogee: 1,000 km (600 mi). References: 2.
1965 February 6 - Launch Site: ETR Launch Area. Launch Complex: -. Launch Pad: -. Launch Vehicle: Polaris. Model: Polaris A2.
  • Operational test Nation: USA. Agency: USN. Apogee: 1,000 km (600 mi). References: 2.
1965 February 6 - Launch Site: ETR Launch Area. Launch Complex: -. Launch Pad: -. Launch Vehicle: Polaris. Model: Polaris A2.
  • Operational test Nation: USA. Agency: USN. Apogee: 1,000 km (600 mi). References: 2.
1965 February 6 - 05:01 GMT - Launch Site: Kagoshima. Launch Complex: -. Launch Pad: -. Launch Vehicle: Kappa. Model: Kappa 9M. LV Configuration: Kappa 9M K-9M-7.
  • Ionosphere mission Nation: Japan. Agency: ISAS. Apogee: 325 km (201 mi). References: 2.
1965 February 6 - 10:02 GMT - Launch Site: Kagoshima. Launch Complex: -. Launch Pad: -. Launch Vehicle: Kappa. Model: Kappa 9M. LV Configuration: Kappa 9M K-9M-6.
  • Solar radio frequencies mission Nation: Japan. Agency: ISAS. Apogee: 335 km (208 mi). References: 2.
1965 February 8 -
  • Requirement deleted for a rendezvous radar in the Apollo CSM Nation: USA. Program: Apollo. Spacecraft: Apollo CSM. MSC deleted the requirement for a rendezvous radar in the CSM. References: 16.
1965 February 8 -
  • Scientists invited to a conference on the Gemini and Apollo missions Nation: USA. Program: Apollo. Spacecraft: Gemini. NASA invited 113 scientists and 23 national space organizations to a conference at MSC to brief them on the Gemini and Apollo missions. As a result of the conference, NASA hoped to receive proposals for biomedical experiments to be performed in Gemini and Apollo spacecraft. References: 16.
1965 February 8 - Launch Vehicle: Titan. Model: Titan 2.
  • Manned Spacecraft Center announced the selection of L. Gordon Cooper, Jr., as command pilot and Charles Conrad, Jr., as pilot for the seven-day Gemini-Titan 5 mission. Nation: USA. Flight: Gemini 5. Backup crew would be Neil A. Armstrong and Elliot M. See, Jr.
1965 February 8 -
  • Voskhod 2 crew vacuum chamber tests Nation: USSR. Program: Voskhod. Spacecraft: Voskhod. Flight: Voskhod 1. Belyayev and Leonov practice deploying and exiting the airlock at 37 km equivalent altitude in the TBK-60 chamber. The Vega system for keeping track of the spacewalking cosmonaut's life signs fails again. Kamanin is infuriated. Later he discusses future spaceflight plans with Korolev, who was supposed to deliver five Voskhods in 1965. Korolev says that three spacecraft will only be completed by October, and should only be available for flights at the end of the year. He wants to use one as a biosat in an unmanned flight of organisms for 30 days; a second for the flight of a cosmonaut pilot and physician for 15 days; and the third for flight of a cosmonaut and engineer to perform an artificial gravity experiment. Two further spacecraft will be finished to the Vykhod configuration in October 1965 for flights in March 1966. Nothing is official yet, and Kamanin urges that the necessary resolutions be passed as soon as possible so that training can begin. He thought before that there was little chance that Yegorov's back-ups, Lazarev and Sorokin would fly, but now he puts them back in training so they will be ready for this flight schedule. But Korolev remains opposed to flying either candidate. References: 376.
1965 February 8 - Launch Site: ETR Launch Area. Launch Complex: -. Launch Pad: -. Launch Vehicle: Polaris. Model: Polaris A3. LV Configuration: Polaris A3P-5.
  • Operational test Nation: USA. Agency: USN. Apogee: 1,000 km (600 mi). References: 2.
1965 February 8 - Launch Site: Vandenberg. Launch Complex: LF09. Launch Pad: LF09?. Launch Vehicle: Minuteman 1. Model: Minuteman 1B. LV Configuration: Minuteman 1B 1142.
  • Operational missile test Nation: USA. Agency: SAC 1STRAD. Apogee: 1,300 km (800 mi). References: 2.
1965 February 8 - 22:15 GMT - Launch Site: Point Barrow. Launch Complex: -. Launch Pad: -. Launch Vehicle: Cajun. Model: Nike Cajun. LV Configuration: Nike Cajun NASA 10.126GA.
  • Grenades Aeronomy mission Nation: USA. Agency: NASA. Apogee: 124 km (77 mi). References: 2.
1965 February 8 - 22:53 GMT - Launch Site: Wallops Island. Launch Complex: -. Launch Pad: -. Launch Vehicle: Cajun. Model: Nike Cajun. LV Configuration: Nike Cajun NASA 10.120GA.
  • Grenades Aeronomy mission Nation: USA. Agency: NASA. Apogee: 107 km (66 mi). References: 2.
1965 February 8 - 22:58 GMT - Launch Site: Fort Churchill. Launch Complex: -. Launch Pad: -. Launch Vehicle: Cajun. Model: Nike Cajun. LV Configuration: Nike Cajun NASA 10.123GA.
  • Grenades Aeronomy mission Nation: USA. Agency: NASA. Apogee: 165 km (102 mi). References: 2.
1965 February 9 - Launch Vehicle: Saturn V.
  • First ground test model of the S-II stage completed Nation: USA. Program: Apollo. North American completed the first ground test model of the S-II stage of the Saturn V. References: 16.
1965 February 9 -
  • Voskhod 2 crew selection. Nation: USSR. Program: Voskhod. Spacecraft: Voskhod. Flight: Voskhod 2. The State Commission meets to consider Voskhod 2 crew assignments. Belyayev and Leonov are named the prime crew, with Zaikin and Khrunov as their back-ups. References: 376.
1965 February 10 - Launch Vehicle: N1.
  • L3 single-launch spacecraft draft project approved. Nation: USSR. Program: Lunar L3. Spacecraft: LK, Soyuz 7K-LOK. Interdepartmental Scientific-Technical Council on Space Research (MNTS-KI) Decree 'On approval of the L3 draft project' was issued. The decree followed a review by a Keldysh-led Academy of Sciences state commission the previous December. The decree moved the first flight of the N1 to the end of 1966. Additional Details: L3 single-launch spacecraft draft project approved.. References: 21, 367, 474.
1965 February 11 -
  • Drogue parachutes tested to ultimate load Nation: USA. Program: Apollo. Spacecraft: Apollo CSM. A drop test at EI Centro, Calif., demonstrated the ability of the drogue parachutes to sustain the ultimate disreefed load that would be imposed upon them during reentry. (For the current CM weight, that maximum load would be 7,711 kg (17,000 lbs) per parachute.) Preliminary data indicated that the two drogues had withstood loads of 8,803 and 8,165 kg (19,600 and 18,000 lbs). One of the drogues emerged unscathed; the other suffered only minor damage near the pocket of the reefing cutter. References: 16.
1965 February 11-18 -
  • Use of the Apollo LEM as a backup for the service propulsion system Nation: USA. Program: Apollo. Spacecraft: Apollo LM. To make room for a rendezvous study, MSC was forced to end, prematurely, its simulations of employing the LEM as a backup for the service propulsion system. Nonetheless, the LEM was evaluated in both manual and automatic operation. Although some sizable attitude changes were required, investigators found no serious problems with either steering accuracy or dynamic stability. References: 16.
1965 February 11-18 -
  • Three-foot probes on the Apollo LEM landing gear Nation: USA. Program: Apollo. Spacecraft: Apollo LM. Evaluations of the three-foot probes on the LEM landing gear showed that the task of shutting off the engine prior to actual touchdown was even more difficult than controlling the vehicle's rate of descent. During simulated landings, about 70 percent of the time the spacecraft was less than 0.3 m (1 ft) high when shutdown came; on 20 percent of the runs, the engine was still burning at touchdown. Some change, either in switch location or in procedure, thus appeared necessary to shorten the delay between contact light and engine cutoff (an average of 0.7 sec). References: 16.
1965 February 11 - 15:19 GMT - Launch Site: Cape Canaveral. Launch Complex: LC20. Launch Pad: -. Launch Vehicle: Titan. Model: Titan 3A. LV Configuration: Titan IIIA 3A-3.
  • LES 1 Nation: USA. Mass: 31 kg (68 lb). Class: Technology. Type: Comsat. Spacecraft: LES. Agency: USAF. Perigee: 2,783 km (1,729 mi). Apogee: 2,809 km (1,745 mi). Inclination: 32.10 deg. Period: 145.80 min. COSPAR: 1965-008C. USAF Sat Cat: 1002. Lincoln Experimental Satellite; communications experiments. Space craft engaged in investigation of spaceflight techniques and technology (US Cat A). References: 2, 6.
1965 February 11 - 17:55 GMT - Launch Site: White Sands. Launch Complex: LC35. Launch Pad: -. Launch Vehicle: Aerobee. Model: Aerobee 150. LV Configuration: Aerobee 150 AE3.153.
  • Solar spectrum Solar ultraviolet / solar extreme ultraviolet mission Nation: USA. Agency: USAF. Apogee: 200 km (120 mi). References: 2.
1965 February 12 - Launch Vehicle: Titan. Model: Titan 2.
  • Gemini-Titan (GT) 3 mission might be flown between March 22 and 25, 1965. Nation: USA. Flight: Gemini 4. Director of Flight Operations Christopher C. Kraft, Jr., told the Manned Spacecraft Center senior staff that the Gemini-Titan (GT) 3 mission might be flown between March 22 and 25, although it was officially scheduled for the second quarter of 1965. In addition, the Houston control center was being considered for use in the GT-4 mission.
1965 February 12 -
  • Cosmos 57 delayed Nation: USSR. Program: Voskhod. Spacecraft: Voskhod. Flight: Voskhod 2. Once again the primary Tral system aboard the spacecraft has failed, and it will take 7 to 8 days to replace. Korolev, Kamanin, and the other leaders return to Moscow. References: 376.
1965 February 12 - Launch Site: ETR Launch Area. Launch Complex: -. Launch Pad: -. Launch Vehicle: Polaris. Model: Polaris A2.
  • Operational test Nation: USA. Agency: USN. Apogee: 1,000 km (600 mi). References: 2.
1965 February 12 - Launch Site: ETR Launch Area. Launch Complex: -. Launch Pad: -. Launch Vehicle: Polaris. Model: Polaris A2.
  • Operational test Nation: USA. Agency: USN. Apogee: 1,000 km (600 mi). References: 2.
1965 February 12 - Launch Site: Hammaguira. Launch Complex: Blandine. Launch Pad: -. Launch Vehicle: Veronique. LV Configuration: Veronique AGI56.
  • Solar mission Nation: France. Agency: FR. Apogee: 95 km (59 mi). References: 2.
1965 February 12 - Launch Site: Green River. Launch Complex: Pad 3. Launch Pad: -. Launch Vehicle: Athena RTV. LV Configuration: Athena D002. FAILURE: Failure.
  • USAF D002 re-entry vehicle test flight Nation: USA. Agency: USAF. Apogee: 0 km ( mi). References: 2.
1965 February 12 - Launch Site: Kapustin Yar. Launch Complex: LC86/1. Launch Pad: -. Launch Vehicle: Kosmos 2. Model: Kosmos 63S1. FAILURE: Second stage failed.
  • DS-P1-Yu s/n 2 Nation: USSR. Program: DS. Payload: DS-P1-Yu. Class: Military. Type: Target. Spacecraft: DS-P1-Yu. Agency: RVSN. COSPAR: F650212A. Development of systems for air defence and the control of outer space. References: 2.
1965 February 15 - 16:30 GMT - Launch Site: ETR Launch Area. Launch Complex: -. Launch Pad: -. Launch Vehicle: Polaris. Model: Polaris A3. LV Configuration: Polaris A3P-171.
  • Operational test Nation: USA. Agency: USN. Apogee: 1,000 km (600 mi). References: 2.
1965 February 16 -
  • Apollo hardware delivery schedules changed Nation: USA. Program: Apollo. Spacecraft: Apollo CSM. In a memorandum to ASPO, Samuel C. Phillips, Apollo Program Director, inquired about realigning the schedules of contractors to meet revised delivery and launch timetables for Apollo. Phillips tentatively set forth deliveries of six spacecraft (CSM/LEMs) during 1967 and eight during each succeeding year; he outlined eight manned launches per year also, starting in 1969. References: 16.
1965 February 16 -
  • Specialty areas for 13 astronauts not assigned to Gemini Nation: USA. Program: Apollo. Spacecraft: Apollo LM. MSC announced a realignment of specialty areas for the 13 astronauts not assigned to forthcoming Gemini missions (GT 3 through 5) or to strictly administrative positions:

    Operations and Training
    Edwin E. Aldrin, branch chief - mission planning

    Charles A. Bassett - operations handbooks, training, and simulators

    Alan L. Bean - recovery systems

    Michael Collins - pressure suits and extravehicular activity

    David R. Scott - mission planning and guidance and navigation

    Clifton C. Williams - range operations, deep space instrumentation, and crew safety.

    Project Apollo
    Richard F. Gordon, branch chief - overall astronaut activities in Apollo area and liaison for CSM development

    Donn F. Eisele - CSM and LEM

    William A. Anders - environmental control system and radiation and thermal systems

    Eugene A. Cernan - boosters, spacecraft propulsion, and the Agena stage

    Roger B. Chaffee - communications, flight controls, and docking

    R. Walter Cunningham - electrical and sequential systems and non-flight experiments

    Russell L. Schweickart - in-flight experiments and future programs.

    References: 16.
1965 February 16 - 05:00 GMT - Launch Site: Green River. Launch Complex: Pad 1. Launch Pad: -. Launch Vehicle: Athena RTV. LV Configuration: Athena D008. FAILURE: Failure.
  • USAF D008 re-entry vehicle test flight Nation: USA. Agency: USAF. Apogee: 10 km (6 mi). References: 2.
1965 February 16 - 14:37 GMT - Launch Site: Cape Canaveral. Launch Complex: LC37B. Launch Pad: -. Launch Vehicle: Saturn I. Model: Saturn I. LV Configuration: Saturn I-Blk2 SA-9.
  • Pegasus 1 Nation: USA. Program: Apollo. Payload: Pegasus 1. Mass: 10,400 kg (22,900 lb). Class: Earth. Type: Micrometeoroid. Spacecraft: Pegasus. Agency: NASA MSF. Perigee: 510 km (310 mi). Apogee: 726 km (451 mi). Inclination: 31.70 deg. Period: 97.00 min. COSPAR: 1965-009A. USAF Sat Cat: 1085. Decay Date: 1978-09-17. A Saturn I vehicle SA-9 launched a multiple payload into a high 744 by 496 km (462 by 308 mi) earth orbit. The rocket carried a boilerplate (BP) CSM (BP-16) and, fitted inside the SM, the Pegasus I meteoroid detection satellite. This was the eighth successful Saturn flight in a row, and the first to carry an active payload. BP-16's launch escape tower was jettisoned following second-stage S-IV ignition. After attaining orbit, the spacecraft were separated from the S-IV. Thereupon the Pegasus I's panels were deployed and were ready to perform their task, i.e., registering meteoroid impact and relaying the information to the ground. References: 2, 6, 16, 26, 27.
  • Apollo-Model 3 Nation: USA. Program: Apollo. Payload: Apollo CSM Boilerplate 16. Class: Manned. Type: Lunar spacecraft. Spacecraft: Apollo CSM. Agency: NASA MSC. Perigee: 500 km (310 mi). Apogee: 736 km (457 mi). Inclination: 31.70 deg. Period: 97.06 min. COSPAR: 1965-009B. USAF Sat Cat: 1088. Decay Date: 1985-07-10. References: 2, 279.
1965 February 17 -
  • Increase in the Apollo CM's land landing capability Nation: USA. Program: Apollo. Spacecraft: Apollo CSM. North American proposed an idea for increasing the CM's land landing capability. This could be done, the company asserted, by raising the water impact limits (thus exceeding normal tolerances) and stiffening the shock struts. Additional Details: Increase in the Apollo CM's land landing capability. References: 16.
1965 February 17 - Launch Vehicle: Titan. Model: Titan 2.
  • Gemini launch vehicle 3 and spacecraft No. 3 were mechanically mated on complex 19. Nation: USA. Flight: Gemini 3. The Electrical Interface Integrated Validation Test was completed February 19, the Joint Guidance and Control Test on February 22. Gemini-Titan 3 combined systems testing included the Joint Combined Systems Test on February 24 and the Flight Configuration Mode Test on March 3.
1965 February 17 - 17:05 GMT - Launch Site: Cape Canaveral. Launch Complex: LC12. Launch Pad: -. Launch Vehicle: Atlas. Model: Atlas Agena B. LV Configuration: Atlas Agena B 196D (AA13) / Agena B 6006 (AA13).
  • Ranger 8 Nation: USA. Program: Ranger. Payload: RA-8. Mass: 366 kg (806 lb). Class: Planetary. Type: Lunar. Spacecraft: Ranger 6-7-8-9. Agency: NASA/JPL. COSPAR: 1965-010A. USAF Sat Cat: 1086. Decay Date: 1965-02-20. Returned 7137 photos before lunar impact. The Atlas- Agena B booster injected the Agena and Ranger 8 into an Earth parking orbit at 185 km altitude 7 minutes after launch. Fourteen minutes later a 90 second burn of the Agena put the spacecraft into lunar transfer trajectory, and several minutes later the Ranger and Agena separated. The Ranger solar panels were deployed, attitude control activated, and spacecraft transmissions switched from the omni-directional antenna to the high-gain antenna by 21:30 GMT. On 18 February at a distance of 160,000 km from Earth the planned mid-course manoeuvre took place, involving reorientation and a 59 second rocket burn. During the 27 minute manoeuvre, spacecraft transmitter power dropped severely, so that lock was lost on all telemetry channels. This continued intermittently until the rocket burn, at which time power returned to normal. The telemetry dropout had no serious effects on the mission. A planned terminal sequence to point the cameras more in the direction of flight just before reaching the Moon was cancelled to allow the cameras to cover a greater area of the Moon's surface.

    Ranger 8 reached the Moon on 20 February 1965. The first image was taken at 9:34:32 GMT at an altitude of 2510 km. Transmission of 7,137 photographs of good quality occurred over the final 23 minutes of flight. The final image taken before impact has a resolution of 1.5 meters. The spacecraft encountered the lunar surface in a direct hyperbolic trajectory, with incoming asymptotic direction at an angle of -13.6 degrees from the lunar equator. The orbit plane was inclined 16.5 degrees to the lunar equator. After 64.9 hours of flight, impact occurred at 09:57:36.756 GMT on 20 February 1965 in Mare Tranquillitatis at approximately 2.67 degrees N, 24.65 degrees E. Impact velocity was slightly less than 2.68 km/s. References: 2, 6, 278, 296.

1965 February 17 - 18:44 GMT - Launch Site: Mud Lake DZ. Launch Complex: -. Launch Pad: 37.9 N x 117.1 W. Launch Vehicle: X-15. LV Configuration: X-15 2-36-63. FAILURE: Landing skid extends at Mach 4.3.
  • X-15A-2 Stability test Nation: USA. Agency: NASA/USAF. Apogee: 29 km (18 mi). Maximum Speed - 5649 kph. Maximum Altitude - 28986 m. Right main landing gear extended at Mach 4.1; normal landing. References: 2.
1965 February 18 -
  • Apollo LEM Test Article 2 shipped Nation: USA. Program: Apollo. Spacecraft: Apollo LM. LEM Test Article 2 was shipped to Marshall Space Flight Center to undergo a series of Saturn booster vibration tests. References: 16.
1965 February 18 -
  • Apollo Extension System (AES) to produce space hardware for future missions at a fraction of the original development cost. Nation: USA. Spacecraft: Apollo X. Testifying before the House Committee on Science and Astronautics during hearings on NASA's Fiscal Year 1966 budget, Associate Administrator for Manned Space Flight George E. Mueller briefly outlined the space agency's immediate post-Apollo objectives: 'Apollo capabilities now under development,' he said, 'will enable us to produce space hardware and fly it for future missions at a small fraction of the original development cost. This is the basic concept in the Apollo Extension System (AES) now under consideration.' Additional Details: Apollo Extension System (AES) to produce space hardware for future missions at a fraction of the original development cost..
1965 February 18 - 20:09 GMT - Launch Site: Fort Churchill. Launch Complex: -. Launch Pad: -. Launch Vehicle: Apache. Model: Nike Apache. LV Configuration: Nike Apache NASA 14.11UA.
  • UM Composition 4? Aeronomy mission Nation: USA. Agency: NASA. Apogee: 195 km (121 mi). References: 2.
1965 February 19 - 00:25 GMT - Launch Site: Eglin. Launch Complex: -. Launch Pad: -. Launch Vehicle: Apache. Model: Nike Apache. LV Configuration: Nike Apache AE5.492.
  • TMA / Grenades Aeronomy mission Nation: USA. Agency: USAF. Apogee: 161 km (100 mi). References: 2.
1965 February 19 - 04:51 GMT - Launch Site: Fort Churchill. Launch Complex: -. Launch Pad: -. Launch Vehicle: Aerobee. Model: Aerobee 150. LV Configuration: Aerobee 150 NASA 04.129CA.
  • JHU Aurora 3 Aeronomy mission Nation: USA. Agency: NASA. Apogee: 159 km (98 mi). References: 2.
1965 February 19 - 04:51 GMT - Launch Site: Fort Churchill. Launch Complex: -. Launch Pad: -. Launch Vehicle: Tomahawk Sandia. Model: Nike Tomahawk. LV Configuration: Nike Tomahawk-9 Sandia 152-72.
  • LASL Aurora Aurora mission Nation: USA. Agency: Sandia. Apogee: 320 km (190 mi). References: 2.
1965 February 19 - 09:17 GMT - Launch Site: Fort Churchill. Launch Complex: -. Launch Pad: -. Launch Vehicle: Apache. Model: Nike Apache. LV Configuration: Nike Apache NASA 14.95UA.
  • UM Composition 5? Aeronomy mission Nation: USA. Agency: NASA. Apogee: 187 km (116 mi). References: 2.
1965 February 20 - Launch Site: Kapustin Yar. Launch Complex: LC86/1. Launch Pad: -. Launch Vehicle: Kosmos 2. Model: Kosmos 63S1. FAILURE: First stage failed 64 seconds after launch.
  • DS-A1 s/n 6 Nation: USSR. Program: DS. Payload: DS-A1. Class: Technology. Type: Navigation. Spacecraft: DS-A1. Agency: RVSN. COSPAR: F650220A. 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.
1965 February 21 - 11:00 GMT - Launch Site: Baikonur. Launch Complex: LC41/15. Launch Pad: -. Launch Vehicle: Kosmos 3. Model: Kosmos 65S3. LV Configuration: Kosmos 65S3 03L.
  • Cosmos 54 Nation: USSR. Program: Strela. Mass: 50 kg (110 lb). Class: Communications. Type: Military Store-dump. Spacecraft: Strela-1. Agency: MO SSSR. Perigee: 269 km (167 mi). Apogee: 1,839 km (1,142 mi). Inclination: 56.10 deg. Period: 106.30 min. COSPAR: 1965-011A. USAF Sat Cat: 1089. Decay Date: 1968-09-15. References: 2, 6.
  • Cosmos 55 Nation: USSR. Program: Strela. Mass: 50 kg (110 lb). Class: Communications. Type: Military Store-dump. Spacecraft: Strela-1. Agency: MO SSSR. Perigee: 261 km (162 mi). Apogee: 1,752 km (1,088 mi). Inclination: 56.00 deg. Period: 105.30 min. COSPAR: 1965-011B. USAF Sat Cat: 1090. Decay Date: 1968-02-02. References: 2, 6.
  • Cosmos 56 Nation: USSR. Program: Strela. Mass: 50 kg (110 lb). Class: Communications. Type: Military Store-dump. Spacecraft: Strela-1. Agency: MO SSSR. Perigee: 259 km (160 mi). Apogee: 1,687 km (1,048 mi). Inclination: 56.00 deg. Period: 104.60 min. COSPAR: 1965-011C. USAF Sat Cat: 1091. Decay Date: 1967-11-02. References: 2, 6.
1965 February 22 - 07:40 GMT - Launch Site: Baikonur. Launch Complex: LC31. Launch Pad: -. Launch Vehicle: Soyuz. Model: Voskhod 11A57. LV Configuration: Voskhod 11A57 R15000-03.
  • Cosmos 57 Nation: USSR. Program: Voskhod. Payload: Voskhod 3KD s/n 1. Mass: 5,682 kg (12,526 lb). Class: Manned. Type: Spacecraft. Spacecraft: Voskhod. Agency: NII-88. Perigee: 159 km (98 mi). Apogee: 708 km (439 mi). Inclination: 64.80 deg. Period: 93.20 min. COSPAR: 1965-012A. USAF Sat Cat: 1093. Duration: 0.22 days. Decay Date: 1965-02-22. Flight: Voskhod 2. Unsuccessful mission. Voskhod 2 test. Immediately after orbital insertion airlock and spacesuit inflated normally. Then two ground control stations sent commands to the spacecraft simultaneously. The combined signals accidentally set off the retrofire sequence, which some time later triggered the self destruct mechanism (designed to prevent the spacecraft from falling into enemy hands).
    Officially: Investigation of the upper atmosphere and outer space. Additional Details: Cosmos 57. References: 2, 6, 376.
1965 February 23 - 14:36 GMT - Launch Site: Cape Canaveral. Launch Complex: LC17B. Launch Pad: -. Launch Vehicle: Delta. Model: Thor DSV-2G. LV Configuration: Thor DSV-2G 248.
  • ASSET 6 re-entry vehicle test flight Nation: USA. Agency: USAF. Apogee: 70 km (43 mi). Suborbital test of small scale spaceplane model to test materials for the X-20 Dynasoar. Reached 6,000 m/s and 4,350 km range. Tested twelve different kinds of refractory metals and covered with 2000 dots of heat-sensitive paint to characterize thermal profile on reentry. Telemetry indicated that the spacecraft survived reentry, but it evidently sank upon impacting the ocean and could not be recovered as planned. References: 2.
1965 February 23 - 17:15 GMT - Launch Site: Eglin. Launch Complex: -. Launch Pad: -. Launch Vehicle: Javelin. Model: Nike Javelin. LV Configuration: Nike Javelin Sphere 14.
  • Sphere Aeronomy mission Nation: USA. Agency: USAF. Apogee: 200 km (120 mi). References: 2.
1965 February 25 -
  • David Clark contracted for Apollo Block I space suits Nation: USA. Program: Apollo. Spacecraft: A7L. MSC and the David Clark Company reached an agreement on a contract for Apollo Block I space suits. The first suits, expected by July 1, would go to North American for testing. References: 16.
1965 February 25 - Launch Vehicle: Titan. Model: Titan 2.
  • Martin-Denver delivered propellant tanks for Gemini launch vehicle (GLV) 7 to Martin-Baltimore. Nation: USA. Flight: Gemini 7. Tank fabrication had begun in May 1964. Martin-Baltimore recleaned and purged the tanks with nitrogen by April 20, 1965. In the meantime, flight engines for GLV-7 arrived from Aerojet-General on April 17. Tank splicing was completed May 6 and engine installation May 20. All horizontal testing was completed June 14. A modification period followed.
1965 February 25 - Launch Site: White Sands. Launch Complex: -. Launch Pad: -. Launch Vehicle: HIBEX.
  • Test mission Nation: USA. Agency: USA/ARPA. Apogee: 20 km (12 mi). References: 2.
1965 February 25 - Launch Site: Eglin. Launch Complex: -. Launch Pad: -. Launch Vehicle: Apache. Model: Nike Apache.
  • Ionosphere winds, T Aeronomy mission Nation: USA. Agency: USAF. Apogee: 200 km (120 mi). References: 2.
1965 February 25 - 21:44 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 432 / Agena D SS-01B 1611.
  • KH-4A 1017 Nation: USA. Payload: KH-4A s/n 1017 / Agena D 1611. Mass: 1,500 kg (3,300 lb). Class: Surveillance. Type: Military. Spacecraft: KH-4A. Agency: NRO/CIA. Perigee: 177 km (109 mi). Apogee: 377 km (234 mi). Inclination: 75.10 deg. Period: 90.10 min. COSPAR: 1965-013A. USAF Sat Cat: 1096. Decay Date: 1965-03-18. KH-4A. Capping shutter malfunction occurred during last 5 passes of mission. References: 2, 6.
1965 February 26 - Launch Vehicle: Titan. Model: Titan 2.
  • A full-scale rehearsal of the flight crew countdown for Gemini-Titan 3 was conducted at the launch site. Nation: USA. Flight: Gemini 3. Procedures were carried out for moving the flight crew from their quarters in the Manned Spacecraft Center operations building at Merritt Island to the pilot's ready room at complex 16 at Cape Kennedy. Complete flight crew suiting operation in the ready room, the transfer to complex 19, and crew ingress into the spacecraft were practiced. Practice countdown proceeded smoothly and indicated that equipment and procedures were flight ready.
1965 February 26 - Launch Site: Baikonur. Launch Complex: LC41/3. Launch Pad: -. Launch Vehicle: R-16. Model: R-16U.
  • PBG Nation: USSR. Agency: RVSN. Apogee: 1,210 km (750 mi). References: 2.
1965 February 26 - 05:02 GMT - Launch Site: Baikonur. Launch Complex: LC31. Launch Pad: -. Launch Vehicle: Soyuz. Model: Vostok 8A92M. LV Configuration: Vostok 8A92M R15000-09.
  • Cosmos 58 Nation: USSR. Payload: Meteor no. 2. Mass: 4,730 kg (10,420 lb). Class: Earth. Type: Weather. Spacecraft: Meteor. Agency: NII-88. Perigee: 333 km (206 mi). Apogee: 345 km (214 mi). Inclination: 65.00 deg. Period: 91.30 min. COSPAR: 1965-014A. USAF Sat Cat: 1097. Decay Date: 1990-02-25. Probable weather satellite. Investigation of the upper atmosphere and outer space. References: 2, 6.
1965 February 26 - 11:10 GMT - Launch Site: Eglin. Launch Complex: -. Launch Pad: -. Launch Vehicle: Apache. Model: Nike Apache. LV Configuration: Nike Apache Sphere 24.
  • Sphere Aeronomy mission Nation: USA. Agency: USAF. Apogee: 150 km (90 mi). References: 2.
1965 February 26 - 19:45 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 1-52-85.
  • X-15A MIT/AirD/Sky Bright Aeronomy mission Nation: USA. Agency: NASA/USAF. Apogee: 46 km (28 mi). Maximum Speed - 6034 kph. Maximum Altitude - 46817 m. References: 2.
1965 February 27 -
  • State Commission on Cosmos 57 Nation: USSR. Program: Voskhod. Spacecraft: Voskhod. Flight: Voskhod 2. The final conclusion is as before, that simultaneous transmission of the air release command from IP-6 and IP-7 started the chain of events leading to the self-destruction of the spacecraft. It is decided that a Zenit planned for 4-8 March will fly with the Vykhod airlock ring, followed by the E-6 launch on 12 March, and the Voskhod-2 launch with a crew aboard for 15-20 March. References: 376.
1965 February 27 - Launch Site: Hammaguira. Launch Complex: Brigitte. Launch Pad: -. Launch Vehicle: Diamant. Model: Emeraude VE121.
  • Test mission Nation: France. Agency: CNES. Apogee: 200 km (120 mi). References: 2.
1965 February 27 - 11:11 GMT - Launch Site: Vandenberg. Launch Complex: 576A1. Launch Pad: -. Launch Vehicle: Atlas. Model: Atlas D. LV Configuration: Atlas D 211D.
  • ABRES LORV-4 re-entry vehicle test flight Nation: USA. Agency: USAF SAC. Apogee: 1,800 km (1,100 mi). References: 2.
1965 February 27 - 21:00 GMT - Launch Site: Eglin. Launch Complex: -. Launch Pad: -. Launch Vehicle: Apache. Model: Nike Apache. LV Configuration: Nike Apache AE5.556.
  • Neutral / Ion / Sphere Aeronomy mission Nation: USA. Agency: USAF. Apogee: 157 km (97 mi). References: 2.
1965 February 27 - 22:30 GMT - Launch Site: Eglin. Launch Complex: -. Launch Pad: -. Launch Vehicle: Apache. Model: Nike Apache. LV Configuration: Nike Apache AE5.486.
  • Neutral / Ion / Sphere Ionosphere mission Nation: USA. Agency: USAF. Apogee: 132 km (82 mi). References: 2.
1965 February 28 - 00:21 GMT - Launch Site: Fort Churchill. Launch Complex: -. Launch Pad: -. Launch Vehicle: Apache. Model: Nike Apache. LV Configuration: Nike Apache NASA 14.196CA.
  • GCA TMA / ionosphere Aeronomy / ionosphere mission Nation: USA. Agency: NASA. Apogee: 170 km (100 mi). References: 2.
1965 February 28 - 04:15 GMT - Launch Site: Eglin. Launch Complex: -. Launch Pad: -. Launch Vehicle: Apache. Model: Nike Apache. LV Configuration: Nike Apache AE5.494.
  • PENNY (TMA / Gren) Aeronomy mission Nation: USA. Agency: USAF. Apogee: 145 km (90 mi). References: 2.
1965 February 28 - 09:15 GMT - Launch Site: Eglin. Launch Complex: -. Launch Pad: -. Launch Vehicle: Apache. Model: Nike Apache. LV Configuration: Nike Apache AE5.553.
  • Neutral / Ion / Sphere Aeronomy mission Nation: USA. Agency: USAF. Apogee: 143 km (88 mi). References: 2.
1965 February 28 - 09:15 GMT - Launch Site: Eglin. Launch Complex: -. Launch Pad: -. Launch Vehicle: Apache. Model: Nike Apache. LV Configuration: Nike Apache AE5.496.
  • SHIRLEY (TMA / Gren) Aeronomy mission Nation: USA. Agency: USAF. Apogee: 200 km (120 mi). References: 2.
1965 February 28 - 11:30 GMT - Launch Site: Eglin. Launch Complex: -. Launch Pad: -. Launch Vehicle: Apache. Model: Nike Apache. LV Configuration: Nike Apache AE5.497.
  • Neutral / Ion / ImpProbe Aeronomy mission Nation: USA. Agency: USAF. Apogee: 139 km (86 mi). References: 2.
1965 March 1 -
  • Soyuz 7K-PPK cancelled. Nation: USSR. Program: Almaz. Class: Manned. Type: Spacecraft. Spacecraft: Soyuz PPK. Based on successful test flights of Chelomei's unmanned interceptor-sputnik prototypes (Polyot 1 and 2), the Soyuz 7K-PPK manned interceptor version is cancelled.
1965 March 1 - Launch Site: ETR Launch Area. Launch Complex: -. Launch Pad: -. Launch Vehicle: Polaris. Model: Polaris A3. LV Configuration: Polaris A3P-172.
  • Operational test Nation: USA. Agency: USN. Apogee: 1,000 km (600 mi). References: 2.
1965 March 1 - Launch Site: Kwajalein. Launch Complex: -. Launch Pad: -. Launch Vehicle: Nike Zeus. Model: Nike Zeus. LV Configuration: Nike Zeus-3.
  • Simulated target Nation: USA. Agency: USA. Apogee: 200 km (120 mi). References: 2.
1965 March 1 - Launch Site: Kwajalein. Launch Complex: -. Launch Pad: -. Launch Vehicle: Nike Zeus. Model: Nike Zeus. LV Configuration: Nike Zeus-3.
  • Simulated target Nation: USA. Agency: USA. Apogee: 200 km (120 mi). References: 2.
1965 March -
  • TRW awarded contract for the Advanced Vela spacecraft Nation: USA. Spacecraft: Advanced Vela. The Advanced series added atmospheric nuclear detonation detection to its capabilities. Additionally, it monitored solar activity, terrestrial lightning, and celestial X/gamma-ray radiation.
1965 March - Launch Vehicle: Martlet. Model: Martlet 4.
  • Martlet 4 orbital gun-launched rocket design. Nation: Canada. It was not until 1964, when agreements between the Canadian and the US governments permitted stable funding over the following three years, that HARP was able to seriously consider an orbital program. The Martlet 4 program began in the spring of 1965 with extensive parametric studies which showed that meaningful payloads could be launched into low Earth orbit from the 16 inch L86 HARP gun on the Barbados flight range using a full bore, 3 stage rocket vehicle.
1965 March 1-2 - Launch Vehicle: Titan. Model: Titan 2.
  • Office of Manned Space Flight held the Gemini manned spa