Chronology - Quarter 2 1965 home
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1965 April 1 -
  • All-battery electrical power system for the Apollo LEM Nation: USA. Program: Apollo. Spacecraft: Apollo LM. Grumman presented to MSC its recommendations for an all-battery electrical power system for the LEM:

    • Two batteries in the ascent stage
    • Four batteries in the descent stage
    • A new power distribution system
    • Active cooling for the descent batteries and electrical control assemblies
    Following a review of cost and resources proposals, MSC approved Grumman's configuration, and on April 15 gave the LEM manufacturer a go-ahead. Additional Details: All-battery electrical power system for the Apollo LEM. References: 16.
1965 April 1 - Launch Vehicle: Saturn I. Model: Saturn IB.
  • First stage of the Saturn IB first static firing at MSFC Nation: USA. Program: Apollo. The first stage of the Saturn IB booster (the S-IB-1) underwent its first static firing at Huntsville, Alabama. The stage's eight uprated H-1 engines produced about 71,168-kilonewtons (1.6 million lbs) thrust. On April 23, Marshall and Rocketdyne announced that the uprated H-1 had passed qualification testing and was ready for flight. References: 16.
1965 April 1 - Launch Vehicle: HY-1.
  • HY missile development Nation: China. Shenguan is authorised to develop and produce a missile based on the Soviet P-15 ('Styx') cruise missile (later designated Haiyang).
1965 April 1 - Launch Site: Mountain Home AFB. Launch Complex: -. Launch Pad: -. Launch Vehicle: Titan. Model: Titan 1.
  • Last Titan I ICBM taken off alert status at Mountain Home AFB Nation: USA.
1965 April 1 - Launch Site: Natal. Launch Complex: -. Launch Pad: -. Launch Vehicle: Sonda. Model: Sonda 1. LV Configuration: Sonda 1 1.
  • Test mission Nation: Brazil. Agency: IAE. Apogee: 65 km (40 mi). References: 2.
1965 April 1-8 -
  • Backup mode of entering and leaving the Apollo LEM while on the moon Nation: USA. Program: Apollo. Spacecraft: Apollo LM. MSC and Grumman reviewed the requirement for a backup mode of entering and leaving the LEM while on the moon. The new rectangular hatch was deemed "inherently highly reliable," and the only failure that was even "remotely possible" was one of the hatch mechanism. The proposal to use the top (or transfer) hatch was impractical, because it would cost 13.6 kg (30 lb) and would impose an undue hazard on both the crew and the spacecraft's thermal shield. References: 16.
Spring 1966 - Launch Vehicle: Titan. Model: Titan 1.
  • Titan I missiles in storage at Mira Loma Air Force Station, Riverside County, California, are scrapped. Nation: USA.
1965 April 1 - 02:07 GMT - Launch Site: Wallops Island. Launch Complex: -. Launch Pad: -. Launch Vehicle: Apache. Model: Nike Apache. LV Configuration: Nike Apache NASA 14.132NA.
  • Airglow Aeronomy mission Nation: USA. Agency: NASA. Apogee: 139 km (86 mi). References: 2.
1965 April 2 - 13:22 GMT - Launch Site: Pacific Ocean. Launch Complex: -. Launch Pad: 12.1 S x 78.2 W. Launch Vehicle: Apache. Model: Nike Apache. LV Configuration: Nike Apache NASA 14.185UE.
  • UNH Particles Plasma mission Nation: USA. Agency: NASA. Apogee: 200 km (120 mi). Launched at 1965 Croatan MRF Expedition LP31 - - Latitude: 12.12 S - Longitude: 78.22 W. References: 2.
1965 April 3 - 12:54 GMT - Launch Site: Salto di Quirra. Launch Complex: -. Launch Pad: -. Launch Vehicle: Skylark. Model: Skylark 7. LV Configuration: Skylark-7 S03/2.
  • ESRO S03 / 2 (SE5) Ionosphere mission Nation: Europe. Agency: ESRO. Apogee: 172 km (106 mi). References: 2.
1965 April 3 - 21:24 GMT - Launch Site: Vandenberg. Launch Complex: SLC4E. Launch Pad: -. Launch Vehicle: Atlas. Model: SLV-3 Agena D. LV Configuration: SLV-3 Agena D 7401.
  • Snapshot Nation: USA. Payload: SNAP 10A / Agena D. Mass: 440 kg (970 lb). Class: Technology. Type: Ion engine. Spacecraft: Snapshot. Agency: USAF/AEC. Perigee: 1,270 km (780 mi). Apogee: 1,314 km (816 mi). Inclination: 90.30 deg. Period: 111.40 min. COSPAR: 1965-027A. USAF Sat Cat: 1314. Only nuclear reactor ever orbited by the United States. The SNAP-10A reactor provided electrical power for an 8.5 mN ion engine using cesium propellant. The engine was shut off after one hour of operation when high-voltage spikes created electromagnetic interference with the satellite's attitude control system sensors. The reactor continued in operation, generating 39 kWt and more than 500 watts of electrical power for 43 days before the spacecraft telemetry failed. References: 2, 6, 278.
  • SECOR 4 Nation: USA. Payload: EGRS 4. Mass: 40 kg (88 lb). Class: Earth. Type: Geodetic. Spacecraft: SECOR. Agency: USA ACE. Perigee: 1,267 km (787 mi). Apogee: 1,316 km (817 mi). Inclination: 90.20 deg. Period: 111.40 min. COSPAR: 1965-027B. USAF Sat Cat: 1315. Failed. Space craft engaged in investigation of spaceflight techniques and technology (US Cat A). References: 2, 6, 278.
1965 April 3 - 21:59 GMT - Launch Site: Fort Churchill. Launch Complex: -. Launch Pad: -. Launch Vehicle: Apache. Model: Nike Apache. LV Configuration: Nike Apache NASA 14.207UE.
  • Auroral fluxes Plasma mission Nation: USA. Agency: NASA. Apogee: 205 km (127 mi). References: 2.
1965 April 4 - 16:06 GMT - Launch Site: Pacific Ocean. Launch Complex: -. Launch Pad: 24.1 S x 76.1 W. Launch Vehicle: Apache. Model: Nike Apache. LV Configuration: Nike Apache NASA 14.66UA.
  • UM Pitot 10 Aeronomy mission Nation: USA. Agency: NASA. Apogee: 139 km (86 mi). Launched at 1965 Croatan MRF Expedition LP32 - - Latitude: 24.08 S - Longitude: 76.13 W. References: 2.
1965 April 5 - Launch Vehicle: Titan. Model: Titan 2.
  • Schirra and Stafford selected for Gemini-Titan 6. Nation: USA. Flight: Gemini 6. Manned Spacecraft Center announced that Walter M. Schirra, Jr., and Thomas P. Stafford had been selected as command pilot and pilot for Gemini-Titan 6, the first Gemini rendezvous and docking mission. Virgil I. Grissom and John W. Young would be the backup crew.
1965 April 5-11 -
  • Qualification tests completed on two Apollo CM reaction control engines Nation: USA. Program: Apollo. Spacecraft: Apollo CSM. Rocketdyne completed qualification tests on two CM reaction control engines. These were successful. One of the nozzle extensions failed to seat, however, and was rejected. Its failure was being analyzed. References: 16.
1965 April 5 - 07:20 GMT - Launch Site: Johnston Island. Launch Complex: LE2. Launch Pad: -. Launch Vehicle: Delta. Model: Thor DSV-2J. LV Configuration: Thor DSV-2J 155.
  • AFP-437 combat training interceptor mission Nation: USA. Agency: USAF. Apogee: 826 km (513 mi). References: 2.
1965 April 5 - 13:45 GMT - Launch Site: Pacific Ocean. Launch Complex: -. Launch Pad: 29.6 S x 75.2 W. Launch Vehicle: Apache. Model: Nike Apache. LV Configuration: Nike Apache NASA 14.230UI.
  • Ionosphere mission Nation: USA. Agency: NASA. Apogee: 177 km (109 mi). Launched at 1965 Croatan MRF Expedition LP33 - - Latitude: 29.57 S - Longitude: 75.22 W. References: 2.
1965 April 5 - 19:42 GMT - Launch Site: Pacific Ocean. Launch Complex: -. Launch Pad: 30.6 S x 75.0 W. Launch Vehicle: Apache. Model: Nike Apache. LV Configuration: Nike Apache NASA 14.184UE.
  • UNH Particles Plasma mission Nation: USA. Agency: NASA. Apogee: 200 km (120 mi). Launched at 1965 Croatan MRF Expedition LP34 - - Latitude: 30.63 S - Longitude: 75.03 W. References: 2.
1965 April 6 - 13:34 GMT - Launch Site: Vandenberg. Launch Complex: 576B1. Launch Pad: -. Launch Vehicle: Atlas. Model: Atlas D. LV Configuration: Atlas D 150D.
  • ABRES WAC-4 re-entry vehicle test flight Nation: USA. Agency: USAF AFSC. Apogee: 1,800 km (1,100 mi). References: 2.
1965 April 6 - 16:34 GMT - Launch Site: Pacific Ocean. Launch Complex: -. Launch Pad: 35.2 S x 74.3 W. Launch Vehicle: Apache. Model: Nike Apache. LV Configuration: Nike Apache NASA 14.26UA.
  • UM Pitot 11 Aeronomy mission Nation: USA. Agency: NASA. Apogee: 142 km (88 mi). Launched at 1965 Croatan MRF Expedition LP35 - - Latitude: 35.23 S - Longitude: 74.25 W. References: 2.
1965 April 6 - 23:47 GMT - Launch Site: Cape Canaveral. Launch Complex: LC17A. Launch Pad: -. Launch Vehicle: Delta. Model: Delta D. LV Configuration: Thor Delta D 426/D30.
  • Intelsat 1 F-1 Nation: International. Program: Intelsat. Payload: Early Bird. Mass: 39 kg (85 lb). Class: Communications. Spacecraft: Intelsat 1. Agency: INTELSAT. Perigee: 35,746 km (22,211 mi). Apogee: 35,819 km (22,256 mi). Inclination: 11.70 deg. Period: 1,435.90 min. COSPAR: 1965-028A. USAF Sat Cat: 1317. Completed Operations Date: 1971-01-01. Over Atlantic. Spacecraft engaged in practical applications and uses of space technology such as weather or communication (US Cat C). Positioned in geosynchronous orbit at 28 deg W in 1965; 38 deg W in 1965-1966. As of 27 July 2001 located at 92.54 deg W drifting at 0.324 deg W per day. As of 2007 Jan 13 located at 47.74W drifting at 0.017E degrees per day. References: 2, 6.
1965 April 9 -
  • Manned space flight control transferred to Houston Nation: USA. Program: Apollo. George E. Mueller, Associate Administrator for Manned Space Flight, announced the transfer of control over manned space flights from Cape Kennedy, Fla., to Houston, Texas. MSC's Mission Control Center would direct the flights from end of liftoff through recovery. References: 16.
1965 April 9 - 01:01 GMT - Launch Site: Woomera. Launch Complex: LA2. Launch Pad: LA2 SL. Launch Vehicle: Skylark. Model: Skylark 7C. LV Configuration: Skylark-7C SL303.
  • LUX Solar AC3 Solar x-ray and ultraviolet mission Nation: Australia. Agency: WRE/RAE. Apogee: 160 km (90 mi). References: 2.
1965 April 9 - 18:10 GMT - Launch Site: Cape Canaveral. Launch Complex: LC18A. Launch Pad: LC18A. Launch Vehicle: Scout. Model: Blue Scout Jr. LV Configuration: Blue Scout Jr 22-9.
  • OAR 22-9 / AFWL-14 Magnetosphere mission Nation: USA. Agency: USAF. Apogee: 25,422 km (15,796 mi). References: 2.
1965 April 9 - 19:18 GMT - Launch Site: Pacific Ocean. Launch Complex: -. Launch Pad: 44.3 S x 77.7 W. Launch Vehicle: Apache. Model: Nike Apache. LV Configuration: Nike Apache NASA 14.231UI.
  • Ionosphere mission Nation: USA. Agency: NASA. Apogee: 191 km (118 mi). Launched at 1965 Croatan MRF Expedition LP36 - - Latitude: 44.25 S - Longitude: 77.67 W. References: 2.
1965 April 9 - 20:26 GMT - Launch Site: Pacific Ocean. Launch Complex: -. Launch Pad: 44.4 S x 77.8 W. Launch Vehicle: Apache. Model: Nike Apache. LV Configuration: Nike Apache NASA 14.63UA.
  • UM Pitot 12 Aeronomy mission Nation: USA. Agency: NASA. Apogee: 147 km (91 mi). Launched at 1965 Croatan MRF Expedition LP37 - - Latitude: 44.38 S - Longitude: 77.78 W. References: 2.
1965 April 10 - Launch Site: Baikonur. Launch Complex: LC1. Launch Pad: -. Launch Vehicle: Soyuz. Model: Molniya 8K78. LV Configuration: Molniya 8K78 R103-26. FAILURE: Stage 3's engine 8D715K failed due to depressurization of the nitrogen pipeline of the LOX tank pressurization system of Block I.
  • Luna failure - stage 3 engine failure. Nation: USSR. Program: Luna. Payload: E-6 s/n 8. Class: Planetary. Type: Lunar. Spacecraft: Luna E-6. Agency: RVSN. COSPAR: F650410A. Decay Date: 1965-04-10. The upper stages fell apart on re-entry into the atmosphere.. References: 64, 65.
1965 April 10 - 08:10 GMT - Launch Site: Vandenberg. Launch Complex: LF09. Launch Pad: LF09?. Launch Vehicle: Minuteman 1. Model: Minuteman 1B. LV Configuration: Minuteman 1B 1150.
  • Operational missile test Nation: USA. Agency: SAC 1STRAD. Apogee: 1,300 km (800 mi). References: 2.
1965 April 12 - Launch Site: Baikonur. Launch Complex: LC60/6. Launch Pad: -. Launch Vehicle: R-16. Model: R-16U.
  • Combat training launch Nation: USSR. Agency: RVSN. Apogee: 1,210 km (750 mi). References: 2.
1965 April 12 - 14:47 GMT - Launch Site: White Sands. Launch Complex: LC35. Launch Pad: -. Launch Vehicle: Aerobee. Model: Aerobee 150. LV Configuration: Aerobee 150 NASA 04.49GS (128-3).
  • Mg II heliogram 1 Solar ultraviolet mission Nation: USA. Agency: NASA. Apogee: 201 km (124 mi). References: 2.
1965 April 12 - 17:14 GMT - Launch Site: Pacific Ocean. Launch Complex: -. Launch Pad: 58.3 S x 78.0 W. Launch Vehicle: Apache. Model: Nike Apache. LV Configuration: Nike Apache NASA 14.232UI.
  • GCA Ionosphere Ionosphere mission Nation: USA. Agency: NASA. Apogee: 187 km (116 mi). Launched at 1965 Croatan MRF Expedition LP38 - - Latitude: 58.32 S - Longitude: 78.00 W. References: 2.
1965 April 12 - 18:37 GMT - Launch Site: Eglin. Launch Complex: -. Launch Pad: -. Launch Vehicle: Nike. Model: Nike Iroquois. LV Configuration: Nike Iroquois AE07.313.
  • Vehicle test Nation: USA. Agency: USAF. Apogee: 143 km (88 mi). References: 2.
1965 April 13 - 04:05 GMT - Launch Site: Pacific Ocean. Launch Complex: -. Launch Pad: 60.0 S x 78.0 W. Launch Vehicle: Apache. Model: Nike Apache. LV Configuration: Nike Apache NASA 14.67UA.
  • UM Pitot 13 Aeronomy mission Nation: USA. Agency: NASA. Apogee: 150 km (90 mi). Launched at 1965 Croatan MRF Expedition LP39 - - Latitude: 60.00 S - Longitude: 78.00 W. References: 2.
1965 April 13 - 16:00 GMT - Launch Site: Pacific Ocean. Launch Complex: -. Launch Pad: 60.0 S x 78.0 W. Launch Vehicle: Apache. Model: Nike Apache. LV Configuration: Nike Apache NASA 14.27UA.
  • UM Pitot 14 Aeronomy mission Nation: USA. Agency: NASA. Apogee: 146 km (90 mi). Launched at 1965 Croatan MRF Expedition LP39 - - Latitude: 60.00 S - Longitude: 78.00 W. References: 2.
1965 April 13 - 17:10 GMT - Launch Site: Pacific Ocean. Launch Complex: -. Launch Pad: 60.0 S x 78.0 W. Launch Vehicle: Apache. Model: Nike Apache. LV Configuration: Nike Apache NASA 14.186UE.
  • UNH Particles Plasma mission Nation: USA. Agency: NASA. Apogee: 200 km (120 mi). Launched at 1965 Croatan MRF Expedition LP39 - - Latitude: 60.00 S - Longitude: 78.00 W. References: 2.
1965 April 13 - 19:06 GMT - Launch Site: Pacific Ocean. Launch Complex: -. Launch Pad: 59.9 S x 78.0 W. Launch Vehicle: Apache. Model: Nike Apache. LV Configuration: Nike Apache NASA 14.101UA.
  • Composition Aeronomy mission Nation: USA. Agency: NASA. Apogee: 200 km (120 mi). Launched at 1965 Croatan MRF Expedition LP40 - - Latitude: 59.92 S - Longitude: 77.97 W. References: 2.
1965 April 13 - 21:00 GMT - Launch Site: Vandenberg. Launch Complex: LF08. Launch Pad: -. Launch Vehicle: Minuteman 1. Model: Minuteman 1B. LV Configuration: Minuteman 1B 1165.
  • Operational missile test Nation: USA. Agency: SAC 1STRAD. Apogee: 1,300 km (800 mi). References: 2.
1965 April 13 - 21:00 GMT - Launch Site: Vandenberg. Launch Complex: LF02. Launch Pad: -. Launch Vehicle: Minuteman 1. Model: Minuteman 1B. LV Configuration: Minuteman 1B 851.
  • Operational missile test Nation: USA. Agency: SAC 1STRAD. Apogee: 1,300 km (800 mi). References: 2.
1965 April 14 - Launch Vehicle: Saturn V.
  • Final beam in the structural skeleton of the Vertical Assembly Building Nation: USA. Program: Apollo. Construction workers emplaced the final beam in the structural skeleton of the Vertical Assembly Building at Merritt Island (KSC), Florida. Scheduled for completion in 1966, the cavernous structure (160 m (525 ft) tall and comprising 10,968,476 cu m (129 million cu ft)) would provide a controlled environment for assembling Saturn V launch vehicles and mating them to Apollo spacecraft. References: 16.
1965 April 14 - 14:39 GMT - Launch Site: Wallops Island. Launch Complex: -. Launch Pad: -. Launch Vehicle: Journeyman. LV Configuration: Journeyman NASA 11.07UE.
  • Minnesota Particles Plasma mission Nation: USA. Agency: NASA. Apogee: 1,660 km (1,030 mi). References: 2.
1965 April 15 - Launch Vehicle: Saturn V.
  • First ground test firing of S-II stage Nation: USA. Program: Apollo. References: 26, 27.
1965 April 15 -
  • First firing of the Apollo LEM ascent engine test rig Nation: USA. Program: Apollo. Spacecraft: Apollo LM. The first firing of the LEM ascent engine test rig (HA-3) was successfully conducted at White Sands Missile Range, New Mexico. A second firing on April 23 lasted 14.45 sec instead of 10 sec as planned. A third firing, lasting 30 sec, completed the test series. A helium pressurization system would be installed before additional testing could begin. References: 16.
1965 April 15 - Launch Vehicle: Titan. Model: Titan 2.
  • Martin-Denver delivered the propellant tanks for Gemini launch vehicle 8 to Martin-Baltimore. Nation: USA. Flight: Gemini 8. Tank fabrication had begun September 25, 1964. Aerojet-General delivered the stage I engine on June 16 and the stage II on August 20. In the meantime, tank splicing was completed August 3. Engine installation was completed September 23, and all hoizontal testing ended September 27.
1965 April 15 -
  • Interkosmos program authorised. Nation: USSR. Spacecraft: DS-U1-IK. Central Committee of the Communist Party and Council of Soviet Ministers Decree 'On Co-operation of the USSR and Socialist Countries in the Sphere of Research and Use of Space-international co-operation' was issued. References: 474.
1965 April 15 - 10:45 GMT - Launch Site: White Sands. Launch Complex: LC35. Launch Pad: -. Launch Vehicle: Aerobee. Model: Aerobee 150. LV Configuration: Aerobee 150 NASA 04.127UA.
  • AF-142 thermodynamic comparison Aeronomy mission Nation: USA. Agency: NASA. Apogee: 198 km (123 mi). References: 2.
1965 April 15 - 16:00 GMT - Launch Site: Pacific Ocean. Launch Complex: -. Launch Pad: 52.6 S x 78.3 W. Launch Vehicle: Apache. Model: Nike Apache. LV Configuration: Nike Apache NASA 14.25UA.
  • UM Pitot 15 Aeronomy mission Nation: USA. Agency: NASA. Apogee: 140 km (80 mi). Launched at 1965 Croatan MRF Expedition LP41 - - Latitude: 52.58 S - Longitude: 78.33 W. References: 2.
1965 April 15 - 18:02 GMT - Launch Site: Pacific Ocean. Launch Complex: -. Launch Pad: 52.5 S x 78.2 W. Launch Vehicle: Apache. Model: Nike Apache. LV Configuration: Nike Apache NASA 14.100UA.
  • Composition Aeronomy mission Nation: USA. Agency: NASA. Apogee: 200 km (120 mi). Launched at 1965 Croatan MRF Expedition LP42 - - Latitude: 52.52 S - Longitude: 78.22 W. References: 2.
1965 April 16 - Launch Vehicle: Saturn V.
  • First clustered firing of Saturn V's first stage Nation: USA. Program: Apollo. MSFC conducted the first clustered firing of the Saturn V's first stage (the S-IC). The booster's five F-1 engines burned for about 6½ seconds and produced 33,360 kilonewtons (7.5 million lbs) thrust.

    Eight days later, at its static facility in Santa Susana, California, North American first fired the S-II, intermediate stage of the Saturn V. The event was chronicled as the "second major Saturn V milestone" during April. Additional Details: First clustered firing of Saturn V's first stage. References: 16.

1965 April 16 -
  • Voskhod female crew opposition Nation: USSR. Program: Voskhod. Spacecraft: Voskhod. Flight: Voskhod 3. Gagarin and the rest of the male cosmonauts, as many as other VVS officers, are opposed to Kamanin's plan for a female Voskhod flight. The first cosmonaut group are also opposed to appointment of Beregovoi and Shatalov to flight crews. Tereshkova has lost 5 kg and looks ill, but all the doctors say she is healthy. References: 376.
1965 April 16-May 15 -
  • Two Apollo CSM fuel cells failed qualification testing Nation: USA. Program: Apollo. Spacecraft: Apollo CSM. Two CSM fuel cells failed qualification testing, the first failing after 101.75 hrs of the vacuum endurance test. Pratt and Whitney Aircraft determined that the failure was caused by a cleaning fluid which contaminated and plugged the oxygen lines and contaminated the oxygen gas at the electrodes. Additional Details: Two Apollo CSM fuel cells failed qualification testing. References: 16.
1965 April 16-May 15 -
  • Qualification testing completed on the fuel tanks for the Apollo SM's reaction control system Nation: USA. Program: Apollo. Spacecraft: Apollo CSM. North American completed qualification testing on the fuel tanks for the SM's reaction control system. References: 16.
1965 April 16 - 19:19 GMT - Launch Site: Vandenberg. Launch Complex: 395-C. Launch Pad: -. Launch Vehicle: Titan. Model: Titan 2. LV Configuration: Titan II B-45.
  • Bear Hug operational test Nation: USA. Agency: USAF SAC. Apogee: 1,300 km (800 mi). References: 2.
1965 April 17 -
  • Voskhod plans Nation: USSR. Program: Voskhod. Flight: Voskhod 3, Voskhod 4, Voskhod 5. Despite opposition, Kamanin goes ahead with his plans. The 10-day duration artificial gravity flight is planned for October 1965, with Volynov and Katys as the crew. In the first half of 1966 Beregovoi and Demin will fly the long-duration mission, and Ponomaryova and Solovyova will fly an all-female spacewalk mission. However the Americans have announced they will fly a Gemini mission for a 7 to 8 day duration by the end of the year; the Soviets may have to adjust this plan to ensure that they retain the lead in manned spaceflight. Kamanin has told the female cosmonauts of their planned flight, but also warned them there is serious opposition in some quarters. References: 376.
1965 April 17 - 09:50 GMT - Launch Site: Baikonur. Launch Complex: LC31. Launch Pad: -. Launch Vehicle: Soyuz. Model: Voskhod 11A57. LV Configuration: Voskhod 11A57 G15000-11.
  • Cosmos 65 Nation: USSR. Mass: 6,300 kg (13,800 lb). Class: Surveillance. Type: Military. Spacecraft: Zenit-4. Agency: MOM. Perigee: 207 km (128 mi). Apogee: 315 km (195 mi). Inclination: 65.00 deg. Period: 89.70 min. COSPAR: 1965-029A. USAF Sat Cat: 1320. Duration: 8.00 days. Decay Date: 1965-04-25. High resolution photo reconnaissance satellite; returned film capsule; also carried weather experiments. References: 2, 6.
1965 April 19 - 02:20 GMT - Launch Site: Baikonur. Launch Complex: LC130. Launch Pad: -. Launch Vehicle: UR-100. LV Configuration: UR-100 U106416-01.
  • State trials missile test Nation: USSR. Agency: RVSN. Apogee: 1,000 km (600 mi). References: 2.
1965 April 20 - 15:40 GMT - Launch Site: White Sands. Launch Complex: LC35. Launch Pad: -. Launch Vehicle: Aerobee. Model: Aerobee 150. LV Configuration: Aerobee 150 NE3.156.
  • Solar ultraviolet and x-ray mission Nation: USA. Agency: NRL. Apogee: 201 km (124 mi). References: 2.
1965 April 21 - Launch Vehicle: Titan. Model: Titan 2.
  • The Combined Systems Acceptance Test (CSAT) of Gemini launch vehicle (GLV) 5 was conducted in the vertical test facility at Martin-Baltimore. Nation: USA. Flight: Gemini 5. Four earlier CSAT attempts (April 15-20) were marred by numerous minor anomalies. The vehicle acceptance team inspection began April 26 and concluded April 30, with GLV-5 found acceptable. The vehicle was removed from the test cell May 7-8, formally accepted by the Air Force May 15, and shipped to Cape Kennedy. Stage I arrived at the Cape on May 17 and stage II on May 19.
1965 April 21 - 11:02 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.21.
  • Dazzle re-entry vehicle test Nation: UK. Agency: RAE. Apogee: 651 km (404 mi). References: 2.
1965 April 22 - Launch Vehicle: Titan. Model: Titan 2.
  • The Abort Panel met to review abort criteria for Gemini-Titan (GT) 4 and decided that GT-3 rules would suffice. Nation: USA. Flight: Gemini 4, Gemini 5. Alternate procedures for delayed mode 2 abort would be investigated when the Manned Spacecraft Center abort trainer became available to the GT-5 mission.
1965 April 22-23 -
  • Final zero-g trials of the Apollo CM waste management system Nation: USA. Program: Apollo. Spacecraft: Apollo CSM. North American conducted the final zero-g trials (part of developmental testing on the CM's waste management system) and reported good results for both urine and feces apparatus. References: 16.
1965 April 22 - 05:14 GMT - Launch Site: Fort Churchill. Launch Complex: -. Launch Pad: -. Launch Vehicle: Black Brant. Model: Black Brant 3. LV Configuration: Black Brant III AA-3-11.
  • Aurora / ionosphere mission Aurora / ionosphere mission Nation: Canada. Agency: NRCC. Apogee: 136 km (84 mi). References: 2.
1965 April 23 - Launch Vehicle: Titan. Model: Titan 2.
  • Gemini launch vehicle (GLV) 4 and spacecraft No. 4 were mechanically mated at complex 19. Nation: USA. Flight: Gemini 4. The Electrical Interface Integrated Validation and Joint Guidance and Control Test were completed April 26-29. These had been separate tests for earlier vehicles, but from Gemini-Titan 4 on, the tests were combined and performed as one. The spacecraft/GLV Joint Combined Systems Test followed on April 30. The Flight Configuration Mode Test finished systems testing May 7.
1965 April 23 - 01:55 GMT - Launch Site: Baikonur. Launch Complex: LC1. Launch Pad: -. Launch Vehicle: Soyuz. Model: Molniya 8K78. LV Configuration: Molniya 8K78 U103-35.
  • Molniya 1-01 Nation: USSR. Program: Molniya. Payload: Molniya-1. Mass: 1,600 kg (3,500 lb). Class: Communications. Spacecraft: Molniya-1. Agency: MOM. Perigee: 538 km (334 mi). Apogee: 39,300 km (24,400 mi). Inclination: 65.50 deg. Period: 707.30 min. COSPAR: 1965-030A. USAF Sat Cat: 1324. Decay Date: 1979-08-16. First announced launch of Soviet communications satellite. Television programme transmission and long range two way multi channel telephone and telegraph communications. Orbital characteristics after correction of 2 May 1965. References: 2, 6, 64.
1965 April 23 - 03:01 GMT - Launch Site: Wallops Island. Launch Complex: -. Launch Pad: -. Launch Vehicle: Cajun. Model: Nike Cajun. LV Configuration: Nike Cajun NASA 10.171NA.
  • Release Aeronomy mission Nation: USA. Agency: NASA. Apogee: 128 km (79 mi). References: 2.
1965 April 23 - 04:02 GMT - Launch Site: Wallops Island. Launch Complex: -. Launch Pad: -. Launch Vehicle: Apache. Model: Nike Apache. LV Configuration: Nike Apache NASA 14.255NA.
  • Release Aeronomy mission Nation: USA. Agency: NASA. Apogee: 145 km (90 mi). References: 2.
1965 April 23 - 17:44 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 3-41-64.
  • X-15A HT/Abl TPS/BLN Test/Technology mission Nation: USA. Agency: NASA/USAF. Apogee: 24 km (14 mi). Maximum Speed - 5760 kph. Maximum Altitude - 24293 m. References: 2.
1965 April 26 -
  • First Apollo CM heatshields Nation: USA. Program: Apollo. Spacecraft: Apollo CSM. North American received CM 009 forward and crew compartment heatshields from Avco Corporation. These heatshields were the first CM heatshields received by the contractor with complete ablative application. References: 16.
1965 April 26 - Launch Site: Baikonur. Launch Complex: LC41/4. Launch Pad: -. Launch Vehicle: R-16. Model: R-16U.
  • Operational test launch Nation: USSR. Agency: RVSN. Apogee: 1,210 km (750 mi). References: 2.
1965 April 26-May 2 -
  • Apollo boilerplate 14 simulated the mission for spacecraft 009 Nation: USA. Program: Apollo. Spacecraft: Apollo CSM. Using boilerplate 14, North American simulated the mission for spacecraft 009. The test was conducted in two phases, with the vehicle on external and then internal power. All data showed satisfactory performance. References: 16.
1965 April 27-30 -
  • Apollo CM Block II Critical Design Review Part II Nation: USA. Program: Apollo. Spacecraft: Apollo CSM. Part II of the Critical Design Review of the crew compartment and docking system for the Block II CM was held at Downey, California, using mockups 28 and 27 A. (Part I had been held on March 23-24.) Additional Details: Apollo CM Block II Critical Design Review Part II. References: 16.
1965 April 27 - 05:00 GMT - Launch Site: Baikonur. Launch Complex: LC140/18. Launch Pad: -. Launch Vehicle: Tsiklon. Model: R-36 8K67.
  • Kura state trials missile launch Nation: USSR. Agency: RVSN. Apogee: 870 km (540 mi). References: 2.
1965 April 27 - 06:30 GMT - Launch Site: White Sands. Launch Complex: LC35. Launch Pad: -. Launch Vehicle: Aerobee. Model: Aerobee 150. LV Configuration: Aerobee 150 NB3.176.
  • X-ray astronomy mission Nation: USA. Agency: NRL. Apogee: 193 km (119 mi). References: 2.
1965 April 28 -
  • Shirtsleeve environment in the Apollo CM Nation: USA. Program: Apollo. Spacecraft: Apollo CSM. Flight: Apollo 204. Joseph F. Shea, ASPO Manager, approved Crew Systems Division's recommendation to retain the "shirtsleeve" environment for the CM. The design was simpler and promised greater overall mission reliability; also, it would be more comfortable for the crewmen. Additional Details: Shirtsleeve environment in the Apollo CM. References: 16.
1965 April 28 - Launch Site: Baikonur. Launch Complex: LC41/4. Launch Pad: -. Launch Vehicle: R-16. Model: R-16U. FAILURE: Failure.
  • Operational test launch Nation: USSR. Agency: RVSN. Apogee: 0 km ( mi). References: 2.
1965 April 28-May 3 -
  • Proton irradiation tests conducted for Apollo project Nation: USA. Program: Apollo. Under NASA contract, proton irradiation of primates tests were conducted on the Oak Ridge cyclotron by a team from Brooks AFB and Crew Systems Division. During this period, 136 monkeys and 900 mice were irradiated. References: 16.
1965 April 28 - 20:17 GMT - Launch Site: Vandenberg. Launch Complex: SLC4E. Launch Pad: -. Launch Vehicle: Atlas. Model: SLV-3 Agena D. LV Configuration: SLV-3 Agena D 7107 / Agena D 7107.
  • KH 7-17 Nation: USA. Payload: KH-7 no. 17. Mass: 2,000 kg (4,400 lb). Class: Surveillance. Type: Military. Spacecraft: KH-7. Agency: NRO/USAF. Perigee: 180 km (110 mi). Apogee: 259 km (160 mi). Inclination: 95.60 deg. Period: 89.00 min. COSPAR: 1965-031A. USAF Sat Cat: 1327. Decay Date: 1965-05-03. KH-7 type satellite. Space craft engaged in investigation of spaceflight techniques and technology (US Cat A). References: 2, 6, 278.
  • OPS 6717 Nation: USA. Payload: EHH B1. Mass: 60 kg (132 lb). Class: Sigint. Spacecraft: SSF. Agency: NRO/USAF. Perigee: 506 km (314 mi). Apogee: 547 km (339 mi). Inclination: 95.20 deg. Period: 95.10 min. COSPAR: 1965-031B. USAF Sat Cat: 1329. Decay Date: 1969-10-31. Radar monitoring. References: 2, 6, 172, 278.
1965 April 28 - 20:26 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 2-37-64.
  • X-15A-2 Landing loads,Stab test Nation: USA. Agency: NASA/USAF. Apogee: 28 km (17 mi). Maximum Speed - 5266 kph. Maximum Altitude - 28224 m. First star tracker checkout. References: 2.
1965 April 28 - 23:57 GMT - Launch Site: Thumba. Launch Complex: -. Launch Pad: -. Launch Vehicle: Belier. Model: Centaure. LV Configuration: Centaure C99 TERLS-22?.
  • ISRO 15.02 Aeronomy / ionosphere mission Nation: India. Agency: ISRO. Apogee: 150 km (90 mi). References: 2.
1965 April 29 - Launch Vehicle: CZ-1.
  • Chinese satellite plans. Nation: China. Spacecraft: DFH-1. Tsien says he can orbit a Chiense satellite in 1970 or 1971.
1965 April 29 - 09:03 GMT - Launch Site: Woomera. Launch Complex: LA2. Launch Pad: LA2 SL. Launch Vehicle: Skylark. Model: Skylark 7C. LV Configuration: Skylark-7C SL464. FAILURE: Failure.
  • Grenades / Chaff / Lithium release Aeronomy mission Nation: Australia. Agency: WRE/RAE. Apogee: 140 km (80 mi). References: 2.
1965 April 29 - 11:09 GMT - Launch Site: Woomera. Launch Complex: LA2. Launch Pad: LA2 SL. Launch Vehicle: Skylark. Model: Skylark 7. LV Configuration: Skylark-7 SL363.
  • Grenades Aeronomy mission Nation: Australia. Agency: WRE/RAE. Apogee: 136 km (84 mi). References: 2.
1965 April 29 - 12:25 GMT - Launch Site: Woomera. Launch Complex: LA2. Launch Pad: LA2 SL. Launch Vehicle: Skylark. Model: Skylark 7. LV Configuration: Skylark-7 SL364.
  • Grenades Aeronomy mission Nation: Australia. Agency: WRE/RAE. Apogee: 132 km (82 mi). References: 2.
1965 April 29 - 13:56 GMT - Launch Site: Woomera. Launch Complex: LA2. Launch Pad: LA2 SL. Launch Vehicle: Skylark. Model: Skylark 7. LV Configuration: Skylark-7 SL461.
  • Grenades Aeronomy mission Nation: Australia. Agency: WRE/RAE. Apogee: 124 km (77 mi). References: 2.
1965 April 29 - 14:17 GMT - Launch Site: Wallops Island. Launch Complex: LA3A. Launch Pad: -. Launch Vehicle: Scout. Model: Scout X-4. LV Configuration: Scout X-4 S136R.
  • Explorer 27 Nation: USA. Program: Explorer. Payload: Beacon Explorer C. Mass: 60 kg (132 lb). Class: Earth. Type: Ionosphere. Spacecraft: Beacon. Agency: NASA GSF. Perigee: 932 km (579 mi). Apogee: 1,309 km (813 mi). Inclination: 41.20 deg. Period: 107.70 min. COSPAR: 1965-032A. USAF Sat Cat: 1328. Battery failed in 1968; ionospheric research and geodetic data. Spacecraft engaged in research and exploration of the upper atmosphere or outer space. References: 2, 6.
1965 April 29 - 16:19 GMT - Launch Site: Woomera. Launch Complex: LA2. Launch Pad: LA2 SL. Launch Vehicle: Skylark. Model: Skylark 7. LV Configuration: Skylark-7 SL462.
  • Grenades Aeronomy mission Nation: Australia. Agency: WRE/RAE. Apogee: 140 km (80 mi). References: 2.
1965 April 29 - 17:56 GMT - Launch Site: Woomera. Launch Complex: LA2. Launch Pad: LA2 SL. Launch Vehicle: Skylark. Model: Skylark 7. LV Configuration: Skylark-7 SL463.
  • Grenades Aeronomy mission Nation: Australia. Agency: WRE/RAE. Apogee: 135 km (83 mi). References: 2.
1965 April 29 - 20:40 GMT - Launch Site: Woomera. Launch Complex: LA2. Launch Pad: LA2 SL. Launch Vehicle: Skylark. Model: Skylark 7C. LV Configuration: Skylark-7C SL362.
  • Grenades / Sphere Aeronomy mission Nation: Australia. Agency: WRE/RAE. Apogee: 175 km (108 mi). References: 2.
1965 April 29 - 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 437 / Agena D SS-01B 1614.
  • KH-4A 1019 Nation: USA. Payload: KH-4A s/n 1019 / Agena D 1614. Mass: 1,500 kg (3,300 lb). Class: Surveillance. Type: Military. Spacecraft: KH-4A. Agency: NRO/CIA. Perigee: 181 km (112 mi). Apogee: 461 km (286 mi). Inclination: 85.00 deg. Period: 91.00 min. COSPAR: 1965-033A. USAF Sat Cat: 1330. Decay Date: 1965-05-26. KH-4A. Cameras operated successfully. Malfunction in recovery mode on 1019-2 negated recovery. References: 2, 6.
  • SRV 627 Nation: USA. Payload: SRV 1019-2. Mass: 60 kg (132 lb). Spacecraft: KH-4A. Agency: NRO/CIA. Perigee: 134 km (83 mi). Apogee: 509 km (316 mi). Inclination: 84.90 deg. Period: 91.00 min. COSPAR: 1965-033B. USAF Sat Cat: 1367. Decay Date: 1965-06-08. Cameras operated successfully. Malfunction in recovery mode on 1019-2 negated recovery. References: 2, 6.
1965 April 30 - 19:05 GMT - Launch Site: Vandenberg. Launch Complex: 395-D. Launch Pad: -. Launch Vehicle: Titan. Model: Titan 2. LV Configuration: Titan II B-54.
  • Card Deck operational test Nation: USA. Agency: USAF SAC. Apogee: 1,300 km (800 mi). References: 2.
1965 April 30 - 22:00 GMT - Launch Site: Vandenberg. Launch Complex: LF03. Launch Pad: -. Launch Vehicle: Minuteman 1. Model: Minuteman 1B. LV Configuration: Minuteman 1B 730.
  • Operational missile test Nation: USA. Agency: SAC 1STRAD. Apogee: 1,300 km (800 mi). References: 2.
1965 May -
  • Planned air drop tests of Dynasoar to begin Nation: USA. Spacecraft: Dynasoar. At the time the Dynasoar project was cancelled, completion of the first spacecraft was planned for summer 1964. Air-drop tests from a B-52 carrier aircraft were planned to begin in May 1965. Twenty such drop tests would be conducted up to the first orbital flight in July 1966. References: 26, 152.
1965 May 1 - 23:43 GMT - Launch Site: Thumba. Launch Complex: -. Launch Pad: -. Launch Vehicle: Belier. Model: Centaure. LV Configuration: Centaure C100 TERLS-23?.
  • ISRO 15.01 Ionosphere mission Nation: India. Agency: ISRO. Apogee: 140 km (80 mi). References: 2.
1965 May 5 - 03:23 GMT - Launch Site: Wallops Island. Launch Complex: -. Launch Pad: -. Launch Vehicle: Aerobee. Model: Aerobee 150. LV Configuration: Aerobee 150 NASA 04.89GG.
  • Ultraviolet astronomy mission Nation: USA. Agency: NASA. Apogee: 145 km (90 mi). References: 2.
1965 May 6 -
  • Apollo earth landing system tested Nation: USA. Program: Apollo. Spacecraft: Apollo CSM. The Apollo earth landing system (ELS) was tested in a drop of boilerplate (BP) 19 at El Centro, Calif. The drop removed constraints on the ELS for BP-22; also, it was a "prequalification" trial of the main parachutes before the start of the full qualification test program. References: 16.
1965 May 6-13 -
  • Apollo SLA would not survive a service propulsion system abort Nation: USA. Program: Apollo. Spacecraft: Apollo CSM. Structures and Mechanics Division engineers determined that the spacecraft-LEM-adapter would not survive a service propulsion system abort immediately after jettisoning of the launch escape tower. North American planned to strengthen the upper hinges and fasteners and to resize the shock attenuators on spacecraft 009. References: 16.
1965 May 6 - 15:00 GMT - Launch Site: Cape Canaveral. Launch Complex: LC20. Launch Pad: -. Launch Vehicle: Titan. Model: Titan 3A. LV Configuration: Titan IIIA 3A-6.
  • LES 2 Nation: USA. Mass: 37 kg (81 lb). Class: Technology. Type: Comsat. Spacecraft: LES. Agency: USAF. Perigee: 2,771 km (1,721 mi). Apogee: 14,810 km (9,200 mi). Inclination: 32.20 deg. Period: 309.90 min. COSPAR: 1965-034B. USAF Sat Cat: 1360. Experimental commsat. Space craft engaged in investigation of spaceflight techniques and technology (US Cat A). References: 2, 6.
  • LCS 1 Nation: USA. Mass: 34 kg (74 lb). Class: Calibration. Spacecraft: LCS. Agency: USAF. Perigee: 2,786 km (1,731 mi). Apogee: 2,795 km (1,736 mi). Inclination: 32.10 deg. Period: 145.60 min. COSPAR: 1965-034C. USAF Sat Cat: 1361. Aluminum sphere used for radar calibration. Space craft engaged in investigation of spaceflight techniques and technology (US Cat A). References: 2, 6.
1965 May 7 -
  • First Apollo launch escape system completion Nation: USA. Program: Apollo. Spacecraft: Apollo CSM. Launch escape system (LES) installation for CSM 009 was completed, marking the first LES completion. References: 16.
1965 May 7 - 09:50 GMT - Launch Site: Baikonur. Launch Complex: LC31. Launch Pad: -. Launch Vehicle: Soyuz. Model: Vostok 8A92. LV Configuration: Vostok 8A92 R15002-04.
  • Cosmos 66 Nation: USSR. Payload: Zenit-2 11F61 s/n 27. Mass: 4,720 kg (10,400 lb). Class: Surveillance. Type: Military. Spacecraft: Zenit-2. Agency: MOM. Perigee: 285 km (177 mi). Apogee: 397 km (246 mi). Inclination: 64.90 deg. Period: 91.30 min. COSPAR: 1965-035A. USAF Sat Cat: 1362. Duration: 8.00 days. Decay Date: 1965-05-15. Returned after 8 days. Unsuccessful mission. Parachute deployment failure. Spacecraft destroyed in crash. References: 2, 6,93.
1965 May 8 -
  • Voskhod-2 design review Nation: USSR. Program: Voskhod. Spacecraft: Voskhod. Flight: Voskhod 2. A meeting between the cosmonauts and OKB-1 becomes heated on the question of the Voskhod design. Korolev and his specialists attempt to minimise the design approach that made manual re-entry for Voskhod-2 so difficult. In fact the state commission concluded that it was impossible to conduct a manual re-entry with the crew in their seats. Korolev agreed that later Voskhods will be equipped with instruments allowing manual re-entry with the astronauts seated, and apologised for the oversight. References: 376.
1965 May 8 - Launch Site: Cape Canaveral. Launch Complex: LC32B. Launch Pad: -. Launch Vehicle: Minuteman 2. LV Configuration: Minuteman 2 455.
  • Research and development launch Nation: USA. Agency: USAF AFSC. Apogee: 1,300 km (800 mi). References: 2.
1965 May 9 - 07:49 GMT - Launch Site: Baikonur. Launch Complex: LC1. Launch Pad: -. Launch Vehicle: Soyuz. Model: Molniya 8K78M. LV Configuration: Molniya 8K78M U103-30.
  • Luna 5 Nation: USSR. Program: Luna. Payload: E-6 s/n 10. Mass: 1,474 kg (3,249 lb). Class: Planetary. Type: Lunar. Spacecraft: Luna E-6. Agency: MOM. Perigee: 159 km (98 mi). Apogee: 219 km (136 mi). Inclination: 64.80 deg. Period: 88.27 min. COSPAR: 1965-036A. USAF Sat Cat: 1366. Decay Date: 1965-05-12. Soft lunar landing attempt. The retrorocket system failed, and the spacecraft impacted the lunar surface at the Sea of Clouds. Western observers, among them England's Sir Bernard Lovell, correctly speculated that the craft's mission was a soft landing. References: 2, 6, 16, 64, 296.
1965 May 10 - Launch Site: Vandenberg. Launch Complex: LF09. Launch Pad: LF09?. Launch Vehicle: Minuteman 1. Model: Minuteman 1B. LV Configuration: Minuteman 1B 1003.
  • Operational missile test Nation: USA. Agency: SAC 1STRAD. Apogee: 1,300 km (800 mi). References: 2.
1965 May 10 - 07:30 GMT - Launch Site: Carnarvon. Launch Complex: CARN2. Launch Pad: -. Launch Vehicle: HAD. LV Configuration: HAD 165.
  • Falling sphere Aeronomy mission Nation: Australia. Agency: WRE. Apogee: 115 km (71 mi). References: 2.
1965 May 10 - 10:20 GMT - Launch Site: Carnarvon. Launch Complex: CARN2. Launch Pad: -. Launch Vehicle: HAD. LV Configuration: HAD 164.
  • Falling sphere Aeronomy mission Nation: Australia. Agency: WRE. Apogee: 116 km (72 mi). References: 2.
1965 May 10 - 13:20 GMT - Launch Site: Carnarvon. Launch Complex: CARN2. Launch Pad: -. Launch Vehicle: HAD. LV Configuration: HAD 162.
  • Falling sphere Aeronomy mission Nation: Australia. Agency: WRE. Apogee: 116 km (72 mi). References: 2.
1965 May 10 - 16:20 GMT - Launch Site: Carnarvon. Launch Complex: CARN2. Launch Pad: -. Launch Vehicle: HAD. LV Configuration: HAD 158.
  • Falling sphere Aeronomy mission Nation: Australia. Agency: WRE. Apogee: 109 km (67 mi). References: 2.
1965 May 10 - 19:20 GMT - Launch Site: Carnarvon. Launch Complex: CARN2. Launch Pad: -. Launch Vehicle: HAD. LV Configuration: HAD 170.
  • Falling sphere Aeronomy mission Nation: Australia. Agency: WRE. Apogee: 115 km (71 mi). References: 2.
1965 May 11 - 00:45 GMT - Launch Site: Carnarvon. Launch Complex: CARN2. Launch Pad: -. Launch Vehicle: HAD. LV Configuration: HAD 154.
  • Falling sphere Aeronomy mission Nation: Australia. Agency: WRE. Apogee: 111 km (68 mi). References: 2.
1965 May 11 - 03:10 GMT - Launch Site: Carnarvon. Launch Complex: CARN2. Launch Pad: -. Launch Vehicle: HAD. LV Configuration: HAD 155.
  • Falling sphere Aeronomy mission Nation: Australia. Agency: WRE. Apogee: 113 km (70 mi). References: 2.
1965 May 11 - 08:39 GMT - Launch Site: Woomera. Launch Complex: LA2. Launch Pad: -. Launch Vehicle: HAD. LV Configuration: HAD 160.
  • Aeronomy mission Nation: Australia. Agency: WRE. Apogee: 114 km (70 mi). References: 2.
1965 May 11 - 20:40 GMT - Launch Site: Woomera. Launch Complex: LA2. Launch Pad: LA2 SL. Launch Vehicle: Skylark. Model: Skylark 7C. LV Configuration: Skylark-7C SL361.
  • Sphere / Li Aeronomy mission Nation: Australia. Agency: WRE/RAE. Apogee: 181 km (112 mi). References: 2.
1965 May 12 - Launch Vehicle: Saturn I. Model: Saturn IB.
  • Thrust of the H-1 engine uprated Nation: USA. Program: Apollo. MSFC informed MSC that the thrust of the H-1 engine was being uprated to 1,000 kilonewtons (205,000 lbs), thus increasing the Saturn IB's payload capability. References: 16.
1965 May 12 -
  • Testing begins on rockets that would allow soft landing for Apollo CM Nation: USA. Program: Apollo. Spacecraft: Apollo CSM. Developmental testing began on a new landing device for the CM, one using rockets (mounted on the heatshield) that would be ignited immediately before impact. The current method for ensuring the integrity of the spacecraft during a landing in rough water involved strengthening of the aft structure. The new concept, should it prove practicable, would offer a twofold advantage: first, it would lighten the CM considerably; second, it would provide an improved emergency landing capability. References: 16.
1965 May 12 - 16:00 GMT - Launch Site: Cape Canaveral. Launch Complex: LC18A. Launch Pad: LC18A. Launch Vehicle: Scout. Model: Blue Scout Jr. LV Configuration: Blue Scout Jr 22-8.
  • OAR 22-8 / AFCRL-335 Magnetosphere mission Nation: USA. Agency: USAF. Apogee: 13,586 km (8,441 mi). References: 2.
1965 May 13 - 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 May 13 - 16:05 GMT - Launch Site: Woomera. Launch Complex: LA2. Launch Pad: LA2 SL. Launch Vehicle: Skylark. Model: Skylark 7C. LV Configuration: Skylark-7C SL139.
  • Electron density Ionosphere mission Nation: Australia. Agency: WRE/RAE. Apogee: 187 km (116 mi). References: 2.
1965 May 14 - 19:12 GMT - Launch Site: Kapustin Yar. Launch Complex: V-2. Launch Pad: -. Launch Vehicle: R-11. Model: R-11.
  • Ionosphere mission? Nation: USSR. Agency: RVSN. Apogee: 200 km (120 mi). References: 2.
1965 May 15 -
  • Institute of Space Research Created. Nation: USSR. Central Committee of the Communist Party and Council of Soviet Ministers Decree 'On establishment of the Institute of Space Research in the USSR Academy of Sciences on July 14. 1965' was issued. References: 474.
1965 May 16-June 15 -
  • Third series of Apollo water impact tests Nation: USA. Program: Apollo. Spacecraft: Apollo CSM. North American conducted the third in a series of water impact tests on boilerplate 1 to measure pressures on forward portions of the spacecraft. Data from the series supported those from tests with one- tenth scale models of the CM. The manufacturer reported, therefore, that it planned no further full-scale testing. References: 16.
1965 May 18 - Launch Site: Hammaguira. Launch Complex: Bacchus. Launch Pad: -. Launch Vehicle: VE. Model: Topaze VE111L. LV Configuration: Topaze VE111L LG1.
  • Test mission Nation: France. Agency: ONERA. Apogee: 100 km (60 mi). References: 2.
1965 May 18 - Launch Site: Vandenberg. Launch Complex: LF07. Launch Pad: -. Launch Vehicle: Minuteman 1. Model: Minuteman 1B. LV Configuration: Minuteman 1B 1115.
  • Operational missile test Nation: USA. Agency: SAC 1STRAD. Apogee: 1,300 km (800 mi). References: 2.
1965 May 18 - 05:00 GMT - Launch Site: Baikonur. Launch Complex: LC140/18. Launch Pad: -. Launch Vehicle: Tsiklon. Model: R-36 8K67.
  • Kura state trials missile launch Nation: USSR. Agency: RVSN. Apogee: 870 km (540 mi). References: 2.
1965 May 18 - 17:56 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 2-38-66.
  • X-15A-2 Stab, landing, ST test Nation: USA. Agency: NASA/USAF. Apogee: 31 km (19 mi). Maximum Speed - 5697 kph. Maximum Altitude - 31120 m. References: 2.
1965 May 18 - 18:02 GMT - Launch Site: Vandenberg. Launch Complex: SLC1W. Launch Pad: -. Launch Vehicle: Delta. Model: Thor SLV-2A Agena D. LV Configuration: Thor SLV-2A Agena D 438 / Agena D SS-01B 1615.
  • KH-4A 1021 Nation: USA. Payload: KH-4A s/n 1021 / Agena D 1615. Mass: 1,500 kg (3,300 lb). Class: Surveillance. Type: Military. Spacecraft: KH-4A. Agency: NRO/CIA. Perigee: 321 km (199 mi). Apogee: 399 km (247 mi). Inclination: 75.00 deg. Period: 91.70 min. COSPAR: 1965-037A. USAF Sat Cat: 1374. Decay Date: 1965-06-15. KH-4A. Aft camera ceased operation on pass 102. References: 2, 6.
1965 May 19 -
  • Apollo mission A-003 Nation: USA. Program: Apollo. Apollo mission A-003, a planned high-altitude abort test, was flown at WSMR. About 25 seconds after launch, and at an altitude of about three miles, the Little Joe II booster disintegrated as a result of violent - and unprogrammed - roll. The launch escape system (LES) functioned perfectly, however, and lifted the spacecraft (boilerplate 22) clear of the vehicle. ASPO Manager Joseph F. Shea, while acknowledging that A-003's "prime objectives . . . were not met," rightly observed that the LES nonetheless "proved its mettle in an actual emergency," References: 16.
1965 May 19 - 05:25 GMT - Launch Site: Woomera. Launch Complex: LA2. Launch Pad: LA2 SL. Launch Vehicle: Skylark. Model: Skylark 7C. LV Configuration: Skylark-7C SL138.
  • Solar X-rays / Electron density Ionosphere / solar x-rays mission Nation: Australia. Agency: WRE/RAE. Apogee: 179 km (111 mi). References: 2.
1965 May 19 - 13:01 GMT - Launch Site: White Sands. Launch Complex: LC36. Launch Pad: -. Launch Vehicle: Little Joe II. Model: Little Joe II 0-3-3. LV Configuration: Little Joe II-0-3-3 LJII-4 (12-51-2). FAILURE: Failure.
  • Apollo A-003 Nation: USA. Agency: NASA. Apogee: 6.00 km (3.70 mi). References: 2.
1965 May 19 - 20:11 GMT - Launch Site: Wallops Island. Launch Complex: -. Launch Pad: -. Launch Vehicle: Javelin. LV Configuration: Javelin NASA 8.29UI.
  • M / DTR Ionosphere mission Nation: USA. Agency: NASA. Apogee: 947 km (588 mi). References: 2.
1965 May 20 - 03:45 GMT - 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 May 20 - 16:30 GMT - Launch Site: Vandenberg. Launch Complex: SLC10W. Launch Pad: -. Launch Vehicle: Delta. Model: Thor Burner 1. LV Configuration: Thor Burner 1 282.
  • DMSP-Block-4A F3 Nation: USA. Program: DMSP. Payload: DAPP 12. Mass: 130 kg (280 lb). Class: Earth. Type: Weather. Spacecraft: DMSP Block 4A. Agency: USAF. Perigee: 503 km (312 mi). Apogee: 731 km (454 mi). Inclination: 98.10 deg. Period: 97.10 min. COSPAR: 1965-038A. USAF Sat Cat: 1377. Defense Meteorological Satellite Program. References: 2, 6.
1965 May 21 -
  • Preliminary flight rating tests on the Apollo reaction control engine Nation: USA. Program: Apollo. Spacecraft: Apollo CSM. Marquardt Corporation completed preliminary flight rating tests on the reaction control engine for the SM. References: 16.
1965 May 21 - Launch Site: Hammaguira. Launch Complex: Bacchus. Launch Pad: -. Launch Vehicle: VE. Model: Topaze VE111L. LV Configuration: Topaze VE111L LG2.
  • Test mission Nation: France. Agency: ONERA. Apogee: 100 km (60 mi). References: 2.
1965 May 21 - 23:53 GMT - Launch Site: Vandenberg. Launch Complex: 395-B. Launch Pad: -. Launch Vehicle: Titan. Model: Titan 2. LV Configuration: Titan II B-51.
  • Front Sight operational test Nation: USA. Agency: USAF SAC. Apogee: 1,300 km (800 mi). References: 2.
1965 May 22 - 02:02 GMT - Launch Site: Ascension. Launch Complex: -. Launch Pad: -. Launch Vehicle: Apache. Model: Nike Apache. LV Configuration: Nike Apache NASA 14.47UA.
  • UM Pitot 16 / FIRE cal Aeronomy mission Nation: USA. Agency: NASA. Apogee: 147 km (91 mi). References: 2.
1965 May 22 - 06:29 GMT - Launch Site: Baikonur. Launch Complex: LC41/3. Launch Pad: -. Launch Vehicle: R-16. Model: R-16U.
  • Military training launch to Kamchatka Nation: USSR. Agency: RVSN. Apogee: 920 km (570 mi). References: 2.
1965 May 22 - 14:00 GMT - Launch Site: Ascension. Launch Complex: -. Launch Pad: -. Launch Vehicle: Apache. Model: Nike Apache. LV Configuration: Nike Apache NASA 14.48UA.
  • UM Pitot 17 / FIRE cal Aeronomy mission Nation: USA. Agency: NASA. Apogee: 158 km (98 mi). References: 2.
1965 May 22 - 21:55 GMT - Launch Site: Cape Canaveral. Launch Complex: LC12. Launch Pad: -. Launch Vehicle: Atlas. Model: Atlas D. LV Configuration: Atlas D 264D.
  • FIRE 2 Nation: USA. Agency: USAF. Apogee: 817 km (507 mi). Suborbital reentry heating experiment using the FIRE subscale Apollo capsule. An Atlas D booster propelled the instrumented probe, called a "flying thermometer," into a ballistic trajectory over 805 km (500 mi) high. After 26 minutes of flight, when the spacecraft began its descent, a solid-fueled Antares rocket accelerated its fall.

    The probe entered the atmosphere at a speed of 40,877 km (25,400 mph) and generated temperatures of about 11,206K (20,000 degrees F). Data on heating were transmitted to ground stations throughout the descent. Thirty-two minutes after the launch - and but six minutes after the Antares was fired - the device impacted in the Atlantic about 8,256 km (5,130 mi) southeast of the Cape. References: 2.

1965 May 23 -
  • American Apollo astronauts returning from the moon to be quarantined Nation: USA. Program: Apollo. The Life Sciences Committee of the National Academy of Sciences' Space Science Board recommended to NASA that American astronauts returning from the moon and planets be kept in quarantine for at least three weeks to prevent possible contamination of the earth by extraterrestrial organisms, Additional Details: American Apollo astronauts returning from the moon to be quarantined. References: 16.
1965 May 25 - Launch Site: Woomera. Launch Complex: LA2. Launch Pad: -. Launch Vehicle: HAD.
  • Aeronomy mission Nation: Australia. Agency: WRE. Apogee: 110 km (60 mi). References: 2.
1965 May 25 - 07:35 GMT - Launch Site: Cape Canaveral. Launch Complex: LC37B. Launch Pad: -. Launch Vehicle: Saturn I. Model: Saturn I. LV Configuration: Saturn I-Blk2 SA-8.
  • Pegasus 2 Nation: USA. Program: Apollo. Payload: Pegasus 2. Mass: 10,464 kg (23,069 lb). Class: Earth. Type: Micrometeoroid. Spacecraft: Pegasus. Agency: NASA MSF. Perigee: 502 km (311 mi). Apogee: 740 km (450 mi). Inclination: 31.70 deg. Period: 97.00 min. COSPAR: 1965-039A. USAF Sat Cat: 1381. Decay Date: 1979-11-03. Pegasus 2 was a meteoroid detection satellite. The Saturn I launch vehicle (SA-8) placed the spacecraft, protected by a boilerplate CSM (BP-26), into a 740-by-509-km (460-by-316-mi) orbit. Once in orbit, the dummy CSM was jettisoned. Pegasus 2, still attached to the second stage of the launch vehicle, then deployed its 29-m (96-ft) winglike panels. Within several hours, the device began registering meteoroid hits. References: 2, 6, 16, 26, 27.
  • Apollo-Model 4 Nation: USA. Program: Apollo. Payload: Apollo CSM Boilerplate 26. Class: Manned. Type: Lunar spacecraft. Spacecraft: Apollo CSM. Agency: NASA MSC. Perigee: 511 km (317 mi). Apogee: 739 km (459 mi). Inclination: 31.70 deg. Period: 97.21 min. COSPAR: 1965-039B. USAF Sat Cat: 1385. Decay Date: 1989-07-08. References: 2, 279.
1965 May 25 - 10:48 GMT - Launch Site: Baikonur. Launch Complex: LC31. Launch Pad: -. Launch Vehicle: Soyuz. Model: Voskhod 11A57. LV Configuration: Voskhod 11A57 R15001-04.
  • Cosmos 67 Nation: USSR. Payload: Zenit-4. Mass: 6,300 kg (13,800 lb). Class: Surveillance. Type: Military. Spacecraft: Zenit-4. Agency: MOM. Perigee: 203 km (126 mi). Apogee: 351 km (218 mi). Inclination: 51.80 deg. Period: 90.10 min. COSPAR: 1965-040A. USAF Sat Cat: 1382. Duration: 8.00 days. Decay Date: 1965-06-02. High resolution photo reconnaissance satellite; returned film capsule References: 2, 6.
1965 May 25 - 18:12 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 1-54-88.
  • X-15A IFDS/MIT/RAS modification technology / test Nation: USA. Agency: NASA/USAF. Apogee: 54 km (33 mi). Maximum Speed - 5100 kph. Maximum Altitude - 54803 m. References: 2.
1965 May 25 - 23:20 GMT - Launch Site: Eglin. Launch Complex: -. Launch Pad: -. Launch Vehicle: Exos. LV Configuration: Exos CRL AD13.815.
  • EM Absorption Ionosphere mission Nation: USA. Agency: USAF. Apogee: 488 km (303 mi). References: 2.
1965 May 26 -
  • Apollo LEM control weight revised Nation: USA. Program: Apollo. Spacecraft: Apollo LM. ASPO requested the Apollo Program Director to revise the LEM control weight at translunar injection as follows:

    • Ascent stage - 2,193kg (4,835lbs)
    • Descent stage - 2,166kg (4,775lbs)
    • Total LEM (fueled) - 14,515kg (32,000lbs)
    The increase would be made possible by reductions of service propulsion system propellant requirements associated with the revised delta-V budget. ASPO pointed out that existing CSM and adapter control weight propellant requirements allowed a maximum LEM injected weight of 14,877 kg (32,800 lbs) with no increase in the launch vehicle payload requirement. References: 16.
1965 May 26 - Launch Site: White Sands. Launch Complex: LC50. Launch Pad: -. Launch Vehicle: Sprint.
  • Test mission Nation: USA. Agency: USA. Apogee: 3.00 km (1.80 mi). References: 2.
1965 May 26 - Launch Site: Cape Canaveral. Launch Complex: LC32B. Launch Pad: -. Launch Vehicle: Minuteman 2. LV Configuration: Minuteman 2 456.
  • Research and development launch Nation: USA. Agency: USAF AFSC. Apogee: 1,300 km (800 mi). References: 2.
1965 May 26 - 19:01 GMT - Launch Site: Wallops Island. Launch Complex: -. Launch Pad: -. Launch Vehicle: Javelin. LV Configuration: Javelin NASA 8.37GI. FAILURE: Failure.
  • Ionosphere mission Nation: USA. Agency: NASA. Apogee: 320 km (190 mi). References: 2.
1965 May 26 - 23:20 GMT - Launch Site: Eglin. Launch Complex: -. Launch Pad: -. Launch Vehicle: Exos. LV Configuration: Exos CRL AD13.812.
  • EM Absorption Ionosphere mission Nation: USA. Agency: USAF. Apogee: 488 km (303 mi). References: 2.
1965 May 27 - Launch Site: Hammaguira. Launch Complex: Blandine. Launch Pad: -. Launch Vehicle: Veronique. Model: Veronique 61. LV Configuration: Veronique 61 VA79.
  • FU-144 Lyra alpha Solar ultraviolet mission Nation: France. Agency: FR. Apogee: 70 km (43 mi). FU144 Atomic H (Ly-alpha) mission. References: 2.
1965 May 27 - 19:30 GMT - Launch Site: Vandenberg. Launch Complex: SLC4E. Launch Pad: -. Launch Vehicle: Atlas. Model: SLV-3 Agena D. LV Configuration: SLV-3 Agena D 7108 / Agena D 7108.
  • KH 7-18 Nation: USA. Payload: KH-7 no. 18. Mass: 2,000 kg (4,400 lb). Class: Surveillance. Type: Military. Spacecraft: KH-7. Agency: NRO/USAF. Perigee: 149 km (92 mi). Apogee: 267 km (165 mi). Inclination: 95.60 deg. Period: 88.70 min. COSPAR: 1965-041A. USAF Sat Cat: 1386. Decay Date: 1965-06-01. KH-7 type satellite. Space craft engaged in investigation of spaceflight techniques and technology (US Cat A). References: 2, 6, 278.
1965 May 27 - 23:56 GMT - Launch Site: Fort Churchill. Launch Complex: -. Launch Pad: -. Launch Vehicle: Black Brant. Model: Black Brant 2. LV Configuration: Black Brant II BB-2A-51. FAILURE: Failure.
  • Ionosphere mission Nation: Canada. Agency: NRCC. Apogee: 27 km (16 mi). References: 2.
1965 May 28 - 02:23 GMT - Launch Site: Baikonur. Launch Complex: LC60/6. Launch Pad: -. Launch Vehicle: R-16. Model: R-16U.
  • Military training launch to Kamchatka Nation: USSR. Agency: RVSN. Apogee: 743 km (461 mi). References: 2.
1965 May 28 - 02:54 GMT - Launch Site: Vandenberg. Launch Complex: 576B3. Launch Pad: -. Launch Vehicle: Atlas. Model: Atlas D. LV Configuration: Atlas D 68D / OV-1. FAILURE: Failure.
  • OV1-03 Nation: USA. Class: Earth. Type: Magnetosphere. Spacecraft: OV1. Agency: USAF AFSC. COSPAR: F650528A. Decay Date: 1965-05-28. References: 126, 278.
1965 May 28 - 17:43 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 3-42-65.
  • X-15A Radiometer/Scan/BLN Test/Aeronomy mission Nation: USA. Agency: NASA/USAF. Apogee: 63 km (39 mi). Maximum Speed - 6040 kph. Maximum Altitude - 63886 m. References: 2.
1965 May 29 - 12:00 GMT - Launch Site: Cape Canaveral. Launch Complex: LC17B. Launch Pad: -. Launch Vehicle: Delta. Model: Thor Delta C. LV Configuration: Thor Delta C 441/D31.
  • Explorer 28 Nation: USA. Program: Explorer. Payload: IMP C. Mass: 58 kg (127 lb). Class: Earth. Type: Magnetosphere. Spacecraft: IMP. Agency: NASA GSF. Perigee: 229 km (142 mi). Apogee: 261,206 km (162,305 mi). Inclination: 30.50 deg. Period: 8,419.70 min. COSPAR: 1965-042A. USAF Sat Cat: 1388. Decay Date: 1968-07-04. Magnetic field, radiation data. Spacecraft engaged in research and exploration of the upper atmosphere or outer space (US Cat B). References: 2, 6.
1965 May 30 - 20:00 GMT - Launch Site: Rarotonga. Launch Complex: -. Launch Pad: -. Launch Vehicle: Tomahawk Sandia. Model: Nike Tomahawk. LV Configuration: Nike Tomahawk-9 Sandia 152-78.
  • LASL Eclipse Solar x-ray mission Nation: USA. Agency: Sandia. Apogee: 270 km (160 mi). References: 2.
1965 May 30 - 20:00 GMT - Launch Site: Rarotonga. Launch Complex: -. Launch Pad: -. Launch Vehicle: Tomahawk Sandia. Model: Nike Tomahawk. LV Configuration: Nike Tomahawk-9 Sandia 152-77.
  • LASL Eclipse Solar x-ray mission Nation: USA. Agency: Sandia. Apogee: 270 km (160 mi). References: 2.
1965 May 30 - 20:00 GMT - Launch Site: Rarotonga. Launch Complex: -. Launch Pad: -. Launch Vehicle: Tomahawk Sandia. Model: Nike Tomahawk. LV Configuration: Nike Tomahawk-9 Sandia 152-75.
  • LASL Eclipse Solar x-ray mission Nation: USA. Agency: Sandia. Apogee: 270 km (160 mi). References: 2.
1965 May 30 - 20:00 GMT - Launch Site: Rarotonga. Launch Complex: -. Launch Pad: -. Launch Vehicle: Tomahawk Sandia. Model: Nike Tomahawk. LV Configuration: Nike Tomahawk-9 Sandia 152-76.
  • LASL Eclipse Solar x-ray mission Nation: USA. Agency: Sandia. Apogee: 270 km (160 mi). References: 2.
1965 May 30 - 20:00 GMT - Launch Site: Rarotonga. Launch Complex: -. Launch Pad: -. Launch Vehicle: Tomahawk Sandia. Model: Nike Tomahawk. LV Configuration: Nike Tomahawk-9 Sandia 152-74.
  • LASL Eclipse Solar x-ray mission Nation: USA. Agency: Sandia. Apogee: 270 km (160 mi). References: 2.
1965 May 31 - 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 May 31 - 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 May 31 - Launch Site: Hammaguira. Launch Complex: Bacchus. Launch Pad: -. Launch Vehicle: Diamant. Model: Rubis. LV Configuration: Rubis R5.
  • A-1 capsule Nation: France. Agency: ONERA. Apogee: 2,000 km (1,200 mi). References: 2.
1965 May -
  • Qualification testing on the Apollo tower jettison motor completed Nation: USA. Program: Apollo. Spacecraft: Apollo CSM. Thiokol Chemical Company completed qualification testing on the tower jettison motor. An ignition delay on February 22 had necessitated a redesign of the igniter cartridge. Subsequently, Thiokol developed a modified pyrogen seal, which the firm tested during late August and early September. References: 16.
1965 May -
  • Three flights made with Apollo LLRV Nation: USA. Program: Apollo. Spacecraft: Apollo LLRV. Three flights were made with the lunar landing research vehicle (LLRV) by FRC pilot Don Mallick for the purpose of checking the initial weighing, the thrust-to-weight, and the automatic throttle systems.

    General Electric would update the LLRV CF-700 jet engines at their Edwards AFB facility rather than at Lynn, Mass. The change in work location would mean an earlier delivery date and a significant cost reduction. The updating would make the engines comparable to the production engines and would add an additional 890 newtons (200 lbs) of thrust. References: 16.

1965 June 1 -
  • Beginning of Project Spiral Nation: USSR. Class: Manned. Type: Spaceplane. Spacecraft: MiG 105-11. With the cancellation of Chelomei's desultory R spaceplane development, the job is handed to 'the profis' - the fighter design bureaus of MiG and Sukhoi. Both would use an air breathing first stage (the XB-70 clone T-4 in Sukhoi's case, a huge new Tupolev hypersonic aircraft 'to be developed' in MiG's case). Second stage would be a conventional expendable rocket stage which would carry the relatively small Spiral spaceplane into orbit. Korolev had been doing some 'back door' work with MiG in competition to Chelomei's R project for some time (Began with 1962 Mikoyan study '50-50': Hypersonic first stage to Mach 5.5; rocket stage with one man), and immediately proposed tests from atop R-7 rockets as early as 1967. At the time all this was begun Dyna Soar was still an active US program. References: 83.
1965 June 1 -
  • Voskhod Physician Cosmonaut Training Group selected. Nation: USSR. The group was selected to provide trainees for planned Voskhod long-duration biomedical spaceflights to be made with a physician aboard.
1965 June 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 June 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 June 1 - Launch Site: Shijiedu. Launch Complex: -. Launch Pad: -. Launch Vehicle: T-7. Model: T-7A-S.
  • Life Science (mice) Biological mission Nation: China. Agency: Shanghai. Apogee: 70 km (43 mi). References: 2.
1965 June 2 - 06:22 GMT - Launch Site: White Sands. Launch Complex: LC35. Launch Pad: -. Launch Vehicle: Aerobee. Model: Aerobee 150. LV Configuration: Aerobee 150 NASA 04.17UG.
  • Princeton UVS Ultraviolet astronomy mission Nation: USA. Agency: NASA. Apogee: 181 km (112 mi). References: 2.
1965 June 2 - 10:19 GMT - Launch Site: Eglin. Launch Complex: -. Launch Pad: -. Launch Vehicle: Cajun. Model: Nike Cajun. LV Configuration: Nike Cajun AD6.850.
  • Ionosphere winds, T Aeronomy mission Nation: USA. Agency: USAF. Apogee: 121 km (75 mi). References: 2.
1965 June 2 - 10:30 GMT - Launch Site: Eglin. Launch Complex: -. Launch Pad: -. Launch Vehicle: Cajun. Model: Nike Cajun. LV Configuration: Nike Cajun AE6.498.
  • BETH Aeronomy mission Nation: USA. Agency: USAF. Apogee: 121 km (75 mi). References: 2.
1965 June 2 - 10:40 GMT - Launch Site: Vandenberg. Launch Complex: LF08. Launch Pad: -. Launch Vehicle: Minuteman 1. Model: Minuteman 1B. LV Configuration: Minuteman 1B 1054.
  • Operational missile test Nation: USA. Agency: SAC 1STRAD. Apogee: 1,300 km (800 mi). References: 2.
1965 June 2 - 14:19 GMT - Launch Site: Fort Churchill. Launch Complex: -. Launch Pad: -. Launch Vehicle: Black Brant. Model: Black Brant 2. LV Configuration: Black Brant II BB-2A-50.
  • Aurora / ionosphere mission Aurora / ionosphere mission Nation: Canada. Agency: NRCC. Apogee: 150 km (90 mi). References: 2.
1965 June 3 -
  • Qualification testing of the earth landing system for Apollo Nation: USA. Program: Apollo. Spacecraft: Apollo CSM. Northrop-Ventura began qualification testing of the earth landing system for Apollo with a drop of boilerplate 19 at El Centro, Calif. The entire landing sequence took place as planned; all parachutes performed well. References: 16.
1965 June 3 - Launch Site: Hammaguira. Launch Complex: Bacchus. Launch Pad: -. Launch Vehicle: Diamant. Model: Rubis. LV Configuration: Rubis R6.
  • A-1 capsule Nation: France. Agency: ONERA. Apogee: 2,000 km (1,200 mi). References: 2.
1965 June 3 - 10:38 GMT - Launch Site: Vandenberg. Launch Complex: 576B2. Launch Pad: -. Launch Vehicle: Atlas. Model: Atlas D. LV Configuration: Atlas D 177D.
  • NTMP RMV-304 re-entry vehicle test flight Nation: USA. Agency: USAF AFSC. Apogee: 1,800 km (1,100 mi). References: 2.
1965 June 3 - 15:16 GMT - Launch Site: Cape Canaveral. Launch Complex: LC19. Launch Pad: -. Launch Vehicle: Titan. Model: Titan II GLV. LV Configuration: Titan II GLV GT-4 / 62-12559.
  • Gemini 4 Nation: USA. Program: Gemini. Payload: Gemini SC4. Mass: 3,574 kg (7,879 lb). Class: Manned. Type: Spacecraft. Spacecraft: Gemini. Location of Spacecraft: National Air and Space Museum (Smithsonian Institution), Washington, DC. Agency: NASA MSC. Perigee: 162 km (100 mi). Apogee: 281 km (174 mi). Inclination: 32.50 deg. Period: 88.80 min. COSPAR: 1965-043A. USAF Sat Cat: 1390. Duration: 4.08 days. Decay Date: 1965-06-07. Crew: McDivitt, White. Flight: Gemini 4. The second manned and first long-duration mission in the Gemini program. Major objectives of the four-day mission were demonstrating and evaluating the performance of spacecraft systems in a long-duration flight and evaluating effects on the crew of prolonged exposure to the space environment. Secondary objectives included demonstrating extravehicular activity (EVA) in space, conducting stationkeeping and rendezvous maneuvers with the second stage of the launch vehicle, performing significant in-plane and out-of-plane maneuvers, demonstrating the ability of the orbit attitude and maneuver system (OAMS) to back up the retrorockets, and executing 11 experiments. The stationkeeping exercise was terminated at the end of the first revolution because most of the OAMS propellant allocated for the exercise had been used; further efforts would jeopardize primary mission objectives and could mean the cancellation of several secondary objectives. No rendezvous was attempted. The only other major problem to mar the mission was the inadvertent alteration of the computer memory during the 48th revolution in an attempt to correct an apparent malfunction. This made the planned computer-controlled reentry impossible and required an open-loop ballistic reentry. All other mission objectives were met. The flight crew began preparing for EVA immediately after terminating the stationkeeping exercise. Although preparations went smoothly, McDivitt decided to delay EVA for one revolution, both because of the high level of activity required and because deletion of the rendezvous attempt reduced the tightness of the schedule. Ground control approved the decision. The spacecraft hatch was opened at 4 hours 18 minutes into the flight and White exited 12 minutes later, using a hand-held maneuvering gun. White reentered the spacecraft 20 minutes after leaving it. The hatch was closed at 4 hours 54 minutes ground elapsed time. Drifting flight was maintained for the next two and one-half days to conserve propellant. The spacecraft landed in the Atlantic Ocean about 725 km east of Cape Kennedy - some 65 km from its nominal landing point. The crew boarded a helicopter 34 minutes after landing and was transported to the prime recovery ship, the aircraft carrier Wasp. Spacecraft recovery was completed at 2:28 p.m., a little more than 100 hours after Gemini 4 had been launched. Gemini 4 was the first mission to be controlled from the mission control center in Houston.

    The space walk was hurriedly included after the Russian first in Voskhod 2. White seemed to have a lot more fun than Leonov and McDivitt took the pictures that came to symbolize man in space. With this flight the US finally started to match Russian flight durations. References: 2, 6, 16, 26, 33,60.

1965 June 3 - 19:46 GMT -
  • EVA Gemini 4-1 Nation: USA. Program: Gemini. Class: Manned. Type: Spacecraft. Spacecraft: Gemini. Crew: White. Flight: Gemini 4. EVA Duration: 0.0250 days. First American walk in space; tested spacesuit and ability to manoeuvre. References: 66.
1965 June 3 - 20:54 GMT - Launch Site: Barbados. Launch Complex: HARP. Launch Pad: -. Launch Vehicle: Martlet. Model: Martlet 2.
  • Ionosphere mission Nation: Canada. Agency: HARP. Apogee: 105 km (65 mi). References: 2.
1965 June 5 - Launch Site: Shijiedu. Launch Complex: -. Launch Pad: -. Launch Vehicle: T-7. Model: T-7A-S.
  • Life Science (mice) Biological mission Nation: China. Agency: Shanghai. Apogee: 70 km (43 mi). References: 2.
1965 June 5 - 05:40 GMT - Launch Site: Hammaguira. Launch Complex: Bacchus. Launch Pad: -. Launch Vehicle: Diamant. Model: Rubis. LV Configuration: Rubis R7.
  • Rubis 01/D-1 Test/Ionosphere mission Nation: France. Agency: CNES. Apogee: 2,020 km (1,250