Atlas Family
From left - MX-774 of 1946; MX-1593 of 1953; Atlas A, B, D; Atlas Agena D; Atlas Centaur; Atlas I, IIA, IIAS, IIIA, IIIB, V
Credit: © Mark Wade
New Generation LVs
From left: 3 versions of Atlas 5, 5 versions of Delta 4, 3 versions of Chinese NGLV, Ariane 5. Vertical scale is 10 m intervals.
Credit: © Mark Wade
WS-107
WS-107 Concept 1. Before the Tea Pot report, Atlas was to have five thrust chambers and double the throw weight.
Credit: Ronald Wade
WS-107
WS-107 Concept 2. First mock-up of the Atlas missile in the three-chamber configuration.
Credit: Ronald Wade
The Atlas rocket, originally developed as America's first ICBM, was the basis for most early American space exploration and was that country's most successful medium-lift commercial launch vehicle. It launched America's first astronaut into orbit; the first generations of spy satellites; the first lunar orbiters and landers; the first probes to Venus, Mars, Mercury, Jupiter, and Saturn; and was America's most successful commercial launcher of communications satellites. Its innovative stage-and-a-half and 'balloon tank' design provided the best dry-mass fraction of any launch vehicle ever built. It was retired in 2004 after 576 launches in a 47-year career.
Atlas began with a US Army Air Corps request for proposal in October 1945 for long-range missile designs. By 10 January 1946, Consolidated-Vultee's engineers, under the leadership of Belgian-born Karel Bossart, submitted their proposals for two 6,000-nautical mile missiles: one subsonic, winged, and jet powered; the other supersonic, ballistic, and rocket powered. New technologies proposed for the ballistic missile included extremely low structural weight through use of steel monocoque single-wall construction tanks, kept rigid by internal tank pressure; gimbaled rocket engines; a detachable warhead section; and nearly single-stage to orbit performance through the ‘stage-and-a-half' approach of jettisoning the booster engines during the ascent.
On 19 April Convair received a contract for $1,893,000 to fabricate and test ten MX-774 Hiroc missiles to verify Bossart's innovative ballistic missile concepts. Captive testing of the MX-774 research rockets began in San Diego in 1947. In June, Consolidated Vultee was notified that it had lost the cruise missile competition; Northrop and Martin received contracts for development of their subsonic jet-powered cruise missile designs. Defense cutbacks forced the Air Force to terminate the MX-774 contract in July 1947, only three months before the first scheduled flight. The remaining contract funds allowed three MX-774's to be test-launched at White Sands Proving Ground in July-December 1947. Further work at Convair was reduced to ‘Mafia' low-level design activity using company funds.
The outbreak of the Korean war and the beginning of the cold war loosened the federal purse strings. Convair received a new contract (MX-1593) in September 1951 to begin design of a ballistic missile incorporating the design features validated by the MX-774. In 1953 the now-Convair Division of General Dynamics presented a plan to the Air Force for an accelerated program.
A major propulsion problem in the early 1950's was that liquid rocket motor ignition reliability was less than 50 percent. This led to the stage-and-a-half concept, with all engines ignited prior to lift-off and the booster engines jettisoned during flight. This allowed confirmation that all engines were functioning correctly before releasing the missile for flight.
A full go-ahead for the Atlas design was ordered in January 1955 as Weapon System WS107A-l. At Convair the project was known the Model 7 (in Russia, Korolev was working on the competing R-7 ICBM - evidently both sides wanted to use the lucky number). In September 1955, faced with intelligence reports of Russian progress on their ICBM, the Atlas received the highest national development priority. The project became one of the largest and most complex production, testing, and construction programs ever undertaken. The first propulsion system and component tests were conducted in June 1956; the first captive and flight-test missiles were completed later the same year.
The first Atlas A flight took place on 11 June 1957. In a tremendous national effort, by 1959 a peak of 33,000 personnel were working on the project. Total cost of the Atlas ICBM program to the United States was $8 billion. About a quarter of this went to Convair to design and develop the missile and launch facilities. The balance was for the tremendous cost of the ICBM launch facilities. For all of this effort, the Atlas was quickly obsolete, and the facilities were closed by 1966 after five years of service. However surplus ICBM's were stored, refurbished, and used as space launch vehicles until the last was flown in 1995 - 33 years after it was manufactured.
The first operational missile, the Atlas D, was the basis for launching the Mercury manned spacecraft into orbit. By use of Agena and Centaur upper stages, the Atlas became the medium-lift workhorse of American manned, reconnaissance, planetary, and geosynchronous-orbit space programs. After the retirement of the Atlas-Agena in 1978, the Centaur stage became standard on Atlas launch vehicles.
Centaur began with a contract awarded to General Dynamics by the Advanced Research Project Agency in 1958. The first space vehicle to use liquid hydrogen, Centaur was a pioneering project that solved the many technical problems of using the super-cryogenic and highly volatile fuel. Pratt & Whitney Aircraft was awarded the contract to develop Centaur's RL-10 engines. The US Air Force had already built the first large-quantity liquid hydrogen production facility for the deep black Suntan reconnaissance program.
In 1962, with the hydrogen propulsion technology being vital to the success of the Apollo program, Centaur management was transferred to NASA's Lewis Research Center. Lewis had fired their first experimental Lox/LH2 engine of 5,000 pounds thrust in 1953. The Centaur project was given the highest DX priority, but suffered delays due to management problems at both NASA and Convair. The first successful flight of Centaur atop Atlas occurred in November 1963. However thereafter von Braun's Saturn S-IV stage, using six of the RL-10 motors, leapfrogged the Centaur program . By the time of the first operational Centaur mission in May 1966, the S-IV had already completed its test series of six orbital flights. Yet thirty years later, the Saturn was long gone, and the Centaur continued, having been launched or planned for launch from Atlas, Titan, Delta, and Shuttle vehicles. Production continued into the 21st century, and no replacement for the RL-10 engine, the ultimate engine using the ultimate propellants, was ever put into production.
More... - Chronology...
Associated Spacecraft
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Score American communications technology satellite. One launch, 1958.12.18. Signal Communication by Orbiting Relay Equipment; first communications satellite; transmitted taped messages for 13 days. More...
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Mercury American manned spacecraft. 18 launches, 1960.01.21 (Mercury LJ-1B) to 1963.05.15 (Mercury MA-9). America's first man-in-space project. The capsule had to be as small as possible to match the orbital payload capability of America's first ICBM, the Atlas. More...
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Pioneer P 3 American lunar orbiter. 4 launches, 1959.11.26 (Pioneer (P 3)) to 1960.12.15 (Pioneer (P 31)). The least successful lunar spacecraft; none even achieved orbit in four attempts. More...
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Midas American military early warning satellite. 18 launches, 1960.02.26 (Midas 1) to 1966.10.05 (Midas 12). Part of a then-secret USAF program known as WS-117L, the MIDAS (Missile Defense Alarm System) program began in November 1958. More...
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Samos American military surveillance satellite. 17 launches, 1960.10.11 (Samos 1) to 1962.11.11 (Samos 11). First generation photo surveillance; return of camera and film by capsule; program still partially classified, evidently due to embarrassment. More...
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Ranger 1-2 American lunar impact probe. 2 launches, 1961.08.23 (Ranger 1) to 1961.11.18 (Ranger 2). More...
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Westford Needles American passive communications satellite. 3 launches, 1961.10.21 (Westford) to 1963.05.09 (Westford). In an attempt to lay a radio-reflective ring around the world, small metal dipole needles were allowed to sublimate out of a matrix. More...
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SECOR American earth geodetic satellite. 13 launches, 1962.01.24 (Secor) to 1969.04.14 (SECOR 13). More...
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Ranger 3-4-5 American lunar lander. 3 launches, 1962.01.26 (Ranger 3) to 1962.10.18 (Ranger 5). More...
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Mariner 1-2 American Venus probe. 2 launches, 1962.07.22 (Mariner 1) to 1962.08.27 (Mariner 2). The world's first successful interplanetary spacecraft. More...
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ERS American earth magnetosphere satellite. 7 launches, 1962.09.17 (TRS) to 1967.04.28. Environmental Research Satellites were especially designed for piggyback launching from large primary mission vehicles. More...
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SSF American military naval signals reconnaisance satellite. 54 launches, 1963.03.18 (P-11 No. 1) to 1989.08.08 (USA 41). More...
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TRS American technology satellite. 5 launches, 1963.05.09 (TRS 2) to 1964.07.17 (TRS 6). TRS satellites undertook a range of engineering experiments related to radiation-hardening of solar cells and spacecraft electronics. More...
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Dash American military technology satellite. 2 launches, 1963.05.09 (Dash 1) and 1963.07.18 (Dash 2). Space craft engaged in investigation of spaceflight techniques and technology. More...
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KH-7 American military surveillance satellite. 43 launches, 1963.07.12 (KH 7-01 (Gambit)) to 1967.06.04 (KH 7-38). US reconnaissance satellite. Still classified. Camera believed to have ground resolution of 0.46 m. Film returned in two capsules. More...
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Vela American nuclear detection surveillance satellite. 6 launches, 1963.10.17 (Vela 2) to 1965.07.20 (Vela 6). The Vela (meaning "watchman" in Spanish) series of spacecraft were designed to monitor world-wide compliance with the 1963 nuclear test ban treaty. More...
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Surveyor American lunar lander. 13 launches, 1963.11.27 (Atlas Centaur 2) to 1968.01.07 (Surveyor 7). Jet Propulsion Laboratory's Surveyor series soft-landed on the moon, provided images of the lunar surface, and tested the characteristics of the lunar soil. More...
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Ranger 6-7-8-9 American lunar impact probe. 4 launches, 1964.01.30 (Ranger 6) to 1965.03.21 (Ranger 9). After a series of failures with the more ambitious early Ranger spacecraft, the design was simplified and the lander was deleted. More...
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OGO American earth magnetosphere satellite. 6 launches, 1964.09.05 (OGO 1) to 1969.06.05 (OGO 6). More...
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Calsphere American military target satellite. 11 launches, 1964.10.06 (Calsphere 1) to 1971.02.17 (Calsphere 5). Radar calibration objects (but also cover for other classified subsatellites). More...
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Mariner 3-4 American Mars flyby probe. 2 launches, 1964.11.05 (Mariner 3) to 1964.11.28 (Mariner 4). This spacecraft completed the first successful flyby of the planet Mars, returning the first pictures of the Martian surface. More...
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OV1 American earth magnetosphere satellite. 27 launches, 1965.01.21 (OV1-1) to 1971.08.07 (OV1-21P). More...
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Snapshot American ion engine technology satellite. One launch, 1965.04.03. Carried SNAP-9A nuclear power source. The on-board reactor provided electrical power for a 2.2-lb ion engine. More...
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LCS American military target satellite. 3 launches, 1965.05.06 (LCS 1) to 1971.08.07 (LCS 4). Aluminum sphere used for radar calibration. More...
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Bluebell American military target satellite. 2 launches, 1966.02.15 (Bluebell 2C (Cylinder)) and (Bluebell 2S (Sphere)). Space craft engaged in investigation of spaceflight techniques and technology. More...
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OAO American visible astronomy satellite. 4 launches, 1966.04.08 (OAO 1) to 1972.08.21 (OAO 3). More...
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Atlas Target Docking Adapter American logistics spacecraft. One launch, 1966.06.01, Gemini 9 ATDA. An unpowered Gemini docking collar less the Agena rocket stage, launched one time by an Atlas when the Agena stage was not available. Fairing separation failed. More...
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Lunar Orbiter American lunar orbiter. 5 launches, 1966.08.10 (Lunar Orbiter 1) to 1967.08.01 (Lunar Orbiter 5). Photography of the moon's surface from selenocentric orbit. The Lunar Orbiter series took photos of lunar surface from selenocentric orbit. More...
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ATS-1 American communications technology satellite. One launch, 1966.12.07, ATS 1. During its 18 year lifetime, ATS-1 examined spin stabilization techniques, investigated the geostationary environment, and performed several communications experiments. More...
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ATS-2 American communications technology satellite. One launch, 1967.04.06, ATS 2. ATS-2 was placed into an undesirable orbit due to a launch vehicle failure. More...
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OV5 American earth magnetosphere satellite. 8 launches, 1967.04.28 (OV5-03) to 1969.05.23 (OV5-09). OV5 was a version of the USAF Environmental Research Satellites dedicated to radiation research and VLF plasma wave detection. More...
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Mariner 5 American Venus probe. One launch, 1967.06.14. Mariner 5 was a refurbished backup spacecraft for the Mariner 4 Mars mission converted to fly a Venus mission. More...
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ATS-3 American communications technology satellite. One launch, 1967.11.05, ATS 3. The goals for ATS-3 included investigations of spin stabilization techniques and VHF and C-band communications experiments. More...
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Canyon American military naval signals reconnaisance satellite. 7 launches, 1968.08.06 (Canyon 1) to 1977.05.23 (Canyon 7). The first large US signals intelligence satellite. More...
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ATS-4 American communications technology satellite. One launch, 1968.08.10, ATS 4. A launch vehicle failure stranded ATS-4 in a much lower than planned orbit, making the satellite nearly useless. More...
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RADCAT American military technology satellite. 2 launches, 1968.08.16 (Radcat) and 1972.10.02 (RADCAT). Space craft engaged in investigation of spaceflight techniques and technology. More...
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Orbiscal American earth ionosphere satellite. 7 launches, 1968.08.16 (AVL-802 Grid Sphere 7-1) to (AVL-802 Grid Sphere 7-1). Investigate effects of ionosphere on radio signals. More...
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RM American earth micrometeoroid satellite. 2 launches, 1968.08.16 (RM-18) and 1970.11.09 (RM-1; RMS). Spacecraft engaged in research and exploration of the upper atmosphere or outer space. More...
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Mariner 6-7 American Mars flyby probe. 2 launches, 1969.02.25 (Mariner 6) to 1969.03.27 (Mariner 7). Mariner 6 and 7 comprised a dual-spacecraft mission to Mars. More...
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ATS-5 American communications technology satellite. One launch, 1969.08.12, ATS 5. More...
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Rhyolite American military naval signals reconnaisance satellite. 4 launches, 1970.06.19 (Rhyolite 1) to 1978.04.07 (Rhyolite 4). More...
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Intelsat 4 American communications satellite. 8 launches, 1971.01.26 (Intelsat 4 F-2) to 1975.05.22 (Intelsat 4 F-1). The Intelsat 4 series continued the growth of the Intelsat communications network. More...
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Mariner 8-9 American Mars orbiter. 2 launches, 1971.05.09 (Mariner H) to 1971.05.30 (Mariner 9). The Mariner Mars 71 mission was planned to consist of two spacecraft on complementary missions. More...
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Cannonball American military target satellite. One launch, 1971.08.07. Space craft engaged in investigation of spaceflight techniques and technology. More...
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Musketball American technology satellite. One launch, 1971.08.07. Space craft engaged in investigation of spaceflight techniques and technology. More...
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Gridsphere American technology satellite. 2 launches, 1971.08.07 (Gridsphere 1) and (Gridsphere 2). Space craft engaged in investigation of spaceflight techniques and technology. More...
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Mylar American technology satellite. One launch, 1971.08.07. Space craft engaged in investigation of spaceflight techniques and technology. More...
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Rigidsphere American military target satellite. One launch, 1971.08.07. Space craft engaged in investigation of spaceflight techniques and technology. More...
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NOSS American military naval signals reconnaisance satellite. 22 launches, 1971.12.14 (OPS 7898 P/L 1) to 1993.08.02 (TLD). Ocean surveillance; aka White Cloud type spacecraft; Navy Ocean Surveillance Satellite; PARCAE. More...
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Pioneer 10-11 American outer planets probe. 2 launches, 1972.03.03 (Pioneer 10) to 1973.04.06 (Pioneer 11). Pioneers 10 and 11 were the first spacecraft to fly by Jupiter (Pioneer 10 and 11) and Saturn (Pioneer 11 only). More...
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Radsat American military technology satellite. One launch, 1972.10.02. Space craft engaged in investigation of spaceflight techniques and technology. More...
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NTS American navigation technology satellite. 2 launches, 1974.07.14 (NTS 1) and 1977.06.23 (NTS 2). Demonstrated navigation technologies. More...
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P 72 American military technology satellite. One launch, 1975.04.13. Unknown satellite lost on a single Atlas launch failure. Evidently not repeated. More...
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Spacebus 100 French communications satellite. 12 launches, 1975.08.26 (Symphonie 2) to 1994.01.24 (Eutelsat II F5). 3-axis stabilized using bipropellant thrusters (750 kg propellant - unified with apogee insertion and maneuvering propulsion) and momentum wheels. More...
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Intelsat 4A American communications satellite. 10 launches, 1975.09.26 (Intelsat 4A F-1) to 1981.02.21 (Comstar 4). Intelsat 4A satellites increased satellite capacity to 7250 voice circuits or 2 TV channels. More...
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NOSS-Subsat American military naval signals reconnaisance satellite. 27 launches, 1976.04.30 (SSU 1 (NOSS 1)) to 1996.05.12 (USA 121). Detected the location of naval vessels using radio interferometry. More...
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HEAO American x-ray astronomy satellite. 3 launches, 1977.08.12 (HEAO 1) to 1979.09.20 (HEAO 3). The 3 satellites of the High Energy Astronomical Observatory program surveyed the celestial sphere for X-ray sources and gamma and cosmic ray phenomena. More...
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FLTSATCOM American military communications satellite. 8 launches, 1978.02.09 (Fltsatcom 1) to 1989.09.25 (USA 46). More...
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GPS Block 1 American navigation satellite. 11 launches, 1978.02.22 (Navstar 1) to 1985.10.09 (USA 10). GPS Block 1 prototype satellites formed the GPS Demonstration system and were followed by the Block 2 operational system. More...
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Pioneer 12 American Venus probe. One launch, 1978.05.20, Pioneer Venus Orbiter. Pioneer Venus Orbiter. Part of the Pioneer program Pioneer Venus Orbiter was designed to perform long-term observations of the Venusian atmosphere and surface features. More...
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Seasat American earth resources radar satellite. One launch, 1978.06.27. Seasat was the first satellite designed for remote sensing of the Earth's oceans with synthetic aperture radar (SAR). More...
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Pioneer 13 American Venus probe. 5 launches, 1978.08.08 (Pioneer Venus 2) to (Pioneer Venus Probe 4). The Pioneer Venus Multiprobe consisted of a bus which carried one large and three small atmospheric probes. More...
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Tiros N American earth weather satellite. 6 launches, 1978.10.13 (Tiros N) to 2002.06.24 (NOAA 17). Tiros N was part of the ongoing US series of polar-orbiting weather satellites. These were preceded by the TIROS series and the ITOS (Improved TIROS) series. More...
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Solwind American earth magnetosphere satellite. One launch, 1979.02.24. Ionosphere and magnetosphere studies; destroyed 9/13/85 (while still functioning) as part of ASAT test. More...
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HS 376 American communications satellite. 56 launches, 1980.11.15 (SBS 1) to 2003.09.27 (E-Bird). Mass 654 kg at beginning-of-life in geosynchronous orbit. Spin stabilized at 50 rpm by 4 hydrazine thrusters with 136 kg propellant. More...
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Intelsat 5 American communications satellite. 9 launches, 1980.12.06 (Intelsat 5 F-2) to 1984.06.09 (Intelsat 5 F-9). The last five of the nine spacecraft in this block carry a maritime mobile payload (seven additional transponders) for lease by Inmarsat. More...
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LIPS American tether technology satellite. 3 launches, 1980.12.09 (LIPS 1) to 1987.05.15 (LIPS 3). More...
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AS 3000 American communications satellite. 25 launches, 1981.11.20 (RCA Satcom 4; RCA Satcom 3R) to 1996.01.14 (Koreasat 2). More...
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DSCS III American military communications satellite. 15 launches, 1982.10.30 (DSCS III-01) to 2003.08.29 (USA 170). DSCS satellites provided secure voice and data communications for the US military. More...
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DMSP Block 5D-2 American earth weather satellite. 9 launches, 1982.12.21 (AMS 5) to 1997.04.04 (USA 131). DMSP 5D-2 was the military's sixth generation of weather satellites. More...
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Geosat American earth resources radar satellite. One launch, 1985.03.13. Geosat was a US Navy satellite designed to measure sea surface heights to within 5 cm. More...
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Intelsat 5A American communications satellite. 6 launches, 1985.03.22 (Intelsat 5A F-10) to 1989.01.27 (Intelsat 5A F-15). The Intelsat 5A series was derived from the Intelsat 5. More...
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AS 4000 American communications satellite. 8 launches, 1985.11.27 (Satcom K2) to 1998.02.04 (Inmarsat 3 F5). 3-axis stabilization with momentum wheels, magnetic torquers, Earth sensors and 16 blowdown monopropellant hydrazine thrusters. More...
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Eurostar 2000 French communications satellite. 24 launches, 1988.03.11 (Telecom 1C) to 2006.11.08 (Badr 4 ARABSAT 4B). More...
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FS-1300 American communications satellite bus. Operational, first launch 1989.06.05. More...
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HS 601 American communications satellite bus. First launch 1990.01.09. 3-axis unified ARC 22 N and one Marquardt 490 N bipropellant thrusters, Sun and Barnes Earth sensors and two 61 Nms 2-axis gimbaled momentum bias wheels. More...
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Stacksat P87-2 American technology satellite. 3 launched, 1990.04.11 (USA 56) to (USA 58). The U. S. military's STACKSAT mission involved the launch of three similar spacecraft, POGS, TEX and SCE. More...
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CRRES American earth magnetosphere satellite. One launch, 1990.07.25. Combined Release and Radiation Effects Satellite. Chemical release experiment. More...
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AS 5000 American communications satellite. 4 launches, 1991.03.02 (Astra 1B) to 1992.06.10 (Intelsat K). 3-axis stabilization with momentum wheels, magnetic torquers, Earth sensors and 20 blowdown monopropellant hydrazine thrusters. More...
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AS 7000 American communications satellite. 13 launches, 1993.12.16 (Telstar 401) to 1998.06.18 (Intelsat 805). 3-axis stabilized. Two large solar panels with 1-axis articulation. More...
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GOES-Next American earth weather satellite. 3 launches, 1994.04.13 (GOES 8) to 1997.04.25 (GOES 10). Geostationary Environmental Satellite. More...
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SOHO European solar satellite. One launch, 1995.12.02. SOHO was a component of the Collaborative Solar-Terrestrial Research (COSTR) Program of the International Solar Terrestrial Physics (ISTP) Program. More...
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SAX Italian x-ray astronomy satellite. One launch, 1996.04.30, Beppo SAX. Satellite per Astronomia a raggi X; X-ray celestial observatory More...
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AS 2100 American communications satellite. Operational, first launch 1996.09.08 (GE 1). Cost per satellite $100 million for the spacecraft including ground support equipment, but not including launch costs. 3-axis stabilized. More...
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Falcon Gold American navigation technology satellite. One launch, 1997.10.25. US Air Force Academy experiment to demonstrate use of GPS navigation in geosynchronous orbit. More...
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CAPRICORN American military communications satellite. One launch, 1998.01.29, USA 137. There was no firm information on this classified satellite for the National Reconnaissance Office. More...
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Terra American earth land resources satellite. One launch, 1999.12.18. NASA's Terra satellite (originally known as Earth Observing System EOS AM-1) was the first spacecraft in the EOS program. More...
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SDS-3 American military communications satellite, provided data relay services for optical reconnaissance and other military spacecraft. Operational, first launch 2000.12.06. More...
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NOSS-3 American military naval signals reconnaisance satellite. Operational, first launch 2001.09.08. More...
Associated Launch Vehicles
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Atlas The Atlas rocket, originally developed as America's first ICBM, was the basis for most early American space exploration and was that country's most successful medium-lift commercial launch vehicle. It launched America's first astronaut into orbit; the first generations of spy satellites; the first lunar orbiters and landers; the first probes to Venus, Mars, Mercury, Jupiter, and Saturn; and was America's most successful commercial launcher of communications satellites. Its innovative stage-and-a-half and 'balloon tank' design provided the best dry-mass fraction of any launch vehicle ever built. It was retired in 2004 after 576 launches in a 47-year career. More...
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MX-774 American test vehicle. Project MX-774 inaugurated by AAF with Consolidated-Vultee to study rocket capabilities with an ICBM as a final objective. Limited funds permitted a few test launches. These rockets demonstrated technologies that woud later be applied to the Atlas. More...
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Concept ICBM American orbital launch vehicle. The January 1951 design for the Atlas used seven main engines plus two vernier engines to hurl the 3600 kg nuclear warhead over a 9300 km range. CEP was optimistically estimated as 460 m. More...
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MX-1593 American orbital launch vehicle. The September 1951 design for the Atlas used seven main engines to hurl the 3600 kg nuclear warhead over a 9300 km range. CEP was 1850 m. More...
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Proposed Atlas American orbital launch vehicle. The April 1953 design for the Atlas at the time of Convair's proposal used five main engines to power a 200 metric tone rocket able to send a 1400 kg nuclear warhead over a 10,200 km range. CEP was 1850 m. More...
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Contracted Atlas American orbital launch vehicle. The 1954 design for the Atlas as contracted for by the Air Force used three main engines to power a 110 metric ton rocket able to send a 1400 kg nuclear warhead over a 10,200 km range. CEP was 3700 m. The missile actually delivered six years later would have the same dimensions and launch mass, but 63% more range and four times better accuracy. More...
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World Series American orbital launch vehicle. In May 1956 the Air Force proposed mating an Atlas A with an Aerobee-Hi upper stage in order to launch a satellite during the International Geophysical Year (1957-1958). The Eisenhower administration selected the Vanguard instead. After Sputnik, an Atlas B with no upper stage orbited the Score satellite as a reply to the Soviet's Sputnik 3. More...
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Atlas A American test vehicle. First test model of Atlas ICBM. Two booster engines, no sustainer, dummy warhead. 50% reliability in 8 flight tests. More...
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Atlas B American test vehicle. First all-up test version of the Atlas ICBM, with jettisonable booster engines and a single engine sustainer on core - a '1 1/2' stage launch vehicle. More...
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Atlas C American test vehicle. Last development version of Atlas. Never deployed operationally or used for space launches. More...
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Atlas Vega American orbital launch vehicle. Atlas-Vega consisted of an Atlas booster with a storable propellant upper stage. It was planned by NASA at its inception for deep space and planetary missions before the Atlas Centaur was available. Work had already begun when NASA discovered that the CIA and the US Air Force had an essentially identical launch vehicle (Atlas-Hustler, later called Atlas-Agena) in development for the highly classified Corona reconnaisance satellite program. Atlas-Vega was accordingly cancelled. More...
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Atlas D American intercontinental ballistic missile. Rocket used both as a space launcher and ICBM. More...
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Atlas C Able American orbital launch vehicle. Version with Atlas C first stage, Able AJ10-101A second stage, Altair solid third stage. More...
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Atlas Able American orbital launch vehicle. Atlas with upper stage based on Vanguard second stage. More...
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Atlas D Able American orbital launch vehicle. Version with Atlas D first stage, Able AJ10-101A second stage, Altair solid third stage. More...
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Atlas Agena A American orbital launch vehicle. Atlas D + 1 x Agena A upper stage. Agena originally called 'Hustler', based on engine for cancelled rocket-propelled nuclear warhead pod for B-58 Hustler bomber. More...
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Atlas E American intercontinental ballistic missile. Initial fully operational version of Atlas ICBM. Differed in guidance system from Atlas F. Deployed as missiles from 1960 to 1966. After retirement, the ICBM's were refurbished and used over twenty years as space launch vehicles. More...
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CGM-16E American intercontinental ballistic missile. ICBM version More...
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HGM-16F American intercontinental ballistic missile. ICBM version. Also CGM-16F More...
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Atlas Agena B American orbital launch vehicle. Atlas D with improved, enlarged Agena upper stage. More...
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Atlas F American intercontinental ballistic missile. Final operational version of Atlas ICBM. Differed in guidance systems. Deployed as missiles from 1961 to 1966. After retirement, the ICBM's were refurbished and used for over thirty years as space launch vehicles. More...
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Atlas Centaur American orbital launch vehicle. First test version of Atlas with Centaur upper stage. More...
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Atlas Agena D American orbital launch vehicle. Atlas D with further improved and lightened Agena upper stage. More...
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Atlas SLV-3 American orbital launch vehicle. Standardized Atlas booster with no or small solid upper stage. More...
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SLV-3 Agena B American orbital launch vehicle. Standardized Atlas booster with Agena B upper stage. More...
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Atlas F/SVS American orbital launch vehicle. Atlas F + 1 x Star 37E + 1 x Star 37E upper stages. More...
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Atlas E/SVS American orbital launch vehicle. Atlas E + 1 x Star 37E + 1 x Star 37E upper stages. More...
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Atlas H American orbital launch vehicle. Atlas H used the Atlas first stage developed for the Atlas G vehicle. It was flown without the Centaur upper stage. More...
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Atlas E/SGS-2 American orbital launch vehicle. Atlas E + 1 x Star 48 + 1 x Star 48 upper stages. More...
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LV-3B American orbital launch vehicle. First operational version of Atlas ICBM and used as launch vehicle for Project Mercury. More...
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Atlas I American orbital launch vehicle. The Atlas I launch vehicle was derived from the Atlas G, and included the same basic vehicle components (Atlas booster and Centaur upper stage). Significant improvements in the guidance and control system were made with an emphasis on replacing analog flight control components with digital units interconnected with a digital data bus. More...
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Atlas II American orbital launch vehicle. The Atlas II booster was 2.7-meters longer than an Atlas I and included uprated Rocketdyne MA-5A engines. The Atlas I vernier engines were replaced with a hydrazine roll control system. The Centaur stage was stretched 0.9-meters compared to the Centaur I stage. Fixed foam insulation replaced Atlas I's jettisonable insulation panels. The original Atlas II model was developed to support the United States Air Force Medium Launch Vehicle II program. Its Centaur used RL10A-3-3A engines operating at an increased mixture ratio. The first Atlas II flew on 7 December 1991, successfully delivering AC-102/Eutelsat II F3 to orbit. More...
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Atlas IIA American orbital launch vehicle. Atlas IIA was a commercial derivative of the Atlas II developed for the US Air Force. Higher performance RL10A-4 (or RL10A-4-1) engines replaced Atlas II's RL10A-3-3A engines. More...
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Atlas IIAS American orbital launch vehicle. The Atlas II booster was 2.7-meters longer than the Atlas I and included uprated Rocketdyne MA-5A engines. The Atlas I vernier engines were replaced with a hydrazine roll control system. The Centaur stage was stretched 0.9-meters compared to the Centaur I stage. Fixed foam insulation replaced Atlas I's jettisonable insulation panels. Higher performance RL10A-4 or RL10A-4-1 engines replaced Atlas II's RL10A-3-3A. The Atlas IIAS model added four Thiokol Castor IVA solid rocket boosters (SRBs) to the core Atlas stage to augment thrust for the first two minutes of flight. More...
Associated Launch Sites
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White Sands White Sands Missile Range occupies an area 160 x 65 km in the Tularosa Basin of southern New Mexico, across the Sacramento Mountain range from Roswell. In the 1930's, Robert Goddard, after surveying weather conditions and population densities, had selected Roswell for his pioneering rocket tests. White Sands, a true desert area, was even more unpopulated than Roswell. German advances in rocketry during World War II impelled the US Army to begin programs to exploit this technology. The White Sands Proving Ground was established for testing German and American long-range rockets on 9 July 1945. Seven days later the first atomic bomb was exploded at Trinity Site, near the north boundary of the range. The first launch of a Tiny Tim rocket was on 26 September 1945. On 11 October a Tiny Tim boosted a WAC Corporal rocket from the tower. This was the first use of Launch Complex 33, later to be used for V-2, Nike, Viking, Corporal, Lance and Multiple Launch Rocket System testing. More...
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Cape Canaveral America's largest launch center, used for all manned launches. Today only six of the 40 launch complexes built here remain in use. Located at or near Cape Canaveral are the Kennedy Space Center on Merritt Island, used by NASA for Saturn V and Space Shuttle launches; Patrick AFB on Cape Canaveral itself, operated the US Department of Defense and handling most other launches; the commercial Spaceport Florida; the air-launched launch vehicle and missile Drop Zone off Mayport, Florida, located at 29.00 N 79.00 W, and an offshore submarine-launched ballistic missile launch area. All of these take advantage of the extensive down-range tracking facilities that once extended from the Cape, through the Caribbean, South Atlantic, and to South Africa and the Indian Ocean. More...
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Vandenberg Vandenberg Air Force Base is located on the Central Coast of California about 240 km northwest of Los Angeles. It is used for launches of unmanned government and commercial satellites into polar orbit and intercontinental ballistic missile test launches toward the Kwajalein Atoll. More...
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Altus AFB Atlas F ICBM (SMS 577) base, 1962-1965. The 12 missiles here constituted America's ICBM deterrent force during the Cuban Missile Crisis. More...
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Walker AFB Operational US Atlas F (SMS 579) ICBM base, location of several fuelling accidents in 1963-1964. More...
Atlas Chronology
1945 October 31 - .
LV Family:
Atlas;
Mace;
Matador;
Navaho;
Snark.
Launch Vehicle:
Rascal.
- US Strategic Missile Programs Begin - .
Nation: USA. Program: Navaho. Request For Proposals were issued to 17 contractors by the US Army Air Force for studies of a 10-year R&D program of four missile types. The missiles were to be air-, rail-, road-, or ship- transportable, and fit in three range categories: 280 to 800 km; 800 to 2400 km; and 2400 to 8000 km. Minimum speed was 970 kph, requiring turbojet, ramjet, or rocket propulsion.
1946 January 11 - .
LV Family:
Atlas.
Launch Vehicle:
Atlas.
- Strategic Missile Proposals - .
Nation: USA. Bids were received in response to the USAAF request for proposal of the previous October. Vultee submitted proposals for two types (glide and ballistic) of 8000-km range missiles. North American proposed a three-year development program for a supersonic 800-km range missile, culminating in a production run of 50 missiles.
March to April 1946 - .
LV Family:
Atlas;
Mace;
Matador;
Navaho;
Snark.
Launch Vehicle:
Rascal.
- Army Air Force awards nine one-year missile study contracts. - .
Nation: USA. Program: Navaho. The MX-770 contract for an 800-km range boost-glide missile derived from the German A9 concept went to North American; this would evolve into the Navaho triple-sonic intercontinental cruise missile. Martin received a contract for development of the MX-771, a subsonic ground-launched cruise missile with an 800-km range; it would evolve into the Matador and Mace missiles. Curtiss-Wright and Republic received contracts for the MX-772 and MX-773 surface-to-surface missiles; they never advanced beyond the initial study stage. Convair received the contract for long-range rocket-powered missiles; this evolved into the Atlas ICBM. Northrtop received the MX-775 contract for a 5000-km range cruise missile; this eventually flew as the Snark. Bell receives a contract to develop the MX-776, a 160-km range rocket-powered supersonic missile to be launched from B-29 bombers. This would evolve into the Rascal. McDonnell received a study contract for the MX-777 air-to-surface missile; this evolved into the anti-submarine 'hydrobomb' concept and was eventually transferred to the Navy. Goodyear received contracts for the MX-778 and MX-779 air-to-surface missiles; these never advanced beyond the preliminary study stage. Concurrently, the USAAF had the GARPA surface-to-air missile project underway, which would evolve into Bomarc; the USA Army the Corporal and Hermes (later Redstone) surface-to-surface missiles and the Nike and Hermes A1 surface-to-air missiles; and the Navy a range of missile technology development projects (Regulus, Bat, Kingfisher, Little Joe, Lark, Bumblebee, Gorgon, Dove).
1946 April 2 - .
LV Family:
Atlas.
Launch Vehicle:
Atlas.
- MX-774 strategic missile study contract awarded - .
Nation: USA. Summary: Convair received contract W33-038-AC-14168 for a $1.4 million, one-year study of two missile designs..
1946 December - .
LV Family:
Atlas.
Launch Vehicle:
Atlas.
- MX-774 Azusa tracking - .
Nation: USA. Summary: Study report submitted to Air Force on proposed Azusa tracking/guidance system. MX-774 funding cut back..
Early 1947 - .
LV Family:
Atlas.
Launch Vehicle:
Atlas.
- MX-774 Azusa tracking tests - .
Nation: USA. Summary: Tracking tests started with experimental Azusa equipment.
1947 July 1 - .
LV Family:
Atlas.
Launch Vehicle:
Atlas.
- MX-774 cancelled. - .
Nation: USA. Contract with Convair for the MX-774 "Upper Air Test Vehicle," predecessor of the Atlas ICBM, was cancelled by the AAF. However the service approves Convair use of unexpended MX-774 funds to launch the MX-774 test vehicles already built. The decision made to move Vultee operations to San Diego.
1947 September 15 - .
LV Family:
Atlas;
Navaho;
Snark.
- US Army Air Corps assigned control of surface-to-surface strategic missiles - .
Nation: USA. Program: Navaho.
1947 September 18 - .
LV Family:
Atlas;
Matador;
Navaho;
Snark.
- U.S. Army Air Corps becomes U.S. Air Force - .
Nation: USA. Program: Navaho. The Air Force was now a separate service from the US Army. The agreement was made that the Air Force would only handle missiles with ranges over 1600 km. So the range requirement for the MX-770 (later the Navaho) was increased to 1600 km, while carrying a 1350-kg payload with an 800 m CEP, and it became an Air Force missile. The 800-km MX-771 (later Matador) became an Army missile. The MX-775 Snark already had an intercontinental range requirement, and became an Air Force missile.
1947 October - .
LV Family:
Atlas.
Launch Vehicle:
Atlas.
- First complete MX-774 moved to Pt. Loma for test - .
Nation: USA.
1947 November 20 - .
LV Family:
Atlas.
Launch Vehicle:
Atlas.
- First static firing of MX-774 - .
Nation: USA. Summary: Unsuccessful, small fire..
1948 January - .
LV Family:
Atlas.
Launch Vehicle:
Atlas.
- Second MX-774 static firing - .
Nation: USA. Summary: Successful, at Point Loma..
1948 May 6 - .
LV Family:
Atlas.
Launch Vehicle:
Atlas.
- MX-774 static firing tests at Pt Loma completed. - .
Nation: USA.
1948 June - .
LV Family:
Atlas.
Launch Vehicle:
Atlas.
- First MX-774 arrives at White Sands Proving Ground - .
Nation: USA.
1948 July 14 - .
01:05 GMT - .
Launch Site:
White Sands.
Launch Complex:
White Sands LC33.
LV Family:
Atlas.
Launch Vehicle:
MX-774.
FAILURE: Cutoff after half of the propellants were used..
Failed Stage: 1.
- MX-774 Flight 1 - .
Nation: USA. Agency: USAF. Apogee: 1.00 km (0.60 mi). Summary: First Convair MX-774 (RTV-A-2) test rocket was successfully launched, first demonstrating use of gimballed engines and design features later incorporated in the Atlas ICBM. This was the first of three Convair-sponsored test flights..
1948 August - .
LV Family:
Atlas;
Navaho;
Snark.
- Spaatz calls for American ICBM. - .
Nation: USA. Program: Navaho. Summary: General Spaatz (Tooey Spaatz) calls for US development of missile with 10,200 km range.
1948 September 27 - .
Launch Site:
White Sands.
Launch Complex:
White Sands LC33.
LV Family:
Atlas.
Launch Vehicle:
MX-774.
FAILURE: Cutoff at 16 km altitude..
Failed Stage: 1.
- MX-774 Flight 2 - .
Nation: USA. Agency: USAF. Apogee: 47 km (29 mi). Summary: Second Corvair MX-774 test rocket fired. Shut down at 15 km; reached 65 km before malfunction of unknown origin caused self-destruction..
1948 December 2 - .
22:01 GMT - .
Launch Site:
White Sands.
Launch Complex:
White Sands LC33.
LV Family:
Atlas.
Launch Vehicle:
MX-774.
FAILURE: Vibration closed valve early..
- MX-774 Flight 3 - .
Nation: USA. Agency: USAF. Apogee: 50 km (31 mi). Summary: Third (last) MX-774 launched, WSPG; shut down at 51 seconds attaining an altitude of 48 km. Self-destructed at high altitude..
1949 February - .
LV Family:
Atlas.
Launch Vehicle:
Atlas.
- All MX-774 work shut off by Air Force - .
Nation: USA.
During 1949 - .
LV Family:
Atlas.
Launch Vehicle:
Atlas.
- MX-774 unexpended funds run out in 1950. - .
Nation: USA. Summary: Convair allocated R&D funds to ICBM studies and marketing, running into 1950.
1950 October 1 - .
LV Family:
Atlas.
Launch Vehicle:
Atlas A.
- RAND studies ICBM's. - .
Nation: USA. Summary: Rand Corp. completed missile feasibility studies begun in 1949, which confirmed the military practicability of long-range rocket weapons..
1951 - .
LV Family:
Atlas.
Launch Vehicle:
Atlas A.
- Atlas tracking system. - .
Nation: USA. Summary: Azusa tracking system reaching advanced stage of development.
1951 January 16 - .
LV Family:
Atlas.
Launch Vehicle:
Atlas A.
- Project MX-1593 (Project Atlas) begins. - .
Nation: USA. Air Force established Project MX-1593 (Project Atlas), study phase for an intercontinental missile. Requirements included 8000-pound warhead, 5000 nautical mile range, to hit within 1500 ft. CEP. $1.5 million study contract was awarded to Consolidated-Vultee Aircraft on January 23. This was the follow-on to Project MX-774 terminated in 1947. Several test vehicles had been fired using residual funds in 1948 and 1949, after which the Convair MX-774 (Atlas) missile project had been shelved. The company, however, had continued to fund a research program.
1951 August - .
LV Family:
Atlas.
Launch Vehicle:
Atlas A.
- Atlas XB-65 configuration. - .
Nation: USA. Summary: MX-1593 named "Project Atlas" as XB-65; 120 feet long, 12-foot diameter, 7 engines, 8000-pound warhead, CEP 1 nautical mile.
1951 August - .
LV Family:
Atlas.
Launch Vehicle:
Atlas A.
- Atlas to be accelerated. - .
Nation: USA. Summary: AF Gen. John Sessums proposes Atlas acceleration.
1951 September 1 - .
LV Family:
Atlas.
Launch Vehicle:
Atlas A.
- Atlas project to concentrate on ballistic missile. - .
Nation: USA. Summary: MX-1593 glide missile cancelled. USAF directed all work in Project MX-1593 (Atlas) be for development of a rocket-powered ballistic missile..
Late 1951/early 1952 - .
LV Family:
Atlas.
Launch Vehicle:
Atlas A.
- Reports of large Russian rocket engines - .
Nation: USA.
During 1952 - .
LV Family:
Atlas.
Launch Vehicle:
Atlas A.
- Reduced thermonuclear warhead size will allow American ICBM's to be smaller. - .
Nation: USA. Summary: Atlas 3000-pound warhead anticipated, 1500-foot CEP.
1952 March - .
LV Family:
Atlas.
Launch Vehicle:
Atlas A.
- Gen. Joseph McNarney joins Convair - .
Nation: USA.
1953 January - .
LV Family:
Atlas.
Launch Vehicle:
Atlas A.
- Millikan Committee Report - .
Nation: USA. Summary: Millikan Committee report issued, saying Atlas could be operational by 1963.
Spring 1953 - .
LV Family:
Atlas.
Launch Vehicle:
Atlas A.
- Atlas size reduced. - .
Nation: USA. Summary: Atlas 12-foot diameter, 110 feet long, 440,000 pounds, 3000-pound warhead, 5500 nautical mile range, 1500-foot CEP.
1953 June - .
LV Family:
Atlas.
Launch Vehicle:
Atlas A.
- Defense Secretary Wilson institutes reviews of guided missiles' status - .
Nation: USA.
1953 July - .
LV Family:
Atlas.
Launch Vehicle:
Atlas A.
- J.R. Dempsey joins Convair - .
Nation: USA.
1953 September - .
LV Family:
Atlas.
Launch Vehicle:
Atlas A.
- Von Neumann's "Teapot Committee" established - .
Nation: USA.
1953 October - .
LV Family:
Atlas.
Launch Vehicle:
Atlas A.
- Teapot Committee's first output - .
Nation: USA. Summary: ICBM could use smaller warhead.
1953 December 3 - .
LV Family:
Atlas.
Launch Vehicle:
Atlas A.
- Convair leases test facility. - .
Nation: USA. Summary: A five-year Pt. Loma lease was approved..
1954 February 10 - .
LV Family:
Atlas.
Launch Vehicle:
Atlas A.
- Teapot Report - .
Nation: USA. Summary: The ICBM design feasible, as was acceleration of the program; Rand Corporation Report: Atlas ICBM could be operational by 1960-62 and should have crash project status.
1954 March - .
LV Family:
Atlas.
Launch Vehicle:
Atlas A.
- First Atlas hardware. - .
Nation: USA. Summary: 12-foot diameter Atlas tank completed by Solar.
1954 March - .
LV Family:
Atlas.
Launch Vehicle:
Atlas A.
- Operation Castle thermonuclear tests confirm feasibility of small warheads - .
Nation: USA.
1954 March 1 - .
LV Family:
Atlas.
Launch Vehicle:
Atlas A.
- Atlas propulsion system work begins. - .
Nation: USA. Summary: Work on MA-2 propulsion system for Atlas by Rocketdyne was begun, drawing upon the experience in developing the regeneratively cooled chamber developed for the Navaho..
1954 March 8 - .
LV Family:
Atlas.
Launch Vehicle:
Atlas A.
- First public indication that Project Atlas exists - .
Nation: USA.
May 1954 - .
LV Family:
Atlas.
Launch Vehicle:
Atlas A.
- Atlas receives high priority. - .
Nation: USA. Summary: Highest AF development priority (and accelerated schedule) assigned Atlas.
1954 May 17 - .
LV Family:
Atlas.
Launch Vehicle:
Atlas A.
- Ramo-Woolridge to manage Atlas. - .
Nation: USA. Summary: Ramo-Wooldridge given letter contract as Technical Director and Systems Integrator for Atlas program.
1954 June 21 - .
LV Family:
Atlas.
Launch Vehicle:
Atlas A.
- Schriever named head of Atlas program. - .
Nation: USA. Summary: Brigadier-General Bernard A. Schriever, ARDC, assigned to head Atlas program.
1954 July - .
LV Family:
Atlas.
Launch Vehicle:
Atlas A.
- Scientific Advisory Board recommendations rejected. - .
Nation: USA. Summary: Scientific Advisory Board recommendations differing from Teapot Committee rejected.
1954 July 1 - .
LV Family:
Atlas.
Launch Vehicle:
Atlas A.
- Rocketdyne put on contract for Atlas engines. - .
Nation: USA. Summary: Western Development Division (WDD) established by AF under ARDC to manage Atlas development; .
1954 July 1 - .
LV Family:
Atlas.
Launch Vehicle:
Atlas A.
- Western Development Division (WDD) established by USAF - .
Nation: USA. Summary: Western Development Division (WDD) established by AF under ARDC to manage Atlas development; Rocketdyne put on contract for propulsion system.
1954 August - .
LV Family:
Atlas.
Launch Vehicle:
Atlas A.
- First USAF WDD Facility - .
Nation: USA. Summary: Inglewood "Schoolhouse" WDD facility established.
Late 1954 - .
LV Family:
Atlas.
Launch Vehicle:
Atlas A.
- Atlas further reduced in size - .
Nation: USA. Summary: Atlas size reduced from 12-foot to 10-foot diameter, with 3 large engines.
1954 December - .
LV Family:
Atlas.
Launch Vehicle:
Atlas A.
- Atlas full-scale development - .
Nation: USA. Summary: First major Atlas WS107A1 development and construction contract awarded Convair; CEP 2-3 NM, IOC by 1960-62.
1954 December 16 - .
LV Family:
Atlas.
Launch Vehicle:
Atlas A.
- Atlas publicly announced. - .
Nation: USA. Summary: USAF announced Atlas ICBM under construction by Convair..
Early 1955 - .
LV Family:
Atlas.
Launch Vehicle:
Atlas A.
- Atlas fabrication begins - .
Nation: USA.
1955 March 6 - .
LV Family:
Atlas.
Launch Vehicle:
Atlas A.
- Atlas given top development priority. - .
Nation: USA. Summary: USAF Chief of Staff, Nathan F. Twining, reported that ICBM's were receiving priority in the AF program because of known Soviet progress. Navaho, Snark, and Atlas programs accelerated..
1955 April - .
LV Family:
Atlas.
Launch Vehicle:
Atlas A.
- New WDD complex - .
Nation: USA. Summary: New WDD complex activated on Arbor Vitae Blvd. in Los Angeles.
Late 1955 - .
LV Family:
Atlas.
Launch Vehicle:
Atlas A.
- Atlas program assigned top priority in the nation - .
Nation: USA. Summary: Atlas program assigned top priority in the nation (was highest priority only for AF).
1956 May - .
LV Family:
Atlas.
Launch Vehicle:
Atlas A.
- Atlas production plant at Kearney Mesa - .
Nation: USA. Summary: New Astronautics plant announced—$20 million funding by General Dynamics, with the Air Force to match, for tooling and special equipment.
1956 May 3 - .
LV Family:
Atlas.
Launch Vehicle:
Atlas A.
- Convair announced as the prime contractorfor the Atlas - .
Nation: USA. Summary: The Air Force disclosed that a $41 million guided missile production facility would be built at Sorrento, California, for the Atlas launch vehicle. Convair was announced as the prime contractor..
1956 May 28 - .
LV Family:
Atlas.
Launch Vehicle:
Atlas Able.
- RAND lunar instrument carrier based on the Atlas booster - .
Nation: USA. The RAND Corporation issued the first of a series of reports on the feasibility of a lunar instrument carrier, based on the use of an Atlas booster. A braking rocket would decelerate the vehicle before lunar landing, and a penetration spike on the forward point of the instrument package would help to absorb the 500 feet per second impact velocity. Instruments would then transmit information on the lunar surface to earth.
1956 June 21 - .
Launch Site:
Edwards.
LV Family:
Atlas.
Launch Vehicle:
Atlas A.
- Atlas ICBM first test firing - .
Nation: USA. First captive Atlas first test firing. The 'battleship' missile was installed at test stand 1-4, Edwards Air Force Base. The test was a failure due to inadvertant closure of the fuel prevalve, leading to duct collapse, and a turbine overspeed cutoff. No damage was sustained and the first successful firing came the next day.
Atlas, First successful captive test firing, June 22, 1956, Edwards
Rocket Base, duration - 4 seconds. Successful.
1956 June 22 - .
Launch Site:
Edwards.
LV Family:
Atlas.
Launch Vehicle:
Atlas A.
- Atlas ICBM first successful test firing - .
Nation: USA. Summary: First successful captive test firing of the Atlas ICBM at Edwards
Air Force Base, duration - 4 seconds..
1956 June 23 - .
LV Family:
Atlas.
Launch Vehicle:
Atlas A.
- First Atlas battleship tests - .
Nation: USA. Summary: First system engine tests on ERB 1-4 battleship setup.
1956 September - .
LV Family:
Atlas.
Launch Vehicle:
Atlas A.
- Atlas 1A - .
Nation: USA. Summary: Missile 1A delivered to Sycamore for captive tests.
1956 November 16 - .
Launch Site:
Vandenberg.
LV Family:
Atlas.
Launch Vehicle:
Atlas D.
- Vandenberg selected as first ICBM base. - .
Nation: USA. Department of Defense transferred northern portion of Camp Cooke, Calif. (now Vandenberg AFB), to the Air Force to be used as first ICBM base. The Secretary of Defense directed the United States Army to transfer 64,000 acres of Camp Cooke's 86,000 acres to the Air Force.
1956 December - .
LV Family:
Atlas.
Launch Vehicle:
Atlas A.
- First Atlas firing, stand S-l, Sycamore - .
Nation: USA.
1956 December - .
LV Family:
Atlas.
Launch Vehicle:
Atlas A.
- Scheduled design complete (95%) for Atlas A-series missiles - .
Nation: USA.
1956 December 21 - .
LV Family:
Atlas.
Launch Vehicle:
Atlas A.
- Atlas 1A destroyed in test. - .
Nation: USA. Summary: Missile 1A burned on second run at S-l with stand damage.
Spring 1957 - .
LV Family:
Atlas.
Launch Vehicle:
Atlas A.
- First flight Atlas missile, 4A, delivered, and shipped to AMR - .
Nation: USA.
1957 March - .
LV Family:
Atlas.
Launch Vehicle:
Atlas A.
- Atlas 4A erected on AMR LC-14 - .
Nation: USA.
1957 June - .
LV Family:
Atlas.
Launch Vehicle:
Atlas A.
- WDD renamed Ballistic Missiles Division (BMD) - .
Nation: USA.
1957 June 11 - .
19:37 GMT - .
Launch Site:
Cape Canaveral.
Launch Complex:
Cape Canaveral LC14.
LV Family:
Atlas.
Launch Vehicle:
Atlas A.
LV Configuration: Atlas A 4A.
FAILURE: Failure in the booster fuel system..
Failed Stage: 1.
- Research and development test - .
Nation: USA. Agency: USAF. Apogee: 3.00 km (1.80 mi). Summary: First test flight of prototype WS-107A Atlas was detonated by command signal at 10,000 feet following a failure in the booster fuel system. The 23-second flight was considered a partial success..
1957 July 1 - .
Launch Site:
Vandenberg.
LV Family:
Atlas.
Launch Vehicle:
Atlas D.
- First Atlas wing activated at Cooke AFB. - .
Nation: USA. Summary: Air Research and Development Command activated the 704th Strategic Missile Wing (Atlas) at Cooke AFB..
1957 August 1 - .
LV Family:
Atlas.
Launch Vehicle:
Atlas D.
- Atlas IOC delayed. - .
Nation: USA. Summary: Estimated operational capability date for Atlas changed from March 1959 to June 1959..
1957 September - .
LV Family:
Atlas.
Launch Vehicle:
Atlas B.
- Scheduled design complete (95%) for Atlas B-series missiles - .
Nation: USA.
1957 September 25 - .
19:57 GMT - .
Launch Site:
Cape Canaveral.
Launch Complex:
Cape Canaveral LC14.
LV Family:
Atlas.
Launch Vehicle:
Atlas A.
LV Configuration: Atlas A 6A.
FAILURE: Failure in the booster fuel system..
Failed Stage: 1.
- Research and development test - .
Nation: USA. Agency: USAF. Apogee: 4.00 km (2.40 mi). Summary: Atlas was again destroyed by command signal at three minutes into flight following a failure in the booster fuel system. The 50-second active flight was considered a partial success..
1957 December 17 - .
17:39 GMT - .
Launch Site:
Cape Canaveral.
Launch Complex:
Cape Canaveral LC14.
LV Family:
Atlas.
Launch Vehicle:
Atlas A.
LV Configuration: Atlas A 12A.
- Research and development test - .
Nation: USA. Agency: USAF. Apogee: 120 km (70 mi). Summary: First successful test firing of USAF Atlas ICBM, the missile landing in the target area after a flight of 600 miles..
1958 January - .
LV Family:
Atlas.
Launch Vehicle:
Atlas C.
- Scheduled design complete (95%) for Atlas C-series missiles - .
Nation: USA.
During 1958 - .
LV Family:
Atlas.
Launch Vehicle:
Atlas Vega.
- NASA sketches two-crew Mercury follow-on spacecraft - .
Nation: USA. Related Persons: Johnson, Caldwell. Program: Gemini. Spacecraft: Gemini. In 1958 H. Kurt Strass and Caldwell C. Johnson of NASA's Space Task Group at Langley Field, Virginia.sketched a spacecraft design concept for a two-man orbiting laboratory to be launched by an Atlas-Vega booster. This was one of the earliest sketches of a two-crew Mercury follow-on. The Vega stage was dropped in favour of the Agena a year later, and a similar one-crew Mercury-Agena space station was proposed by McDonnell some years later.
1958 - During the year - .
LV Family:
Atlas.
Launch Vehicle:
Atlas D.
- Outpost four-man space station. - .
Nation: USA. Related Persons: Ehricke. Spacecraft: Outpost. In 1958, the year after Sputnik 1, Krafft Ehricke, then with General Dynamics' Convair Division, designed a four-man space station known as Outpost. Ehricke proposed that the Atlas ICBM being developed by Convair could be adapted as the station's basic structure. The Atlas, 3 m in diameter and 22.8 m long, was America's largest rocket at the time.
1958 January 10 - .
15:48 GMT - .
Launch Site:
Cape Canaveral.
Launch Complex:
Cape Canaveral LC12.
LV Family:
Atlas.
Launch Vehicle:
Atlas A.
LV Configuration: Atlas A 10A.
- Research and development test - .
Nation: USA. Agency: USAF. Apogee: 120 km (70 mi). Summary: A successful limited flight was made by the fourth Atlas fired from Cape Canaveral..
1958 February 7 - .
19:37 GMT - .
Launch Site:
Cape Canaveral.
Launch Complex:
Cape Canaveral LC14.
LV Family:
Atlas.
Launch Vehicle:
Atlas A.
LV Configuration: Atlas A 13A.
FAILURE: Failure.
Failed Stage: 1.
- Research and development launch - .
Nation: USA. Agency: USAF. Apogee: 120 km (70 mi).
1958 February 20 - .
17:46 GMT - .
Launch Site:
Cape Canaveral.
Launch Complex:
Cape Canaveral LC12.
LV Family:
Atlas.
Launch Vehicle:
Atlas A.
LV Configuration: Atlas A 11A.
FAILURE: Failure.
Failed Stage: 1.
- Research and development launch - .
Nation: USA. Agency: USAF.
1958 April 5 - .
17:01 GMT - .
Launch Site:
Cape Canaveral.
Launch Complex:
Cape Canaveral LC14.
LV Family:
Atlas.
Launch Vehicle:
Atlas A.
LV Configuration: Atlas A 15A.
FAILURE: Failure.
Failed Stage: 1.
- Research and development test - .
Nation: USA. Agency: USAF. Apogee: 100 km (60 mi). Summary: USAF Atlas A ICBM was successfully flown from Cape Canaveral, Fla., to the impact area some 600 miles away..
1958 May 28 - .
LV Family:
Atlas.
Launch Vehicle:
Atlas D.
- Atlas production facility opens. - .
Nation: USA. Summary: Open house, new Astronautics facility on Kearny Mesa.
1958 June 3 - .
21:28 GMT - .
Launch Site:
Cape Canaveral.
Launch Complex:
Cape Canaveral LC12.
LV Family:
Atlas.
Launch Vehicle:
Atlas A.
LV Configuration: Atlas A 16A.
- Research and development test - .
Nation: USA. Agency: USAF. Apogee: 120 km (70 mi). Summary: Last Atlas A flight, considered fully successful. Four of the eight flights were considered successful..
1958 July - .
LV Family:
Atlas.
Launch Vehicle:
Atlas D.
- Atlas ICBM soft pad design complete. - .
Nation: USA. Summary: Design of vertical initial operational capability ground support equipment.
1958 July 19 - .
17:36 GMT - .
Launch Site:
Cape Canaveral.
Launch Complex:
Cape Canaveral LC11.
LV Family:
Atlas.
Launch Vehicle:
Atlas B.
LV Configuration: Atlas B 3B.
FAILURE: Flight Control Failure.
Failed Stage: G.
- Research and development test - .
Nation: USA. Agency: USAF. Apogee: 10 km (6 mi). Summary: First full-powered flight of USAF Atlas B ICBM using both the sustainer and booster engines. 'Marginally successful'..
1958 August - .
LV Family:
Atlas.
Launch Vehicle:
Atlas D.
- Scheduled design complete (95%) for Atlas D-series missiles - .
Nation: USA.
1958 August 2 - .
22:16 GMT - .
Launch Site:
Cape Canaveral.
Launch Complex:
Cape Canaveral LC13.
LV Family:
Atlas.
Launch Vehicle:
Atlas B.
LV Configuration: Atlas B 4B.
- Research and development test - .
Nation: USA. Agency: USAF. Apogee: 900 km (550 mi). Summary: Second full-powered flight of USAF Atlas ICBM traveled 2,500 miles with radio-inertial guidance, fully successful..
1958 August 29 - .
04:30 GMT - .
Launch Site:
Cape Canaveral.
Launch Complex:
Cape Canaveral LC11.
LV Family:
Atlas.
Launch Vehicle:
Atlas B.
LV Configuration: Atlas B 5B.
- Research and development / AFSWC-1 test - .
Nation: USA. Agency: USAF. Apogee: 900 km (550 mi).
1958 September 14 - .
05:24 GMT - .
Launch Site:
Cape Canaveral.
Launch Complex:
Cape Canaveral LC14.
LV Family:
Atlas.
Launch Vehicle:
Atlas B.
LV Configuration: Atlas B 8B.
- Research and development / AFSWC-2 test - .
Nation: USA. Agency: USAF. Apogee: 900 km (550 mi).
1958 September 18 - .
21:27 GMT - .
Launch Site:
Cape Canaveral.
Launch Complex:
Cape Canaveral LC13.
LV Family:
Atlas.
Launch Vehicle:
Atlas B.
LV Configuration: Atlas B 6B.
FAILURE: Failure.
Failed Stage: 1.
- Research and development launch - .
Nation: USA. Agency: USAF. Apogee: 100 km (60 mi).
1958 October 1 - .
LV Family:
Atlas.
Launch Vehicle:
Atlas Centaur LV-3C.
- Centaur engine contract awarded. - .
Nation: USA. Summary: Air Force awarded contract Pratt & Whitney for Centaur vehicle with hydrogen-burning chamber based on research of Lewis Research Center between 1953 and 1957. Centaur project later transferred to NASA..
1958 October 17-18 - .
LV Family:
Atlas.
Launch Vehicle:
Atlas D.
- Negotiations for Mercury Atlas launch vehicles - .
Nation: USA. Program: Mercury. Summary: Langley Research Center personnel visited the Air Force Ballistic Missile Division, Inglewood, California, to open negotiations for procuring Atlas launch vehicles for the manned satellite project..
1958 November 18 - .
04:00 GMT - .
Launch Site:
Cape Canaveral.
Launch Complex:
Cape Canaveral LC11.
LV Family:
Atlas.
Launch Vehicle:
Atlas B.
LV Configuration: Atlas B 9B.
- Research and development launch - .
Nation: USA. Agency: USAF. Apogee: 800 km (490 mi).
1958 November 24 - .
LV Family:
Atlas.
Launch Vehicle:
Atlas D.
- Space Task Group orders first Mercury Atlas missile. - .
Nation: USA. Program: Mercury. The Space Task Group placed an order for one Atlas launch vehicle with the Air Force Missile Division, Inglewood, California, as part of a preliminary research program leading to manned space flight. The National Aeronautics and Space Administration Headquarters requested that the Air Force construct and launch one Atlas C launch vehicle to check the aerodynamics of the spacecraft. It was the intention to launch this missile about May 1959 in a ballistic trajectory. This was to be the launch vehicle for the Big Joe reentry test shot, but plans were later changed and an Atlas Model D launch vehicle was used instead.
1958 November 29 - .
02:27 GMT - .
Launch Site:
Cape Canaveral.
Launch Complex:
Cape Canaveral LC14.
LV Family:
Atlas.
Launch Vehicle:
Atlas B.
LV Configuration: Atlas B 12B.
- Research and development / AFSWC-3 test - .
Nation: USA. Agency: USAF. Apogee: 900 km (550 mi). Summary: Less than 18 months after the first flight, a USAF Atlas made its first successful full-range operational test flight in a 6,325 statute-mile flight, landed close to its target..
1958 December 8 - .
LV Family:
Atlas.
Launch Vehicle:
Atlas D.
- Nine Atlas launch vehicles required for Project Mercury - .
Nation: USA. Program: Mercury. Summary: The Space Task Group indicated that nine Atlas launch vehicles were required in support of the Project Mercury manned and unmanned flights and these were ordered from the Air Force Ballistic Missile Division..
1958 December 18 - .
23:02 GMT - .
Launch Site:
Cape Canaveral.
Launch Complex:
Cape Canaveral LC11.
LV Family:
Atlas.
Launch Vehicle:
Atlas B.
LV Configuration: Atlas B 10B.
- Score - .
Mass: 70 kg (154 lb). Nation: USA. Agency: DARPA. Class: Technology. Type: Communications technology satellite. Spacecraft: Score. Decay Date: 1959-01-21 . USAF Sat Cat: 10 . COSPAR: 1958-Zeta-1. Apogee: 1,484 km (922 mi). Perigee: 185 km (114 mi). Inclination: 32.3000 deg. Period: 101.50 min. Summary: Signal Communication by Orbiting Relay Equipment; first commsat; transmitted taped messages for 13 days..
1958 December 24 - .
04:45 GMT - .
Launch Site:
Cape Canaveral.
Launch Complex:
Cape Canaveral LC12.
LV Family:
Atlas.
Launch Vehicle:
Atlas C.
LV Configuration: Atlas C 3C.
- Research and development test - .
Nation: USA. Agency: USAF. Apogee: 900 km (550 mi). Summary: First Atlas C flight (3C), successful..
1959 January - .
LV Family:
Atlas.
Launch Vehicle:
Atlas D.
- Strategic Air Command takes over Atlas ICBM facilities. - .
Nation: USA. Summary: VAFB SMS 576A facilities turned over to SAC.
1959 January 15 - .
LV Family:
Atlas.
Launch Vehicle:
Atlas Centaur LV-3C.
- Centaur first contract. - .
Nation: USA. Summary: Centaur project (Atlas upper stage) contracted for $7 million in its first year.
1959 January 16 - .
04:00 GMT - .
Launch Site:
Cape Canaveral.
Launch Complex:
Cape Canaveral LC14.
LV Family:
Atlas.
Launch Vehicle:
Atlas B.
LV Configuration: Atlas B 13B.
FAILURE: Failure.
Failed Stage: 1.
- Research and development launch - .
Nation: USA. Agency: USAF. Apogee: 100 km (60 mi).
1959 January 27 - .
LV Family:
Atlas;
Nova;
Saturn I.
- NASA National Space Vehicle Program - .
Nation: USA. Program: Apollo. After consultation and discussion with DOD, NASA formulated a national space vehicle program. The central idea of the program was that a single launch vehicle should be developed for use in each series of future space missions. The launch vehicle would thus achieve a high degree of reliability, while the guidance and payload could be varied according to purpose of the mission. Four general-purpose launch vehicles were described: Vega, Centaur, Saturn, and Nova. The Nova booster stage would be powered by a cluster of four F-1 engines, the second stage by a single F-1, and the third stage would be the size of an intercontinental ballistic missile but would use liquid hydrogen as a fuel. This launch vehicle would be the first in a series that could transport a man to the lunar surface and return him safely to earth in a direct ascent mission. Four additional stages would be required in such a mission.
1959 January 27 - .
23:34 GMT - .
Launch Site:
Cape Canaveral.
Launch Complex:
Cape Canaveral LC12.
LV Family:
Atlas.
Launch Vehicle:
Atlas C.
LV Configuration: Atlas C 4C.
- Mod II re-entry vehicle research and development mission - .
Nation: USA. Agency: USAF. Apogee: 990 km (610 mi).
1959 February - .
LV Family:
Atlas.
Launch Vehicle:
Atlas D.
- NASA/USAF responsibilities for the first two Mercury Atlas firings. - .
Nation: USA. Program: Mercury. During a meeting between personnel of the Space Task Group and the Air Force Ballistic Missile Division, the responsibilities of the two organizations were outlined for the first two Atlas firings. Space Technology Laboratories, under Air Force Ballistic Missile Division direction, would select the design trajectories according to the specifications set forth by the Space Task Group. These specifications were to match a point in the trajectory at about 450,000 feet, corresponding to a normal reentry condition for the manned spacecraft after firing of the retrorockets at an altitude of 120 nautical miles. Space Technology Laboratories would also provide impact dispersion data, data for range safety purposes, and the necessary reprograming of the guidance computers. The spacecraft for the suborbital Atlas flights would be manufactured under the deriction of the Lewis Research Center, based on Space Task Group designs. Space Task Group was developing the spacecraft instrumentation, with a contingent of personnel at the Lewis Research Center. The attitude control system was being developed by Lewis.
1959 February - .
LV Family:
Atlas.
Launch Vehicle:
Atlas D.
- Atlas ICBM coffin launcher design completed. - .
Nation: USA. Summary: Design of horizontal operational ground support equipment (coffin configuration) completed.
1959 February 4 - .
08:01 GMT - .
Launch Site:
Cape Canaveral.
Launch Complex:
Cape Canaveral LC11.
LV Family:
Atlas.
Launch Vehicle:
Atlas B.
LV Configuration: Atlas B 11B.
- Research and development / AFSWC-4? test - .
Nation: USA. Agency: USAF. Apogee: 990 km (610 mi). Summary: Last Atlas B flight, fully successful.
1959 February 12-13 - .
LV Family:
Atlas.
Launch Vehicle:
Atlas D.
- Atlas launch vehicles in Project Mercury. - .
Nation: USA. Program: Mercury. Discussions were held at Langley Field between the Space Task Group and the Air Force Ballistic Missile Division covering aspects of the use of Atlas launch vehicles in Project Mercury. Specifically discussed were technical details of the first Atlas test flight (Big Joe), the abort sensing capability for later flights, and overall program objectives.
1959 February 15 - .
LV Family:
Atlas;
Nova;
Saturn I.
- NASA Booster Development Plan for 60's - .
Nation: USA. Program: Apollo. Class: Manned. Type: Manned space station. Summary: NASA issues plan for development in next decade of Vega (later cancelled as too similar to Agena), Centaur, Saturn, and Nova launch vehicles. Juno V renamed Saturn I..
1959 February 20 - .
05:38 GMT - .
Launch Site:
Cape Canaveral.
Launch Complex:
Cape Canaveral LC12.
LV Family:
Atlas.
Launch Vehicle:
Atlas C.
LV Configuration: Atlas C 5C.
FAILURE: Failure.
Failed Stage: 1.
- Research and development launch - .
Nation: USA. Agency: USAF. Apogee: 100 km (60 mi).
1959 March - .
LV Family:
Atlas.
Launch Vehicle:
Atlas C.
LV Configuration: Atlas C 6C.
- Atlas 6C blows up. - .
Nation: USA. Summary: Missile 6C blows up, destroying ERB Stand 1-A..
1959 March 19 - .
00:59 GMT - .
Launch Site:
Cape Canaveral.
Launch Complex:
Cape Canaveral LC12.
LV Family:
Atlas.
Launch Vehicle:
Atlas C.
LV Configuration: Atlas C 7C.
FAILURE: Failure.
Failed Stage: 1.
- RVX-2 re-entry vehicle research and development mission - .
Nation: USA. Agency: USAF. Apogee: 200 km (120 mi).
1959 April - .
LV Family:
Atlas.
Launch Vehicle:
Atlas E.
- Scheduled design complete (95%) for Atlas E-series missiles - .
Nation: USA.
1959 April 14 - .
21:46 GMT - .
Launch Site:
Cape Canaveral.
Launch Complex:
Cape Canaveral LC13.
LV Family:
Atlas.
Launch Vehicle:
Atlas D.
LV Configuration: Atlas D 3D.
FAILURE: Failure.
Failed Stage: 1.
- Research and development launch - .
Nation: USA. Agency: USAF. Apogee: 1.00 km (0.60 mi).
1959 May 9 - .
LV Family:
Atlas.
Launch Vehicle:
Atlas Vega.
- High-resolution photographs of the moon using Vega rocket - .
Nation: USA. Related Persons: Rosen, Milton. Program: Apollo. Spacecraft: Lunar Orbiter. Milton W. Rosen of NASA Headquarters proposed a plan for obtaining high-resolution photographs of the moon. A three-stage Vega would place the payload within a 500-mile diameter circle on the lunar surface. A stabilized retrorocket fired at 500 miles above the moon would slow the instrument package sufficiently to permit 20 photographs to be transmitted at a rate of one picture per minute. Additional Details: here....
1959 May 19 - .
04:30 GMT - .
Launch Site:
Cape Canaveral.
Launch Complex:
Cape Canaveral LC14.
LV Family:
Atlas.
Launch Vehicle:
Atlas D.
LV Configuration: Atlas D 7D.
FAILURE: Failure.
Failed Stage: 1.
- Research and development launch - .
Nation: USA. Agency: USAF. Apogee: 1.00 km (0.60 mi).
1959 June - .
LV Family:
Atlas.
Launch Vehicle:
Atlas D.
LV Configuration: Atlas D 2D.
- Atlas 2D blows up. - .
Nation: USA. Summary: Missile 2D blows up on Sycamore stand S-2, after a total of 1486 seconds running time.
1959 June 5 - .
LV Family:
Atlas.
Launch Vehicle:
Atlas D.
- Flight instrumentation necessary to support the Mercury-Atlas program. - .
Nation: USA. Program: Mercury. Space Technology Laboratories and Convair completed an analysis of flight instrumentation necessary to support the Mercury-Atlas program. The primary objective of the study was to select a light-weight telemetry system. A system weighing 270 pounds was recommended, and the National Aeronautics and Space Administration concurred with the proposal.
1959 June 6 - .
17:39 GMT - .
Launch Site:
Cape Canaveral.
Launch Complex:
Cape Canaveral LC13.
LV Family:
Atlas.
Launch Vehicle:
Atlas D.
LV Configuration: Atlas D 5D.
FAILURE: Failure.
Failed Stage: 1.
- Research and development launch - .
Nation: USA. Agency: USAF.
1959 July 12 - .
LV Family:
Atlas.
Launch Vehicle:
Atlas D.
- Instrumentation to measure noise level during the Mercury Big Joe-Atlas launching. - .
Nation: USA. Program: Mercury. An agreement was made with the Air Force for Space Task Group to place microphone pickups on the skin of the Atlas launch vehicle as a part of the instrumentation to measure noise level during the Big Joe-Atlas launching. Distribution of the microphones was as follows: one inside the Mercury spacecraft, three externally about midway of the launch vehicle, and one on the Atlas skirt.
1959 July 21 - .
05:22 GMT - .
Launch Site:
Cape Canaveral.
Launch Complex:
Cape Canaveral LC12.
LV Family:
Atlas.
Launch Vehicle:
Atlas C.
LV Configuration: Atlas C 8C.
- Research and development / AFSWC-5 test / particles mission - .
Nation: USA. Agency: USAF. Apogee: 900 km (550 mi). Summary: A full-scale USAF Atlas ICBM nose cone recovered for the first time after flight down the AMR..
1959 July 29 - .
04:10 GMT - .
Launch Site:
Cape Canaveral.
Launch Complex:
Cape Canaveral LC11.
LV Family:
Atlas.
Launch Vehicle:
Atlas D.
LV Configuration: Atlas D 11D.
- Research and development test - .
Nation: USA. Agency: USAF. Apogee: 1,800 km (1,100 mi). Summary: First Atlas successful D missile flight..
1959 August 11 - .
18:01 GMT - .
Launch Site:
Cape Canaveral.
Launch Complex:
Cape Canaveral LC13.
LV Family:
Atlas.
Launch Vehicle:
Atlas D.
LV Configuration: Atlas D 14D.
- Research and development launch - .
Nation: USA. Agency: USAF. Apogee: 1,800 km (1,100 mi).
1959 August 24 - .
15:53 GMT - .
Launch Site:
Cape Canaveral.
Launch Complex:
Cape Canaveral LC12.
LV Family:
Atlas.
Launch Vehicle:
Atlas C.
LV Configuration: Atlas C 11C.
- Research and development / AFSWC-6 test - .
Nation: USA. Agency: USAF. Apogee: 1,400 km (800 mi). Summary: Last successful Atlas C flight (11C); 9C exploded one month later during the Able static firing..
1959 August 28 - .
LV Family:
Atlas.
Launch Vehicle:
Atlas D.
- Additional Atlas launch vehicles in support of Project Mercury. - .
Nation: USA. Program: Mercury. NASA Headquarters authorized the Space Task Group to enter into negotiations with the Air Force Ballistic Missile Division for the procurement of additional Atlas launch vehicles in support of Project Mercury. The authorization was to be incorporated into Contract No. HS-36.
1959 September 1 - .
Launch Site:
Vandenberg.
LV Family:
Atlas.
Launch Vehicle:
Atlas D.
- Atlas D ICBM operational. - .
Nation: USA. Summary: USAF Atlas ICBM officially declared operational and taken over by the Strategic Air Command, at Vandenberg AFB..
1959 September 9 - .
08:19 GMT - .
Launch Site:
Cape Canaveral.
Launch Complex:
Cape Canaveral LC14.
LV Family:
Atlas.
Launch Vehicle:
Atlas D.
LV Configuration: Atlas D 10D.
FAILURE: Failure.
Failed Stage: 1.
- Mercury BJ-1 - .
Nation: USA. Agency: USAF. Apogee: 153 km (95 mi). Summary: NASA boilerplate model of Mercury capsule successfully launched on an Atlas (Big Joe) missile from AMR and recovered in South Atlantic after surviving reentry heat of more than 10,000°F..
1959 September 9 - .
17:50 GMT - .
Launch Site:
Vandenberg.
Launch Complex:
Vandenberg 576A2.
LV Family:
Atlas.
Launch Vehicle:
Atlas D.
LV Configuration: Atlas D 12D.
- Initial operational capability demonstration launch - .
Nation: USA. Agency: USAF SAC. Apogee: 1,800 km (1,100 mi). First SAC operational (IOC) launch, 576th SMS, successful: impacted within one mile of target near Wake Island, a 4,480 nautical mile flight. Afterwards, General Thomas S. Power, Commander in Chief of Strategic Air Command, declared the Atlas system to be operational.
1959 September 17 - .
02:09 GMT - .
Launch Site:
Cape Canaveral.
Launch Complex:
Cape Canaveral LC13.
LV Family:
Atlas.
Launch Vehicle:
Atlas D.
LV Configuration: Atlas D 17D.
FAILURE: Failure.
Failed Stage: 1.
- Research and development launch - .
Nation: USA. Agency: USAF. Apogee: 1,000 km (600 mi).
1959 September 24 - .
Launch Site:
Cape Canaveral.
Launch Complex:
Cape Canaveral LC12.
LV Family:
Atlas.
Launch Vehicle:
Atlas C Able.
LV Configuration: Atlas C Able 9C / Able-5.
FAILURE: Vehicle exploded on pad..
Failed Stage: 1.
1959 October 6 - .
05:55 GMT - .
Launch Site:
Cape Canaveral.
Launch Complex:
Cape Canaveral LC11.
LV Family:
Atlas.
Launch Vehicle:
Atlas D.
LV Configuration: Atlas D 18D.
- Mk 3 Mod 1 re-entry vehicle research and development mission - .
Nation: USA. Agency: USAF. Apogee: 1,800 km (1,100 mi).
1959 October 10 - .
03:10 GMT - .
Launch Site:
Cape Canaveral.
Launch Complex:
Cape Canaveral LC13.
LV Family:
Atlas.
Launch Vehicle:
Atlas D.
LV Configuration: Atlas D 22D.
- Research and development launch - .
Nation: USA. Agency: USAF. Apogee: 1,800 km (1,100 mi).
1959 October 29 - .
07:20 GMT - .
Launch Site:
Cape Canaveral.
Launch Complex:
Cape Canaveral LC11.
LV Family:
Atlas.
Launch Vehicle:
Atlas D.
LV Configuration: Atlas D 26D.
- Research and development test - .
Nation: USA. Agency: USAF. Apogee: 1,800 km (1,100 mi). Summary: USAF Atlas successfully launched from Cape Canaveral carrying a nose-cone camera which took a series of photographs of the earth's cloud cover from a 300-mile altitude..
1959 November 4 - .
21:37 GMT - .
Launch Site:
Cape Canaveral.
Launch Complex:
Cape Canaveral LC13.
LV Family:
Atlas.
Launch Vehicle:
Atlas D.
LV Configuration: Atlas D 28D.
- Research and development launch - .
Nation: USA. Agency: USAF. Apogee: 1,800 km (1,100 mi).
1959 November 24 - .
19:48 GMT - .
Launch Site:
Cape Canaveral.
Launch Complex:
Cape Canaveral LC13.
LV Family:
Atlas.
Launch Vehicle:
Atlas D.
LV Configuration: Atlas D 15D.
- Research and development launch - .
Nation: USA. Agency: USAF. Apogee: 1,800 km (1,100 mi).
1959 November 26 - .
07:26 GMT - .
Launch Site:
Cape Canaveral.
Launch Complex:
Cape Canaveral LC14.
LV Family:
Atlas.
Launch Vehicle:
Atlas Able.
LV Configuration: Atlas Able 20D / Able-5.
FAILURE: Payload shroud failed after 45 sec, broke away prematurely..
Failed Stage: S.
- Pioneer (P 3) - .
Payload: Pioneer P 3 / Able IVB. Mass: 168 kg (370 lb). Nation: USA. Agency: NASA. Program: Pioneer. Class: Moon. Type: Lunar probe. Spacecraft: Pioneer P 3. Decay Date: 1959-11-26 . COSPAR: F591126A. Apogee: 1,000 km (600 mi). An intended lunar probe launched from the Atlantic Missile Range by an Atlas-Able booster disintegrated about 45 seconds later when the protective sheath covering the payload detached prematurely. The probe was sponsored by NASA, developed by the Jet Propulsion Laboratory, and launched by the Air Force Ballistic Missile Division.
1959 December 9 - .
00:10 GMT - .
Launch Site:
Cape Canaveral.
Launch Complex:
Cape Canaveral LC13.
LV Family:
Atlas.
Launch Vehicle:
Atlas D.
LV Configuration: Atlas D 31D.
- Research and development launch - .
Nation: USA. Agency: USAF. Apogee: 1,800 km (1,100 mi).
1959 December 19 - .
00:48 GMT - .
Launch Site:
Cape Canaveral.
Launch Complex:
Cape Canaveral LC13.
LV Family:
Atlas.
Launch Vehicle:
Atlas D.
LV Configuration: Atlas D 40D.
- Research and development test - .
Nation: USA. Agency: USAF. Apogee: 1,800 km (1,100 mi). Summary: Atlas ICBM made second successful 6,325-mile flight at AMR..
1960 January 7 - .
01:40 GMT - .
Launch Site:
Cape Canaveral.
Launch Complex:
Cape Canaveral LC13.
LV Family:
Atlas.
Launch Vehicle:
Atlas D.
LV Configuration: Atlas D 43D.
- Research and development test - .
Nation: USA. Agency: USAF. Apogee: 1,800 km (1,100 mi). Summary: 43D achieved a 6300 NM (7200 SM) flight from AMR with enough residual fuel for an additional 2000 miles.
1960 January 18 - .
LV Family:
Atlas.
Launch Vehicle:
Atlas D.
- Mercury-Atlas flight test working group to become a standing coordination body. - .
Nation: USA. Program: Mercury. A proposal was made by Walter C. Williams, Associate Director of Project Mercury Operations, that the Mercury-Atlas flight test working group become an official and standing coordination body. This group brought together representation from the Space Task Group, Air Force Ballistic Missile Division, Convair Astronautics, McDonnell Aircraft Corporation, and the Atlantic Missile Range. Personnel from these organizations had met informally in the past on several occasions.
1960 January 21 - .
LV Family:
Atlas.
Launch Vehicle:
Atlas D.
- 15 Atlas launch vehicles and 26 Mercury spacecraft purchased. - .
Nation: USA. Program: Mercury. Spacecraft: Mercury. Summary: At a meeting to draft fiscal year 1962 funding estimates, the total purchase of Atlas launch vehicles was listed as 15, and the total purchase of Mercury spacecraft was listed as 26..
1960 January 26 - .
23:43 GMT - .
Launch Site:
Vandenberg.
Launch Complex:
Vandenberg 576A3.
LV Family:
Atlas.
Launch Vehicle:
Atlas D.
LV Configuration: Atlas D 6D.
FAILURE: Failure.
- Initial operational capability demonstration launch - .
Nation: USA. Agency: USAF SAC. Apogee: 1,800 km (1,100 mi). Summary: Two Atlas ICBMs launched within two hours - one by SAC at VAFB, one by GD/A at AMR; both successful..
1960 January 27 - .
01:31 GMT - .
Launch Site:
Cape Canaveral.
Launch Complex:
Cape Canaveral LC13.
LV Family:
Atlas.
Launch Vehicle:
Atlas D.
LV Configuration: Atlas D 44D.
- Research and development launch - .
Nation: USA. Agency: USAF. Apogee: 1,800 km (1,100 mi).
1960 January 31 - .
LV Family:
Atlas;
Redstone.
- Six chimpanzees ready for Mercury missions. - .
Nation: USA. Program: Mercury. Summary: Six chimpanzees were rated as being trained and ready to support Mercury-Redstone or Mercury-Atlas missions. Other chimpanzees were being shipped from Africa to enter the animal training program..
1960 February 12 - .
04:11 GMT - .
Launch Site:
Cape Canaveral.
Launch Complex:
Cape Canaveral LC13.
LV Family:
Atlas.
Launch Vehicle:
Atlas D.
LV Configuration: Atlas D 49D.
- Research and development launch - .
Nation: USA. Agency: USAF. Apogee: 1,800 km (1,100 mi).
1960 February 15 - .
Launch Site:
Cape Canaveral.
Launch Complex:
Cape Canaveral LC13.
LV Family:
Atlas.
Launch Vehicle:
Atlas Able.
LV Configuration: Atlas D / Able-5.
FAILURE: Vehicle exploded in static firing..
Failed Stage: 1.
- Pioneer (P 31) - .
Payload: Pioneer P 31. Nation: USA. Program: Pioneer. Class: Moon. Type: Lunar probe. Spacecraft: Pioneer P 3. Decay Date: 1960-02-15 . COSPAR: F600215A.
1960 February 26 - .
17:25 GMT - .
Launch Site:
Cape Canaveral.
Launch Complex:
Cape Canaveral LC14.
LV Family:
Atlas.
Launch Vehicle:
Atlas Agena A.
LV Configuration: Atlas Agena A 29D / Agena A 1008.
FAILURE: Second stage failed to separate..
Failed Stage: 2.
- Midas 1 - .
Payload: Midas / Agena TV 1008. Mass: 2,025 kg (4,464 lb). Nation: USA. Agency: USAF. Class: Military. Type: Early warning satellite. Spacecraft: Midas. Decay Date: 1960-02-26 . COSPAR: F600226A. Summary: Missile Defense Alarm System..
1960 March-April - .
LV Family:
Atlas.
Launch Vehicle:
Atlas D.
- Mercury-Atlas working panels - .
Nation: USA. Program: Mercury. The Mercury-Atlas working panels were reorganized into four groups: coordination, flight test, trajectory analysis, and change control. Each panel was composed of at least one representative from NASA (Space Task Group), McDonnell, Air Force Ballistic Missile Division, Space Technology Laboratory, and Convair-Astronautics.
1960 March 8 - .
13:10 GMT - .
Launch Site:
Cape Canaveral.
Launch Complex:
Cape Canaveral LC11.
LV Family:
Atlas.
Launch Vehicle:
Atlas D.
LV Configuration: Atlas D 42D.
- Research and development test - .
Nation: USA. Agency: USAF. Apogee: 1,800 km (1,100 mi). Summary: First USAF Atlas R&D flight using all-inertial guidance system..
1960 March 11 - .
00:36 GMT - .
Launch Site:
Cape Canaveral.
Launch Complex:
Cape Canaveral LC13.
LV Family:
Atlas.
Launch Vehicle:
Atlas D.
LV Configuration: Atlas D 51D.
FAILURE: Failure.
Failed Stage: 1.
- Research and development launch - .
Nation: USA. Agency: USAF.
1960 March 16 - .
LV Family:
Atlas.
Launch Vehicle:
Atlas D.
- The Space Task Group published recovery requirements for the Mercury-Atlas 1 (MA-1) flight test. - .
Nation: USA. Program: Mercury. Spacecraft: Mercury.
1960 April 8 - .
02:06 GMT - .
Launch Site:
Cape Canaveral.
Launch Complex:
Cape Canaveral LC11.
LV Family:
Atlas.
Launch Vehicle:
Atlas D.
LV Configuration: Atlas D 48D.
FAILURE: Failure.
Failed Stage: 1.
- Research and development launch - .
Nation: USA. Agency: USAF. Apogee: 1.00 km (0.60 mi).
1960 April 22 - .
19:39 GMT - .
Launch Site:
Vandenberg.
Launch Complex:
Vandenberg 576B2.
LV Family:
Atlas.
Launch Vehicle:
Atlas D.
LV Configuration: Atlas D 25D.
- Initial operational capability operational readiness test launch - .
Nation: USA. Agency: USAF SAC. Apogee: 1,800 km (1,100 mi).
1960 May 6 - .
16:47 GMT - .
Launch Site:
Vandenberg.
Launch Complex:
Vandenberg 576B2.
LV Family:
Atlas.
Launch Vehicle:
Atlas D.
LV Configuration: Atlas D 23D.
FAILURE: Failure.
Failed Stage: 1.
- Initial operational capability operational readiness test launch - .
Nation: USA. Agency: USAF SAC. Apogee: 2.00 km (1.20 mi).
1960 May 20 - .
15:00 GMT - .
Launch Site:
Cape Canaveral.
Launch Complex:
Cape Canaveral LC12.
LV Family:
Atlas.
Launch Vehicle:
Atlas D.
LV Configuration: Atlas D 56D.
- Research and development test - .
Nation: USA. Agency: USAF. Apogee: 1,800 km (1,100 mi). Summary: Atlas ICBM fired 9,040 statute miles from AMR to Indian Ocean, with operational weight nose cone plus instrumentation, longest known flight of an ICBM to date. Missile attained an apogee of about 1,000 miles..
1960 May 24 - .
17:36 GMT - .
Launch Site:
Cape Canaveral.
Launch Complex:
Cape Canaveral LC14.
LV Family:
Atlas.
Launch Vehicle:
Atlas Agena A.
LV Configuration: Atlas Agena A 45D / Agena A 1007.
- Midas 2 - .
Payload: Midas / Agena TV 1007. Mass: 2,300 kg (5,000 lb). Nation: USA. Agency: USAF. Class: Military. Type: Early warning satellite. Spacecraft: Midas. Decay Date: 1974-02-07 . USAF Sat Cat: 43 . COSPAR: 1960-Zeta-1. Apogee: 494 km (306 mi). Perigee: 473 km (293 mi). Inclination: 33.0000 deg. Period: 94.30 min. Summary: Missile Defense Alarm System. Test launch with W-17 sensor..
1960 June 11 - .
06:30 GMT - .
Launch Site:
Cape Canaveral.
Launch Complex:
Cape Canaveral LC11.
LV Family:
Atlas.
Launch Vehicle:
Atlas D.
LV Configuration: Atlas D 54D.
- Research and development launch - .
Nation: USA. Agency: USAF. Apogee: 1,800 km (1,100 mi).
1960 June 18 - .
LV Family:
Atlas.
Launch Vehicle:
Atlas D.
- Atlas launch vehicle 50-D was delivered for the first Mercury-Atlas mission (MA-1). - .
Nation: USA. Program: Mercury.
1960 June 22 - .
14:49 GMT - .
Launch Site:
Cape Canaveral.
Launch Complex:
Cape Canaveral LC14.
LV Family:
Atlas.
Launch Vehicle:
Atlas D.
LV Configuration: Atlas D 62D.
FAILURE: Electrical Failure.
- Research and development test - .
Nation: USA. Agency: USAF. Apogee: 1,800 km (1,100 mi). Summary: 50th Atlas to be flown at AMR, successful.
1960 June 28 - .
02:30 GMT - .
Launch Site:
Cape Canaveral.
Launch Complex:
Cape Canaveral LC12.
LV Family:
Atlas.
Launch Vehicle:
Atlas D.
LV Configuration: Atlas D 27D.
- Research and development / ionosphere mission - .
Nation: USA. Agency: USAF. Apogee: 1,800 km (1,100 mi).
1960 July 2 - .
06:58 GMT - .
Launch Site:
Cape Canaveral.
Launch Complex:
Cape Canaveral LC11.
LV Family:
Atlas.
Launch Vehicle:
Atlas D.
LV Configuration: Atlas D 60D.
- Research and development launch - .
Nation: USA. Agency: USAF. Apogee: 1,800 km (1,100 mi).
1960 July 7 - .
LV Family:
Atlas;
Redstone.
- Reporting plan for Mercury-Atlas and Mercury-Redstone missions - .
Nation: USA. Program: Mercury. Summary: A reporting plan for Mercury-Atlas and Mercury-Redstone missions was issued. This document was amended on February 17, 1961, and April 10, 1961..
1960 July 11 - .
LV Family:
Atlas.
Launch Vehicle:
Atlas D.
- Atlas operational plans given high priority - .
Nation: USA. Summary: M. Gen. Tom Gerrity appointed head of new BMC for operational site selection through turnover.
1960 July 22 - .
23:46 GMT - .
Launch Site:
Vandenberg.
Launch Complex:
Vandenberg 576B1.
LV Family:
Atlas.
Launch Vehicle:
Atlas D.
LV Configuration: Atlas D 74D.
FAILURE: Failure.
Failed Stage: 1.
- Initial operational capability operational readiness test launch - .
Nation: USA. Agency: USAF SAC. Apogee: 20 km (12 mi).
1960 July 29 - .
13:13 GMT - .
Launch Site:
Cape Canaveral.
Launch Complex:
Cape Canaveral LC14.
LV Family:
Atlas.
Launch Vehicle:
Atlas D.
LV Configuration: Atlas D 50D.
FAILURE: Structural failure of Atlas..
Failed Stage: 1.
- Mercury MA-1 - .
Nation: USA. Agency: USAF. Program: Mercury. Spacecraft: Mercury. Apogee: 13 km (8 mi). Mercury-Atlas 1 (MA-1) was launched from the Atlantic Missile Range in a test of spacecraft structural integrity under maximum heating conditions. After 58.5 seconds of flight, MA-1 exploded and the spacecraft was destroyed upon impact off-shore. None of the primary capsule test objectives were met. The mission objectives were to check the integrity of the spacecraft structure and afterbody shingles for a reentry associated with a critical abort and to evaluate the open-loop performance of the Atlas abort-sensing instrumentation system. The spacecraft contained no escape system and no test subject. Standard posigrade rockets were used to separate the spacecraft from the Atlas, but the retrorockets were dummies. The flight was terminated because of a launch vehicle and adapter structural failure. The spacecraft was destroyed upon impact with the water because the recovery system was not designed to actuate under the imposed flight conditions. Later most of the spacecraft, the booster engines, and the liquid oxygen vent valve were recovered from the ocean floor. Since none of the primary flight objectives was achieved, Mercury-Atlas 2 (MA-2) was planned to fulfill the mission.
1961 August 1960 to February - .
LV Family:
Atlas.
Launch Vehicle:
Atlas D.
- Exhaustive review of Mercury-Atlas after dual Atlas failures. - .
Nation: USA. Program: Mercury. Summary: Because of the failure of the Big Joe Atlas test flight and the Mercury-Atlas 1 (MA-1) flight to attain all its mission objectives, the overall Mercury-Atlas program underwent an exhaustive review. . Additional Details: here....
1960 August 9 - .
18:09 GMT - .
Launch Site:
Cape Canaveral.
Launch Complex:
Cape Canaveral LC12.
LV Family:
Atlas.
Launch Vehicle:
Atlas D.
LV Configuration: Atlas D 32D.
- Research and development / aeronomy mission - .
Nation: USA. Agency: USAF. Apogee: 1,800 km (1,100 mi).
1960 August 11 - .
LV Family:
Atlas.
Launch Vehicle:
Atlas D.
- Mercury-Atlas 1 (MA-1) mission malfunction discussed. - .
Nation: USA. Related Persons: Chamberlin. Program: Mercury. Summary: Representatives of NASA, McDonnell, Ballistic Missile Division, Space Technology Laboratories, and Convair met at Cape Canaveral and later at Convair Astronautics (Aug. 30, 1960) to discuss the Mercury-Atlas 1 (MA-1) mission malfunction. . Additional Details: here....
1960 August 12 - .
13:00 GMT - .
Launch Site:
Cape Canaveral.
Launch Complex:
Cape Canaveral LC11.
LV Family:
Atlas.
Launch Vehicle:
Atlas D.
LV Configuration: Atlas D 66D.
- Research and development launch - .
Nation: USA. Agency: USAF. Apogee: 1,800 km (1,100 mi).
1960 September 2 - .
Launch Site:
Warren AFB.
LV Family:
Atlas.
Launch Vehicle:
Atlas D.
- Atlas SMS 564 operational. - .
Nation: USA. Summary: Warren -1 AFB SMS 564 operational.
1960 September 12 - .
20:38 GMT - .
Launch Site:
Vandenberg.
Launch Complex:
Vandenberg 576B3.
LV Family:
Atlas.
Launch Vehicle:
Atlas D.
LV Configuration: Atlas D 47D.
FAILURE: Failure.
Failed Stage: 1.
- Initial operational capability demonstration and shakedown operations launch - .
Nation: USA. Agency: USAF SAC. Apogee: 1,000 km (600 mi).
1960 September 17 - .
00:50 GMT - .
Launch Site:
Cape Canaveral.
Launch Complex:
Cape Canaveral LC11.
LV Family:
Atlas.
Launch Vehicle:
Atlas D.
LV Configuration: Atlas D 76D.
- Research and development launch - .
Nation: USA. Agency: USAF. Apogee: 1,800 km (1,100 mi).
1960 September 19 - .
18:31 GMT - .
Launch Site:
Cape Canaveral.
Launch Complex:
Cape Canaveral LC14.
LV Family:
Atlas.
Launch Vehicle:
Atlas D.
LV Configuration: Atlas D 79D.
- Research and development test - .
Nation: USA. Agency: USAF. Apogee: 1,800 km (1,100 mi). Summary: Atlas ICBM fired 9030 statute miles, from Cape Canaveral to the Indian Ocean off the Cape of Good Hope in 50 minutes, the second record distance flight..
1960 September 20 - .
LV Family:
Atlas.
Launch Vehicle:
Atlas D.
- Mercury Atlas launch vehicle 67-D delivered to Cape Canaveral - .
Nation: USA. Program: Mercury. Summary: The Atlas launch vehicle 67-D was delivered to Cape Canaveral for the Mercury-Atlas 2 (MA-2) reentry test mission..
1960 September 25 - .
15:13 GMT - .
Launch Site:
Cape Canaveral.
Launch Complex:
Cape Canaveral LC12.
LV Family:
Atlas.
Launch Vehicle:
Atlas Able.
LV Configuration: Atlas Able 80D / Able-5.
FAILURE: Second stage exploded..
Failed Stage: 2.
- Pioneer (P 30) - .
Payload: Pioneer P 30 / Able VA. Mass: 175 kg (385 lb). Nation: USA. Agency: NASA. Program: Pioneer. Class: Moon. Type: Lunar probe. Spacecraft: Pioneer P 3. Decay Date: 1960-09-25 . COSPAR: F600925A. Apogee: 1,290 km (800 mi). Summary: An attempt to launch a Pioneer satellite into lunar orbit failed when one of the upper stages of the Atlas- Able rocket malfunctioned..
1960 September 26 - .
LV Family:
Atlas.
Launch Vehicle:
Atlas D.
- Roll-out inspection of Mercury Atlas launch vehicle 77-D - .
Nation: USA. Program: Mercury. Summary: The roll-out inspection of Mercury Atlas launch vehicle 77-D was conducted at Convair-Astronautics. This launch vehicle was allocated for the Mercury-Atlas 3 (MA-3) mission, but was later canceled and Atlas booster 100-D was used instead..
1960 September 29 - .
20:31 GMT - .
Launch Site:
Vandenberg.
Launch Complex:
Vandenberg 576B2.
LV Family:
Atlas.
Launch Vehicle:
Atlas D.
LV Configuration: Atlas D 33D.
FAILURE: Failure.
Failed Stage: 1.
- Initial operational capability demonstration and shakedown operations launch - .
Nation: USA. Agency: USAF SAC. Apogee: 500 km (310 mi).
1960 October 11 - .
19:15 GMT - .
Launch Site:
Cape Canaveral.
Launch Complex:
Cape Canaveral LC13.
LV Family:
Atlas.
Launch Vehicle:
Atlas E.
LV Configuration: Atlas E 3E.
FAILURE: Failure.
Failed Stage: 1.
- Research and development test - .
Nation: USA. Agency: USAF. Apogee: 1,000 km (600 mi). Summary: First E missile flown with MA-3 engine, unsuccessful.
1960 October 11 - .
20:33 GMT - .
Launch Site:
Vandenberg.
Launch Complex:
Vandenberg SLC3W.
LV Family:
Atlas.
Launch Vehicle:
Atlas Agena A.
LV Configuration: Atlas Agena A 57D / Agena A 2101.
FAILURE: Second stage failure..
Failed Stage: 2.
- Samos 1 - .
Payload: Samos E-1 no. 1. Mass: 1,845 kg (4,067 lb). Nation: USA. Agency: USAF. Class: Surveillance. Type: Military surveillance satellite. Spacecraft: Samos. Decay Date: 1960-10-11 . COSPAR: F601011A. Summary: First generation photo surveillance; radio relay of images; Satellite and Missile Observation Satellite..
1960 October 13 - .
04:53 GMT - .
Launch Site:
Vandenberg.
Launch Complex:
Vandenberg 576B3.
LV Family:
Atlas.
Launch Vehicle:
Atlas D.
LV Configuration: Atlas D 81D.
FAILURE: Failure.
Failed Stage: 1.
- Initial operational capability demonstration and shakedown operations launch - .
Nation: USA. Agency: USAF SAC. Apogee: 20 km (12 mi).
1960 October 13 - .
09:34 GMT - .
Launch Site:
Cape Canaveral.
Launch Complex:
Cape Canaveral LC11.
LV Family:
Atlas.
Launch Vehicle:
Atlas D.
LV Configuration: Atlas D 71D.
- Research and development test - .
Nation: USA. Agency: USAF. Apogee: 1,800 km (1,100 mi). Summary: USAF Atlas launched at AMR placed nose cone containing three black mice 650 miles up and 5,000 miles downrange at 17,000 mph. Nose cone was recovered in target area near Ascension Island, the three mice surviving the flight in "good condition.".
1960 October 22 - .
05:13 GMT - .
Launch Site:
Cape Canaveral.
Launch Complex:
Cape Canaveral LC14.
LV Family:
Atlas.
Launch Vehicle:
Atlas D.
LV Configuration: Atlas D 55D.
- Research and development launch - .
Nation: USA. Agency: USAF. Apogee: 1,800 km (1,100 mi).
November 1960-August 1961 - .
LV Family:
Atlas.
Launch Vehicle:
Atlas D.
- Crash program instigated to get Atlas sites operational. - .
Nation: USA. Summary: Golden Ram program accomplished at SMS 576-B2 & B3.
1960 November 1 - .
LV Family:
Atlas.
Launch Vehicle:
Atlas Centaur LV-3C.
- Centaur tracking network test. - .
Nation: USA. Under arrangements of the AACB (Aeronautics and Astronautics Coordinating Board), NASA will utilize existing NASA tracking stations for initial Centaur development vehicles and switch to the Advent network (which is to be planned, funded, and constructed by DOD) when Centaur is operational, perhaps as early as the fourth of 10 development launchings of Centaur.
1960 November 15 - .
LV Family:
Atlas.
Launch Vehicle:
Atlas D.
- Atlas D/AIG (All Inertial Guidance) scheduled design 95 % complete - .
Nation: USA.
1960 November 15 - .
05:54 GMT - .
Launch Site:
Cape Canaveral.
Launch Complex:
Cape Canaveral LC12.
LV Family:
Atlas.
Launch Vehicle:
Atlas D.
LV Configuration: Atlas D 83D.
- Research and development launch - .
Nation: USA. Agency: USAF. Apogee: 1,800 km (1,100 mi).
1960 November 18 - .
LV Family:
Atlas.
Launch Vehicle:
Atlas D.
- Mercury Spacecraft No. 8 delivered to Cape Canaveral - .
Nation: USA. Program: Mercury. Spacecraft: Mercury. Summary: Spacecraft No. 8 was delivered to Cape Canaveral for the Mercury-Atlas 3 (MA-3) unmanned orbital mission..
1960 November 30 - .
01:12 GMT - .
Launch Site:
Cape Canaveral.
Launch Complex:
Cape Canaveral LC13.
LV Family:
Atlas.
Launch Vehicle:
Atlas E.
LV Configuration: Atlas E 4E.
FAILURE: Failure.
Failed Stage: 1.
- Research and development launch - .
Nation: USA. Agency: USAF. Apogee: 1,000 km (600 mi).
1960 December 15 - .
09:10 GMT - .
Launch Site:
Cape Canaveral.
Launch Complex:
Cape Canaveral LC12.
LV Family:
Atlas.
Launch Vehicle:
Atlas Able.
LV Configuration: Atlas Able 91D / Able-5.
FAILURE: Atlas exploded 70 seconds after liftoff..
Failed Stage: 1.
- Pioneer (P 31) - .
Payload: Pioneer P 31 / Able VB. Mass: 175 kg (385 lb). Nation: USA. Agency: NASA. Program: Pioneer. Class: Moon. Type: Lunar probe. Spacecraft: Pioneer P 3. Decay Date: 1960-12-15 . COSPAR: F601215A. Apogee: 13 km (8 mi). Summary: The final launch in the Pioneer lunar probe program was unsuccessful; the Atlas-Able booster rocket went out of control and exploded at an altitude of 12,200 m off Cape Canaveral..
1960 December 16 - .
20:35 GMT - .
Launch Site:
Vandenberg.
Launch Complex:
Vandenberg 576B3.
LV Family:
Atlas.
Launch Vehicle:
Atlas D.
LV Configuration: Atlas D 99D.
- Research and development launch - .
Nation: USA. Agency: USAF. Apogee: 1,800 km (1,100 mi).
1961 January 23 - .
21:02 GMT - .
Launch Site:
Cape Canaveral.
Launch Complex:
Cape Canaveral LC12.
LV Family:
Atlas.
Launch Vehicle:
Atlas D.
LV Configuration: Atlas D 90D.
- Research and development test - .
Nation: USA. Agency: USAF. Apogee: 1,800 km (1,100 mi). Summary: Final test flight of USAF Atlas D traveled 5,000 miles to target down Atlantic Missile Range, representing 35 successes, 8 partials, and 6 failures in 49 test launchings for D model. 75th Atlas launched at AMR, successful.
1961 January 24 - .
21:55 GMT - .
Launch Site:
Cape Canaveral.
Launch Complex:
Cape Canaveral LC13.
LV Family:
Atlas.
Launch Vehicle:
Atlas E.
LV Configuration: Atlas E 8E.
FAILURE: Failure.
Failed Stage: 1.
- Research and development launch - .
Nation: USA. Agency: USAF. Apogee: 500 km (310 mi).
1961 January 31 - .
20:21 GMT - .
Launch Site:
Vandenberg.
Launch Complex:
Vandenberg SLC3W.
LV Family:
Atlas.
Launch Vehicle:
Atlas Agena A.
LV Configuration: Atlas Agena A 70D / Agena A 2102.
- Samos 2 - .
Payload: Samos E-1 no. 2. Mass: 1,900 kg (4,100 lb). Nation: USA. Agency: USAF. Class: Surveillance. Type: Military surveillance satellite. Spacecraft: Samos. Decay Date: 1973-10-21 . USAF Sat Cat: 70 . COSPAR: 1961-Alpha-1. Apogee: 557 km (346 mi). Perigee: 474 km (294 mi). Inclination: 97.4000 deg. Period: 95.00 min. Summary: First generation photo surveillance; radio relay of images; micrometeoroid impact data. Poor results..
1961 February 6 - .
Launch Site:
Wallops Island.
LV Family:
Atlas.
Launch Vehicle:
Atlas Centaur LV-3C.
- Liquid hydrogen tests. - .
Nation: USA. Summary: NASA Aerobee-Hi successfully reached 96 miles above Wallops Station in test of behavior of liquid hydrogen in zero gravity for Lewis Research Center hydrogen propulsion development..
1961 February 7 - .
LV Family:
Atlas.
Launch Vehicle:
Atlas Centaur LV-3C.
- Centaur development milestones set. - .
Nation: USA. Summary: Meeting of NASA and contractor personnel held at NASA headquarters to review Centaur development program..
1961 February 17 - .
LV Family:
Atlas.
Launch Vehicle:
Atlas D.
- Space Task Group selected severe flight trajectory for Mercury-Atlas 2 - .
Nation: USA. Program: Mercury. Spacecraft: Mercury. Summary: Information was released by NASA Headquarters that Space Task Group engineers directing Project Mercury had selected the flight trajectory for the Mercury-Atlas 2 (MA-2) mission. . Additional Details: here....
1961 February 17-20 - .
LV Family:
Atlas.
Launch Vehicle:
Atlas D.
- Rules for the Mercury MA-2 - .
Nation: USA. Program: Mercury. Spacecraft: Mercury. Summary: Spacecraft, mission, and launch vehicle flight safety rules for the Mercury-Atlas 2 (MA-2) mission were reviewed by Space Task Group personnel..
1961 February 21 - .
14:12 GMT - .
Launch Site:
Cape Canaveral.
Launch Complex:
Cape Canaveral LC14.
LV Family:
Atlas.
Launch Vehicle:
Atlas D.
LV Configuration: Atlas D 67D.
- Mercury MA-2 - .
Nation: USA. Agency: USAF. Program: Mercury. Spacecraft: Mercury. Apogee: 182 km (113 mi). Mercury-Atlas 2 (MA-2) was launched from Cape Canaveral in a test to check maximum heating and its effects during the worst reentry design conditions. The flight closely matched the desired trajectory and attained a maximum altitude of 114.04 statute miles and a range of 1,431.6 statute miles. Inspection of the spacecraft aboard the recovery ship some 55 minutes after launch (actual flight time was 17.56 minutes) indicated that test objectives were met, since the structure and heat protection elements appeared to be in excellent condition. The flight control team obtained satisfactory data; and the complete launch computing and display system, operating for the first time in a flight, performed satisfactorily.
1961 February 24 - .
LV Family:
Atlas.
Launch Vehicle:
Atlas D.
- Mercury spacecraft No. 9 was delivered to Cape Canaveral - .
Nation: USA. Program: Mercury. Spacecraft: Mercury. Summary: Spacecraft No. 9 was delivered to Cape Canaveral for the Mercury-Atlas 5 (MA-5) orbital primate (Enos) mission..
1961 February 24 - .
18:29 GMT - .
Launch Site:
Cape Canaveral.
Launch Complex:
Cape Canaveral LC13.
LV Family:
Atlas.
Launch Vehicle:
Atlas E.
LV Configuration: Atlas E 9E.
- Research and development test - .
Nation: USA. Agency: USAF. Apogee: 1,500 km (900 mi). Summary: First successful Atlas E flight..
1961 March 3 - .
LV Family:
Atlas.
Launch Vehicle:
Atlas D.
- Mercury Atlas launch vehicle No. 100-D rolled out. - .
Nation: USA. Program: Mercury. Summary: Factory roll-out inspection of Atlas launch vehicle No. 100-D was conducted at Convair-Astronautics. This launch vehicle was allocated for the Mercury-Atlas 3 (MA-3) mission..
1961 March 7 - .
Launch Site:
Warren AFB.
LV Family:
Atlas.
Launch Vehicle:
Atlas D.
- Atlas SMS 565 operational. - .
Nation: USA. Summary: Warren-2 AFB SMS 565 operational .
1961 March 14 - .
LV Family:
Atlas.
Launch Vehicle:
Atlas D.
- Mercury Atlas launch vehicle 100-D delivered to Cape Canaveral - .
Nation: USA. Program: Mercury. Summary: Atlas launch vehicle 100-D was delivered to Cape Canaveral for the Mercury-Atlas 3 (MA-3) mission..
1961 March 14 - .
04:17 GMT - .
Launch Site:
Cape Canaveral.
Launch Complex:
Cape Canaveral LC13.
LV Family:
Atlas.
Launch Vehicle:
Atlas E.
LV Configuration: Atlas E 13E.
FAILURE: Failure.
Failed Stage: 1.
- Research and development launch - .
Nation: USA. Agency: USAF. Apogee: 500 km (310 mi).
1961 March 21 - .
LV Family:
Atlas.
Launch Vehicle:
Atlas D.
- The Mercury-Atlas Missile Range Projects Office designated as a staff function - .
Nation: USA. Program: Mercury. Summary: The Mercury-Atlas Missile Range Projects Office, headed by Elmer H. Buller, was designated as a staff function of the Space Task Group Director's office..
1961 March 25 - .
01:49 GMT - .
Launch Site:
Cape Canaveral.
Launch Complex:
Cape Canaveral LC13.
LV Family:
Atlas.
Launch Vehicle:
Atlas E.
LV Configuration: Atlas E 16E.
FAILURE: Failure.
Failed Stage: 1.
- Research and development launch - .
Nation: USA. Agency: USAF. Apogee: 1,000 km (600 mi).
1961 March 30 - .
Launch Site:
Offutt AFB.
LV Family:
Atlas.
Launch Vehicle:
Atlas D.
- Atlas SMS 566 operational. - .
Nation: USA. Summary: Offutt AFB SMS 566 operational.
1961 April 25 - .
16:15 GMT - .
Launch Site:
Cape Canaveral.
Launch Complex:
Cape Canaveral LC14.
LV Family:
Atlas.
Launch Vehicle:
Atlas D.
LV Configuration: Atlas D 100D.
FAILURE: Destroyed by range safety..
Failed Stage: G.
- Mercury MA-3 - .
Payload: Mercury SC8. Nation: USA. Agency: NASA. Program: Mercury. Class: Manned. Type: Manned spacecraft. Spacecraft: Mercury. Decay Date: 1961-04-25 . COSPAR: F610425A. Mercury-Atlas 3 (MA-3) was launched from Cape Canaveral in an attempt to orbit the spacecraft with a 'mechanical astronaut' aboard. After lift-off, the launch vehicle failed to roll to a 70 degree heading and to pitch over into the proper trajectory. The abort-sensing system activated the escape rockets prior to the launch vehicle's destruction by the range safety officer after approximately 40 seconds of flight that had attained an altitude of 16,400 feet. The spacecraft then coasted up to 24,000 feet, deployed its parachutes, and landed in the Atlantic Ocean 2,000 yards north of the launch pad. The spacecraft was recovered and was found to have incurred only superficial damage; it was then shipped to McDonnell for refitting.
1961 May 11 - .
LV Family:
Atlas.
Launch Vehicle:
Atlas D.
- Mercury spacecraft 8A delivered to Cape Canaveral - .
Nation: USA. Program: Mercury. Spacecraft: Mercury. Summary: Mercury spacecraft 8A was delivered to Cape Canaveral for the Mercury-Atlas 4 (MA-4) orbital unmanned (mechanical astronaut) mission..
1961 May 13 - .
02:00 GMT - .
Launch Site:
Cape Canaveral.
Launch Complex:
Cape Canaveral LC11.
LV Family:
Atlas.
Launch Vehicle:
Atlas E.
LV Configuration: Atlas E 12E.
- Research and development launch - .
Nation: USA. Agency: USAF. Apogee: 1,500 km (900 mi).
1961 May 17 - .
LV Family:
Atlas.
Launch Vehicle:
Atlas D.
- Mercury MA-3 investigation board - .
Nation: USA. Program: Mercury. Summary: An Atlas investigation board was convened to study the cause of the Mercury-Atlas 3 (MA-3) mission launch vehicle failure. Several possible areas were considered, and three were isolated as probable causes based on a review of test data..
1961 May 24 - .
21:50 GMT - .
Launch Site:
Vandenberg.
Launch Complex:
Vandenberg 576B2.
LV Family:
Atlas.
Launch Vehicle:
Atlas D.
LV Configuration: Atlas D 95D.
- Research and development launch - .
Nation: USA. Agency: USAF. Apogee: 1,800 km (1,100 mi).
1961 May 26 - .
02:26 GMT - .
Launch Site:
Cape Canaveral.
Launch Complex:
Cape Canaveral LC13.
LV Family:
Atlas.
Launch Vehicle:
Atlas E.
LV Configuration: Atlas E 18E.
- Research and development launch - .
Nation: USA. Agency: USAF. Apogee: 1,500 km (900 mi).
1961 May 29 - .
LV Family:
Atlas.
Launch Vehicle:
Atlas D.
- Centrifuge training for Mercury-Atlas orbital missions. - .
Nation: USA. Program: Mercury. Summary: A 30 day centrifuge training program was conducted at the Aviation Medical Acceleration Laboratory directed entirely toward training the astronauts for the Mercury-Atlas orbital missions..
1961 May 29 - .
LV Family:
Atlas.
Launch Vehicle:
SLV-3 Agena B.
- Ranger booster erected. - .
Nation: USA. Program: Ranger. Class: Moon. Type: Lunar probe. Spacecraft: Ranger 1-2. Summary: Atlas booster 111-D, to be used for Ranger I, was erected on the launch pad at Cape Canaveral..
1961 June 1 - .
LV Family:
Atlas.
Launch Vehicle:
Atlas D.
- Prelaunch mission rules for Mercury-Atlas 4 (MA-4) were published. - .
Nation: USA. Program: Mercury.
1961 June 7 - .
21:37 GMT - .
Launch Site:
Vandenberg.
Launch Complex:
Vandenberg OSTF1.
LV Family:
Atlas.
Launch Vehicle:
Atlas E.
LV Configuration: Atlas E 27E.
FAILURE: Failure.
Failed Stage: 1.
- Research and development Category II test - .
Nation: USA. Agency: USAF. Summary: First E launched at SMS 576 from OSTF-1, unsuccessful.
1961 June 8 - .
LV Family:
Atlas.
Launch Vehicle:
Atlas D.
- Mercury-Atlas 4 (MA-4) recovery requirements were published. - .
Nation: USA. Program: Mercury.
1961 June 23 - .
03:00 GMT - .
Launch Site:
Cape Canaveral.
Launch Complex:
Cape Canaveral LC11.
LV Family:
Atlas.
Launch Vehicle:
Atlas E.
LV Configuration: Atlas E 17E.
FAILURE: Failure.
Failed Stage: 1.
- Research and development launch - .
Nation: USA. Agency: USAF. Apogee: 10 km (6 mi).
1961 June 29-30 - .
LV Family:
Atlas.
Launch Vehicle:
Atlas D.
- Mercury Atlas vehicle 88-D roll-out - .
Nation: USA. Program: Mercury. Summary: Factory roll-out inspection of Atlas launch vehicle 88-D, designated for the Mercury-Atlas 4 (MA-4) mission, was conducted at Convair..
1961 July 7 - .
LV Family:
Atlas.
Launch Vehicle:
Atlas Centaur LV-3C.
- McDonnell studies of the redesigned Mercury spacecraft. - .
Nation: USA. Program: Gemini. Spacecraft: Gemini; Gemini Ejection; Gemini Parachute. Walter F. Burke of McDonnell summarized the company's studies of the redesigned Mercury spacecraft for Space Task Group's senior staff. McDonnell had considered three configurations: (1) the minimum-change capsule, modified only to improve accessibility and handling, with an adapter added to carry such items as extra batteries; (2) a reconfigured capsule with an ejection seat installed and most of the equipment exterior to the pressure vessel on highly accessible pallets; and (3) a two-man capsule, similar to the reconfigured capsule except for the modification required for two rather than one-man operation. The capsule would be brought down on two Mercury-type main parachutes, the ejection seat serving as a redundant system. In evaluating the trajectory of the two-man capsule, McDonnell used Atlas Centaur booster performance data.
1961 July 7 - .
04:51 GMT - .
Launch Site:
Cape Canaveral.
Launch Complex:
Cape Canaveral LC13.
LV Family:
Atlas.
Launch Vehicle:
Atlas E.
LV Configuration: Atlas E 22E.
- Research and development test - .
Nation: USA. Agency: USAF. Apogee: 1,500 km (900 mi). Summary: Successful Atlas E flight, 9054 miles, from AMR to Indian Ocean (with GE Mark 3 nose cone).
1961 July 12 - .
15:11 GMT - .
Launch Site:
Vandenberg.
Launch Complex:
Vandenberg SLC3E.
LV Family:
Atlas.
Launch Vehicle:
Atlas Agena B.
LV Configuration: Atlas Agena B 97D / Agena B 1201.
- Midas 3 - .
Payload: Midas / Agena TV 1201. Mass: 1,600 kg (3,500 lb). Nation: USA. Agency: USAF. Class: Military. Type: Early warning satellite. Spacecraft: Midas. USAF Sat Cat: 163 . COSPAR: 1961-Sigma-1. Apogee: 3,540 km (2,190 mi). Perigee: 3,343 km (2,077 mi). Inclination: 91.2000 deg. Period: 161.40 min. Summary: Missile Defense Alarm System..
1961 July 15 - .
LV Family:
Atlas.
Launch Vehicle:
Atlas D.
- Mercury Atlas launch vehicle 88-D delivered to Cape Canaveral - .
Nation: USA. Program: Mercury. Summary: Atlas launch vehicle 88-D was delivered to Cape Canaveral for the Mercury-Atlas 4 (MA-4) mission..
1961 July 31 - .
21:32 GMT - .
Launch Site:
Cape Canaveral.
Launch Complex:
Cape Canaveral LC11.
LV Family:
Atlas.
Launch Vehicle:
Atlas E.
LV Configuration: Atlas E 21E.
- Research and development launch - .
Nation: USA. Agency: USAF. Apogee: 1,500 km (900 mi).
1961 August 1 - .
LV Family:
Atlas.
Launch Vehicle:
Atlas Centaur LV-3C.
- Centaur operational contracts initiated. - .
Nation: USA. Summary: NASA directed Marshall Space Flight Center to enter contract negotiations with contractors for procurement of five operational Atlas-Centaur vehicles. These launchings were planned to begin in second quarter of 1964..
1961 August 9 - .
LV Family:
Atlas.
Launch Vehicle:
Atlas D.
- Retrofire-from-orbit mission rules for Mercury MA-4 - .
Nation: USA. Program: Mercury. Spacecraft: Mercury; Mercury Retrorockets. Summary: Retrofire-from-orbit mission rules were published for the unmanned Mercury-Atlas 4 (MA-4) orbital flight..
1961 August 9 - .
LV Family:
Atlas.
Launch Vehicle:
Atlas D.
- Key personnel operational assignments for the Mercury MA-4 - .
Nation: USA. Program: Mercury. Summary: Key personnel operational assignments for the Mercury-Atlas 4 (MA-4) unmanned orbital mission were made by the Space Task Group..
1961 August 9 - .
04:31 GMT - .
Launch Site:
Cape Canaveral.
Launch Complex:
Cape Canaveral LC13.
LV Family:
Atlas.
Launch Vehicle:
Atlas F.
LV Configuration: Atlas F 2F.
- Research and development test - .
Nation: USA. Agency: USAF. Apogee: 1,400 km (800 mi). Summary: First F flight, at AMR), successful.
1961 August 23 - .
01:16 GMT - .
Launch Site:
Vandenberg.
Launch Complex:
Vandenberg 576B3.
LV Family:
Atlas.
Launch Vehicle:
Atlas D.
LV Configuration: Atlas D 101D.
- Research and development launch - .
Nation: USA. Agency: USAF. Apogee: 1,800 km (1,100 mi).
1961 August 23 - .
10:04 GMT - .
Launch Site:
Cape Canaveral.
Launch Complex:
Cape Canaveral LC12.
LV Family:
Atlas.
Launch Vehicle:
Atlas Agena B.
LV Configuration: Atlas Agena B 111D (AA1) / Agena B 6001 (AA1).
FAILURE: Agena B second stage failure..
Failed Stage: 2.
- Ranger 1 - .
Payload: NASA P-32 (RA-1). Mass: 306 kg (674 lb). Nation: USA. Agency: NASA. Program: Ranger. Class: Moon. Type: Lunar probe. Spacecraft: Ranger 1-2. Decay Date: 1961-08-30 . USAF Sat Cat: 173 . COSPAR: 1961-Phi-1. Apogee: 446 km (277 mi). Perigee: 179 km (111 mi). Inclination: 32.9000 deg. Period: 90.60 min. Lunar probe; failed to leave Earth orbit. Ranger 1, a test version of the spacecraft which would attempt an unmanned crash landing on the moon, was launched from the Atlantic Missile Range by an Atlas-Agena B booster. The 306 kg spacecraft did not attain the scheduled extremely elongated orbit because of the misfiring of the Agena B rocket. Although the spacecraft systems were tested successfully, only part of the eight project experiments could be carried out. Ranger 1 reentered on August 29 after 111 orbits. Ranger 1's primary mission was to test the performance of those functions and parts that are necessary for carrying out subsequent lunar and planetary missions using essentially the same spacecraft design.
1961 August 24 - .
LV Family:
Atlas.
Launch Vehicle:
Atlas D.
- Mercury-Atlas 4 (MA-4) unmanned orbital flight was postponed. - .
Nation: USA. Program: Mercury.
1961 September 9 - .
01:42 GMT - .
Launch Site:
Cape Canaveral.
Launch Complex:
Cape Canaveral LC13.
LV Family:
Atlas.
Launch Vehicle:
Atlas E.
LV Configuration: Atlas E 26E.
FAILURE: Failure.
Failed Stage: 1.
- Research and development launch - .
Nation: USA. Agency: USAF. Apogee: 1,000 km (600 mi).
1961 September 9 - .
19:28 GMT - .
Launch Site:
Vandenberg.
Launch Complex:
Vandenberg SLC3W.
LV Family:
Atlas.
Launch Vehicle:
Atlas Agena B.
LV Configuration: Atlas Agena B 106D / Agena B 2120.
FAILURE: Exploded on launch pad..
Failed Stage: 1.
- Samos 3 - .
Payload: Samos E-2 no. 1. Mass: 1,890 kg (4,160 lb). Nation: USA. Agency: USAF. Class: Surveillance. Type: Military surveillance satellite. Spacecraft: Samos. Decay Date: 1961-09-09 . COSPAR: F610909A. Summary: First generation photo surveillance; radio relay of images..
1961 September 13 - .
14:04 GMT - .
Launch Site:
Cape Canaveral.
Launch Complex:
Cape Canaveral LC14.
LV Family:
Atlas.
Launch Vehicle:
Atlas D.
LV Configuration: Atlas D 88D.
- Mercury MA-4 - .
Payload: Mercury SC8A. Mass: 1,200 kg (2,600 lb). Nation: USA. Agency: NASA. Program: Mercury. Class: Manned. Type: Manned spacecraft. Spacecraft: Mercury. Decay Date: 1961-09-13 . USAF Sat Cat: 183 . COSPAR: 1961-A-Alpha-1. Apogee: 248 km (154 mi). Perigee: 156 km (96 mi). Inclination: 32.8000 deg. Period: 88.40 min. Mercury-Atlas 4 (MA-4) was launched from Cape Canaveral with special vibration and noise instrumentation and a mechanical crewman simulator aboard in addition to the normal spacecraft equipment. This was the first Mercury spacecraft to attain an earth orbit. The orbital apogee was 123 nautical miles and the perigee was 86 nautical miles. After one orbit, the spacecraft's orbital timing device triggered the retrograde rockets, and the spacecraft splashed in the Atlantic Ocean 161 miles east of Bermuda. Recovery was made by the USS Decatur. During the flight, only three slight deviations were noted - a small leak in the oxygen system; loss of voice contact over Australia; and the failure of an inverter in the environmental control system. Overall, the flight was highly successful: the Atlas booster performed well and demonstrated that it was ready for the manned flight, the spacecraft systems operated well, and the Mercury global tracking network and telemetry operated in an excellent manner and was ready to support manned orbital flight.
1961 September 18 - .
LV Family:
Atlas.
Launch Vehicle:
Atlas D.
- Mission rules for the Mercury-Atlas 5 (MA-5) orbital flight. - .
Nation: USA. Program: Mercury. Summary: Mission rules for the Mercury-Atlas 5 (MA-5) orbital flight were published. Revisions were issued on October 16 and 25, 1961, and November 11, 1961..
1961 September 28 - .
Launch Site:
Fairchild AFB.
LV Family:
Atlas.
Launch Vehicle:
Atlas E.
- Atlas SMS 567 operational. - .
Nation: USA. Summary: Fairchild AFB SMS 567 operational.
1961 September 28 - .
LV Family:
Atlas.
Launch Vehicle:
Atlas Centaur LV-3C.
- Mariner moved to Atlas-Agena due to Centaur delay. - .
Nation: USA. Program: Mariner. Class: Venus. Type: Venus probe. Spacecraft: Mariner 1-2. Summary: NASA announced that instrumented Venus probe to be launched next year would be launched by an Atlas-Agena B rather than a Centaur rocket as originally planned..
1961 October 1 - .
LV Family:
Atlas.
Launch Vehicle:
Atlas D.
- Factory roll-out inspection of Mercury Atlas booster No. 93-D - .
Nation: USA. Program: Mercury. Summary: Factory roll-out inspection of Atlas booster No. 93-D was conducted at Convair. This booster was designated for the Mercury-Atlas 5 (MA-5) mission..
1961 October 2 - .
18:23 GMT - .
Launch Site:
Cape Canaveral.
Launch Complex:
Cape Canaveral LC11.
LV Family:
Atlas.
Launch Vehicle:
Atlas E.
LV Configuration: Atlas E 25E.
- Research and development / Pod 7 test - .
Nation: USA. Agency: USAF. Apogee: 1,500 km (900 mi).
1961 October 5 - .
13:42 GMT - .
Launch Site:
Cape Canaveral.
Launch Complex:
Cape Canaveral LC13.
LV Family:
Atlas.
Launch Vehicle:
Atlas E.
LV Configuration: Atlas E 30E.
- Research and development test - .
Nation: USA. Agency: USAF. Apogee: 1,500 km (900 mi). Summary: USAF Atlas fired 9,000 miles for Atlantic Missile Range into Indian Ocean, carrying dummy nuclear warhead and a data capsule which was recovered..
1961 October 9 - .
LV Family:
Atlas.
Launch Vehicle:
Atlas D.
- Mercury Atlas booster No. 93-D delivered to Cape Canaveral - .
Nation: USA. Program: Mercury. Summary: Atlas booster No. 93-D was delivered to Cape Canaveral for the Mercury-Atlas 5 (MA-5) orbital flight mission..
1961 October 10 - .
Launch Site:
Forbes AFB.
LV Family:
Atlas.
Launch Vehicle:
Atlas E.
- Atlas SMS 548 operational. - .
Nation: USA. Summary: Forbes AFB SMS 548 operational.
1961 October 20 - .
LV Family:
Atlas;
Nova;
Saturn I.
1961 October 21 - .
13:53 GMT - .
Launch Site:
Vandenberg.
Launch Complex:
Vandenberg SLC3E.
LV Family:
Atlas.
Launch Vehicle:
Atlas Agena B.
LV Configuration: Atlas Agena B 105D.
- Midas 4 - .
Payload: Midas / Agena TV 1202. Mass: 1,800 kg (3,900 lb). Nation: USA. Agency: USAF. Class: Military. Type: Early warning satellite. Spacecraft: Midas. USAF Sat Cat: 192 . COSPAR: 1961-A-Delta-1. Apogee: 3,763 km (2,338 mi). Perigee: 3,482 km (2,163 mi). Inclination: 95.9000 deg. Period: 165.90 min. Summary: Missile Defense Alarm System. Deployed subsatellites..
- Westford - .
Payload: Westford. Nation: USA. Agency: USAF. Spacecraft: WestFord Needles. USAF Sat Cat: 194 . COSPAR: 1961-A-Delta-3.
1961 October 27 - .
LV Family:
Atlas;
Titan.
- Program of manned spaceflight for 1963-1965. - .
Nation: USA. Related Persons: Low, George. Spacecraft: Gemini. Space Task Group (STG), assisted by George M. Low, NASA Assistant Director for Space Flight Operations, and Warren J. North of Low's office, prepared a project summary presenting a program of manned spaceflight for 1963-1965. This was the final version of the Project Development Plan, work on which had been initiated August 14. Additional Details: here....
1961 November 10 - .
14:55 GMT - .
Launch Site:
Cape Canaveral.
Launch Complex:
Cape Canaveral LC13.
LV Family:
Atlas.
Launch Vehicle:
Atlas E.
LV Configuration: Atlas E 32E.
FAILURE: Sustainer engine failed 15 seconds after launch..
Failed Stage: 1.
- Research and development test / Pod 13 chemical release - .
Nation: USA. Agency: USAF. Apogee: 10 km (6 mi). Summary: USAF Atlas with capsule containing squirrel monkey destroyed by range safety officer at Atlantic Missile Range when main sustainer engine failed 15 seconds after launch..
1961 November 12 - .
LV Family:
Atlas.
Launch Vehicle:
Atlas D.
- Mercury 5 launch postponed - .
Nation: USA. Program: Mercury. Class: Manned. Type: Manned spacecraft. Spacecraft: Mercury. Summary: Mercury-Atlas 5, scheduled for launch no earlier than November 14, ran into technical difficulties, postponing launch for several days..
1961 November 18 - .
08:12 GMT - .
Launch Site:
Cape Canaveral.
Launch Complex:
Cape Canaveral LC12.
LV Family:
Atlas.
Launch Vehicle:
Atlas Agena B.
LV Configuration: Atlas Agena B 117D (AA2) / Agena B 6002 (AA2).
FAILURE: Agena B Second Stage failed to restart..
Failed Stage: 2.
- Ranger 2 - .
Payload: NASA P-33 (RA-2). Mass: 304 kg (670 lb). Nation: USA. Agency: NASA. Program: Ranger. Class: Moon. Type: Lunar probe. Spacecraft: Ranger 1-2. Decay Date: 1961-11-20 . USAF Sat Cat: 206 . COSPAR: 1961-A-Theta-1. Apogee: 242 km (150 mi). Perigee: 150 km (90 mi). Inclination: 33.3000 deg. Period: 88.30 min. This was a flight test of the Ranger spacecraft system designed for future lunar and interplanetary missions. The spacecraft was launched into a low earth parking orbit, but an inoperative roll gyro prevented Agena restart resulting in Ranger 2 being stranded in low earth orbit. The orbit decayed and the spacecraft reentered Earth's atmosphere on 20 November 1961.
1961 November 19 - .
LV Family:
Atlas.
Launch Vehicle:
Atlas Centaur LV-3C.
- RL-10 flight rating complete. - .
Nation: USA. NASA announced the completion of the preliminary flight rating test of the Nation's first liquid-hydrogen rocket engine. The engine, the RL-10, was designed and developed by Pratt and Whitney, of United Aircraft, for the Marshall Space Flight Center, and 20 captive firings were competed within 5 days under simulated space conditions, consistently producing 15,000 pounds of thrust. RL-10, previously known as XLR-115, was initiated in October 1958 and over 700 firings were conducted in its development.
1961 November 20 - .
Launch Site:
Warren AFB.
LV Family:
Atlas.
Launch Vehicle:
Atlas E.
- Atlas SMS 549 operational. - .
Nation: USA. Summary: Warren-3 AFB SMS 549 operational.
1961 November 22 - .
20:45 GMT - .
Launch Site:
Vandenberg.
Launch Complex:
Vandenberg SLC3W.
LV Family:
Atlas.
Launch Vehicle:
Atlas Agena B.
LV Configuration: Atlas Agena B 108D / Agena B 2202.
FAILURE: Failure..
Failed Stage: U.
- Samos 4 - .
Payload: Samos E-5 no. 1. Mass: 1,860 kg (4,100 lb). Nation: USA. Agency: USAF. Class: Surveillance. Type: Military surveillance satellite. Spacecraft: Samos. Decay Date: 1961-11-22 . COSPAR: F611122A. Apogee: 200 km (120 mi). Summary: First generation photo surveillance; return of camera and film by capsule; SAMOS type satellite..
1961 November 22 - .
21:04 GMT - .
Launch Site:
Cape Canaveral.
Launch Complex:
Cape Canaveral LC11.
LV Family:
Atlas.
Launch Vehicle:
Atlas F.
LV Configuration: Atlas F 4F.
- Research and development / Pod 3, 22 test / ionosphere / aeronomy mission - .
Nation: USA. Agency: USAF. Apogee: 1,400 km (800 mi).
1961 November 29 - .
15:07 GMT - .
Launch Site:
Cape Canaveral.
Launch Complex:
Cape Canaveral LC14.
LV Family:
Atlas.
Launch Vehicle:
Atlas D.
LV Configuration: Atlas D 93D.
- Mercury MA-5 - .
Payload: Mercury SC9. Mass: 1,300 kg (2,800 lb). Nation: USA. Agency: NASA. Program: Mercury. Class: Manned. Type: Manned spacecraft. Spacecraft: Mercury. Decay Date: 1961-11-29 . USAF Sat Cat: 208 . COSPAR: 1961-A-Iota-1. Apogee: 237 km (147 mi). Perigee: 158 km (98 mi). Inclination: 32.6000 deg. Period: 88.30 min. Mercury-Atlas 5 (MA-5), the second and final orbital qualification of the spacecraft prior to manned flight was launched from Cape Canaveral with Enos, a 37.5 pound chimpanzee, aboard. Scheduled for three orbits, the spacecraft was returned to earth after two orbits due to the failure of a roll reaction jet and to the overheating of an inverter in the electrical system. Both of these difficulties could have been corrected had an astronaut been aboard. The spacecraft was recovered 255 miles southeast of Bermuda by the USS Stormes. During the flight, the chimpanzee performed psychomotor duties and upon recovery was found to be in excellent physical condition. The flight was termed highly successful and the Mercury spacecraft well qualified to support manned orbital flight.
1961 November 29 - .
23:01 GMT - .
Launch Site:
Vandenberg.
Launch Complex:
Vandenberg 576B2.
LV Family:
Atlas.
Launch Vehicle:
Atlas D.
LV Configuration: Atlas D 53D.
- Operational missile test - .
Nation: USA. Agency: USAF SAC. Apogee: 1,800 km (1,100 mi).
1961 November 30 - .
LV Family:
Atlas.
Launch Vehicle:
Atlas D.
- Mercury Atlas launch vehicle 109-D delivered to Cape Canaveral - .
Nation: USA. Program: Mercury. Summary: Atlas launch vehicle 109-D was delivered to Cape Canaveral for the Mercury-Atlas 6 (MA-6) first manned orbital mission..
1961 December 1 - .
20:40 GMT - .
Launch Site:
Cape Canaveral.
Launch Complex:
Cape Canaveral LC13.
LV Family:
Atlas.
Launch Vehicle:
Atlas E.
LV Configuration: Atlas E 35E.
- Research and development / Pod 23 test - .
Nation: USA. Agency: USAF. Apogee: 1,600 km (900 mi).
1961 December 7 - .
LV Family:
Atlas;
Titan.
- NASA announced plans to develop a two-man Mercury capsule. - .
Nation: USA. Related Persons: Gilruth. Program: Gemini. Spacecraft: Gemini. In Houston, Director Robert R. Gilruth of Manned Spacecraft Center announced plans to develop a two-man Mercury capsule. Built by McDonnell, it would be similar in shape to the Mercury capsule but slightly larger and from two to three times heavier. Its booster would be a modified Titan II. A major program objective would be orbital rendezvous. The two-man spacecraft would be launched into orbit and would attempt to rendezvous with an Agena stage put into orbit by an Atlas. Total cost of 12 capsules plus boosters and other equipment was estimated at $500 million. The two-man flight program would begin in the 1963-1964 period with several unmanned ballistic flights to test overall booster-spacecraft compatibility and system engineering. Several manned orbital flights would follow. Besides rendezvous flybys of the target vehicle, actual docking missions would be attempted in final flights. The spacecraft would be capable of missions of a week or more to train pilots for future long-duration circumlunar and lunar landing flights. The Mercury astronauts would serve as pilots for the program, but additional crew members might be phased in during the latter portions of the program.
1961 December 7 - .
LV Family:
Atlas;
Titan.
- Recommendations to Secretary of Defense Robert S. McNamara on the division of effort between NASA and DOD in the Mark II program. - .
Nation: USA. Related Persons: McNamara. Spacecraft: Gemini. NASA Associate Administrator Robert C. Seamans, Jr., and John H. Rubel, Department of Defense (DOD) Deputy Director for Defense Research and Engineering, offered recommendations to Secretary of Defense Robert S. McNamara on the division of effort between NASA and DOD in the Mark II program. They stressed NASA's primary responsibility for managing and directing the program, although attaining the program objectives would be facilitated by using DOD (especially Air Force) resources in a contractor relation to NASA. In addition, DOD personnel would aquire useful experience in manned spaceflight design, development, and operations. Space Systems Division of Air Force Systems Command became NASA's contractor for developing, procuring, and launching Titan II and Atlas-Agena vehicles for the Mark II program.
1961 December 7 - .
21:18 GMT - .
Launch Site:
Vandenberg.
Launch Complex:
Vandenberg 576B3.
LV Family:
Atlas.
Launch Vehicle:
Atlas D.
LV Configuration: Atlas D 82D.
- Operational missile test - .
Nation: USA. Agency: USAF SAC. Apogee: 1,800 km (1,100 mi).
1961 December 12 - .
20:16 GMT - .
Launch Site:
Cape Canaveral.
Launch Complex:
Cape Canaveral LC11.
LV Family:
Atlas.
Launch Vehicle:
Atlas F.
LV Configuration: Atlas F 5F.
FAILURE: Failure.
Failed Stage: 1.
- Research and development / Pod 24 test - .
Nation: USA. Agency: USAF. Apogee: 1,000 km (600 mi).
1961 December 20 - .
03:32 GMT - .
Launch Site:
Cape Canaveral.
Launch Complex:
Cape Canaveral LC13.
LV Family:
Atlas.
Launch Vehicle:
Atlas E.
LV Configuration: Atlas E 36E.
- Research and development/Pod Test/Chemical release mission - .
Nation: USA. Agency: USAF. Apogee: 1,800 km (1,100 mi).
1961 December 21 - .
03:35 GMT - .
Launch Site:
Cape Canaveral.
Launch Complex:
Cape Canaveral LC11.
LV Family:
Atlas.
Launch Vehicle:
Atlas F.
LV Configuration: Atlas F 6F.
FAILURE: Failure.
Failed Stage: 1.
- Research and development test / Pod 15, 25 chemical release / ionosphere / meteorite mission - .
Nation: USA. Agency: USAF. Apogee: 500 km (310 mi).
1961 December 22 - .
19:12 GMT - .
Launch Site:
Vandenberg.
Launch Complex:
Vandenberg SLC3E.
LV Family:
Atlas.
Launch Vehicle:
Atlas Agena B.
LV Configuration: Atlas Agena B 114D / Agena B 2203.
- Samos 5 - .
Payload: Samos E-5 no. 2. Mass: 1,860 kg (4,100 lb). Nation: USA. Agency: USAF. Class: Surveillance. Type: Military surveillance satellite. Spacecraft: Samos. Decay Date: 1962-01-09 . USAF Sat Cat: 218 . COSPAR: 1961-A-Lambda-2. Apogee: 310 km (190 mi). Perigee: 187 km (116 mi). Inclination: 89.6000 deg. Period: 89.40 min. First generation photo surveillance; return of camera and film by capsule; SAMOS type satellite. Reached orbit but failed to deorbit and be recovered. In his memoirs Sergei Khrushchev recounts recovery of what he believed to be a recoverable Samos, except the date given is the winter before tests of this configuration actually started. He relates that a second American capsule was recovered in the spring of 1961. It was equipped with a 30 cm lens and 100’s of metres of 10 cm wide film. Also recovered were a pear-shaped module made of fibreglass, and an inertial orientation system powered by electric motors. It may have been a SAMOS prototype. The capsule was found by tractor drivers, who disassembled it and used the film to wrap around the frame of their outhouse to provide some privacy in the treeless area. Unfortunately this ruined the film, preventing the Russians from developing it and discovering the technical capabilities of the system.
1961 December 29 - .
LV Family:
Atlas;
Titan.
- NASA issued the Gemini Operational and Management Plan, which outlined the roles and responsibilities of NASA and Department of Defense in the Gemini (Mercury Mark II) program. - .
Nation: USA. Related Persons: Holmes, Brainard; Schriever. Spacecraft: Gemini. NASA would be responsible for overall program planning, direction, systems engineering, and operation-including Gemini spacecraft development; Gemini/Agena rendezvous and docking equipment development; Titan II/Gemini spacecraft systems integration; launch, flight, and recovery operations; command, tracking, and telemetry during orbital operations; and reciprocal support of Department of Defense space projects and programs within the scope of the Gemini program. Department of Defense would be responsible for: Titan II development and procurement, Atlas procurement, Agena procurement, Atlas-Agena systems integration, launch of Titan II and Atlas-Agena vehicles, range support, and recovery support. A slightly revised version of the plan was signed in approval on March 27 by General Bernard A. Schriever, Commander, Air Force Systems Command, for the Air Force, and D. Brainerd Holmes, Director of Manned Space Flight, for NASA.
1962 January 15-17 - .
LV Family:
Atlas.
Launch Vehicle:
Atlas D.
- Recovery swimmers trained for Mercury MA-6. - .
Nation: USA. Program: Mercury. Summary: Recovery area swimmers were trained at the Pensacola Naval Air Station, Florida, for use in the Mercury-Atlas 6 (MA-6) manned orbital mission. Instruction included films, briefings, auxiliary flotation collar deployment, and jumps from a helicopter..
1962 January 16 - .
LV Family:
Atlas.
Launch Vehicle:
Atlas D.
- Mercury spacecraft 16 delivered to Cape Canaveral - .
Nation: USA. Program: Mercury. Spacecraft: Mercury. Summary: Spacecraft 16 was delivered to Cape Canaveral for the third manned (Schirra) orbital flight, Mercury-Atlas 8 (MA-8)..
1962 January 17 - .
21:02 GMT - .
Launch Site:
Vandenberg.
Launch Complex:
Vandenberg 576B2.
LV Family:
Atlas.
Launch Vehicle:
Atlas D.
LV Configuration: Atlas D 123D.
- Operational missile test - .
Nation: USA. Agency: USAF SAC. Apogee: 1,800 km (1,100 mi).
1962 January 23 - .
21:28 GMT - .
Launch Site:
Vandenberg.
Launch Complex:
Vandenberg 576B3.
LV Family:
Atlas.
Launch Vehicle:
Atlas D.
LV Configuration: Atlas D 132D.
- Operational missile test - .
Nation: USA. Agency: USAF SAC. Apogee: 1,800 km (1,100 mi).
1962 January 26 - .
20:30 GMT - .
Launch Site:
Cape Canaveral.
Launch Complex:
Cape Canaveral LC12.
LV Family:
Atlas.
Launch Vehicle:
Atlas Agena B.
LV Configuration: Atlas Agena B 121D (AA3) / Agena B 6003 (AA3).
FAILURE: Agena B second stage guidance system failure.
Failed Stage: 2.
- Ranger 3 - .
Payload: NASA P-34 (RA-3). Mass: 327 kg (720 lb). Nation: USA. Agency: NASA. Program: Ranger. Class: Moon. Type: Lunar probe. Spacecraft: Ranger 3-4-5. USAF Sat Cat: 221 . COSPAR: 1962-Alpha-1. Lunar impact probe; missed the moon by 36,874 km and went into solar orbit. A malfunction in the booster guidance system resulted in excessive spacecraft speed. Reversed command signals caused the telemetry antenna to lose earth acquisition, and mid-course correction was not possible. Some useful data were obtained from the flight. Of four scientific experiments only one was partially completed: gamma-ray readings of the lunar surface. Attempts to relay television pictures of the moon and to bounce radar signals off the moon at close range were unsuccessful.
1962 January 27 - .
LV Family:
Atlas.
Launch Vehicle:
Atlas D.
- Mercury MA-6 postponed at T-minus 29 minutes - .
Nation: USA. Program: Mercury. Summary: The Mercury-Atlas 6 (MA-6) manned orbital flight was postponed at T-minus 29 minutes due to weather conditions..
1962 January 30 - .
LV Family:
Atlas.
Launch Vehicle:
Atlas D.
- Mercury MA-6 postponed - .
Nation: USA. Program: Mercury. Summary: The Mercury-Atlas 6 (MA-6) mission was postponed because of technical difficulties with the launch vehicle..
1962 February 13 - .
20:55 GMT - .
Launch Site:
Cape Canaveral.
Launch Complex:
Cape Canaveral LC13.
LV Family:
Atlas.
Launch Vehicle:
Atlas E.
LV Configuration: Atlas E 40E.
- Research and development test - .
Nation: USA. Agency: USAF. Apogee: 1,600 km (900 mi). Summary: Last Atlas E R&D flight..
1962 February 14 - .
LV Family:
Atlas.
Launch Vehicle:
Atlas D.
- Mercury MA-6 postponed. - .
Nation: USA. Program: Mercury. Summary: Unfavorable weather conditions caused the Mercury-Atlas 6 (MA-6) manned orbital mission to be postponed..
1962 February 16 - .
23:04 GMT - .
Launch Site:
Vandenberg.
Launch Complex:
Vandenberg 576B2.
LV Family:
Atlas.
Launch Vehicle:
Atlas D.
LV Configuration: Atlas D 137D.
- Operational missile test - .
Nation: USA. Agency: USAF SAC. Apogee: 1,800 km (1,100 mi).
1962 February 18 - .
LV Family:
Atlas.
Launch Vehicle:
Atlas D.
- NASA announced Project Fire - .
Nation: USA. Program: Apollo. Spacecraft: FIRE. NASA announced Project Fire, a high-speed reentry heat research program to obtain data on materials, heating rates, and radio signal attenuation on spacecraft reentering the atmosphere at speeds of about 24,500 miles per hour. Information from the program would support technology for manned and unmanned reentry from lunar missions. Under the management of the Langley Research Center, Project Fire would use Atlas D boosters and the reentry package would be powered by an Antares solid-fuel motor (third stage of the Scout).
1962 February 20 - .
14:47 GMT - .
Launch Site:
Cape Canaveral.
Launch Complex:
Cape Canaveral LC14.
LV Family:
Atlas.
Launch Vehicle:
Atlas D.
LV Configuration: Atlas D 109D.
- Mercury MA-6 - .
Call Sign: Friendship 7. Crew: Glenn. Backup Crew: Carpenter. Payload: Mercury SC13. Mass: 1,355 kg (2,987 lb). Nation: USA. Related Persons: Glenn; Carpenter. Agency: NASA. Program: Mercury. Class: Manned. Type: Manned spacecraft. Flight: Mercury MA-6. Spacecraft: Mercury. Duration: 0.21 days. Decay Date: 1962-02-20 . USAF Sat Cat: 240 . COSPAR: 1962-Gamma-1. Apogee: 265 km (164 mi). Perigee: 159 km (98 mi). Inclination: 32.5000 deg. Period: 88.60 min. First US manned orbital mission. John Glenn finally puts America in orbit. False landing bag deploy light led to reentry being started with retropack left in place on heat shield. It turned out that indicator light was false and a spectacular reentry ensued, with glowing chunks of the retropack whizzing by the window. After four hours and 43 minutes the spacecraft reentered the atmosphere and landed at 2:43 pm EST in the planned recovery area NE of the Island of Puerto Rico. All flight objectives were achieved. Glenn was reported to be in excellent condition. Beause of failure of one of the automatic systems, the astronaut took over manual control of the spacecraft during part of the flight. With this flight, the basic objectives of Project Mercury had been achieved.
1962 February 21 - .
22:30 GMT - .
Launch Site:
Vandenberg.
Launch Complex:
Vandenberg 576B3.
LV Family:
Atlas.
Launch Vehicle:
Atlas D.
LV Configuration: Atlas D 52D.
FAILURE: Failure.
Failed Stage: 1.
- Operational missile test - .
Nation: USA. Agency: USAF SAC. Apogee: 1,800 km (1,100 mi).
1962 February 25 - .
LV Family:
Atlas.
Launch Vehicle:
Atlas D.
- Factory roll-out inspection of Mercury Atlas launch vehicle 107-D. - .
Nation: USA. Program: Mercury. Flight: Mercury MA-7. Summary: Factory roll-out inspection of Atlas launch vehicle 107-D, designated for the Mercury-Atlas 7 (MA-7) manned orbital mission, was conducted at Convair..
1962 March 1 - .
00:14 GMT - .
Launch Site:
Vandenberg.
Launch Complex:
Vandenberg OSTF1.
LV Family:
Atlas.
Launch Vehicle:
Atlas E.
LV Configuration: Atlas E 66E.
- Research and development Category II test - .
Nation: USA. Agency: USAF. Apogee: 1,600 km (900 mi).
1962 March 5 - .
LV Family:
Atlas.
Launch Vehicle:
Atlas Agena D SLV-3.
- Westinghouse Electric Corporation, Baltimore, Maryland, received a $6.8 million subcontract from McDonnell to provide the rendezvous radar and transponder system for the Gemini spacecraft. - .
Nation: USA. Spacecraft: Gemini; Gemini Radar. Purpose of the rendezvous radar, sited in the recovery section of the spacecraft, was to locate and track the target vehicle during rendezvous maneuvers. The transponder, a combined receiver and transmitter designed to transmit signals automatically when triggered by an interrogating signal, was located in the Agena target vehicle.
1962 March 6 - .
LV Family:
Atlas.
Launch Vehicle:
Atlas D.
- Mercury Atlas launch vehicle 107-D delivered to Cape Canaveral - .
Nation: USA. Program: Mercury. Summary: Atlas launch vehicle 107-D was delivered to Cape Canaveral for the Mercury-Atlas 7 (MA-7) mission..
1962 March 7 - .
22:10 GMT - .
Launch Site:
Vandenberg.
Launch Complex:
Vandenberg SLC3E.
LV Family:
Atlas.
Launch Vehicle:
Atlas Agena B.
LV Configuration: Atlas Agena B 112D / Agena B 2204.
- Samos 6 - .
Payload: Samos E-5 no. 3. Mass: 1,860 kg (4,100 lb). Nation: USA. Agency: USAF. Class: Surveillance. Type: Military surveillance satellite. Spacecraft: Samos. Decay Date: 1963-06-07 . USAF Sat Cat: 259 . COSPAR: 1962-Eta-3. Apogee: 686 km (426 mi). Perigee: 236 km (146 mi). Inclination: 90.9000 deg. Period: 93.90 min. Summary: First generation photo surveillance; return of camera and film by capsule; SAMOS type satellite. Failed to return camera and film. Samos film return project cancelled; remaining 4 cameras placed in warehouse and later used on KH-6 Lanyard..
1962 March 15 - .
LV Family:
Atlas.
Launch Vehicle:
Atlas D.
- Carpenter replaces Slayton on Mercury-Atlas 7 (MA-7) - .
Nation: USA. Program: Mercury. Flight: Mercury MA-7. Summary: NASA Headquarters publicly announced that Scott Carpenter would pilot the Mercury-Atlas 7 (MA-7) manned orbital mission replacing Donald Slayton. The latter, formerly scheduled for the flight, was disqualified because of a minor erratic heart rate..
1962 March 24 - .
00:39 GMT - .
Launch Site:
Vandenberg.
Launch Complex:
Vandenberg 576B2.
LV Family:
Atlas.
Launch Vehicle:
Atlas D.
LV Configuration: Atlas D 134D.
- Demonstration and shakedown operations launch - .
Nation: USA. Agency: USAF SAC. Apogee: 1,800 km (1,100 mi). Summary: President John F. Kennedy visited Vandenberg AFB and witnessed the launch of Atlas 134D..
1962 April - .
LV Family:
Atlas.
Launch Vehicle:
Atlas F.
- Atlas F training facility activated. - .
Nation: USA. Summary: VAFB Atlas F training facility turned over to SAC.
1962 April - .
LV Family:
Atlas.
Launch Vehicle:
Atlas D.
- Crash program completed to clear Atlas configuration problems. - .
Nation: USA. Summary: Golden Ram follow-on completed at all Atlas D operational bases.
1962 April 6 - .
LV Family:
Atlas.
Launch Vehicle:
Atlas D.
- Symposium on the results of Mercury MA-6 - .
Nation: USA. Program: Mercury. Summary: NASA sponsored a 1-day symposium in Washington on the results of the Mercury-Atlas 6 (MA-6) three-orbit flight of John Glenn. One of the items of particular interest was Glenn's 'fire-flies,' or luminous particles, and their possible origin..
1962 April 9 - .
15:04 GMT - .
Launch Site:
Vandenberg.
Launch Complex:
Vandenberg SLC3E.
LV Family:
Atlas.
Launch Vehicle:
Atlas Agena B.
LV Configuration: Atlas Agena B 110D.
- Midas 5 - .
Payload: Midas / Agena TV 1203. Mass: 1,860 kg (4,100 lb). Nation: USA. Agency: USAF. Class: Military. Type: Early warning satellite. Spacecraft: Midas. USAF Sat Cat: 271 . COSPAR: 1962-Kappa-1. Apogee: 3,405 km (2,115 mi). Perigee: 2,784 km (1,729 mi). Inclination: 86.7000 deg. Period: 152.90 min. Summary: Missile Defense Alarm System..
- West Ford Drag - .
Payload: West Ford Drag Experiment. Nation: USA. Agency: USAF. Spacecraft: WestFord Needles. Decay Date: 1962-05-04 . USAF Sat Cat: 272 . COSPAR: 1962-Kappa-2.
1962 April 9 - .
20:50 GMT - .
Launch Site:
Cape Canaveral.
Launch Complex:
Cape Canaveral LC11.
LV Family:
Atlas.
Launch Vehicle:
Atlas F.
LV Configuration: Atlas F 11F.
FAILURE: Failure.
Failed Stage: 1.
- Research and development launch - .
Nation: USA. Agency: USAF.
1962 April 12 - .
01:57 GMT - .
Launch Site:
Vandenberg.
Launch Complex:
Vandenberg 576B2.
LV Family:
Atlas.
Launch Vehicle:
Atlas D.
LV Configuration: Atlas D 129D.
- Demonstration and shakedown operations launch - .
Nation: USA. Agency: USAF SAC. Apogee: 1,800 km (1,100 mi).
1962 April 23 - .
20:50 GMT - .
Launch Site:
Cape Canaveral.
Launch Complex:
Cape Canaveral LC12.
LV Family:
Atlas.
Launch Vehicle:
Atlas Agena B.
LV Configuration: Atlas Agena B 133D (AA4) / Agena B 6004 (AA4).
- Ranger 4 - .
Mass: 328 kg (723 lb). Nation: USA. Agency: NASA. Program: Ranger. Class: Moon. Type: Lunar probe. Spacecraft: Ranger 3-4-5. Decay Date: 1962-04-26 . USAF Sat Cat: 280 . COSPAR: 1962-Mu-1. Ranger IV was launched by an Atlas-Agena B booster from the Atlantic Missile Range, attained a parking orbit, and was fired into the proper lunar trajectory by the restart of the Agena B engine. Failure of a timer in the spacecraft payload caused loss of both internal and ground control over the vehicle. The Goldstone Tracking Station maintained contact with the spacecraft until it passed behind the left edge of the moon on April 26. It impacted at a speed of 9,617 km per hour, the first American spacecraft to land on the lunar surface. The Agena B second stage passed to the right of the moon and later went into orbit around the sun. Lunar photography objectives were not achieved.
1962 April 26 - .
18:56 GMT - .
Launch Site:
Vandenberg.
Launch Complex:
Vandenberg SLC3W.
LV Family:
Atlas.
Launch Vehicle:
Atlas Agena B.
LV Configuration: Atlas Agena B 118D / Agena B SPS 2401.
- Samos 7 - .
Payload: Samos E-6 no. 1 / Agena B 2401. Mass: 1,588 kg (3,500 lb). Nation: USA. Agency: USAF. Class: Surveillance. Type: Military surveillance satellite. Spacecraft: Samos. Decay Date: 1962-04-28 . USAF Sat Cat: 286 . COSPAR: 1962-Pi-1. Summary: Second generation photo surveillance; radio relay of images; Satellite and Missile Observation Satellite. Poor results..
- FTV 2401 RV - .
Payload: E-6 RV. Nation: USA. Agency: USAF. Spacecraft: Samos. COSPAR: 1962-Pi-xx.
1962 April 27 - .
23:24 GMT - .
Launch Site:
Vandenberg.
Launch Complex:
Vandenberg 576B2.
LV Family:
Atlas.
Launch Vehicle:
Atlas D.
LV Configuration: Atlas D 140D.
- Demonstration and shakedown operations launch - .
Nation: USA. Agency: USAF SAC. Apogee: 1,800 km (1,100 mi).
1962 April 30 - .
LV Family:
Atlas.
Launch Vehicle:
Atlas D.
- Swimmer training for Mercury MA-7 - .
Nation: USA. Program: Mercury. Summary: Swimmer training was started for the Mercury-Atlas 7 (MA-7) manned orbital mission recovery area. Instruction consisted of films, briefings, exercises in deploying the auxiliary flotation collar, and jumps from a helicopter..
1962 May 1 - .
LV Family:
Atlas.
Launch Vehicle:
Atlas Agena D SLV-3.
- Small working group to discuss the feasibility of making the Gemini telemetry system a full PCM system. - .
Nation: USA. Following a Lockheed briefing on pulse-code-modulation (PCM) instrumentation systems, representatives of Goddard Space Flight Center and Manned Spacecraft Center (MSC) formed a small working group to discuss the feasibility of making the Gemini telemetry system a full PCM system. PCM was a digital telemetry system which could provide more channels of information, faster data rates, improved accuracy, and less weight of equipment per data channel. Goddard had already reviewed several PCM ground station proposals and had concluded that such a system could handle future NASA programs. All who attended the meeting agreed that a full PCM telemetry system, airborne and ground, could be implemented in time to support the Gemini program. Gemini Project Office approved the formation of an MSC-Gemini PCM Instrumentation Working Group to be responsible for the implementation and compatibility of the airborne and ground PCM system for Gemini. On June 27, Walter C. Williams, MSC Associated Director, notified Goddard of NASA's decision 'to utilize a PCM telemetry system for Gemini and Agena real time data.' Ten sites were selected for the installation of PCM equipment; each of these also received dual acquisition equipment, dual digital command system, and pulse coders for distinguishing between the manned Gemini spacecraft and the Agena target when both were in orbit.
1962 May 8 - .
19:49 GMT - .
Launch Site:
Cape Canaveral.
Launch Complex:
Cape Canaveral LC36A.
LV Family:
Atlas.
Launch Vehicle:
Atlas Centaur.
LV Configuration: Atlas Centaur F-1.
FAILURE: Vehicle exploded due to insulation problems on the Atlas..
Failed Stage: 1.
- Research and development test - .
Nation: USA. Agency: NASA. Apogee: 6.00 km (3.70 mi). Summary: First Centaur flight (unsuccessful)..
1962 May 12 - .
LV Family:
Atlas;
Titan.
- Project Gemini cost estimates had tripled from the original estimate of $250 million. - .
Nation: USA. Related Persons: Webb. Program: Gemini. Spacecraft: Gemini; Gemini Paraglide. James E. Webb, NASA's new Administrator, reviewed the Gemini program. Project Gemini cost estimates at this point ($744.3 million) had increased substantially over the original estimate of $250 million. Estimated spacecraft cost had risen from $240.5 to $391.6 million; Titan II cost, from $113.0 to $161.8 million; Atlas-Agena, from $88.0 to $106.3 million; and supporting development (including the paraglider program), from $29.0 to $36.8 million. Estimated operations costs had declined from $59.0 to $47.8 million.
1962 May 12 - .
00:31 GMT - .
Launch Site:
Vandenberg.
Launch Complex:
Vandenberg 576B3.
LV Family:
Atlas.
Launch Vehicle:
Atlas D.
LV Configuration: Atlas D 127D.
- Demonstration and shakedown operations launch - .
Nation: USA. Agency: USAF SAC. Apogee: 1,800 km (1,100 mi).
1962 May 24 - .
12:45 GMT - .
Launch Site:
Cape Canaveral.
Launch Complex:
Cape Canaveral LC14.
LV Family:
Atlas.
Launch Vehicle:
Atlas D.
LV Configuration: Atlas D 107D.
- Mercury MA-7 - .
Call Sign: Aurora 7. Crew: Carpenter. Backup Crew: Schirra. Payload: Mercury SC18. Mass: 1,349 kg (2,974 lb). Nation: USA. Related Persons: Carpenter; Schirra. Agency: NASA. Program: Mercury. Class: Manned. Type: Manned spacecraft. Flight: Mercury MA-7. Spacecraft: Mercury. Duration: 0.21 days. Decay Date: 1962-05-24 . USAF Sat Cat: 295 . COSPAR: 1962-Tau-1. Apogee: 260 km (160 mi). Perigee: 154 km (95 mi). Inclination: 32.5000 deg. Period: 88.50 min. Scott Carpenter in Aurora 7 is enthralled by his environment but uses too much orientation fuel. Yaw error and late retrofire caused the landing impact point to be over 300 km beyond the intended area and beyond radio range of the recovery forces. Landing occurred 4 hours and 56 minutes after liftoff. Astronaut Carpenter was later picked up safely by a helicopter after a long wait in the ocean and fears for his safety. NASA was not impressed and Carpenter left the agency soon thereafter to become an aquanaut.
1962 June 17 - .
18:14 GMT - .
Launch Site:
Vandenberg.
Launch Complex:
Vandenberg SLC3W.
LV Family:
Atlas.
Launch Vehicle:
Atlas Agena B.
LV Configuration: Atlas Agena B 115D / Agena B SPS 2402.
- Samos 8 - .
Payload: Samos E-2 no. 2 / Agena B 2402. Mass: 1,860 kg (4,100 lb). Nation: USA. Agency: USAF. Class: Surveillance. Type: Military surveillance satellite. Spacecraft: Samos. Decay Date: 1962-06-18 . USAF Sat Cat: 307 . COSPAR: 1962-Psi-1. Apogee: 198 km (123 mi). Perigee: 198 km (123 mi). Inclination: 96.2000 deg. Period: 88.40 min. Summary: First generation photo surveillance; radio relay of images; Satellite and Missile Observation Satellite. Poor results..
- FTV 2402 RV - .
Payload: E-6 RV. Nation: USA. Agency: USAF. Spacecraft: Samos. COSPAR: 1962-Psi-xx.
1962 June 26 - .
10:57 GMT - .
Launch Site:
Vandenberg.
Launch Complex:
Vandenberg 576B3.
LV Family:
Atlas.
Launch Vehicle:
Atlas D.
LV Configuration: Atlas D 21D.
- NTMP K-1 Target mission - .
Nation: USA. Agency: USAF SAC. Apogee: 1,800 km (1,100 mi). Summary: First launch of an Atlas from Vandenberg AFB as a target for an Army Nike-Zeus from Kwajalein..
1962 July 12 - .
16:57 GMT - .
Launch Site:
Vandenberg.
Launch Complex:
Vandenberg 576B2.
LV Family:
Atlas.
Launch Vehicle:
Atlas D.
LV Configuration: Atlas D 141D.
- NTMP K-2 Target mission - .
Nation: USA. Agency: USAF SAC. Apogee: 1,800 km (1,100 mi).
1962 July 13 - .
21:11 GMT - .
Launch Site:
Vandenberg.
Launch Complex:
Vandenberg OSTF1.
LV Family:
Atlas.
Launch Vehicle:
Atlas E.
LV Configuration: Atlas E 67E.
FAILURE: Failure.
Failed Stage: 1.
- Research and development Category II test - .
Nation: USA. Agency: USAF. Apogee: 1,800 km (1,100 mi).
1962 July 18 - .
20:51 GMT - .
Launch Site:
Vandenberg.
Launch Complex:
Vandenberg SLC3W.
LV Family:
Atlas.
Launch Vehicle:
Atlas Agena B.
LV Configuration: Atlas Agena B 120D.
- Samos 9 - .
Payload: Samos E-2 no. 3 / Agena B 2403. Mass: 1,860 kg (4,100 lb). Nation: USA. Agency: USAF. Class: Surveillance. Type: Military surveillance satellite. Spacecraft: Samos. Decay Date: 1962-07-25 . USAF Sat Cat: 342 . COSPAR: 1962-A-Zeta-1. Apogee: 234 km (145 mi). Perigee: 184 km (114 mi). Inclination: 96.0000 deg. Period: 88.60 min. Summary: First generation photo surveillance; radio relay of images; Satellite and Missile Observation Satellite. Poor results..
- FTV 2403 RV - .
Payload: E-6 RV. Nation: USA. Agency: USAF. Spacecraft: Samos. Decay Date: 1962-07-27 . USAF Sat Cat: 343 . COSPAR: 1962-A-Zeta-2. Apogee: 215 km (133 mi). Perigee: 163 km (101 mi). Inclination: 96.1000 deg. Period: 88.30 min.
1962 July 19 - .
11:05 GMT - .
Launch Site:
Vandenberg.
Launch Complex:
Vandenberg 576B1.
LV Family:
Atlas.
Launch Vehicle:
Atlas D.
LV Configuration: Atlas D 13D.
- Demonstration and shakedown operations launch - .
Nation: USA. Agency: USAF SAC. Apogee: 1,800 km (1,100 mi).
1962 July 22 - .
09:21 GMT - .
Launch Site:
Cape Canaveral.
Launch Complex:
Cape Canaveral LC12.
LV Family:
Atlas.
Launch Vehicle:
Atlas Agena B.
LV Configuration: Atlas Agena B 145D (AA5) / Agena B 6901 (AA5).
FAILURE: Destroyed by range safety..
Failed Stage: U.
- Mariner 1 - .
Payload: Mariner R-1. Mass: 200 kg (440 lb). Nation: USA. Agency: NASA. Program: Mariner. Class: Venus. Type: Venus probe. Spacecraft: Mariner 1-2. Decay Date: 1962-07-22 . COSPAR: F620722A. Summary: Venus probe..
1962 July 27 - .
LV Family:
Atlas.
Launch Vehicle:
Atlas D.
- Mercury Atlas launch vehicle No. 113-D accepted - .
Nation: USA. Program: Mercury. Summary: Atlas launch vehicle No. 113-D was inspected at Convair and accepted for the Mercury-Atlas 8 (MA-8) manned orbital mission..
1962 August 1 - .
21:07 GMT - .
Launch Site:
Vandenberg.
Launch Complex:
Vandenberg 576E.
LV Family:
Atlas.
Launch Vehicle:
Atlas F.
LV Configuration: Atlas F 15F.
- Research and development test - .
Nation: USA. Agency: USAF. Apogee: 1,400 km (800 mi). Summary: First successful Atlas F flight at operational site, SMS 576E (15F).
1962 August 5 - .
Launch Site:
Vandenberg.
Launch Complex:
Vandenberg SLC3W.
LV Family:
Atlas.
Launch Vehicle:
Atlas Agena B.
LV Configuration: Atlas Agena B 124D / Agena B SPS 2404.
- Samos 10 - .
Payload: Samos E-6 no. 2 / Agena B 2404. Mass: 1,860 kg (4,100 lb). Nation: USA. Agency: USAF. Class: Surveillance. Type: Military surveillance satellite. Spacecraft: Samos. Decay Date: 1962-08-06 . USAF Sat Cat: 361 . COSPAR: 1962-A-Lambda-2. Apogee: 203 km (126 mi). Perigee: 201 km (124 mi). Inclination: 96.2000 deg. Period: 88.50 min. Summary: Second generation photo surveillance; radio relay of images; Satellite and Missile Observation Satellite. Poor results..
- FTV 2404 - .
Payload: AFP-201 PVP 854. Nation: USA. Agency: USAF. Spacecraft: Samos. Decay Date: 1962-08-06 . USAF Sat Cat: 361 . COSPAR: 1962-A-Lambda-1. Apogee: 203 km (126 mi). Perigee: 203 km (126 mi). Inclination: 96.3000 deg. Period: 88.50 min.
- FTV 2404 RV - .
Payload: E-6 RV. Nation: USA. Agency: USAF. Spacecraft: Samos. COSPAR: 1962-A-Lambda-xx.
1962 August 8 - .
LV Family:
Atlas.
Launch Vehicle:
Atlas D.
- Mercury Atlas launch vehicle 113-D delivered to Cape Canaveral - .
Nation: USA. Program: Mercury. Summary: Atlas launch vehicle 113-D was delivered to Cape Canaveral for the Mercury-Atlas 8 (MA-8) manned orbital mission..
1962 August 9 - .
22:51 GMT - .
Launch Site:
Vandenberg.
Launch Complex:
Vandenberg 576B3.
LV Family:
Atlas.
Launch Vehicle:
Atlas D.
LV Configuration: Atlas D 8D.
- Demonstration and shakedown operations launch - .
Nation: USA. Agency: USAF SAC. Apogee: 1,800 km (1,100 mi).
1962 August 9 - .
23:05 GMT - .
Launch Site:
Vandenberg.
Launch Complex:
Vandenberg 576B2.
LV Family:
Atlas.
Launch Vehicle:
Atlas D.
LV Configuration: Atlas D 87D.
- Demonstration and shakedown operations launch - .
Nation: USA. Agency: USAF SAC. Apogee: 1,800 km (1,100 mi).
1962 August 10 - .
21:11 GMT - .
Launch Site:
Vandenberg.
Launch Complex:
Vandenberg OSTF2.
LV Family:
Atlas.
Launch Vehicle:
Atlas F.
LV Configuration: Atlas F 57F.
FAILURE: Failure.
Failed Stage: 1.
- Research and development launch - .
Nation: USA. Agency: USAF. Apogee: 10 km (6 mi).
1962 August 13 - .
22:00 GMT - .
Launch Site:
Cape Canaveral.
Launch Complex:
Cape Canaveral LC11.
LV Family:
Atlas.
Launch Vehicle:
Atlas F.
LV Configuration: Atlas F 7F.
- Research and development / Pod 16 test - .
Nation: USA. Agency: USAF. Apogee: 1,400 km (800 mi).
1962 August 27 - .
06:53 GMT - .
Launch Site:
Cape Canaveral.
Launch Complex:
Cape Canaveral LC12.
LV Family:
Atlas.
Launch Vehicle:
Atlas Agena B.
LV Configuration: Atlas Agena B 179D (AA6) / Agena B 6902 (AA6).
- Mariner 2 - .
Payload: Mariner R-2. Mass: 201 kg (443 lb). Nation: USA. Agency: NASA. Program: Mariner. Class: Venus. Type: Venus probe. Spacecraft: Mariner 1-2. USAF Sat Cat: 374 . COSPAR: 1962-A-Rho-1. Mariner 2 was the first spacecraft to successfully flyby another planet. It was a backup for the Mariner 1 mission which failed shortly after launch to Venus. After launch and termination of the Agena first burn, the Agena-Mariner was in a 118 km altitude Earth parking orbit. The Agena second burn injected the Mariner 2 spacecraft into a geocentric escape hyperbola at 26 minutes 3 seconds after lift-off. Solar panel extension was completed about 44 minutes after launch. On 29 August 1962 cruise science experiments were turned on. A midcourse maneuver was initiated at 22:49:00 GMT on 4 September and completed at 2:45:25 GMT 5 September. On 8 September at 17:50 GMT the spacecraft suddenly lost its attitude control, which was restored by the gyroscopes 3 minutes later. The cause was unknown but may have been a collision with a small object. On October 31 the output from one solar panel deteriorated abruptly, and the science cruise instruments were turned off. A week later the panel resumed normal function and instruments were turned back on. The panel permanently failed on 15 November, but Mariner 2 was close enough to the Sun that one panel could supply adequate power. On December 14 the radiometers were turned on. Mariner 2 approached Venus from 30 degrees above the dark side of the planet, and passed below the planet at its closest distance of 34,773 km at 19:59:28 GMT 14 December 1962. After encounter, cruise mode resumed. Spacecraft perihelion occurred on 27 December at a distance of 105,464,560 km. The last transmission from Mariner 2 was received on 3 January 1963 at 07:00 GMT. Mariner 2 remains in heliocentric orbit. Scientific discoveries made by Mariner 2 included a slow retrograde rotation rate for Venus, hot surface temperatures and high surface pressures, a predominantly carbon dioxide atmosphere, continuous cloud cover with a top altitude of about 60 km, and no detectable magnetic field. It was also shown that in interplanetary space the solar wind streams continuously and the cosmic dust density is much lower than the near-Earth region. Improved estimates of Venus' mass and the value of the astronomical unit were made.
1962 September - .
Launch Site:
Schilling AFB.
LV Family:
Atlas.
Launch Vehicle:
Atlas F.
- Atlas SMS 560 operational. - .
Nation: USA. Summary: Schilling AFB SMS 550 operational.
1962 September 8 - .
LV Family:
Atlas.
Launch Vehicle:
Atlas D.
- Mercury Atlas vehicle 113-D static-fired - .
Nation: USA. Program: Mercury. Summary: Atlas launch vehicle 113-D for the Mercury-Atlas 8 (MA-8) manned orbital mission was static-fired at Cape Canaveral. This test was conducted to check modifications that had been made to the booster for the purpose of smoother engine combustion..
1962 September 15 - .
Launch Site:
Lincoln AFB.
LV Family:
Atlas.
Launch Vehicle:
Atlas F.
- Atlas SMS 551 operational. - .
Nation: USA. Summary: Lincoln AFB SMS 551 operational.
1962 September 19 - .
19:30 GMT - .
Launch Site:
Cape Canaveral.
Launch Complex:
Cape Canaveral LC11.
LV Family:
Atlas.
Launch Vehicle:
Atlas F.
LV Configuration: Atlas F 8F.
- Research and development / Pod 17 test - .
Nation: USA. Agency: USAF. Apogee: 1,400 km (800 mi).
1962 September 25 - .
LV Family:
Atlas.
Launch Vehicle:
Atlas Agena D SLV-3.
- A preliminary design criteria review conference for complex 14, held in Los Angeles, resulted in ground rules for all contractors. - .
Nation: USA. Target dates established were (1) stand availability, July 1, 1963; (2) estimated beneficial occupancy date, November 1, 1963; and (3) vehicle on-stand date, February 1, 1964. Complex 14 would be used for launching the Gemini-Agena target vehicle and Mariner spacecraft, but basic modifications would be primarily for the Gemini program. On November 15, 1962, Air Force Space Systems Division reviewed the criteria summary report for complex 14 modifications and suggested only minor engineering changes.
1962 October 2 - .
11:46 GMT - .
Launch Site:
Vandenberg.
Launch Complex:
Vandenberg 576B2.
LV Family:
Atlas.
Launch Vehicle:
Atlas D.
LV Configuration: Atlas D 4D.
FAILURE: Failure.
Failed Stage: 1.
- NTMP K-3 Target mission - .
Nation: USA. Agency: USAF SAC. Apogee: 500 km (310 mi).
1962 October 3 - .
12:15 GMT - .
Launch Site:
Cape Canaveral.
Launch Complex:
Cape Canaveral LC14.
LV Family:
Atlas.
Launch Vehicle:
Atlas D.
LV Configuration: Atlas D 113D.
- Mercury MA-8 - .
Call Sign: Sigma 7. Crew: Schirra. Backup Crew: Cooper. Payload: Mercury SC16. Mass: 1,374 kg (3,029 lb). Nation: USA. Related Persons: Schirra; Cooper. Agency: NASA. Program: Mercury. Class: Manned. Type: Manned spacecraft. Flight: Mercury MA-8. Spacecraft: Mercury. Duration: 0.38 days. Decay Date: 1962-10-03 . USAF Sat Cat: 433 . COSPAR: 1962-B-Delta-1. Apogee: 285 km (177 mi). Perigee: 153 km (95 mi). Inclination: 32.5000 deg. Period: 88.80 min. The Sigma 7 spacecraft with Astronaut Walter M. Schirra, Jr., as pilot was launched into orbit by a Mercury-Atlas vehicle from Atlantic Missile Range. In the most successful American manned space flight to date, Schirra traveled nearly six orbits, returning to earth at a predetermined point in the Pacific Ocean 9 hours, 13 minutes after liftoff. Within 40 minutes after landing, he and his spacecraft were safely aboard the aircraft carrier U.S.S. Kearsarge. Schirra attempted and achieved a nearly perfect mission by sticking rigorously to mission plan.
1962 October 7 - .
LV Family:
Atlas.
Launch Vehicle:
Atlas D.
- The Mercury-Atlas 8 (MA-8) press conference was held at the Rice University, Houston, Texas. - .
Nation: USA. Related Persons: Schirra. Program: Mercury. Summary: Astronaut Schirra expressed his belief that the spacecraft was ready for the 1-day mission, that he experienced absolutely no difficulties with his better than 9 hours of weightlessness, and that the flight was of the 'textbook' variety..
1962 October 9 - .
LV Family:
Atlas.
Launch Vehicle:
Atlas D.
- Mercury spacecraft 20 delivered to Cape Canaveral - .
Nation: USA. Program: Mercury. Flight: Mercury MA-9. Spacecraft: Mercury. Summary: Spacecraft 20 was delivered to Cape Canaveral for the Mercury-Atlas 9 (MA-9) 1-day mission flight..
1962 October 9 - .
Launch Site:
Altus AFB.
LV Family:
Atlas.
Launch Vehicle:
Atlas F.
- Atlas SMS 577 operational. - .
Nation: USA. Summary: Altus AFB SMS 577 operational.
1962 October 18 - .
16:59 GMT - .
Launch Site:
Cape Canaveral.
Launch Complex:
Cape Canaveral LC12.
LV Family:
Atlas.
Launch Vehicle:
Atlas Agena B.
LV Configuration: Atlas Agena B 215D (AA7) / Agena B 6005 (AA7).
- Ranger 5 - .
Mass: 340 kg (740 lb). Nation: USA. Agency: NASA. Program: Ranger. Class: Moon. Type: Lunar probe. Spacecraft: Ranger 3-4-5. USAF Sat Cat: 439 . COSPAR: 1962-B-Eta-1. The Ranger V lunar probe was launched from Atlantic Missile Range by an Atlas-Agena B launch vehicle. The Agena B stage attained parking orbit and 25 minutes later reignited to send Ranger V toward the moon. A malfunction in the Agena B guidance system resulted in excessive spacecraft velocity. The spacecraft's solar cells did not provide power and reversed command signals caused the telemetry antenna to lose earth acquisition. This made reception of the flight-path correction signal impossible and rendering its television cameras useless. Reversed command signals caused the telemetry antenna to lose earth acquisition, and mid-course correction was not possible. The spacecraft missed the Moon by 725 km and went into solar orbit. Gamma-ray data were collected for 4 hours prior to the loss of power. Ranger V was to have relayed television pictures of the lunar surface and rough-landed an instrumented capsule containing a seismometer. The spacecraft was tracked for 8 hours, 44 minutes, before its small reserve battery went dead. Additional Details: here....
1962 October 19 - .
LV Family:
Atlas.
Launch Vehicle:
Atlas Agena D SLV-3.
- NASA Headquarters' recent decision to cut the MSC budget for fiscal year 1963 from $687 million to $660 million. - .
Nation: USA. Related Persons: Chamberlin. Spacecraft: Gemini; Gemini Paraglide. Wesley L. Hjornevik, Manned Spacecraft Center (MSC) Assistant Director for Administration, described to members of MSC's senior staff the implications of NASA Headquarters' recent decision to cut the MSC budget for fiscal year 1963 from $687 million to $660 million, the entire reduction to be borne by the Gemini program. Hjornevik feared that the Gemini budget, already tight, could absorb so large a cut only by dropping the paraglider, Agena, and all rendezvous equipment from the program. Gemini Project Office (GPO) reported that funding limitations had already forced Martin and McDonnell to reduce their level of activity. The first Gemini flight (unmanned) was rescheduled for December 1963, with the second (manned) to follow three months later, and subsequent flights at two-month intervals, with the first Agena (fifth mission) in August or September 1964. This four-month delay imposed by budget limitations required a large-scale reprogramming of Gemini development work, reflected chiefly in drastic reduction in the scale of planned test programs. Details of the necessary reprogramming had been worked out by December 20, when GPO Manager James A. Chamberlin reported that December 1963 was a realistic date for the first Gemini flight. Gemini funding for fiscal year 1963 totaled $232.8 million.
1962 October 19 - .
18:15 GMT - .
Launch Site:
Cape Canaveral.
Launch Complex:
Cape Canaveral LC11.
LV Family:
Atlas.
Launch Vehicle:
Atlas F.
LV Configuration: Atlas F 14F.
- Research and development launch - .
Nation: USA. Agency: USAF AFSC. Apogee: 1,400 km (800 mi).
1962 October 25 - .
LV Family:
Atlas.
Launch Vehicle:
Atlas Agena D SLV-3.
- Manned Spacecraft Center informed Lockheed that Gemini program budget readjustments required reprogramming the Gemini-Agena program. - .
Nation: USA. Subsequent meetings on November 2 and November 20 worked out the changes necessary to implement the Agena program at minimum cost. The overall test program for the Agena and its propulsion systems was significantly reduced, but in general neither the scope nor the requirements of the Agena program were altered. The major result of the reprogramming was a four-month slip in the scheduled launch date of the first Agena (to September 1964); this delay was about a month and a half less than had been anticipated when reprogramming began. In addition, Lockheed was to continue its program at a reduced level through the rest of 1962, a period of about six weeks, and to resume its normal level of activity on January 1, 1963.
1962 October 26 - .
10:59 GMT - .
Launch Site:
Vandenberg.
Launch Complex:
Vandenberg 576A1.
LV Family:
Atlas.
Launch Vehicle:
Atlas D.
LV Configuration: Atlas D 159D.
- NTMP K-5 / Pod 20 Target - .
Nation: USA. Agency: USAF AFSC. Apogee: 1,800 km (1,100 mi).
1962 November 7 - .
19:43 GMT - .
Launch Site:
Cape Canaveral.
Launch Complex:
Cape Canaveral LC11.
LV Family:
Atlas.
Launch Vehicle:
Atlas F.
LV Configuration: Atlas F 16F.
- Research and development launch - .
Nation: USA. Agency: USAF AFSC. Apogee: 1,400 km (800 mi).
1962 November 11 - .
20:17 GMT - .
Launch Site:
Vandenberg.
Launch Complex:
Vandenberg SLC3W.
LV Family:
Atlas.
Launch Vehicle:
Atlas Agena B.
LV Configuration: Atlas Agena B 128D / Agena B SPS 2405.
- Samos 11 - .
Payload: Samos E-6 no. 3 / TRS 1 / Agena B 2405. Mass: 1,860 kg (4,100 lb). Nation: USA. Agency: USAF. Class: Surveillance. Type: Military surveillance satellite. Spacecraft: Samos. Decay Date: 1962-11-12 . USAF Sat Cat: 455 . COSPAR: 1962-B-Pi-1. Apogee: 292 km (181 mi). Perigee: 128 km (79 mi). Inclination: 96.0000 deg. Period: 88.70 min. Summary: Second generation photo surveillance; radio relay of images; Satellite and Missile Observation Satellite. Poor results. SAMOS project cancelled..
- TRS 1 - .
Payload: ERS 1. Nation: USA. Agency: USAF AFSC. Class: Earth. Type: Magnetosphere satellite. Spacecraft: ERS. COSPAR: 1962-B-Pi-xx.
- FTV 2405 RV - .
Payload: E-6 RV. Nation: USA. Agency: USAF AFSC. Spacecraft: Samos. COSPAR: 1962-B-Pi-xx.
1962 November 13 - .
LV Family:
Atlas.
Launch Vehicle:
Atlas D.
- Cooper named for Mercury MA-9 1-day orbital mission - .
Nation: USA. Related Persons: Cooper; Shepard. Program: Mercury. Flight: Mercury MA-9. Summary: Gordon Cooper was named as the pilot for Mercury-Atlas 9 (MA-9) 1-day orbital mission slated for April 1963. Alan Shepard, pilot of Mercury-Redstone 3 (MR-3) was designated as backup pilot..
1962 November 14 - .
22:36 GMT - .
Launch Site:
Vandenberg.
Launch Complex:
Vandenberg OSTF2.
LV Family:
Atlas.
Launch Vehicle:
Atlas F.
LV Configuration: Atlas F 13F.
FAILURE: Failure.
Failed Stage: 1.
- Research and development launch - .
Nation: USA. Agency: USAF AFSC. Apogee: 300 km (180 mi).
1962 November 15 - .
Launch Site:
Dyess AFB.
LV Family:
Atlas.
Launch Vehicle:
Atlas F.
- Atlas SMS 578 operational. - .
Nation: USA. Summary: Dyess AFB SMS 578 operational.
1962 November 16 - .
LV Family:
Atlas.
Launch Vehicle:
Atlas D.
- Mercury spacecraft 15A delivered to Cape Canaveral - .
Nation: USA. Program: Mercury. Flight: Mercury MA-10. Spacecraft: Mercury. Summary: Mercury spacecraft 15A was delivered to Cape Canaveral for the Mercury-Atlas 10 (MA-10) orbital manned 1-day mission..
1962 November 16 - .
LV Family:
Atlas.
Launch Vehicle:
Atlas Agena D SLV-3.
- "T-back" pod proposed as the Gemini rendezvous target instead of the Agena. - .
Nation: USA. Andre J. Meyer, Jr., of Gemini Project Office reported that Space Technology Laboratories was conducting a study for NASA Headquarters on a 'T-back' pod to be used in the spacecraft adapter as the rendezvous target instead of the Agena. The pod would be stabilized but would have no translation capabilities. Although it would be almost as expensive as the Agena, it would avoid separate launch problems.
1962 November 28 - .
LV Family:
Atlas.
Launch Vehicle:
Atlas D.
- Mercury Simulator 2 modified to the 1-day configuration. - .
Nation: USA. Program: Mercury. Flight: Mercury MA-9. Spacecraft: Mercury. Summary: Mercury Simulator 2 was modified to the 1-day Mercury orbital configuration in preparation for the Mercury-Atlas 9 (MA-9) flight..
1962 November 28 - .
LV Family:
Atlas.
Launch Vehicle:
Atlas D.
- Retrofire initiated 2 seconds late during Mercury MA-8 - .
Nation: USA. Program: Mercury. Retrofire was reported to have initiated 2 seconds late during the Mercury-Atlas 8 (MA-8) mission. Because of this, the mechanics and tolerances of the Mercury orbital timing device were reviewed for the benefit of operational personnel, and the procedural sequence for Mercury retrofire initiation was outlined.
1962 November 30 - .
Launch Site:
Walker AFB.
LV Family:
Atlas.
Launch Vehicle:
Atlas F.
- Atlas SMS 579 operational. - .
Nation: USA. Summary: Walker AFB SMS 579 operational.
By the end of 1962 - .
LV Family:
Atlas.
Launch Vehicle:
Atlas D.
LV Configuration: Atlas D Mercury s/n 77D.
- Mercury MA-9A (cancelled) - .
Call Sign: Faith 7. Crew: Cooper. Backup Crew: Shepard. Payload: Mercury SC19. Nation: USA. Related Persons: Kennedy; Cooper; Shepard. Program: Mercury. Flight: Mercury MA-9A. Spacecraft: Mercury. NASA’s Mercury orbital operations plan of July 19, 1961 had four spacecraft equipped for three-orbit flights. However by Schirra’s flight the seven-astronaut corps was down to four. So even thought the flight-ready SC19 had been delivered to Cape Canaveral on March 20, 1962, the decision was taken to cancel the remaining short-duration mission and move directly to an 18 orbit mission.
1962 December 5 - .
21:25 GMT - .
Launch Site:
Cape Canaveral.
Launch Complex:
Cape Canaveral LC11.
LV Family:
Atlas.
Launch Vehicle:
Atlas F.
LV Configuration: Atlas F 21F.
- Research and development test - .
Nation: USA. Agency: USAF AFSC. Apogee: 1,400 km (800 mi). Summary: Last Atlas F R&D flight..
1962 December 12 - .
11:38 GMT - .
Launch Site:
Vandenberg.
Launch Complex:
Vandenberg 576A3.
LV Family:
Atlas.
Launch Vehicle:
Atlas D.
LV Configuration: Atlas D 161D.
- NTMP K-6 Target mission - .
Nation: USA. Agency: USAF AFSC. Apogee: 1,800 km (1,100 mi).
1962 December 17 - .
20:36 GMT - .
Launch Site:
Vandenberg.
Launch Complex:
Vandenberg SLC3E.
LV Family:
Atlas.
Launch Vehicle:
Atlas Agena B.
LV Configuration: Atlas Agena B 131D / Agena B 1205.
FAILURE: Failure.
Failed Stage: U.
- Midas 6 - .
Payload: Midas / Agena TV 1205. Mass: 2,000 kg (4,400 lb). Nation: USA. Agency: USAF. Class: Military. Type: Early warning satellite. Spacecraft: Midas. Decay Date: 1962-12-17 . COSPAR: F621217A. Summary: Missile Defense Alarm System. Carried ERS-3, ERS-4 subsatellites..
- TRS 3 - .
Payload: ERS 3. Nation: USA. Agency: USAF AFSC. Spacecraft: Midas. COSPAR: F621217B.
- TRS 4 - .
Payload: ERS 4. Nation: USA. Agency: USAF AFSC. Spacecraft: Midas. COSPAR: F621217C.
1962 December 18 - .
17:26 GMT - .
Launch Site:
Vandenberg.
Launch Complex:
Vandenberg OSTF1.
LV Family:
Atlas.
Launch Vehicle:
Atlas E.
LV Configuration: Atlas E 64E.
FAILURE: Failure.
Failed Stage: 1.
- NTMP K-4 ABM test - .
Nation: USA. Agency: USAF AFSC. Apogee: 10 km (6 mi).
1962 December 20 - .
Launch Site:
Plattsburgh AFB.
LV Family:
Atlas.
Launch Vehicle:
Atlas F.
- Atlas SMS 556 - last Atlas squadron - operational. - .
Nation: USA. Summary: Plattsburgh AFB SMS 556 (last Atlas squadron) operational.
1962 December 22 - .
09:29 GMT - .
Launch Site:
Vandenberg.
Launch Complex:
Vandenberg 576A1.
LV Family:
Atlas.
Launch Vehicle:
Atlas D.
LV Configuration: Atlas D 160D.
- NTMP K-7 / Pod 4 ABM sensor test / plume characterization mission - .
Nation: USA. Agency: USAF SAC. Apogee: 2,259 km (1,403 mi).
1963 January 3 - .
LV Family:
Atlas.
Launch Vehicle:
Atlas D.
- Mercury MA-9 flight to go 22 orbits. - .
Nation: USA. Program: Mercury. Summary: Tentative plans were made by NASA to extend the Mercury-Atlas 9 (MA-9) flight from 18 to 22 orbits..
1963 January 9 - .
LV Family:
Atlas.
Launch Vehicle:
Atlas Agena D SLV-3.
- Flight Operations Division outlined detailed requirements for the remote stations of the worldwide tracking network. - .
Nation: USA. Summary: Each station would need five consoles: Gemini system, Agena system, command, aeromedical, and maintenance and operations. The Gemini and Agena consoles would have 42 analog display meters and 40 on/off indicators..
1963 January 14 - .
LV Family:
Atlas.
Launch Vehicle:
Atlas Agena D SLV-3.
- MSC assumed complete responsibility for the Gemini target vehicle program. - .
Nation: USA. Manned Spacecraft Center (MSC) assumed complete responsibility for the Gemini target vehicle program from Marshall Space Flight Center following a meeting between MSC and Marshall on January 11 establishing procedures for the transfer. Marshall was to continue to participate actively in an advisory capacity until March 1 and thereafter as technical consultant to MSC upon request. All other NASA Atlas-Agena programs were transferred to Lewis Research Center in a move aimed at freeing Marshall to concentrate on Saturn launch vehicle development and consolidating Atlas launch vehicle technology at Lewis. NASA Headquarters had decided to effect the transfer on October 12, 1962.
1963 January 21 - .
LV Family:
Atlas;
Titan.
- James E Webb, Administrator of NASA, and Robert S McNamara, Secretary of Defense, concluded a major policy agreement defining the roles of NASA and Department of Defense (DOD) in Project Gemini. - .
Nation: USA. The agreement provided for the establishment of a joint NASA-DOD Gemini Program Planning Board. The board would plan experiments, conduct flight tests, and analyze and disseminate results. NASA would continue to manage Project Gemini, while DOD would take part in Gemini development, pilot training, preflight checkout, launch, and flight operations, and would be specifically responsible for the Titan II launch vehicle and the Atlas-Agena target vehicle. DOD would also contribute funds toward the attainment of Gemini objectives.
1963 January 25 - .
10:44 GMT - .
Launch Site:
Vandenberg.
Launch Complex:
Vandenberg 576B2.
LV Family:
Atlas.
Launch Vehicle:
Atlas D.
LV Configuration: Atlas D 39D.
FAILURE: Failure.
Failed Stage: 1.
- NTMP K-9/OT ABM test - .
Nation: USA. Agency: USAF SAC. Apogee: 100 km (60 mi).
1963 January 31 - .
08:51 GMT - .
Launch Site:
Vandenberg.
Launch Complex:
Vandenberg 576A3.
LV Family:
Atlas.
Launch Vehicle:
Atlas D.
LV Configuration: Atlas D 176D.
- NTMP K-12 ABM test - .
Nation: USA. Agency: USAF SAC. Apogee: 1,800 km (1,100 mi).
1963 February 5-6 - .
LV Family:
Atlas.
Launch Vehicle:
Atlas Agena D SLV-3.
- Gemini Rendezvous and Reentry Panel meeting. - .
Nation: USA. Summary: At a Gemini Rendezvous and Reentry Panel meeting, it was reported that attempts to obtain information on flight controller procedures to command the Agena in orbit had been delayed by the Air Force Agena security program. .
1963 February 12 - .
LV Family:
Atlas.
Launch Vehicle:
Atlas D.
- The Manned Spacecraft Center announced a mid-May flight for Mercury-Atlas 9 (MA-9). - .
Nation: USA. Program: Mercury. Flight: Mercury MA-9. Summary: Originally scheduled for April, the launch date was delayed by a decision to rewire the Mercury-Atlas flight control system, as a result of the launch vehicle checkout at the plant inspection meeting..
1963 February 12 - .
LV Family:
Atlas.
Launch Vehicle:
Atlas D.
- Objectives of the Mercury-Atlas 9 (MA-9) manned 1-day mission were published. - .
Nation: USA. Program: Mercury. Flight: Mercury MA-9. Summary: This was the ninth flight of a production Mercury spacecraft to be boosted by an Atlas launch vehicle and the sixth manned United States space flight. . Additional Details: here....
1963 February 13 - .
11:55 GMT - .
Launch Site:
Vandenberg.
Launch Complex:
Vandenberg 576A1.
LV Family:
Atlas.
Launch Vehicle:
Atlas D.
LV Configuration: Atlas D 182D.
- NTMP K-8 / NC20.133 ABM test - .
Nation: USA. Agency: USAF SAC. Apogee: 1,800 km (1,100 mi).
1963 February 15 - .
LV Family:
Atlas.
Launch Vehicle:
Atlas Agena D SLV-3.
- Agena target vehicle checkout plans were presented at a meeting of the Gemini Management Panel. - .
Nation: USA. Spacecraft: Gemini; Gemini Radar. Upon receipt at Cape Canaveral, the target vehicle would be inspected and certified. After this action, mechanical mate and interface checks with the target docking adapter would be accomplished. Agena-Gemini spacecraft compatibilty tests would then be conducted, and the Agena would undergo validation and weight checks. Subsequently, a joint checkout of the spacecraft and Agena would be conducted with tests on the Merritt Island radar tower.
1963 February 28 - .
09:02 GMT - .
Launch Site:
Vandenberg.
Launch Complex:
Vandenberg 576A3.
LV Family:
Atlas.
Launch Vehicle:
Atlas D.
LV Configuration: Atlas D 188D.
- NTMP K-10 ABM test - .
Nation: USA. Agency: USAF SAC. Apogee: 1,800 km (1,100 mi).
1963 March 1 - .
21:00 GMT - .
Launch Site:
Cape Canaveral.
Launch Complex:
Cape Canaveral LC11.
LV Family:
Atlas.
Launch Vehicle:
Atlas F.
LV Configuration: Atlas F 134F.
- ABRES REX-I / Pod 1 Re-entry vehicle test - .
Nation: USA. Agency: USAF AFSC. Apogee: 1,800 km (1,100 mi).
1963 March 5 - .
LV Family:
Atlas.
Launch Vehicle:
Atlas Agena D SLV-3.
- Gemini Project Office discussed with contractors the establishment of a philosophy for the final phase of the rendezvous mission. - .
Nation: USA. Spacecraft: Gemini; Gemini Radar. They agreed on the following general rules: (1) when the launch was on time, the terminal maneuver would be initiated when the Agena came within range of the spacecraft's sensors, which would occur between spacecraft insertion and first apogee; (2) automatic and optical terminal guidance techniques would always back each other up, one method being selected as an objective for each mission and the other serving as a standby; (3) during early rendezvous missions, the terminal phase would be initiated by the third spacecraft apogee or delayed until the twelfth because of range radar tracking limitations; (4) for the same reason, no midcourse corrections should be made during orbits 4 through 11; (5) in case of extreme plane or phase errors, the Agena would be maneuvered to bring it within the spacecraft's maneuver capability; and (6) after such gross Agena maneuvers, the Agena orbit would be recircularized and two orbits of spacecraft catchup would precede the initiation of terminal rendezvous plan.
1963 March 10 - .
02:42 GMT - .
Launch Site:
Vandenberg.
Launch Complex:
Vandenberg 576B3.
LV Family:
Atlas.
Launch Vehicle:
Atlas D.
LV Configuration: Atlas D 102D.
FAILURE: Failure.
Failed Stage: 1.
- Operational missile test - .
Nation: USA. Agency: USAF SAC. Apogee: 0 km ( mi).
1963 March 12 - .
05:21 GMT - .
Launch Site:
Vandenberg.
Launch Complex:
Vandenberg 576B2.
LV Family:
Atlas.
Launch Vehicle:
Atlas D.
LV Configuration: Atlas D 64D.
- Operational missile test - .
Nation: USA. Agency: USAF SAC. Apogee: 1,800 km (1,100 mi).
1963 March 15 - .
11:38 GMT - .
Launch Site:
Vandenberg.
Launch Complex:
Vandenberg 576B1.
LV Family:
Atlas.
Launch Vehicle:
Atlas D.
LV Configuration: Atlas D 46D.
FAILURE: Failure.
Failed Stage: 1.
- TALL TREE 1 operational test launch - .
Nation: USA. Agency: USAF SAC. Apogee: 300 km (180 mi).
1963 March 16 - .
02:05 GMT - .
Launch Site:
Vandenberg.
Launch Complex:
Vandenberg 576D.
LV Family:
Atlas.
Launch Vehicle:
Atlas F.
LV Configuration: Atlas F 63F.
- OT TALL TREE 5 operational test launch - .
Nation: USA. Agency: USAF SAC. Apogee: 1,400 km (800 mi).
1963 March 16 - .
08:32 GMT - .
Launch Site:
Vandenberg.
Launch Complex:
Vandenberg 576A1.
LV Family:
Atlas.
Launch Vehicle:
Atlas D.
LV Configuration: Atlas D 193D.
FAILURE: Failure.
Failed Stage: 1.
- NTMP K-14/NC20.145 Target/Aeronomy mission - .
Nation: USA. Agency: USAF SAC. Apogee: 300 km (180 mi).
1963 March 21 - .
21:10 GMT - .
Launch Site:
Vandenberg.
Launch Complex:
Vandenberg OSTF2.
LV Family:
Atlas.
Launch Vehicle:
Atlas F.
LV Configuration: Atlas F 83F.
- Research and development launch - .
Nation: USA. Agency: USAF AFSC. Apogee: 1,400 km (800 mi).
1963 March 24 - .
00:29 GMT - .
Launch Site:
Vandenberg.
Launch Complex:
Vandenberg 576E.
LV Family:
Atlas.
Launch Vehicle:
Atlas F.
LV Configuration: Atlas F 52F.
FAILURE: Failure.
Failed Stage: 1.
- OT TALL TREE 4 operational test launch - .
Nation: USA. Agency: USAF SAC. Apogee: 10 km (6 mi).
1963 April - .
LV Family:
Atlas.
Launch Vehicle:
Atlas Agena D SLV-3.
- Bell Aerosystems successfully completed initial firing of the Gemini Agena Model 8247 engine at its Buffalo plant early in the month. - .
Nation: USA. The Model 8247 engine for the Gemini Agena's primary propulsion system was developed from the Model 8096 currently being flown in satellite and probe programs for NASA and the Air Force. Unlike the operational engine, the new engine was capable of being restarted several times in orbit, a Gemini program requirement. The principle change in the new engine was the substitution of liquid propellants for solid pyrotechnic 'starter cans' to start the gas generator. The unit tested was the development engine that had been assembled in March. In mid-April, the test engine was shipped to Arnold Engineering Development Center (AEDC), Tullahoma, Tennessee, for further development tests. At AEDC, test cell arrangements were completed April 12, with testing scheduled to begin in May.
1963 April 22 - .
LV Family:
Atlas.
Launch Vehicle:
Atlas Agena D SLV-3.
- Representatives of Air Force Space Systems Division (SSD), Manned Spacecraft Center, and Lockheed met in Sunnyvale for the first management review of the Gemini Agena target vehicle (GATV). - .
Nation: USA. Patterned after similar meetings regularly held between SSD, Lewis Research Center, and Lockheed on medium space vehicle satellite and probe programs, the Gemini Target Management Review Meetings encompassed a comprehensive monthly review of the status of the GATV program.
1963 April 22 - .
LV Family:
Atlas.
Launch Vehicle:
Atlas D.
- Mercury Spacecraft 20 mated to Atlas launch vehicle - .
Nation: USA. Program: Mercury. Flight: Mercury MA-9. Spacecraft: Mercury. Summary: Spacecraft 20 was moved from Hanger S at Cape Canaveral to Complex 14 and mated to Atlas launch vehicle 130-D in preparation for the Mercury-Atlas 9 (MA-9) mission. The first simulated flight test was begun immediately..
1963 April 24 - .
20:59 GMT - .
Launch Site:
Vandenberg.
Launch Complex:
Vandenberg OSTF1.
LV Family:
Atlas.
Launch Vehicle:
Atlas E.
LV Configuration: Atlas E 65E.
- Research and development test - .
Nation: USA. Agency: USAF AFSC. Apogee: 1,600 km (900 mi). Summary: First successful E missile from OSTF-1, SMS 576.
1963 April 27 - .
02:03 GMT - .
Launch Site:
Cape Canaveral.
Launch Complex:
Cape Canaveral LC11.
LV Family:
Atlas.
Launch Vehicle:
Atlas F.
LV Configuration: Atlas F 135F.
- ABRES REX-II re-entry vehicle test flight - .
Nation: USA. Agency: USAF AFSC. Apogee: 1,400 km (800 mi).
1963 April 29 - .
LV Family:
Atlas.
Launch Vehicle:
Atlas Agena D SLV-3.
- NASA Headquarters approved rescheduling of the Gemini flight program as proposed by Gemini Project Office (GPO). - .
Nation: USA. Spacecraft: Gemini; Gemini Parachute; Gemini Paraglide. Late delivery of the spacecraft systems coupled with the unexpectedly small number of Mercury systems incorporated in the Gemini spacecraft had forced GPO to review the flight program critically. In the revised program, the first flight was still set for December 1963 and was still to be unmanned, but it was now to be orbital rather than suborbital to flight-qualify launch vehicle subsystems and demonstrate the compatibility of the launch vehicle and spacecraft; no separation or recovery was planned. The second mission, originally a manned orbital flight, now became an unmanned suborbital ballistic flight schedule for July 1964. Its primary objection was to test spacecraft reentry under maximum heating-rate reentry conditions; it would also qualify the launch vehicle and all spacecraft systems required for manned orbital flight. The third flight, formerly planned as a manned orbital rendezvous mission, became the first manned flight, a short-duration (probably three-orbit) systems evaluation flight scheduled for October 1964. Subsequent flights were to follow at three-month intervals, ending in January 1967. Rendezvous terminal maneuvers were planned for missions 3 (if flight duration permitted) and 4, a seven-day mission using a rendezvous pod. The sixth flight was to be a 14-day long-duration mission identical to 4 except that no rendezvous maneuver missions with the Atlas-launched Agena D target vehicle. Water landing by parachute was planned for the first six flights and land landing by paraglider from flight 7 on.
1963 April 30 - .
LV Family:
Atlas.
Launch Vehicle:
Atlas D.
- Improvements to the Mercury pressure suit for Mercury MA-9 - .
Nation: USA. Program: Mercury. Flight: Mercury MA-9. Spacecraft: Mercury Space Suit. Summary: A number of improvements had been made to the Mercury pressure suit for the Mercury-Atlas 9 (MA-9) flight. . Additional Details: here....
1963 May 2 - .
LV Family:
Atlas;
Titan.
- Charles W Mathews, new Acting Manager of Project Gemini, reviewed the current status of the spacecraft, launch vehicles, and ground facilities for the Gemini Management Panel. - .
Nation: USA. Modifications of launch complexes 19 and 14, of the tracking network, and of Atlantic Missile Range checkout facilities were all on schedule, although no margin remained for complex 19 work. The Atlas and Agena presented no problems, but the Gemini launch vehicle schedule was tight; technical problems, notably stage I longitudinal oscillations and stage II engine instability, were compounded by funding difficulties. The Gemini spacecraft, suffering from late deliveries by subcontractors, was being reprogrammed.
1963 May 9 - .
20:06 GMT - .
Launch Site:
Vandenberg.
Launch Complex:
Vandenberg SLC3E.
LV Family:
Atlas.
Launch Vehicle:
Atlas Agena B.
LV Configuration: Atlas Agena B 119D / Agena B S01 1206.
- Midas 7 - .
Payload: Midas / Agena TV 1206. Mass: 2,000 kg (4,400 lb). Nation: USA. Agency: USAF. Class: Military. Type: Early warning satellite. Spacecraft: Midas. USAF Sat Cat: 574 . COSPAR: 1963-014A. Apogee: 3,680 km (2,280 mi). Perigee: 3,609 km (2,242 mi). Inclination: 87.3000 deg. Period: 166.40 min. Summary: MIDAS 7 was the first operational MIDAS mission and the first equipped with the W-37 sensor. During its six weeks of operation, MIDAS 7 recorded nine US ICBM launches, including the first missile launch ever detected from space..
- TRS 3 - .
Payload: ERS 6. Mass: 1.00 kg (2.20 lb). Nation: USA. Agency: USAF. Class: Technology. Type: Navigation technology satellite. Spacecraft: TRS. USAF Sat Cat: 608 . COSPAR: 1963-014C. Apogee: 3,691 km (2,293 mi). Perigee: 3,591 km (2,231 mi). Inclination: 87.3000 deg. Period: 166.40 min. Summary: Solar cells damage data. Space craft engaged in investigation of spaceflight techniques and technology (US Cat A). .
- Dash 1 - .
Nation: USA. Agency: USAF. Class: Technology. Type: Military technology satellite. Spacecraft: Dash. USAF Sat Cat: 589 . COSPAR: 1963-014D. Apogee: 3,724 km (2,313 mi). Perigee: 3,558 km (2,210 mi). Inclination: 87.3000 deg. Period: 166.30 min.
- TRS 2 - .
Payload: ERS 5. Mass: 1.00 kg (2.20 lb). Nation: USA. Agency: USAF. Class: Technology. Type: Navigation technology satellite. Spacecraft: TRS. Decay Date: 1973-07-31 . USAF Sat Cat: 579 . COSPAR: 1963-014B. Apogee: 4,902 km (3,045 mi). Perigee: 2,269 km (1,409 mi). Inclination: 87.2000 deg. Period: 165.00 min. Summary: Solar cells damage data. Space craft engaged in investigation of spaceflight techniques and technology (US Cat A). .
1963 May 15 - .
13:04 GMT - .
Launch Site:
Cape Canaveral.
Launch Complex:
Cape Canaveral LC14.
LV Family:
Atlas.
Launch Vehicle:
Atlas D.
LV Configuration: Atlas D 130D.
- Mercury MA-9 - .
Call Sign: Faith 7. Crew: Cooper. Backup Crew: Shepard. Payload: Mercury SC20. Mass: 1,376 kg (3,033 lb). Nation: USA. Related Persons: Cooper; Shepard. Agency: NASA Houston. Program: Mercury. Class: Manned. Type: Manned spacecraft. Flight: Mercury MA-9. Spacecraft: Mercury. Duration: 1.43 days. Decay Date: 1963-05-16 . USAF Sat Cat: 576 . COSPAR: 1963-015A. Apogee: 265 km (164 mi). Perigee: 163 km (101 mi). Inclination: 32.5000 deg. Period: 88.70 min. Summary: Final Mercury mission, Faith 7, was piloted by Astronaut L. Gordon Cooper, Jr..
1963 June 1 - .
LV Family:
Atlas.
Launch Vehicle:
Atlas F.
- Atlas F propellant loading accident. - .
Nation: USA. Summary: Exploded during propellant loading (Walker AFB 1).
1963 June 2 - .
00:26 GMT - .
Launch Site:
Walker AFB.
Launch Complex:
Walker AFB Missile Site 579.
Launch Pad: 579-1.
LV Family:
Atlas.
Launch Vehicle:
Atlas F.
LV Configuration: Atlas F 77F.
- Error mission - .
Nation: USA. Agency: USAF. Apogee: 0 km ( mi).
1963 June 4 - .
20:12 GMT - .
Launch Site:
Vandenberg.
Launch Complex:
Vandenberg OSTF1.
LV Family:
Atlas.
Launch Vehicle:
Atlas E.
LV Configuration: Atlas E 62E.
- Research and development launch - .
Nation: USA. Agency: USAF AFSC. Apogee: 1,600 km (900 mi).
1963 June 8 - .
LV Family:
Atlas.
Launch Vehicle:
Atlas D.
- Mercury MA-10 environmental control system changes - .
Nation: USA. Program: Mercury. Flight: Mercury MA-10. Spacecraft: Mercury; Mercury ECS. In preparation for the Mercury-Atlas 10 (MA-10) mission, should the flight be approved by NASA Headquarters, several environmental control system changes were made in spacecraft 15B. Particularly involved were improvements in the hardware and flexibility of the urine and condensate systems. With regard to the condensate portion, Gordon Cooper, in his press conference, indicated that the system was not easy to operate during the flight of Faith 7 (MA-9).
1963 June 12 - .
Launch Site:
Vandenberg.
Launch Complex:
Vandenberg SLC3E.
LV Family:
Atlas.
Launch Vehicle:
Atlas Agena B.
LV Configuration: Atlas Agena B 139D / Agena B SPS 1204.
FAILURE: Failure.
Failed Stage: U.
- Midas 8 - .
Payload: Midas / Agena TV 1204. Mass: 2,000 kg (4,400 lb). Nation: USA. Agency: USAF. Class: Military. Type: Early warning satellite. Spacecraft: Midas. Decay Date: 1963-06-12 . COSPAR: F630613A. Summary: Missile Defense Alarm System. Carried ERS-7, ERS-8 subsatellites..
- TRS 7 - .
Payload: ERS 7. Nation: USA. Agency: USAF AFSC. Spacecraft: Midas. COSPAR: F630613B.
- TRS 8 - .
Payload: ERS 8. Nation: USA. Agency: USAF AFSC. Spacecraft: Midas. COSPAR: F630613C.
1963 June 12 - .
09:03 GMT - .
Launch Site:
Vandenberg.
Launch Complex:
Vandenberg 576A3.
LV Family:
Atlas.
Launch Vehicle:
Atlas D.
LV Configuration: Atlas D 198D.
- NTMP - .
Nation: USA. Agency: USAF SAC. Apogee: 1,800 km (1,100 mi).
1963 June 19 - .
LV Family:
Atlas.
Launch Vehicle:
Atlas Agena D SLV-3.
- The Cape Gemini/Agena Test Integration Working Group met to define "Plan X" test procedures and responsibilities. - .
Nation: USA. Spacecraft: Gemini; Gemini Radar. The purpose of Plan X was to verify the Gemini spacecraft's ability to command the Agena target vehicle both by radio and hardline; to exercise all command, data, and communication links between the spacecraft, target vehicle, and mission control in all practical combinations, first with the two vehicles about six feet apart, then with the vehicles docked and latched but not rigidized; and to familiarize the astronauts with operating the spacecraft/target vehicle combination in a simulated rendezvous mission. Site of the test was to be the Merritt Island Launch Area Radar Range Boresight Tower ('Timber Tower'), a 65 x 25 x 50-foot wooden structure.
1963 July 3 - .
21:13 GMT - .
Launch Site:
Vandenberg.
Launch Complex:
Vandenberg 576C.
LV Family:
Atlas.
Launch Vehicle:
Atlas E.
LV Configuration: Atlas E 69E.
- Demonstration and shakedown operations launch - .
Nation: USA. Agency: USAF SAC. Apogee: 1,600 km (900 mi).
1963 July 12 - .
20:45 GMT - .
Launch Site:
Vandenberg.
Launch Complex:
Vandenberg SLC4W.
LV Family:
Atlas.
Launch Vehicle:
Atlas Agena D.
LV Configuration: Atlas Agena D 201D / Agena D S01A 4702.
- KH 7-01 (Gambit) - .
Payload: KH-7 no. 1. Mass: 2,000 kg (4,400 lb). Nation: USA. Agency: NRO; USAF. Class: Surveillance. Type: Military surveillance satellite. Spacecraft: KH-7. Decay Date: 1963-07-17 . USAF Sat Cat: 618 . COSPAR: 1963-028A. Apogee: 212 km (131 mi). Perigee: 173 km (107 mi). Inclination: 95.3000 deg. Period: 88.30 min. Summary: KH-7 type satellite. Space craft engaged in investigation of spaceflight techniques and technology (US Cat A). .
1963 July 15 - .
LV Family:
Atlas.
Launch Vehicle:
Atlas Agena D SLV-3.
- Development tests of the Agena 8247 engine ended in an emergency shutdown. - .
Nation: USA. Development tests of the Agena Model 8247 main engine at Arnold Engineering Development Center ended when the latch-type gas generator valve failed in testing, making an emergency shutdown of the engine necessary. The wrong choice of emergency shutdown procedures caused turbine overspeed and total failure of the engine's turbine pump assembly. As a result of this failure, the valve was redesigned. Because success of the new design was doubtful, a parallel program was initiated to design and develop an alternative valve configuration, solenoid-operated rather than latch-type. Intensive development testing followed; and in a meeting at Bell Aerosystems on November 15, the solenoid type was selected for use in the first flight system of the Agena target vehicle. The new valve allowed significant reductions in engine complexity and increased reliability, but the development effort imposed a serious delay in Preliminary Flight Rating Tests, which had been scheduled to begin in September 1963.
1963 July 19 - .
03:51 GMT - .
Launch Site:
Vandenberg.
Launch Complex:
Vandenberg SLC3E.
LV Family:
Atlas.
Launch Vehicle:
Atlas Agena B.
LV Configuration: Atlas Agena B 75D / Agena B S01 1207.
- Midas 9 - .
Payload: Midas / Agena TV 1207. Mass: 2,000 kg (4,400 lb). Nation: USA. Agency: USAF. Class: Military. Type: Early warning satellite. Spacecraft: Midas. USAF Sat Cat: 622 . COSPAR: 1963-030A. Apogee: 3,726 km (2,315 mi). Perigee: 3,676 km (2,284 mi). Inclination: 88.4000 deg. Period: 167.90 min. Summary: Missile Defense Alarm System. Did not eject ERS 10 subsatellite..
- TRS 10 - .
Payload: ERS 10. Nation: USA. Agency: USAF AFSC. Class: Earth. Type: Magnetosphere satellite. Spacecraft: ERS. COSPAR: 1963-030xx.
- Dash 2 - .
Nation: USA. Agency: USAF. Class: Technology. Type: Military technology satellite. Spacecraft: Dash. Decay Date: 1971-04-12 . USAF Sat Cat: 624 . COSPAR: 1963-030D. Apogee: 3,839 km (2,385 mi). Perigee: 3,573 km (2,220 mi). Inclination: 88.5000 deg. Period: 168.00 min. Summary: Space craft engaged in investigation of spaceflight techniques and technology (US Cat A). .
- TRS 4 - .
Payload: ERS 9. Mass: 2.00 kg (4.40 lb). Nation: USA. Agency: USAF. Class: Technology. Type: Navigation technology satellite. Spacecraft: TRS. USAF Sat Cat: 635 . COSPAR: 1963-030B. Apogee: 3,736 km (2,321 mi). Perigee: 3,661 km (2,274 mi). Inclination: 88.4000 deg. Period: 167.80 min. Summary: Radiation damage data. Space craft engaged in investigation of spaceflight techniques and technology (US Cat A). .
1963 July 26 - .
19:19 GMT - .
Launch Site:
Vandenberg.
Launch Complex:
Vandenberg OSTF1.
LV Family:
Atlas.
Launch Vehicle:
Atlas E.
LV Configuration: Atlas E 24E.
FAILURE: Failure.
Failed Stage: 1.
- Demonstration and shakedown operations launch - .
Nation: USA. Agency: USAF SAC. Apogee: 300 km (180 mi).
1963 July 30 - .
18:36 GMT - .
Launch Site:
Vandenberg.
Launch Complex:
Vandenberg 576C.
LV Family:
Atlas.
Launch Vehicle:
Atlas E.
LV Configuration: Atlas E 70E.
- Demonstration and shakedown operations launch - .
Nation: USA. Agency: USAF SAC. Apogee: 1,600 km (900 mi).
1963 July 31 - .
20:52 GMT - .
Launch Site:
Vandenberg.
Launch Complex:
Vandenberg 576B1.
LV Family:
Atlas.
Launch Vehicle:
Atlas D.
LV Configuration: Atlas D 143D.
- ST COOL WATER I test - .
Nation: USA. Agency: USAF SAC. Apogee: 1,000 km (600 mi).
1963 August 24 - .
09:50 GMT - .
Launch Site:
Vandenberg.
Launch Complex:
Vandenberg OSTF1.
LV Family:
Atlas.
Launch Vehicle:
Atlas E.
LV Configuration: Atlas E 72E.
- NTMP/OT DASO test - .
Nation: USA. Agency: USAF SAC. Apogee: 1,600 km (900 mi).
1963 August 28 - .
23:10 GMT - .
Launch Site:
Vandenberg.
Launch Complex:
Vandenberg 576B3.
LV Family:
Atlas.
Launch Vehicle:
Atlas D.
LV Configuration: Atlas D 142D.
- ST COOL WATER II test - .
Nation: USA. Agency: USAF SAC. Apogee: 1,800 km (1,100 mi).
1963 September 5 - .
LV Family:
Atlas.
Launch Vehicle:
Atlas Agena D SLV-3.
- Lockheed's contract for the Gemini Agena target vehicle (GATV) was amended. - .
Nation: USA. As a result of the seven-and-one-half-month relaxation of the required launch date for the first GATV, Lockheed was directed to use the improved version of the standard Agena, the AD-62 block of vehicles, instead of AD-13. The AD-62 block originally included the multistart engine, subsequently slipped to the AD-71 block. Lockheed accordingly was directed in January 1964 to substitute the AD-71 for AD-62. The combined effect of these changes was to use up much of the seven-and-one-half-month leeway. The change to AD-62 caused a two-month slip, and changing to AD-71 added a five-week slip. With much of the contingency time gone, the Agena schedule was now tight, and further slippage threatened to cause launch delays.
1963 September 6 - .
19:30 GMT - .
Launch Site:
Vandenberg.
Launch Complex:
Vandenberg SLC4W.
LV Family:
Atlas.
Launch Vehicle:
Atlas Agena D.
LV Configuration: Atlas Agena D 212D / Agena D S01A 4701.
- KH 7-02 - .
Payload: KH-7 no. 2. Mass: 2,000 kg (4,400 lb). Nation: USA. Agency: NRO; USAF. Class: Surveillance. Type: Military surveillance satellite. Spacecraft: KH-7. Decay Date: 1963-09-13 . USAF Sat Cat: 641 . COSPAR: 1963-036A. Apogee: 243 km (150 mi). Perigee: 171 km (106 mi). Inclination: 94.4000 deg. Period: 88.70 min. Summary: KH-7 type satellite. Space craft engaged in investigation of spaceflight techniques and technology (US Cat A). .
1963 September 6 - .
21:59 GMT - .
Launch Site:
Vandenberg.
Launch Complex:
Vandenberg 576B2.
LV Family:
Atlas.
Launch Vehicle:
Atlas D.
LV Configuration: Atlas D 63D.
FAILURE: Failure.
Failed Stage: 1.
- ST COOL WATER III test - .
Nation: USA. Agency: USAF SAC. Apogee: 200 km (120 mi).
1963 September 11 - .
21:00 GMT - .
Launch Site:
Vandenberg.
Launch Complex:
Vandenberg 576B1.
LV Family:
Atlas.
Launch Vehicle:
Atlas D.
LV Configuration: Atlas D 84D.
FAILURE: Failure.
Failed Stage: 1.
- ST COOL WATER IV test - .
Nation: USA. Agency: USAF SAC. Apogee: 1,700 km (1,000 mi).
1963 September 25 - .
11:04 GMT - .
Launch Site:
Vandenberg.
Launch Complex:
Vandenberg 576C.
LV Family:
Atlas.
Launch Vehicle:
Atlas E.
LV Configuration: Atlas E 71E.
FAILURE: Failure.
Failed Stage: 1.
- Demonstration and shakedown operations launch - .
Nation: USA. Agency: USAF SAC. Apogee: 100 km (60 mi).
1963 September 27 - .
LV Family:
Atlas.
Launch Vehicle:
Atlas Agena D SLV-3.
- Electro-Mechanical Research successfully tested the compatibility of airborne and ground station PCM (pulse code modulated) telemetry equipment. - .
Nation: USA. Summary: The tests demonstrated that Gemini spacecraft and Agena telemeter and recorder formats were compatible with NASA ground stations..
1963 October - .
LV Family:
Atlas.
Launch Vehicle:
Atlas D.
LV Configuration: Atlas D Mercury s/n 144D.
- Mercury MA-10 (cancelled) - .
Call Sign: Freedom 7 II. Crew: Shepard. Backup Crew: Cooper. Payload: Mercury SC15B. Nation: USA. Related Persons: Shepard; Cooper. Program: Mercury. Flight: Mercury MA-10. Spacecraft: Mercury. Alan Shepard, and others pushed for a six day Mercury 10 endurance mission. This would give America the manned space endurance record for the first time and also cover the biological objectives of the first two Gemini missions. The Mercury 15B capsule had already been modified for long-duration flight and Shepard had the name 'Freedom 7 II' painted on the side. But the risk and work pending on Gemini persuaded NASA managers not to undertake another mission.
1963 October 4 - .
05:17 GMT - .
Launch Site:
Vandenberg.
Launch Complex:
Vandenberg OSTF2.
LV Family:
Atlas.
Launch Vehicle:
Atlas F.
LV Configuration: Atlas F 45F.
FAILURE: Failure.
Failed Stage: 1.
- Research and development launch - .
Nation: USA. Agency: USAF AFSC.
1963 October 7 - .
21:31 GMT - .
Launch Site:
Vandenberg.
Launch Complex:
Vandenberg 576B3.
LV Family:
Atlas.
Launch Vehicle:
Atlas D.
LV Configuration: Atlas D 163D.
FAILURE: Failure.
Failed Stage: 1.
- ST COOL WATER V test - .
Nation: USA. Agency: USAF SAC. Apogee: 10 km (6 mi).
By the end of 1963 - .
LV Family:
Atlas.
Launch Vehicle:
Atlas D.
LV Configuration: Atlas D Mercury s/n 152D.
- Mercury MA-11 (cancelled) - .
Crew: Grissom. Backup Crew: Schirra. Payload: Mercury SC12B. Nation: USA. Related Persons: Grissom; Schirra. Program: Mercury. Flight: Mercury MA-11. Spacecraft: Mercury. From October 25, 1961 until April 1962 NASA’s Mercury program plan included four one-day flights in 1963. By October 1962 the decision had been quietly taken to limit the long-duration flights to only MA-9 and MA-10. MA-10 was fnally cancelled in turn after the successful MA-9 mission.
1963 October 17 - .
02:37 GMT - .
Launch Site:
Cape Canaveral.
Launch Complex:
Cape Canaveral LC13.
LV Family:
Atlas.
Launch Vehicle:
Atlas Agena D.
LV Configuration: Atlas Agena D 197D / Agena D 1801.
- Vela 2 - .
Payload: Vela 1B. Mass: 220 kg (480 lb). Nation: USA. Agency: USAF. Class: Surveillance. Type: Nuclear detection surveillance satellite. Spacecraft: Vela. USAF Sat Cat: 674 . COSPAR: 1963-039A. Apogee: 116,582 km (72,440 mi). Perigee: 101,081 km (62,808 mi). Inclination: 38.7000 deg. Period: 6,486.20 min. Summary: Space craft engaged in investigation of spaceflight techniques and technology (US Cat A)..
- Vela 1 - .
Payload: Vela 1A. Mass: 220 kg (480 lb). Nation: USA. Agency: USAF. Class: Surveillance. Type: Nuclear detection surveillance satellite. Spacecraft: Vela. USAF Sat Cat: 692 . COSPAR: 1963-039C. Apogee: 116,528 km (72,407 mi). Perigee: 101,925 km (63,333 mi). Inclination: 37.8000 deg. Period: 6,519.60 min. Summary: Space craft engaged in investigation of spaceflight techniques and technology (US Cat A)..
- TRS 5 - .
Payload: ERS 12. Mass: 2.00 kg (4.40 lb). Nation: USA. Agency: USAF. Class: Technology. Type: Navigation technology satellite. Spacecraft: TRS. Decay Date: 1963-06-30 . USAF Sat Cat: 675 . COSPAR: 1963-039B. Apogee: 102,372 km (63,610 mi). Perigee: 953 km (592 mi). Inclination: 35.9000 deg. Period: 2,319.40 min. Summary: Decay date suspect Space craft engaged in investigation of spaceflight techniques and technology (US Cat A)..
1963 October 25 - .
Launch Site:
Vandenberg.
Launch Complex:
Vandenberg SLC4W.
LV Family:
Atlas.
Launch Vehicle:
Atlas Agena D.
LV Configuration: Atlas Agena D 224D / Agena D S01A 4703.
- Agena D - .
Nation: USA. Agency: USAF. Spacecraft: KH-7. Decay Date: 1963-10-31 . USAF Sat Cat: 678 . COSPAR: 1963-041B. Apogee: 276 km (171 mi). Perigee: 116 km (72 mi). Inclination: 99.0000 deg. Period: 88.41 min. Summary: Space craft engaged in investigation of spaceflight techniques and technology (US Cat A). .
- KH 7-03 - .
Payload: KH-7 no. 3. Mass: 2,000 kg (4,400 lb). Nation: USA. Agency: NRO; USAF. Class: Surveillance. Type: Military surveillance satellite. Spacecraft: KH-7. Decay Date: 1963-10-29 . USAF Sat Cat: 677 . COSPAR: 1963-041A. Apogee: 312 km (193 mi). Perigee: 123 km (76 mi). Inclination: 99.0000 deg. Period: 88.80 min. Summary: KH-7 type satellite. Space craft engaged in investigation of spaceflight techniques and technology (US Cat A). .
1963 October 28 - .
03:15 GMT - .
Launch Site:
Cape Canaveral.
Launch Complex:
Cape Canaveral LC11.
LV Family:
Atlas.
Launch Vehicle:
Atlas F.
LV Configuration: Atlas F 136F.
FAILURE: Failure.
Failed Stage: 1.
- ABRES WAC-1 / Pod 21 Reentry test / plume mission - .
Nation: USA. Agency: USAF AFSC. Apogee: 500 km (310 mi).
1963 November - .
LV Family:
Atlas.
Launch Vehicle:
Atlas Agena D SLV-3.
- Lockheed included a milestone schedule for the Gemini Agena target vehicle (GATV) in its monthly progress report for the first time since January 1963. - .
Nation: USA. The new schedule reflected the revised Gemini flight program of April 29 and the corresponding revision of the Agena program which followed. It displayed key events in the progress of the first GATV taking place between five and six months later than the January schedule. Engineering development was now scheduled to be completed by May 15, 1964, rather than by December 11, 1963. Completion of modification and final assembly was now planned for June 12 rather than January 10, 1964; preliminary vehicle systems testing was rescheduled from April 10 to September 11, 1964. Special tests, including a Radio frequency Interference Test in the later schedule in addition to the hot-firing scheduled earlier, were to end November 20 instead of May 22, 1964. Final Vehicle Systems Tests were to be completed December 18 instead of June 19, 1964, with shipment to follow on January 6, 1965, rather than June 30, 1964. Launch was now expected on April 15, 1965, seven and one-half months later than the September 1, 1964, date that had been planned in January 1963.
1963 November 4 - .
09:34 GMT - .
Launch Site:
Vandenberg.
Launch Complex:
Vandenberg 576A1.
LV Family:
Atlas.
Launch Vehicle:
Atlas D.
LV Configuration: Atlas D 232D.
- ABRES REX-III re-entry vehicle test flight - .
Nation: USA. Agency: USAF SAC. Apogee: 1,800 km (1,100 mi).
1963 November 13 - .
22:35 GMT - .
Launch Site:
Vandenberg.
Launch Complex:
Vandenberg 576B2.
LV Family:
Atlas.
Launch Vehicle:
Atlas D.
LV Configuration: Atlas D 158D.
FAILURE: Failure.
Failed Stage: 1.
- ST COOL WATER VI test - .
Nation: USA. Agency: USAF SAC. Apogee: 100 km (60 mi).
By the end of 1963 - .
LV Family:
Atlas.
Launch Vehicle:
Atlas D.
LV Configuration: Atlas D Mercury s/n 167D.
- Mercury MA-12 (cancelled) - .
Crew: Schirra. Payload: Mercury SC17. Nation: USA. Related Persons: Schirra. Program: Mercury. Flight: Mercury MA-12. Spacecraft: Mercury. From October 25, 1961 until April 1962 NASA’s Mercury program plan included four one-day flights in 1963. By October 1962 the decision had been quietly taken to limit the long-duration flights to only MA-9 and MA-10. MA-10 was fnally cancelled in turn after the successful MA-9 mission.
1963 November 17 - .
LV Family:
Atlas.
Launch Vehicle:
Atlas Agena D SLV-3.
- Douglas Aircraft Corporation, Tulsa, Oklahoma, began a series of tests to demonstrate the structural integrity of the Gemini target docking adapter (TDA) during shroud separation. - .
Nation: USA. The shroud, which protected the TDA during the launch and ascent of the Agena target vehicle, was tested under simulated altitude conditions to show proper operation of pyrotechnic devices and adequate clearance between shroud and TDA during separation. Successfully concluded on November 21, and tests demonstrated the compatibility of the TDA with the shroud system during operational performance, with no indication of damage or failure of the TDA structure.
1963 November 27 - .
19:03 GMT - .
Launch Site:
Cape Canaveral.
Launch Complex:
Cape Canaveral LC36A.
LV Family:
Atlas.
Launch Vehicle:
Atlas Centaur.
LV Configuration: Atlas Centaur AC-2 / Centaur D 126D.
- Atlas Centaur 2 - .
Payload: Centaur 2B. Mass: 4,620 kg (10,180 lb). Nation: USA. Agency: NASA Cleveland. Class: Moon. Type: Lunar probe. Spacecraft: Surveyor. USAF Sat Cat: 694 . COSPAR: 1963-047A. Apogee: 1,478 km (918 mi). Perigee: 469 km (291 mi). Inclination: 30.4000 deg. Period: 104.60 min. Summary: Launch vehicle test. Launch vehicle put dummy payload into geosynchronous transfer orbit. First successful Centaur (liquid hydrogen-fueled) flight..
1963 December 18 - .
09:52 GMT - .
Launch Site:
Vandenberg.
Launch Complex:
Vandenberg 576A1.
LV Family:
Atlas.
Launch Vehicle:
Atlas D.
LV Configuration: Atlas D 233D.
- ABRES LORV-8 re-entry vehicle test flight - .
Nation: USA. Agency: USAF SAC. Apogee: 1,800 km (1,100 mi).
1963 December 18 - .
21:45 GMT - .
Launch Site:
Vandenberg.
Launch Complex:
Vandenberg SLC4W.
LV Family:
Atlas.
Launch Vehicle:
Atlas Agena D.
LV Configuration: Atlas Agena D 227D / Agena D S01A 4802.
- KH 7-04 - .
Payload: KH-7 no. 4. Mass: 2,000 kg (4,400 lb). Nation: USA. Agency: NRO; USAF. Class: Surveillance. Type: Military surveillance satellite. Spacecraft: KH-7. Decay Date: 1963-12-20 . USAF Sat Cat: 711 . COSPAR: 1963-051A. Apogee: 266 km (165 mi). Perigee: 122 km (75 mi). Inclination: 97.9000 deg. Period: 88.50 min. Summary: KH-7 type satellite. Space craft engaged in investigation of spaceflight techniques and technology (US Cat A). .
1963 December 18 - .
22:56 GMT - .
Launch Site:
Vandenberg.
Launch Complex:
Vandenberg OSTF2.
LV Family:
Atlas.
Launch Vehicle:
Atlas F.
LV Configuration: Atlas F 109F.
- Research and development launch - .
Nation: USA. Agency: USAF AFSC. Apogee: 1,400 km (800 mi).
1964 January 1 - .
LV Family:
Atlas;
Titan.
- NASA Headquarters directed Gemini Project Office to take the radar and rendezvous evaluation pod out of Gemini-Titan (GT) missions 3 and 4. - .
Nation: USA. Flight: Gemini 4; Gemini 5. Spacecraft: Gemini; Gemini Radar; Gemini REP. Summary: GT-4 would be a battery-powered long-duration flight. The pod would go on GT-5, and thus the first planned Agena flight would probably slip in the schedule..
1964 January 30 - .
15:49 GMT - .
Launch Site:
Cape Canaveral.
Launch Complex:
Cape Canaveral LC12.
LV Family:
Atlas.
Launch Vehicle:
Atlas Agena B.
LV Configuration: Atlas Agena B 199D (AA8) / Agena B 6008 (AA8).
- Ranger 6 - .
Payload: RA-6. Mass: 362 kg (798 lb). Nation: USA. Agency: NASA; JPL. Program: Ranger. Class: Moon. Type: Lunar probe. Spacecraft: Ranger 6-7-8-9. Decay Date: 1964-02-02 . USAF Sat Cat: 747 . COSPAR: 1964-007A. Impacted Moon but TV camera malfunctioned. A midcourse trajectory correction was accomplished early in the flight by ground control. On February 2, 1964, 65.5 hours after launch, Ranger 6 impacted the Moon on the eastern edge of Mare Tranquillitatis (Sea of Tranquility). No camera data were obtained, probably because of failure due to an arc-over in the TV power system when it inadvertently turned on during the period of booster-engine separation.
1964 February 5 - .
LV Family:
Atlas.
Launch Vehicle:
Atlas Agena D SLV-3.
- Bell Aerosystems began Preliminary Flight Rating Tests (PFRT) of the Agena primary propulsion system (PPS). - .
Nation: USA. Tests were expected to be completed April 24 but were not actually concluded until late June. Testing proceeded with only minor problems through the first week of April. But in the following week PPS testing encountered what proved to be a six-week delay when the test unit's fuel and oxidizer start tanks failed. The two start tanks, stainless steel canisters with an internal bellows arrangement, supplied the propellants required to initiate the main engine start sequence. Visible longitudinal cracks in the outer shell allowed the gas which forced the propellants out of the tank to escape. Investigation revealed that the cracks had resulted from intergranular corrosion of the stainless steel tanks. The defective tanks were replaced by start tanks with a new heat-treated shell (delivered April 24), and PFRT resumed early in May.
1964 February 12 - .
19:59 GMT - .
Launch Site:
Vandenberg.
Launch Complex:
Vandenberg OSTF1.
LV Family:
Atlas.
Launch Vehicle:
Atlas E.
LV Configuration: Atlas E 48E.
FAILURE: Failure.
Failed Stage: 1.
- ST - .
Nation: USA. Agency: USAF SAC. Apogee: 0 km ( mi).
1964 February 13 - .
18:11 GMT - .
Launch Site:
Walker AFB.
Launch Complex:
Walker AFB Missile Site 579.
Launch Pad: 579-5.
LV Family:
Atlas.
Launch Vehicle:
Atlas F.
LV Configuration: Atlas F 88F.
FAILURE: Exploded during propellant loading..
- Accident - .
Nation: USA. Agency: USAF. Apogee: 0 km ( mi). Summary: Operational ICBM test at Walker AFB..
1964 February 16 - .
LV Family:
Atlas.
Launch Vehicle:
Atlas Agena D SLV-3.
- Bell Aerosystems delivered the first Gemini Agena Model 8247 main engine to Lockheed. - .
Nation: USA. This engine was installed in the propulsion test vehicle assembly (PTVA), a unit to be used for a series of tests on the Agena primary and secondary propulsion systems at Lockheed's Santa Cruz Test Base. Bell delivered the two secondary propulsion system modules for the PTVA on March 6 and 14. Installation was completed and the PTVA delivered to Santa Cruz Test Base on March 26.
1964 February 17 - .
LV Family:
Atlas.
Launch Vehicle:
Atlas Agena D SLV-3.
- Bell Aerosystems began Preliminary Flight Rating Tests (PFRT) of the Agena secondary propulsion system (SPS). - .
Nation: USA. After proceeding through the acceleration and vibration test phases of PFRT without incident, the SPS began calibration firings early in April. The failure of a propellant valve in Unit I (the 16-pound thrust chamber fired prior to starting the main engine in order to orient propellant) of the SPS imposed a minor delay, but a more serious problem emerged late in April during high-temperature firings. The wall of the Unit II 200-pound thrust chamber burned through near the injector face after an accumulated PFRT firing time of 354 seconds, below the specification limit of 400 seconds although well in excess of the maximum orbital useful time of 200 seconds. The thrust chamber was replaced and testing continued, but PFRT, originally scheduled to end June 19, was first slipped to July 8, and finally completed in mid-August. To resolve the burn-through problem, Bell began a test program in September to determine the cause of failure.
1964 February 25 - .
18:59 GMT - .
Launch Site:
Vandenberg.
Launch Complex:
Vandenberg SLC4W.
LV Family:
Atlas.
Launch Vehicle:
Atlas Agena D.
LV Configuration: Atlas Agena D 285D / Agena D S01A 4803.
- KH 7-05 - .
Payload: KH-7 no. 5 / OPS 2423. Mass: 2,000 kg (4,400 lb). Nation: USA. Agency: NRO; USAF. Class: Surveillance. Type: Military surveillance satellite. Spacecraft: KH-7. Decay Date: 1964-03-01 . USAF Sat Cat: 754 . COSPAR: 1964-009A. Apogee: 135 km (83 mi). Perigee: 135 km (83 mi). Inclination: 95.6000 deg. Period: 87.20 min. Summary: KH-7 type satellite. Space craft engaged in investigation of spaceflight techniques and technology (US Cat A). .
1964 February 25 - .
20:22 GMT - .
Launch Site:
Cape Canaveral.
Launch Complex:
Cape Canaveral LC11.
LV Family:
Atlas.
Launch Vehicle:
Atlas E.
LV Configuration: Atlas E 5E.
- ABRES WAC-3 / Pod 18 Re-entry vehicle test - .
Nation: USA. Agency: USAF AFSC. Apogee: 1,600 km (900 mi).
1964 February 28 - .
LV Family:
Atlas.
Launch Vehicle:
Atlas Agena D SLV-3.
- Gemini Project Manager Charles W. Mathews informed Manned Spacecraft Center senior staff of efforts to control Gemini spacecraft weight and configuration more tightly. - .
Nation: USA. Mathews had assigned Lewis R. Fisher of his office to head a Systems Integration Office within Gemini Project Office to oversee these efforts by keeping very precise accounts of spacecraft weight, interface actions between the spacecraft and launch vehicle, and interface actions between the spacecraft and the Agena target vehicle.
1964 March 9 - .
21:54 GMT - .
Launch Site:
Walker AFB.
Launch Complex:
Walker AFB Missile Site 579.
Launch Pad: 579-2.
LV Family:
Atlas.
Launch Vehicle:
Atlas F.
LV Configuration: Atlas F 90F.
FAILURE: Exploded during propellant loading..
- Accident - .
Nation: USA. Agency: USAF. Apogee: 0 km ( mi). Summary: Operational ICBM test at Walker AFB..
1964 March 11 - .
20:14 GMT - .
Launch Site:
Vandenberg.
Launch Complex:
Vandenberg SLC4W.
LV Family:
Atlas.
Launch Vehicle:
Atlas Agena D.
LV Configuration: Atlas Agena D 296D / Agena D S01A 4804.
- KH 7-06 - .
Payload: KH-7 no. 6 / OPS 3435. Mass: 2,000 kg (4,400 lb). Nation: USA. Agency: NRO; USAF. Class: Surveillance. Type: Military surveillance satellite. Spacecraft: KH-7. Decay Date: 1964-03-16 . USAF Sat Cat: 764 . COSPAR: 1964-012A. Apogee: 203 km (126 mi). Perigee: 163 km (101 mi). Inclination: 95.7000 deg. Period: 88.20 min. Summary: KH-7 type satellite. Space craft engaged in investigation of spaceflight techniques and technology (US Cat A). .
1964 March 20 - .
LV Family:
Atlas.
Launch Vehicle:
Atlas Agena D SLV-3.
- Test program to increase confidence in critical components of the Gemini Agena target vehicle. - .
Nation: USA. Manned Spacecraft Center (MSC) approved Air Force Space Systems Division's (SSD) recommendations for a test program to increase confidence in 16 critical electronic and electrical components of the Gemini Agena target vehicle. The program included complete electromagnetic interference (EMI) testing of all components peculiar to the Gemini mission, as well as elevated stress tests and extended life tests. SSD had also recommended subsystem-level, as well as component-level, EMI testing, but this part of the program MSC disapproved. SSD directed Lockheed to proceed with the program on March 23. EMI tests were scheduled to be completed by July 1, stress and life tests by September 1, 1964.
1964 March 25 - .
LV Family:
Atlas.
Launch Vehicle:
Atlas Agena D SLV-3.
- Gemini mission plans for the first Agena rendezvous flight. - .
Nation: USA. Related Persons: Aldrin. Spacecraft: Gemini; Gemini Radar. At a meeting of the Gemini Project Office's Trajectories and Orbits Panel, members of Flight Operations Division described two mission plans currently under consideration for the first Agena rendezvous flight. One was based on the concept of tangential Agena and spacecraft orbits, as proposed by Howard W. Tindall, Jr., and James T. Rose when they were members of Space Task Group. The second plan, based on a proposal by Edwin E. Aldrin, Jr., then of Air Force Space Systems Division, involved orbits which were concentric rather than tangential. The most significant advantage of the second plan was that it provided the greatest utilization of onboard backup techniques; that is, it was specifically designed to make optimum use of remaining onboard systems in the event of failure in the inertial guidance system platform, computer, or radar.
1964 March 26 - .
LV Family:
Atlas.
Launch Vehicle:
Atlas Agena D SLV-3.
- The propulsion test vehicle assembly (PTVA) arrived at Santa Cruz Test Base. - .
Nation: USA. It consisted of a basic Agena structure with propellant pressurization, feed-and-load system, the primary propulsion system (PPS), and two secondary propulsion system (SPS) modules attached to the aft rack. The test program called for loading operations and hot firings of both propulsion systems to establish the adequacy of PPS and SPS propellant loading systems and associated ground equipment, to demonstrate proper overall system operation, and to provide engineering data on systems operation and the resulting environment. Start of testing was delayed by the PPS start tank problems which showed up during Preliminary Flight Rating Tests at Bell Aerosystems during April. Lockheed returned the PTVA main engine start tanks to Bell, where they were inspected and found to be defective. New tanks were ready by mid-May, but additional minor problems delayed the initiation of hot-firing until June 16.
1964 April 1 - .
20:22 GMT - .
Launch Site:
Cape Canaveral.
Launch Complex:
Cape Canaveral LC11.
LV Family:
Atlas.
Launch Vehicle:
Atlas F.
LV Configuration: Atlas F 137F.
- ABRES WAC-2 / Pod 2 Reentry test / plume mission - .
Nation: USA. Agency: USAF AFSC. Apogee: 1,400 km (800 mi).
1964 April 3 - .
20:26 GMT - .
Launch Site:
Vandenberg.
Launch Complex:
Vandenberg OSTF2.
LV Family:
Atlas.
Launch Vehicle:
Atlas F.
LV Configuration: Atlas F 3F.
FAILURE: Failure.
Failed Stage: 1.
- Demonstration and shakedown operations launch - .
Nation: USA. Agency: USAF SAC. Apogee: 0 km ( mi).
1964 April 13 - .
LV Family:
Atlas.
Launch Vehicle:
Atlas Agena D SLV-3.
- Air Force Space Systems Division (SSD) recommended a Gemini Agena launch on a nonrendezvous mission to improve confidence in target vehicle performance before undertaking a rendezvous mission. - .
Nation: USA. Flight: Gemini 12. Summary: Gemini Project Office (GPO) rejected this plan, regarding it as impractical within current schedule, launch sequence, and cost restraints. . Additional Details: here....
1964 April 14 - .
21:42 GMT - .
Launch Site:
Cape Canaveral.
Launch Complex:
Cape Canaveral LC12.
LV Family:
Atlas.
Launch Vehicle:
Atlas D.
LV Configuration: Atlas D 263D.
- FIRE 1 - .
Nation: USA. Agency: NASA. Apogee: 837 km (520 mi). FIRE was a subscale model of the Apollo capsule used to verify the spacecraft's hypersonic flight and thermal characteristics. An Atlas D launch vehicle lifted a Project Fire spacecraft from Cape Kennedy in the first test of the heat that would be encountered by a spacecraft reentering the atmosphere at lunar-return velocity. During the spacecraft's fall toward earth, a solid-fuel Antares II rocket behind the payload fired for 30 seconds, increasing the descent speed to 40,501 kilometers (25,166 miles) per hour. Instruments in the spacecraft radioed temperature data to the ground. The spacecraft exterior reached an estimated temperature of 11,400 K (20,000 degrees F). About 32 minutes after launch, the spacecraft impacted into the Atlantic Ocean. The mission, sponsored by Langley Research Center, provided reentry heating measurements needed to evaluate heatshield materials and information on the communications blackout during reentry.
1964 April 23 - .
16:19 GMT - .
Launch Site:
Vandenberg.
Launch Complex:
Vandenberg SLC4W.
LV Family:
Atlas.
Launch Vehicle:
Atlas Agena D.
LV Configuration: Atlas Agena D 351D / Agena D S01A 4805.
- KH 7-07 - .
Payload: KH-7 no. 7 / OPS 3743. Mass: 2,000 kg (4,400 lb). Nation: USA. Agency: NRO; USAF. Class: Surveillance. Type: Military surveillance satellite. Spacecraft: KH-7. Decay Date: 1964-04-29 . USAF Sat Cat: 786 . COSPAR: 1964-020A. Apogee: 336 km (208 mi). Perigee: 150 km (90 mi). Inclination: 103.6000 deg. Period: 89.40 min. Summary: KH-7 type satellite. Space craft engaged in investigation of spaceflight techniques and technology (US Cat A). .
1964 April 30 - .
LV Family:
Atlas.
Launch Vehicle:
Atlas Agena D SLV-3.
- First Agena D for the Gemini program. - .
Nation: USA. Program: Gemini. Flight: Gemini 12. Spacecraft: Gemini; Gemini Radar. Air Force Space Systems Division (SSD) accepted the first Agena D (AD-71) for the Gemini program. The Agena D was a production-line vehicle procured from Lockheed by SSD for NASA through routine procedures. Following minor retrofit operations, the vehicle, now designated Gemini Agena target vehicle 5001, entered the manufacturing final assembly area at the Lockheed plant on May 14. There began the conversion of the Agena D into a target vehicle for Gemini rendezvous missions. Major modifications were installation of a target docking adapter (supplied by McDonnell), an auxiliary equipment rack, external status displays, a secondary propulsion system, and an L-band tracking radar.
1964 May 11 - .
LV Family:
Atlas.
Launch Vehicle:
Atlas Agena D SLV-3.
- Sea trials of the tracking ship, Rose Knot, were begun on Chesapeake Bay to study the effects of shock vibrations on Gemini equipment. - .
Nation: USA. Summary: A few vibration problems with the pulse-code-modulation system were reported. Gemini-Agena systems were simulated by an instrumented Lockheed Super Constellation aircraft..
1964 May 13 - .
LV Family:
Atlas.
Launch Vehicle:
Atlas Agena D SLV-3.
- Flight Operations Division presented the Gemini Program Office's proposed mission plan No. 3 for the first Agena rendezvous flight to the Trajectories and Orbits Panel. - .
Nation: USA. Summary: Plan No. 3, as yet incomplete, provided for rendezvous at first apogee on a perfectly nominal mission..
1964 May 14 - .
Launch Site:
Altus AFB.
Launch Complex:
Altus AFB 577-6.
LV Family:
Atlas.
Launch Vehicle:
Atlas F.
LV Configuration: Atlas F 61F.
FAILURE: Exploded during propellant loading..
- Accident - .
Nation: USA. Agency: USAF. Apogee: 0 km ( mi). Summary: Operational missile test at Altus AFB..
1964 May 19 - .
19:21 GMT - .
Launch Site:
Vandenberg.
Launch Complex:
Vandenberg SLC4W.
LV Family:
Atlas.
Launch Vehicle:
Atlas Agena D.
LV Configuration: Atlas Agena D 350D / Agena D S01A 4806.
- KH 7-08 - .
Payload: KH-7 no. 8 / OPS 3592. Mass: 2,000 kg (4,400 lb). Nation: USA. Agency: NRO; USAF. Class: Surveillance. Type: Military surveillance satellite. Spacecraft: KH-7. Decay Date: 1964-05-22 . USAF Sat Cat: 799 . COSPAR: 1964-024A. Apogee: 380 km (230 mi). Perigee: 141 km (87 mi). Inclination: 101.1000 deg. Period: 89.70 min. Summary: KH-7 type satellite. Space craft engaged in investigation of spaceflight techniques and technology (US Cat A). .
1964 June 3 - .
LV Family:
Atlas.
Launch Vehicle:
Atlas Agena D SLV-3.
- Lockheed inaugurated the Gemini Extra Care Program to reduce the incidence of equipment failures and discrepancies. - .
Nation: USA. In cooperation with Air Force and NASA, Lockheed inaugurated the Gemini Extra Care Program to reduce the incidence of equipment failures and discrepancies resulting from poor or careless workmanship during the modification and assembly of the Agena target vehicle. The program included increased inspection, exhortation, morale boosters, special awards, and other activities aimed at fostering and maintaining a strong team spirit at all levels. Results of the program were evidenced in a drastic decline in the number of FEDRs (Failed Equipment and Discrepancy Reports) recorded in the Gemini final manufacturing area on successive vehicles.
1964 June 16 - .
LV Family:
Atlas.
Launch Vehicle:
Atlas Agena D SLV-3.
- Lockheed began test-firing the propulsion test vehicle assembly at its Santa Cruz Test Base, after a delay caused primarily by problems with the Agena main engine start tanks. - .
Nation: USA. The program, undertaken because of extensive changes in the propulsion system required to adapt the standard Agena D for use in Gemini missions, comprised three series of static-firing tests. The first series, in addition to providing base line performance for both primary and secondary propulsion systems (PPS and SPS), also subjected one SPS module to the dynamic and acoustic environment created by 55 seconds of PPS firing. The second series, successfully completed July 16, simulated a possible Gemini mission profile, including multiple firings and various coast and burn times on both PPS and SPS units. The third series, which concluded the test program on August 7, involved a maximum number of starts and minimum-impulse firings on both PPS and SPS. All firings were successful, and review of test data revealed only minor anomalies. The entire test program comprised 27 PPS firings for a run time totaling 545 seconds, 30 SPS Unit I firings totaling 286 seconds, and 11 SPS Unit II firings totaling 268 seconds. Post-test disassembly revealed no physical damage to any equipment.
1964 June 18 - .
14:56 GMT - .
Launch Site:
Vandenberg.
Launch Complex:
Vandenberg 576A1.
LV Family:
Atlas.
Launch Vehicle:
Atlas D.
LV Configuration: Atlas D 243D.
- ABRES LORV-1 / Pod 31 Re-entry vehicle test - .
Nation: USA. Agency: USAF SAC. Apogee: 1,800 km (1,100 mi).
1964 June 24 - .
LV Family:
Atlas.
Launch Vehicle:
Atlas Agena D SLV-3.
- Construction of Gemini-Agena facilities at complex 14 was completed. - .
Nation: USA. Summary: General Dynamics finished the installation and checkout of equipment in the Launch Operations Building on July 20. Lockheed equipment in the Launch Operations Building was installed and checked out by July 31..
1964 June 30 - .
14:04 GMT - .
Launch Site:
Cape Canaveral.
Launch Complex:
Cape Canaveral LC36A.
LV Family:
Atlas.
Launch Vehicle:
Atlas Centaur.
LV Configuration: Atlas Centaur AC-3 / Centaur D 135D.
FAILURE: Centaur hydraulics failure..
Failed Stage: 2.
- Centaur AC-3 - .
Payload: Centaur 1C. Mass: 4,815 kg (10,615 lb). Nation: USA. Agency: NASA. Decay Date: 1964-06-30 . COSPAR: F640630A. Apogee: 500 km (310 mi). Summary: Centaur test. Launch vehicle was to have put payload into geosynchronous transfer orbit.
1964 July 6 - .
18:51 GMT - .
Launch Site:
Vandenberg.
Launch Complex:
Vandenberg SLC4W.
LV Family:
Atlas.
Launch Vehicle:
Atlas Agena D.
LV Configuration: Atlas Agena D 352D / Agena D S01A 4807.
- KH 7-09 - .
Payload: KH-7 no. 9 / OPS 3684. Mass: 2,000 kg (4,400 lb). Nation: USA. Agency: NRO; USAF. Class: Surveillance. Type: Military surveillance satellite. Spacecraft: KH-7. Decay Date: 1964-07-08 . USAF Sat Cat: 825 . COSPAR: 1964-036A. Apogee: 345 km (214 mi). Perigee: 121 km (75 mi). Inclination: 92.9000 deg. Period: 89.10 min. Summary: KH-7 type satellite. Space craft engaged in investigation of spaceflight techniques and technology (US Cat A). .
- OPS 4923 - .
Payload: EHH A3. Mass: 80 kg (176 lb). Nation: USA. Agency: NRO; USAF. Class: Military. Type: Military naval signals reconnaisance satellite. Spacecraft: SSF. Decay Date: 1965-01-03 . USAF Sat Cat: 826 . COSPAR: 1964-036B. Apogee: 505 km (313 mi). Perigee: 156 km (96 mi). Inclination: 92.9000 deg. Period: 91.10 min. Summary: Radar monitoring..
1964 July 17 - .
08:22 GMT - .
Launch Site:
Cape Canaveral.
Launch Complex:
Cape Canaveral LC13.
LV Family:
Atlas.
Launch Vehicle:
Atlas Agena D.
LV Configuration: Atlas Agena D 216D / Agena D 1802.
- Vela 3 - .
Payload: Vela 2A / OPS 3662. Mass: 220 kg (480 lb). Nation: USA. Agency: USAF. Class: Surveillance. Type: Nuclear detection surveillance satellite. Spacecraft: Vela. USAF Sat Cat: 836 . COSPAR: 1964-040A. Apogee: 104,101 km (64,685 mi). Perigee: 102,500 km (63,600 mi). Inclination: 39.1000 deg. Period: 6,024.80 min. Summary: Space craft engaged in investigation of spaceflight techniques and technology (US Cat A)..
- Vela 4 - .
Payload: Vela 2B / OPS 3674. Mass: 220 kg (480 lb). Nation: USA. Agency: USAF. Class: Surveillance. Type: Nuclear detection surveillance satellite. Spacecraft: Vela. USAF Sat Cat: 837 . COSPAR: 1964-040B. Apogee: 114,000 km (70,000 mi). Perigee: 92,103 km (57,230 mi). Inclination: 40.8000 deg. Period: 6,004.30 min. Summary: Space craft engaged in investigation of spaceflight techniques and technology (US Cat A)..
- TRS 6 - .
Payload: ERS 13. Mass: 12 kg (26 lb). Nation: USA. Agency: USAF. Class: Technology. Type: Navigation technology satellite. Spacecraft: TRS. Decay Date: 1966-07-01 . USAF Sat Cat: 838 . COSPAR: 1964-040C. Apogee: 104,665 km (65,035 mi). Perigee: 217 km (134 mi). Inclination: 36.7000 deg. Period: 2,366.20 min. Summary: Decay date suspect Space craft engaged in investigation of spaceflight techniques and technology (US Cat A)..
1964 July 28 - .
16:50 GMT - .
Launch Site:
Cape Canaveral.
Launch Complex:
Cape Canaveral LC12.
LV Family:
Atlas.
Launch Vehicle:
Atlas Agena B.
LV Configuration: Atlas Agena B 250D (AA9) / Agena B 6009 (AA9).
- Ranger 7 - .
Mass: 362 kg (798 lb). Nation: USA. Agency: NASA; JPL. Program: Ranger. Class: Moon. Type: Lunar probe. Spacecraft: Ranger 6-7-8-9. Decay Date: 1964-07-31 . USAF Sat Cat: 842 . COSPAR: 1964-041A. First successful Ranger; returned 4,308 photos before lunar impact. The Atlas- Agena B inserted the Agena and Ranger into a 192 km altitude Earth parking orbit. Half an hour after launch a second burn of the Agena engine injected the spacecraft into a lunar intercept trajectory. After separation from the Agena, the solar panels were deployed, attitude control activated, and spacecraft transmissions switched from the omniantenna to the high-gain antenna. The next day the planned mid-course maneuver was successfully initiated at 10:27 GMT. The only anomaly during flight was a brief loss of two-way lock on the spacecraft by the DSIF tracking station at Cape Kennedy following launch.
Ranger 7 reached the Moon on 31 July. The F-channel began its one minute warm up 18 minutes before impact. The first image was taken at 13:08:45 GMT at an altitude of 2110 km. Transmission of 4,308 photographs of excellent quality occurred over the final 17 minutes of flight. The final image taken before impact had a resolution of 0.5 meters. The spacecraft encountered the lunar surface in direct motion along a hyperbolic trajectory, with an incoming asymptotic direction at an angle of -5.57 degrees from the lunar equator. The orbit plane was inclined 26.84 degrees to the lunar equator. After 68.6 hours of flight, Ranger 7 impacted in an area between Mare Nubium and Oceanus Procellarum (subsequently named Mare Cognitum) at approximately 10.35 S latitude, 339.42 E longitude. Impact occurred at 13:25:48.82 GMT at a velocity of 2.62 km/s.
1964 July 29 - .
09:22 GMT - .
Launch Site:
Vandenberg.
Launch Complex:
Vandenberg 576A3.
LV Family:
Atlas.
Launch Vehicle:
Atlas D.
LV Configuration: Atlas D 248D.
- NTMP KX-13 Target mission - .
Nation: USA. Agency: USAF SAC. Apogee: 1,800 km (1,100 mi).
1964 August 7 - .
20:12 GMT - .
Launch Site:
Vandenberg.
Launch Complex:
Vandenberg 576E.
LV Family:
Atlas.
Launch Vehicle:
Atlas F.
LV Configuration: Atlas F 110F.
- Demonstration and shakedown operations launch - .
Nation: USA. Agency: USAF SAC. Apogee: 1,400 km (800 mi).
1964 August 14 - .
22:00 GMT - .
Launch Site:
Vandenberg.
Launch Complex:
Vandenberg SLC4E.
LV Family:
Atlas.
Launch Vehicle:
Atlas Agena D SLV-3.
LV Configuration: SLV-3 Agena D 7101 / Agena D S01A 4808.
- KH 7-10 - .
Payload: KH-7 no. 10 / OPS 3802. Mass: 2,000 kg (4,400 lb). Nation: USA. Agency: NRO; USAF. Class: Surveillance. Type: Military surveillance satellite. Spacecraft: KH-7. Decay Date: 1964-08-23 . USAF Sat Cat: 850 . COSPAR: 1964-045A. Apogee: 300 km (180 mi). Perigee: 165 km (102 mi). Inclination: 95.4000 deg. Period: 89.10 min. Summary: KH-7 type satellite. Space craft engaged in investigation of spaceflight techniques and technology (US Cat A). .
- OPS 3316 - .
Payload: P-11 s/n 4202. Mass: 79 kg (174 lb). Nation: USA. Agency: USAF. Class: Military. Type: Military naval signals reconnaisance satellite. Spacecraft: SSF. Decay Date: 1979-03-08 . USAF Sat Cat: 851 . COSPAR: 1964-045B. Apogee: 3,751 km (2,330 mi). Perigee: 272 km (169 mi). Inclination: 95.7000 deg. Period: 127.40 min.
1964 August 27 - .
09:54 GMT - .
Launch Site:
Vandenberg.
Launch Complex:
Vandenberg OSTF1.
LV Family:
Atlas.
Launch Vehicle:
Atlas E.
LV Configuration: Atlas E 57E.
- ST/KX-48 Target mission - .
Nation: USA. Agency: USAF SAC. Apogee: 1,600 km (900 mi).
1964 August 31 - .
15:46 GMT - .
Launch Site:
Vandenberg.
Launch Complex:
Vandenberg 576D.
LV Family:
Atlas.
Launch Vehicle:
Atlas F.
LV Configuration: Atlas F 36F.
- Demonstration and shakedown operations launch - .
Nation: USA. Agency: USAF SAC. Apogee: 1,400 km (800 mi).
1964 September - .
LV Family:
Atlas.
Launch Vehicle:
Atlas D.
- Atlas SMS 564 deactivated. - .
Nation: USA. Summary: Warren-1 AFB SMS 564 deactivated.
1964 September 5 - .
01:23 GMT - .
Launch Site:
Cape Canaveral.
Launch Complex:
Cape Canaveral LC12.
LV Family:
Atlas.
Launch Vehicle:
Atlas Agena B.
LV Configuration: Atlas Agena B 195D (AA10) / Agena B 6501 (AA10).
- OGO 1 - .
Payload: OGO A. Mass: 487 kg (1,073 lb). Nation: USA. Agency: NASA Greenbelt. Class: Earth. Type: Magnetosphere satellite. Spacecraft: OGO. Decay Date: 1980-08-10 . USAF Sat Cat: 879 . COSPAR: 1964-054A. Apogee: 127,394 km (79,158 mi). Perigee: 21,446 km (13,325 mi). Inclination: 44.6000 deg. Period: 3,809.50 min. Two experiment booms failed to properly deploy, with one of the booms obscuring a horizon scanner's view of earth. As a result, the spacecraft attitude could not be earth oriented and OGO 1 remained spin stabilized at 5 rpm. Nevertheless, data from all 20 experiments on board was received, although at a 'less than expected capacity' from some of them. Twelve of the experiemnts were particle studies and two were magnetic field studies. In addition, there was one experiment for each of the following types of studies: interplanetary dust, VLF, Lyman-alpha, Gegenschein, atmospheric mass, and radio astronomy. During September 1964, acceptable data were received over 70% of the orbital path. By June 1969, data acquisition was limited to 10% of the orbital path. Spacecraft operation was restricted to Spring and Fall due to power supply limitations. There were 11 such 3-month periods prior to the spacecraft being put into stand-by mode on 25 November 1969. By April 1970 the spacecraft perigee had increased to 46,000 km and the inclination had increased to 58.8 deg. All support was terminated November 1, 1971.
1964 September 15 - .
15:27 GMT - .
Launch Site:
Vandenberg.
Launch Complex:
Vandenberg 576A1.
LV Family:
Atlas.
Launch Vehicle:
Atlas D.
LV Configuration: Atlas D 245D.
- ABRES LORV-3 / Pod 26 Re-entry vehicle test - .
Nation: USA. Agency: USAF SAC. Apogee: 1,800 km (1,100 mi).
1964 September 22 - .
13:10 GMT - .
Launch Site:
Vandenberg.
Launch Complex:
Vandenberg 576A3.
LV Family:
Atlas.
Launch Vehicle:
Atlas D.
LV Configuration: Atlas D 247D.
- NTMP KX-19 Target mission - .
Nation: USA. Agency: USAF SAC. Apogee: 1,800 km (1,100 mi).
1964 September 23 - .
LV Family:
Atlas;
Titan.
- Manned Spacecraft Center announced at a Trajectories and Orbit Panel meeting that several changes in the ground rules had been made to the Gemini-Titan 6 mission plan. - .
Nation: USA. Flight: Gemini 6. One change concerned a previous assumption of a 20-day Agena lifetime; it was now established that the Agena would not be modified to provide this. As a result, greater emphasis had to be placed on ensuring spacecraft launch on the same day as the Agena, primarily by relieving the constraint of no Agena maneuvers. The restriction on using Agena maneuvers had been removed to increase the probability of achieving rendezvous within the few days that the Agena would remain an acceptable target.
1964 September 23 - .
20:06 GMT - .
Launch Site:
Vandenberg.
Launch Complex:
Vandenberg SLC4E.
LV Family:
Atlas.
Launch Vehicle:
Atlas Agena D SLV-3.
LV Configuration: SLV-3 Agena D 7102.
- KH 7-11 - .
Payload: KH-7 no. 11 / OPS 4262. Mass: 2,000 kg (4,400 lb). Nation: USA. Agency: NRO; USAF. Class: Surveillance. Type: Military surveillance satellite. Spacecraft: KH-7. Decay Date: 1964-09-28 . USAF Sat Cat: 884 . COSPAR: 1964-058A. Apogee: 303 km (188 mi). Perigee: 143 km (88 mi). Inclination: 92.9000 deg. Period: 88.90 min. Summary: KH-7 type satellite. Space craft engaged in investigation of spaceflight techniques and technology (US Cat A). .
1964 September 24 - .
LV Family:
Atlas.
Launch Vehicle:
Atlas Agena D SLV-3.
- Lockheed completed the modification and final assembly of Gemini Agena target vehicle 5001 and transferred it to systems test complex C-10 at the Lockheed plant. - .
Nation: USA. Flight: Gemini 12. Summary: Lockheed began the task of hooking the vehicle up for systems testing the next day, September 25..
1964 October 8 - .
Launch Site:
Vandenberg.
Launch Complex:
Vandenberg SLC4E.
LV Family:
Atlas.
Launch Vehicle:
Atlas Agena D SLV-3.
LV Configuration: SLV-3 Agena D 7103.
FAILURE: Failure.
Failed Stage: U.
- KH-7 12 - .
Payload: KH-7 no. 12. Mass: 2,000 kg (4,400 lb). Nation: USA. Agency: USAF. Class: Surveillance. Type: Military surveillance satellite. Spacecraft: KH-7. Decay Date: 1964-10-08 . COSPAR: F641008A. Summary: KH-7 type satellite..
1964 October 23 - .
18:30 GMT - .
Launch Site:
Vandenberg.
Launch Complex:
Vandenberg SLC4W.
LV Family:
Atlas.
Launch Vehicle:
Atlas Agena D.
LV Configuration: Atlas Agena D 353D.
- KH 7-13 - .
Payload: KH-7 no. 13 / OPS 4384. Mass: 2,000 kg (4,400 lb). Nation: USA. Agency: NRO; USAF. Class: Surveillance. Type: Military surveillance satellite. Spacecraft: KH-7. Decay Date: 1964-10-28 . USAF Sat Cat: 912 . COSPAR: 1964-068A. Apogee: 267 km (165 mi). Perigee: 140 km (80 mi). Inclination: 95.5000 deg. Period: 88.50 min. Summary: KH-7 type satellite. Space craft engaged in investigation of spaceflight techniques and technology (US Cat A). .
- OPS 5063 - .
Payload: EHH A4. Nation: USA. Agency: USAF AFSC. Class: Military. Type: Military naval signals reconnaisance satellite. Spacecraft: SSF. Decay Date: 1965-02-23 . USAF Sat Cat: 914 . COSPAR: 1964-068xx. Apogee: 185 km (114 mi). Perigee: 185 km (114 mi). Inclination: 95.4000 deg. Period: 88.20 min.
- SRV - .
Mass: 60 kg (132 lb). Nation: USA. Agency: NRO; USAF. Spacecraft: KH-7. Decay Date: 1965-02-23 . USAF Sat Cat: 914 . COSPAR: 1964-068B. Apogee: 344 km (213 mi). Perigee: 311 km (193 mi). Inclination: 95.5000 deg. Period: 91.10 min. Summary: Radar monitoring..
1964 October 28 - .
LV Family:
Atlas.
Launch Vehicle:
Atlas Agena D SLV-3.
- Bell Aerosystems successfully fired the Agena secondary propulsion system (SPS) in a test of the system's ability to survive a launch hold. - .
Nation: USA. Summary: The SPS had first gone through a 20-day dry (unloaded) period, followed by a 20-day wet (loaded) period. The system reverted to hold condition and was successfully refired November 2..
1964 November 5 - .
19:22 GMT - .
Launch Site:
Cape Canaveral.
Launch Complex:
Cape Canaveral LC13.
LV Family:
Atlas.
Launch Vehicle:
Atlas Agena D.
LV Configuration: Atlas Agena D 289D (AA11) / Agena D 6931 (AA11).
FAILURE: Launch fairing failure.
Failed Stage: S.
- Mariner 3 - .
Payload: Mariner C-2. Mass: 260 kg (570 lb). Nation: USA. Agency: NASA; JPL. Program: Mariner. Class: Mars. Type: Mars probe. Spacecraft: Mariner 3-4. USAF Sat Cat: 923 . COSPAR: 1964-073A. Summary: Mars probe; launch fairing failure prevented Mars flyby. Solar Orbit (Heliocentric). Spacecraft engaged in research and exploration of the upper atmosphere or outer space (US Cat B)..
1964 November 10 - .
LV Family:
Atlas.
Launch Vehicle:
Atlas Agena D SLV-3.
- Gemini Agena target vehicle (GATV) 5001 competed a simulated flight (ascent and orbit) at Lockheed test complex C-10. - .
Nation: USA. Flight: Gemini 12. Summary: Minor anomalies required portions of the test to be rerun. This concluded GATV 5001 systems tests in preparation for captive-firing tests to be conducted at Lockheed's Santa Cruz Test Base. The vehicle was shipped November 30..
1964 November 28 - .
14:22 GMT - .
Launch Site:
Cape Canaveral.
Launch Complex:
Cape Canaveral LC12.
LV Family:
Atlas.
Launch Vehicle:
Atlas Agena D.
LV Configuration: Atlas Agena D 288D (AA12) / Agena D 6932 (AA12).
- Mariner 4 - .
Payload: Mariner C-3. Mass: 260 kg (570 lb). Nation: USA. Agency: NASA; JPL. Program: Mariner. Class: Mars. Type: Mars probe. Spacecraft: Mariner 3-4. USAF Sat Cat: 938 . COSPAR: 1964-077A. Mariner 4 provided the first up close pictures of Mars. The protective shroud covering Mariner 4 was jettisoned and the Agena D/Mariner 4 combination separated from the Atlas D booster at 14:27:23 GMT on 28 November 1964. The Agena D first burn from 14:28:14 to 14:30:38 put the spacecraft into an Earth parking orbit and the second burn from 15:02:53 to 15:04:28 injected the craft into a Mars transfer orbit. Mariner 4 separated from the Agena D at 15:07:09 and began cruise mode operations. The solar panels deployed and the scan platform was unlatched at 15:15:00 and Sun acquisition occurred 16 minutes later. A midcourse maneuver made on 5 December 1964.
After a 228 day cruise, the spacecraft flew by Mars on July 14 and 15, 1965. Planetary science mode was turned on at 15:41:49 GMT on 14 July. The camera sequence started at 00:18:36 GMT on July 15 and 21 pictures plus 21 lines of a 22nd picture were taken. The images covered a discontinuous swath of Mars starting near 40 N, 170 E, down to about 35 S, 200 E, and then across to the terminator at 50 S, 255 E, representing about 1% of the planet's surface. The closest approach was 9,846 km from the Martian surface at 01:00:57 GMT 15 July 1965. The images taken during the flyby were stored in the onboard tape recorder. At 02:19:11 GMT Mariner 4 passed behind Mars as seen from Earth and the radio signal ceased. The signal was reacquired at 03:13:04 GMT when the spacecraft reappeared. Cruise mode was then re-established. Transmission of the taped images to Earth began about 8.5 hours after signal reacquisition and continued until 3 August. All images were transmitted twice to insure no data was missing or corrupt.
The spacecraft performed all programmed activities successfully and returned useful data from launch until 22:05:07 GMT on 1 October 1965, when the distance from Earth (309.2 million km) and the antenna orientation temporarily halted signal acquisition. In 1967 Mariner 4 returned to the vicinity of Earth again and engineers decided to use the ageing craft for a series of operational and telemetry tests to improve their knowledge of the technologies that would be needed for future interplanetary spacecraft. The cosmic dust detector registered 17 hits in a 15 minute span on 15 September, part of an apparent micrometeoroid shower which temporarily changed the spacecraft attitude and probably slightly damaged the thermal shield. On 7 December the gas supply in the attitude control system was exhausted, and on December 10 and 11 a total of 83 micrometeoroid hits were recorded which caused perturbation of the attitude and degradation of the signal strength. On 21 December 1967 communications with Mariner 4 were terminated.
Results
The total data returned by the mission was 5.2 million bits. All experiments operated successfully with the exception of the ionization chamber/Geiger counter which failed in February, 1965 and the plasma probe, which had its performance degraded by a resistor failure on 6 December 1964. The images returned showed a Moon-like cratered terrain (which later missions showed was not typical for Mars, but only for the more ancient region imaged by Mariner 4). A surface atmospheric pressure of 4.1 to 7.0 mb was estimated and no magnetic field was detected.
1964 November 30 - .
LV Family:
Atlas.
Launch Vehicle:
Atlas Agena D SLV-3.
- Lockheed shipped Gemini Agena target vehicle (GATV) 5001 to its Santa Cruz Test Base for captive-firing tests. - .
Nation: USA. Flight: Gemini 12. Summary: Primary test objective was verifying the operational capabilities of the GATV during actual firing of the primary and secondary propulsion systems. . Additional Details: here....
1964 December - .
LV Family:
Atlas.
Launch Vehicle:
Atlas D.
- Atlas SMS 565 deactivated. - .
Nation: USA. Summary: Warren-2 AFB SMS 565 deactivated.
1964 December 1 - .
08:45 GMT - .
Launch Site:
Vandenberg.
Launch Complex:
Vandenberg 576A1.
LV Family:
Atlas.
Launch Vehicle:
Atlas D.
LV Configuration: Atlas D 210D.
- ABRES LORV-5 re-entry vehicle test flight - .
Nation: USA. Agency: USAF SAC. Apogee: 1,800 km (1,100 mi).
1964 December 4 - .
11:09 GMT - .
Launch Site:
Vandenberg.
Launch Complex:
Vandenberg 576A3.
LV Family:
Atlas.
Launch Vehicle:
Atlas D.
LV Configuration: Atlas D 300D.
- NTMP RMV-303 Target mission - .
Nation: USA. Agency: USAF SAC. Apogee: 1,800 km (1,100 mi).
1964 December 4 - .
18:57 GMT - .
Launch Site:
Vandenberg.
Launch Complex:
Vandenberg SLC4E.
LV Family:
Atlas.
Launch Vehicle:
Atlas Agena D SLV-3.
LV Configuration: SLV-3 Agena D 7105 / Agena D 7105.
- KH 7-14 - .
Payload: KH-7 no. 14 / OPS 4439. Mass: 2,000 kg (4,400 lb). Nation: USA. Agency: NRO; USAF. Class: Surveillance. Type: Military surveillance satellite. Spacecraft: KH-7. Decay Date: 1964-12-05 . USAF Sat Cat: 946 . COSPAR: 1964-079A. Apogee: 357 km (221 mi). Perigee: 158 km (98 mi). Inclination: 97.0000 deg. Period: 89.70 min. Summary: KH-7 type satellite. Space craft engaged in investigation of spaceflight techniques and technology (US Cat A). .
1964 December 11 - .
14:25 GMT - .
Launch Site:
Cape Canaveral.
Launch Complex:
Cape Canaveral LC36A.
LV Family:
Atlas.
Launch Vehicle:
Atlas Centaur.
LV Configuration: Atlas Centaur AC-4 / Centaur D 146D.
- Surveyor SD-1 - .
Payload: Surveyor SD-1. Mass: 2,944 kg (6,490 lb). Nation: USA. Agency: NASA; JPL. Class: Moon. Type: Lunar probe. Spacecraft: Surveyor. Decay Date: 1964-12-12 . USAF Sat Cat: 951 . COSPAR: 1964-082A. Apogee: 178 km (110 mi). Perigee: 165 km (102 mi). Inclination: 30.7000 deg. Period: 87.80 min. Summary: Launch vehicle test. Centaur AC-4 put dummy Surveyor payload into geosynchronous transfer orbit.
1964 December 12 - .
LV Family:
Atlas.
Launch Vehicle:
Atlas Agena D SLV-3.
- Gemini Program Office (GPO) reported that it had initiated contractual action to delete the eighth Agena from the Gemini Agena target vehicle program. - .
Nation: USA. Summary: On March 6, 1965, GPO reported its decision to eliminate the seventh Agena as well..
1964 December 15 - .
LV Family:
Atlas.
Launch Vehicle:
Atlas D.
- Atlas SMS 566 deactivated. - .
Nation: USA. Summary: Offutt AFB SMS 566 deactivated.
1964 December 17 - .
LV Family:
Atlas.
Launch Vehicle:
Atlas Agena D SLV-3.
- Air Force Space Systems Division officially accepted Agena D (AD-82) for the Gemini program. - .
Nation: USA. Flight: Gemini 6. Summary: Lockheed then transferred it to the vehicle final assembly area for modification to Gemini Agena target vehicle 5002. Work was scheduled to begin in mid-January 1965..
1964 December 22 - .
19:15 GMT - .
Launch Site:
Vandenberg.
Launch Complex:
Vandenberg 576E.
LV Family:
Atlas.
Launch Vehicle:
Atlas F.
LV Configuration: Atlas F 111F.
- ST - .
Nation: USA. Agency: USAF SAC. Apogee: 1,400 km (800 mi).
1965 January 8 - .
18:59 GMT - .
Launch Site:
Vandenberg.
Launch Complex:
Vandenberg OSTF2.
LV Family:
Atlas.
Launch Vehicle:
Atlas F.
LV Configuration: Atlas F 106F.
- ST - .
Nation: USA. Agency: USAF SAC. Apogee: 1,400 km (800 mi).
1965 January 12 - .
14:32 GMT - .
Launch Site:
Vandenberg.
Launch Complex:
Vandenberg 576B1.
LV Family:
Atlas.
Launch Vehicle:
Atlas D.
LV Configuration: Atlas D 166D.
- NTMP RMV-302 Target mission - .
Nation: USA. Agency: USAF SAC. Apogee: 1,800 km (1,100 mi).
1965 January 20 - .
LV Family:
Atlas.
Launch Vehicle:
Atlas Agena D SLV-3.
- Gemini Agena target vehicle 5001 underwent a successful hot-firing test at Lockheed's Santa Cruz Test Base. - .
Nation: USA. Flight: Gemini 12. The test simulated a full 20,000-second mission, including multiple firings of both the primary and secondary propulsion systems and transmission of operational data in real time to two PCM (pulse-code-modulated) telemetry ground stations, one at the test site and one in Sunnyvale. Major test anomaly was a series of command programmer time-accumulator jumps, seven of which totaled 77,899 seconds. The vehicle was removed from the test stand on February 1 and returned to Sunnyvale.
1965 January 21 - .
21:34 GMT - .
Launch Site:
Vandenberg.
Launch Complex:
Vandenberg 576B3.
LV Family:
Atlas.
Launch Vehicle:
Atlas D.
LV Configuration: Atlas D 172D.
FAILURE: Failure.
Failed Stage: 1.
- OV1-01 - .
Payload: ABRES MTV-1. Mass: 85 kg (187 lb). Nation: USA. Agency: USAF. Class: Earth. Type: Magnetosphere satellite. Spacecraft: OV1. Decay Date: 1965-01-21 . COSPAR: F650121A. Summary: Failure..
- OV1-1 - .
Payload: OV1-1. Nation: USA. Agency: USAF SAC. Spacecraft: OV1. COSPAR: F650121B.
1965 January 23 - .
20:09 GMT - .
Launch Site:
Vandenberg.
Launch Complex:
Vandenberg SLC4W.
LV Family:
Atlas.
Launch Vehicle:
Atlas Agena D SLV-3.
LV Configuration: SLV-3 Agena D 7106 / Agena D 7106.
- KH 7-15 - .
Payload: KH-7 no. 15 / OPS 4703. Mass: 2,000 kg (4,400 lb). Nation: USA. Agency: NRO; USAF. Class: Surveillance. Type: Military surveillance satellite. Spacecraft: KH-7. Decay Date: 1965-01-29 . USAF Sat Cat: 980 . COSPAR: 1965-005A. Apogee: 291 km (180 mi). Perigee: 146 km (90 mi). Inclination: 102.5000 deg. Period: 88.90 min. Summary: KH-7 type satellite. Space craft engaged in investigation of spaceflight techniques and technology (US Cat A). .
1965 February 1 - .
LV Family:
Atlas.
Launch Vehicle:
Atlas Agena D SLV-3.
- Gemini Agena target vehicle (GATV) 5001 was removed from the test stand at Santa Cruz Test Base and returned to Sunnyvale. - .
Nation: USA. Flight: Gemini 12. Summary: After a brief stopover in systems test complex C-10, the vehicle was transferred to the anechoic chamber for elecromagnetic interference and radio-frequency-interference tests. . Additional Details: here....
1965 February - .
LV Family:
Atlas.
Launch Vehicle:
Atlas Agena D SLV-3.
- Lockheed initiated a "Ten-point Plan for C&C Equipment." - .
Nation: USA. The Agena command and communication (C and C) system comprised the electronic systems for tracking the vehicle, for monitoring the performance of its various subsystems, and for verifying operating commands for orbital operations. Because of the unique requirements of the Gemini mission, in particular rendezvous and docking, Lockheed had had to design and develop a new C and C system for the Gemini target vehicle. Numerous failures and problems calling for rework during the initial manufacturing stages of the C and C system suggested the existence of mechanical and electronic design deficiencies. Aerospace, which had assumed technical surveillance functions for the Gemini Agena in the fall of 1964, was instrumental in bringing these problems to the attention of Air Force and Lockheed top management. Among the results of the 10-point plan were several redesigned programmer circuits and packaging changes, closer monitoring of vendor work, expedited failure analysis, and improved quality control.
1965 February 17 - .
17:05 GMT - .
Launch Site:
Cape Canaveral.
Launch Complex:
Cape Canaveral LC12.
LV Family:
Atlas.
Launch Vehicle:
Atlas Agena B.
LV Configuration: Atlas Agena B 196D (AA13) / Agena B 6006 (AA13).
- Ranger 8 - .
Payload: RA-8. Mass: 366 kg (806 lb). Nation: USA. Agency: NASA; JPL. Program: Ranger. Class: Moon. Type: Lunar probe. Spacecraft: Ranger 6-7-8-9. Decay Date: 1965-02-20 . USAF Sat Cat: 1086 . COSPAR: 1965-010A. 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.
1965 February 27 - .
11:11 GMT - .
Launch Site:
Vandenberg.
Launch Complex:
Vandenberg 576A1.
LV Family:
Atlas.
Launch Vehicle:
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).
1965 March 2 - .
09:52 GMT - .
Launch Site:
Vandenberg.
Launch Complex:
Vandenberg 576A3.
LV Family:
Atlas.
Launch Vehicle:
Atlas D.
LV Configuration: Atlas D 301D.
- NTMP RMV-301 Target mission - .
Nation: USA. Agency: USAF SAC. Apogee: 1,800 km (1,100 mi).
1965 March 2 - .
13:25 GMT - .
Launch Site:
Cape Canaveral.
Launch Complex:
Cape Canaveral LC36A.
LV Family:
Atlas.
Launch Vehicle:
Atlas Centaur.
LV Configuration: Atlas Centaur AC-5 / Centaur D 156D.
FAILURE: Failure.
Failed Stage: 2.
- Surveyor SD-1 - .
Payload: Surveyor SD-1. Mass: 951 kg (2,096 lb). Nation: USA. Agency: NASA. Spacecraft: Surveyor. Decay Date: 1965-03-02 . COSPAR: F650302A. Summary: Launch vehicle test. Launch vehicle was to have put payload into geosynchronous transfer orbit.
1965 March 9 - .
LV Family:
Atlas.
Launch Vehicle:
Atlas Agena D SLV-3.
- Gemini Agena target vehicle 5001 completed electromagnetic compatibility tests in the anechoic chamber at Sunnyvale. - .
Nation: USA. Flight: Gemini 12. It remained in the chamber, however, until March 17 while Lockheed verified the corrective action that had been taken to eliminate programmer time-accumulator jumps and telemetry synchronization problems. The vehicle was then transferred to systems test complex C-10 for final Vehicle Systems Tests on March 18.
1965 March 10 - .
LV Family:
Atlas;
Titan.
- Air Force Space Systems Division repeated its position that on Gemini-Titan 6 the nominal plan should not call for use in orbit of the Agena primary propulsion system. - .
Nation: USA. Flight: Gemini 6. At a meeting of the Gemini Trajectory and Orbits Panel, Air Force Space Systems Division repeated its position that on Gemini-Titan 6 the nominal plan should not call for use in orbit of the Agena primary propulsion system, since it would not be qualified in actual flight before this mission. Additional Details: here....
1965 March 12 - .
19:25 GMT - .
Launch Site:
Vandenberg.
Launch Complex:
Vandenberg SLC4W.
LV Family:
Atlas.
Launch Vehicle:
Atlas Agena D SLV-3.
LV Configuration: SLV-3 Agena D 7104 / Agena D 7104.
- KH 7-16 - .
Payload: KH-7 no. 16 / OPS 4920. Mass: 2,000 kg (4,400 lb). Nation: USA. Agency: NRO; USAF. Class: Surveillance. Type: Military surveillance satellite. Spacecraft: KH-7. Decay Date: 1965-03-17 . USAF Sat Cat: 1247 . COSPAR: 1965-019A. Apogee: 358 km (222 mi). Perigee: 223 km (138 mi). Inclination: 107.5000 deg. Period: 90.30 min. Summary: KH-7 type satellite. Space craft engaged in investigation of spaceflight techniques and technology (US Cat A). .
1965 March 12 - .
23:21 GMT - .
Launch Site:
Vandenberg.
Launch Complex:
Vandenberg 576B3.
LV Family:
Atlas.
Launch Vehicle:
Atlas D.
LV Configuration: Atlas D 154D.
- ABRES MTV-2 re-entry vehicle test flight - .
Nation: USA. Agency: USAF SAC. Apogee: 1,800 km (1,100 mi).
1965 March 18 - .
LV Family:
Atlas.
Launch Vehicle:
Atlas Agena D SLV-3.
- Gemini Agena target vehicle (GATV) 5001 was transferred from the anechoic chamber to systems test complex C-10. - .
Nation: USA. Flight: Gemini 12. Summary: Six days were scheduled for vehicle modifications before beginning final systems tests. . Additional Details: here....
1965 March 21 - .
21:37 GMT - .
Launch Site:
Cape Canaveral.
Launch Complex:
Cape Canaveral LC12.
LV Family:
Atlas.
Launch Vehicle:
Atlas Agena B.
LV Configuration: Atlas Agena B 204D (AA14) / Agena B 6007 (AA14).
- Ranger 9 - .
Payload: RA-9. Mass: 366 kg (806 lb). Nation: USA. Agency: NASA; JPL. Program: Ranger. Class: Moon. Type: Lunar probe. Spacecraft: Ranger 6-7-8-9. Decay Date: 1965-03-24 . USAF Sat Cat: 1294 . COSPAR: 1965-023A. Ranger 9, last of the series, returned 5814 images before lunar impact. The target was Alphonsus, a large crater about 12 degrees south of the lunar equator. The probe was timed to arrive when lighting conditions would be at their best. The Atlas- Agena B booster injected the Agena and Ranger 9 into an Earth parking orbit at 185 km altitude. A 90 second Agena 2nd burn put the spacecraft into lunar transfer trajectory. This was followed by the separation of the Agena and Ranger. The initial trajectory was highly accurate; uncorrected, the craft would have landed only 650 km north of Alphonsus. 70 minutes after launch the command was given to deploy solar panels, activate attitude control, and switch from the omni-directional antenna to the high-gain antenna. The accuracy of the initial trajectory enabled delay of the planned mid-course correction from 22 March to 23 March when the manoeuvre was initiated at 12:03 GMT. After orientation, a 31 second rocket burn at 12:30 GMT, and reorientation, the manoeuvre was completed at 13:30 GMT. Ranger 9 reached the Moon on 24 March 1965. At 13:31 GMT a terminal manoeuvre was executed to orient the spacecraft so the cameras were more in line with the flight direction to improve the resolution of the pictures. Twenty minutes before impact the one-minute camera system warm-up began. The first image was taken at 13:49:41 at an altitude of 2363 km. Transmission of 5,814 good contrast photographs was made during the final 19 minutes of flight. The final image taken before impact has a resolution of 0.3 meters. The spacecraft encountered the lunar surface with an incoming asymptotic direction at an angle of -5.6 degrees from the lunar equator. The orbit plane was inclined 15.6 degrees to the lunar equator. After 64.5 hours of flight, impact occurred at 14:08:19.994 GMT at approximately 12.83 S latitude, 357.63 E longitude in the crater Alphonsus. Impact velocity was 2.67 km/s. Millions of Americans followed the spacecraft's descent via real time television coverage provided to the three networks of many of the F-channel images (primarily camera B but also some camera A pictures) were provided for this flight.
The pictures showed the rim and floor of the crater in fine detail: in those just prior to impact, objects less than a foot in size were discernible.
A panel of scientists presented some preliminary conclusions from Ranger IX at a press conference that same afternoon. Crater rims and ridges inside the walls, they believed, were harder and smoother than the moon's dusty plains, and therefore were considered likely sites for future manned landings. Generally, the panel was dubious about landing on crater floors however. Apparently, the floors were solidified volcanic material incapable of supporting a spacecraft. Investigators believed several types of craters were seen that were of nonmeteoric origin. These findings reinforced arguments that the moon at one time had experienced volcanic activity. Later the images were shown to the press as a continuous-motion movie, leading astronaut Wally Schirra to yell ‘bail out you fool!’ just before the final frame.
1965 March 23-24 - .
LV Family:
Atlas;
Titan.
- Gemini Agena Target Vehicle (GATV) Management-Technical Review. - .
Nation: USA. Flight: Gemini 12; Gemini 3. Summary: Representatives of Air Force Space Systems Division (SSD), Aerospace, Lockheed, and Gemini Program Office met at Sunnyvale for the monthly Gemini Agena Target Vehicle (GATV) Management-Technical Review. . Additional Details: here....
1965 March 25 - .
LV Family:
Atlas.
Launch Vehicle:
Atlas.
- Six Atlas squadrons deactivated. - .
Nation: USA. Summary: Forbes AFB SMS 548, Warren-3 AFB SMS 549, Altus AFB SMS 577, Dyess AFB SMS 578, Walker AFB SMS 579, and Plattsburgh AFB SMS 556 all deactivated.
1965 March 26 - .
09:01 GMT - .
Launch Site:
Vandenberg.
Launch Complex:
Vandenberg 576A1.
LV Family:
Atlas.
Launch Vehicle:
Atlas D.
LV Configuration: Atlas D 297D.
- ABRES LORV-7 re-entry vehicle test flight - .
Nation: USA. Agency: USAF AFSC. Apogee: 1,800 km (1,100 mi).
1965 April 3 - .
21:24 GMT - .
Launch Site:
Vandenberg.
Launch Complex:
Vandenberg SLC4E.
LV Family:
Atlas.
Launch Vehicle:
Atlas Agena D SLV-3.
LV Configuration: SLV-3 Agena D 7401.
- Snapshot - .
Payload: SNAP 10A / Agena D / OPS 4682. Mass: 440 kg (970 lb). Nation: USA. Agency: USAF; AEC. Class: Technology. Type: Ion engine technology satellite. Spacecraft: Snapshot. USAF Sat Cat: 1314 . COSPAR: 1965-027A. Apogee: 1,314 km (816 mi). Perigee: 1,270 km (780 mi). Inclination: 90.3000 deg. Period: 111.40 min. Only nuclear reactor ever orbited by the United States. The SNAP-10A reactor provided electrical power for an 8.5 mN ion engine using cesium propellant. The engine was shut off after one hour of operation when high-voltage spikes created electromagnetic interference with the satellite's attitude control system sensors. The reactor continued in operation, generating 39 kWt and more than 500 watts of electrical power for 43 days before the spacecraft telemetry failed.
- SECOR 4 - .
Payload: EGRS 4. Mass: 40 kg (88 lb). Nation: USA. Agency: USA ACE. Class: Earth. Type: Geodetic satellite. Spacecraft: SECOR. USAF Sat Cat: 1315 . COSPAR: 1965-027B. Apogee: 1,316 km (817 mi). Perigee: 1,267 km (787 mi). Inclination: 90.2000 deg. Period: 111.40 min. Summary: Failed. Space craft engaged in investigation of spaceflight techniques and technology (US Cat A)..
1965 April 6 - .
13:34 GMT - .
Launch Site:
Vandenberg.
Launch Complex:
Vandenberg 576B1.
LV Family:
Atlas.
Launch Vehicle:
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).
1965 April 28 - .
20:17 GMT - .
Launch Site:
Vandenberg.
Launch Complex:
Vandenberg SLC4E.
LV Family:
Atlas.
Launch Vehicle:
Atlas Agena D SLV-3.
LV Configuration: SLV-3 Agena D 7107 / Agena D 7107.
- KH 7-17 - .
Payload: KH-7 no. 17 / OPS 4983. Mass: 2,000 kg (4,400 lb). Nation: USA. Agency: NRO; USAF. Class: Surveillance. Type: Military surveillance satellite. Spacecraft: KH-7. Decay Date: 1965-05-03 . USAF Sat Cat: 1327 . COSPAR: 1965-031A. Apogee: 259 km (160 mi). Perigee: 180 km (110 mi). Inclination: 95.6000 deg. Period: 89.00 min. Summary: KH-7 type satellite. Space craft engaged in investigation of spaceflight techniques and technology (US Cat A). .
- OPS 6717 - .
Payload: EHH B1. Mass: 60 kg (132 lb). Nation: USA. Agency: NRO; USAF. Class: Military. Type: Military naval signals reconnaisance satellite. Spacecraft: SSF. Decay Date: 1969-10-31 . USAF Sat Cat: 1329 . COSPAR: 1965-031B. Apogee: 547 km (339 mi). Perigee: 506 km (314 mi). Inclination: 95.2000 deg. Period: 95.10 min. Summary: Radar monitoring..
1965 May 6 - .
LV Family:
Atlas.
Launch Vehicle:
Atlas Agena D SLV-3.
- Gemini Agena target vehicle (GATV) 5001 completed vehicle systems testing with a final simulated flight. - .
Nation: USA. Flight: Gemini 12. Summary: The vehicle was disconnected from the test complex on May 14, and data analysis was completed May 19. Meanwhile, the First Article Configuration Inspection on GATV 5001 began on May 10..
1965 May 10 - .
LV Family:
Atlas.
Launch Vehicle:
Atlas Agena D SLV-3.
- First Article Configuration Inspection (FACI) of Gemini Agena target vehicle (GATV) 5001 at Sunnyvale. - .
Nation: USA. Flight: Gemini 12; Gemini 6. Summary: A team of representatives from NASA, Air Force Space Systems Division, Aerospace, and Lockheed began the First Article Configuration Inspection (FACI) of Gemini Agena target vehicle (GATV) 5001 at Sunnyvale. . Additional Details: here....
1965 May 18 - .
LV Family:
Atlas.
Launch Vehicle:
Atlas Agena D SLV-3.
- Gemini Agena target vehicle (GATV) 5002 completed final assembly and was transferred to systems test complex C-10 at Sunnyvale to begin Vehicle Systems Tests. - .
Nation: USA. Flight: Gemini 6. The transfer had been scheduled for May 5 but was delayed by parts shortages, engineering problems, and considerable work backlog. The major source of delay was correcting a gap between the forward auxiliary rack and the vehicle; machining and aligning the rack and refinishing the scraped surfaces proved time-consuming. GATV 5002 was still short several items of command equipment. Systems testing began May 21.
1965 May 22 - .
21:55 GMT - .
Launch Site:
Cape Canaveral.
Launch Complex:
Cape Canaveral LC12.
LV Family:
Atlas.
Launch Vehicle:
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.
1965 May 27 - .
19:30 GMT - .
Launch Site:
Vandenberg.
Launch Complex:
Vandenberg SLC4E.
LV Family:
Atlas.
Launch Vehicle:
Atlas Agena D SLV-3.
LV Configuration: SLV-3 Agena D 7108 / Agena D 7108.
- KH 7-18 - .
Payload: KH-7 no. 18 / OPS 5236. Mass: 2,000 kg (4,400 lb). Nation: USA. Agency: NRO; USAF. Class: Surveillance. Type: Military surveillance satellite. Spacecraft: KH-7. Decay Date: 1965-06-01 . USAF Sat Cat: 1386 . COSPAR: 1965-041A. Apogee: 267 km (165 mi). Perigee: 149 km (92 mi). Inclination: 95.6000 deg. Period: 88.70 min. Summary: KH-7 type satellite. Space craft engaged in investigation of spaceflight techniques and technology (US Cat A). .
1965 May 28 - .
02:54 GMT - .
Launch Site:
Vandenberg.
Launch Complex:
Vandenberg 576B3.
LV Family:
Atlas.
Launch Vehicle:
Atlas D.
LV Configuration: Atlas D 68D / OV-1.
FAILURE: Failure..
Failed Stage: 1.
- OV1-03 - .
Nation: USA. Agency: USAF AFSC. Class: Earth. Type: Magnetosphere satellite. Spacecraft: OV1. Decay Date: 1965-05-28 . COSPAR: F650528A.
1965 May 29 - .
LV Family:
Atlas.
Launch Vehicle:
Atlas Agena D SLV-3.
- Gemini Agena target vehicle 5001 arrived at Cape Kennedy following its conditional acceptance by the Air Force on May 27. - .
Nation: USA. Flight: Gemini 6. It was moved to the Missile Assembly Building (Hanger E) for testing. The target vehicle was mated with target docking adapter No. 1 on June 18, and Combined Interface Tests began June 19. Testing was completed July 8 with secondary propulsion system (SPS) functional and static leak checks, SPS installation and postinstallation checks, and thermal control surface preparation. Target vehicle 5001 was then transferred to complex 14 to be mated to target launch vehicle 5301.
1965 June 3 - .
10:38 GMT - .
Launch Site:
Vandenberg.
Launch Complex:
Vandenberg 576B2.
LV Family:
Atlas.
Launch Vehicle:
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).
1965 June 8 - .
15:17 GMT - .
Launch Site:
Vandenberg.
Launch Complex:
Vandenberg 576A1.
LV Family:
Atlas.
Launch Vehicle:
Atlas D.
LV Configuration: Atlas D 299D.
- ABRES LORV-6 re-entry vehicle test flight - .
Nation: USA. Agency: USAF AFSC. Apogee: 1,800 km (1,100 mi).
1965 June 10 - .
12:26 GMT - .
Launch Site:
Vandenberg.
Launch Complex:
Vandenberg 576A3.
LV Family:
Atlas.
Launch Vehicle:
Atlas D.
LV Configuration: Atlas D 302D.
- NTMP RMV-303 re-entry vehicle test flight - .
Nation: USA. Agency: USAF AFSC. Apogee: 1,800 km (1,100 mi).
1965 June 25 - .
LV Family:
Atlas.
Launch Vehicle:
Atlas.
- Three Atlas squadrons deactivated. - .
Nation: USA. Summary: Fairchild AFB SMS 567, Schilling AFB SMS 550, and Lincoln AFB SMS 551 all deactivated.
1965 June 25 - .
19:30 GMT - .
Launch Site:
Vandenberg.
Launch Complex:
Vandenberg SLC4E.
LV Family:
Atlas.
Launch Vehicle:
Atlas Agena D SLV-3.
LV Configuration: SLV-3 Agena D 7109 / Agena D 7109.
- OPS 6749 - .
Payload: EHH B2. Mass: 60 kg (132 lb). Nation: USA. Agency: NRO; USAF. Class: Military. Type: Military naval signals reconnaisance satellite. Spacecraft: SSF. Decay Date: 1968-08-22 . USAF Sat Cat: 1422 . COSPAR: 1965-050A. Apogee: 510 km (310 mi). Perigee: 496 km (308 mi). Inclination: 107.6000 deg. Period: 94.70 min. Summary: Radar monitoring..
- KH 7-19 - .
Payload: KH-7 no. 19 / OPS 5501. Mass: 2,000 kg (4,400 lb). Nation: USA. Agency: NRO; USAF. Class: Surveillance. Type: Military surveillance satellite. Spacecraft: KH-7. Decay Date: 1965-06-30 . USAF Sat Cat: 1424 . COSPAR: 1965-050B. Apogee: 349 km (216 mi). Perigee: 254 km (157 mi). Inclination: 107.6000 deg. Period: 90.50 min. Summary: KH-7 type satellite. Space craft engaged in investigation of spaceflight techniques and technology (US Cat A). .
1965 June 30 - .
LV Family:
Atlas.
Launch Vehicle:
Atlas Agena D SLV-3.
- Gemini Agena target vehicle 5002 completed Vehicle Systems Tests at Sunnyvale, and the final acceptance test was conducted. - .
Nation: USA. Flight: Gemini 6. Summary: The vehicle was disconnected from the test complex on July 13, after NASA, Air Force Space Systems Division, Aerospace, and Lockheed representatives agreed that all data discrepancies from the final systems tests had been resolved..
1965 July 1 - .
09:54 GMT - .
Launch Site:
Vandenberg.
Launch Complex:
Vandenberg 576B1.
LV Family:
Atlas.
Launch Vehicle:
Atlas D.
LV Configuration: Atlas D 59D.
- NTMP KX-32 re-entry vehicle test flight - .
Nation: USA. Agency: USAF AFSC. Apogee: 1,800 km (1,100 mi).
1965 July 12 - .
19:00 GMT - .
Launch Site:
Vandenberg.
Launch Complex:
Vandenberg SLC4E.
LV Family:
Atlas.
Launch Vehicle:
Atlas Agena D SLV-3.
LV Configuration: SLV-3 Agena D 7112.
FAILURE: Failure.
Failed Stage: U.
- KH-7-20 - .
Payload: KH-7 no. 20. Mass: 2,000 kg (4,400 lb). Nation: USA. Agency: USAF. Class: Surveillance. Type: Military surveillance satellite. Spacecraft: KH-7. Decay Date: 1965-07-12 . COSPAR: F650712A. Summary: KH-7 type satellite..
1965 July 20 - .
08:27 GMT - .
Launch Site:
Cape Canaveral.
Launch Complex:
Cape Canaveral LC13.
LV Family:
Atlas.
Launch Vehicle:
Atlas Agena D.
LV Configuration: Atlas Agena D 225D / Agena D 1803.
- Vela 5 - .
Payload: Vela 3A / OPS 6577. Mass: 235 kg (518 lb). Nation: USA. Agency: USAF. Class: Surveillance. Type: Nuclear detection surveillance satellite. Spacecraft: Vela. USAF Sat Cat: 1458 . COSPAR: 1965-058A. Apogee: 115,839 km (71,978 mi). Perigee: 106,367 km (66,093 mi). Inclination: 35.2000 deg. Period: 6,679.00 min. Summary: Space craft engaged in investigation of spaceflight techniques and technology (US Cat A)..
- ORS 3 - .
Payload: ERS 17. Mass: 5.00 kg (11.00 lb). Nation: USA. Agency: USAF. Class: Earth. Type: Magnetosphere satellite. Spacecraft: ERS. Decay Date: 1968-07-01 . USAF Sat Cat: 1460 . COSPAR: 1965-058C. Apogee: 111,793 km (69,464 mi). Perigee: 566 km (351 mi). Inclination: 36.9000 deg. Period: 2,595.40 min. Summary: Radiation data. Space craft engaged in investigation of spaceflight techniques and technology (US Cat A). .
- Vela 6 - .
Payload: Vela 3B / OPS 6564. Mass: 235 kg (518 lb). Nation: USA. Agency: USAF. Class: Surveillance. Type: Nuclear detection surveillance satellite. Spacecraft: Vela. USAF Sat Cat: 1459 . COSPAR: 1965-058B. Apogee: 121,281 km (75,360 mi). Perigee: 101,715 km (63,202 mi). Inclination: 34.2000 deg. Period: 6,712.70 min. Summary: Space craft engaged in investigation of spaceflight techniques and technology (US Cat A)..
1965 July 22 - .
LV Family:
Atlas;
Titan.
- Simultaneous Launch Demonstration (SLD) of Gemini Atlas-Agena target vehicle and Gemini-Titan (GT) 5. - .
Nation: USA. Flight: Gemini 5. Summary: A Simultaneous Launch Demonstration (SLD) was conducted between the Gemini Atlas-Agena target vehicle on complex 14 and Gemini-Titan (GT) 5 on complex 19, in conjunction with the Wet Mock Simulated Launch (WMSL) of GT-5. . Additional Details: here....
1965 July 23 - .
LV Family:
Atlas.
Launch Vehicle:
Atlas Agena D SLV-3.
- Air Force Space Systems Division formally accepted delivery of Gemini Agena target vehicle (GATV) 5002 after the vehicle acceptance team inspection had been completed. - .
Nation: USA. Flight: Gemini 6. The vehicle was then shipped by air to Eastern Test Range on July 24, arriving July 25. Although GATV 5002 was accepted, several items of equipment remained in 'not qualified' status, including the shroud, secondary and primary propulsion systems, and components of both the electrical power and command systems.
1965 July 23 - .
LV Family:
Atlas.
Launch Vehicle:
Atlas Agena D SLV-3.
- Standard Agena D (AD-108), which had been completed in June and held in storage, was transferred to Building 104 at Sunnyvale for modifications and final assembly as Gemini Agena target vehicle 5003. - .
Nation: USA. Flight: Gemini 8. Summary: While in storage, several pieces of AD-108 equipment had been removed for modification to the Gemini configuration. Final assembly began August 8..
1965 August 3 - .
19:12 GMT - .
Launch Site:
Vandenberg.
Launch Complex:
Vandenberg SLC4E.
LV Family:
Atlas.
Launch Vehicle:
Atlas Agena D SLV-3.
LV Configuration: SLV-3 Agena D 7111 / Agena D 7111.
- KH 7-21 - .
Payload: KH-7 no. 21 / OPS 5698. Mass: 2,000 kg (4,400 lb). Nation: USA. Agency: NRO; USAF. Class: Surveillance. Type: Military surveillance satellite. Spacecraft: KH-7. Decay Date: 1965-08-07 . USAF Sat Cat: 1471 . COSPAR: 1965-062A. Apogee: 352 km (218 mi). Perigee: 278 km (172 mi). Inclination: 107.4000 deg. Period: 90.80 min. Summary: KH-7 type satellite. Space craft engaged in investigation of spaceflight techniques and technology (US Cat A). .
- OPS 6761 - .
Payload: EHH B3. Mass: 60 kg (132 lb). Nation: USA. Agency: NRO; USAF. Class: Military. Type: Military naval signals reconnaisance satellite. Spacecraft: SSF. Decay Date: 1968-06-17 . USAF Sat Cat: 1472 . COSPAR: 1965-062B. Apogee: 515 km (320 mi). Perigee: 501 km (311 mi). Inclination: 107.4000 deg. Period: 94.80 min. Summary: Radar monitoring..
1965 August 4 - .
12:43 GMT - .
Launch Site:
Vandenberg.
Launch Complex:
Vandenberg 576B1.
LV Family:
Atlas.
Launch Vehicle:
Atlas D.
LV Configuration: Atlas D 183D.
- ABRES WAC-5 re-entry vehicle test flight - .
Nation: USA. Agency: USAF AFSC. Apogee: 1,800 km (1,100 mi).
1965 August 5 - .
13:21 GMT - .
Launch Site:
Vandenberg.
Launch Complex:
Vandenberg 576A2.
LV Family:
Atlas.
Launch Vehicle:
Atlas F.
LV Configuration: Atlas F 147F.
- ABRES LORV-2A re-entry vehicle test flight - .
Nation: USA. Agency: USAF AFSC. Apogee: 1,400 km (800 mi).
1965 August 11 - .
14:31 GMT - .
Launch Site:
Cape Canaveral.
Launch Complex:
Cape Canaveral LC36B.
LV Family:
Atlas.
Launch Vehicle:
Atlas Centaur D.
LV Configuration: Atlas Centaur D AC-6 / Centaur D 151D.
- Surveyor; Atlas Centaur 6 - .
Payload: Surveyor-SD-2. Mass: 950 kg (2,090 lb). Nation: USA. Agency: NASA; JPL. Class: Moon. Type: Lunar probe. Spacecraft: Surveyor. USAF Sat Cat: 1503 . COSPAR: 1965-064A. Summary: Centaur AC-6 launched dummy Surveyor payload into a barycentric / translunar orbit..
1965 August 23 - .
LV Family:
Atlas.
Launch Vehicle:
Atlas Agena D SLV-3.
- Gemini Agena target vehicle 5002 completed preliminary systems testing at Hanger E. - .
Nation: USA. Flight: Gemini 6. Gemini Agena target vehicle 5002 completed preliminary systems testing at Hanger E and was transferred to Merritt Island Launch Area, where it was joined by spacecraft No. 6 for Plan X testing. After ground equipment checks, Plan X tests proceeded on August 25. No significant interference problems were found, and testing ended on August 31.
1965 August 26 - .
11:20 GMT - .
Launch Site:
Vandenberg.
Launch Complex:
Vandenberg 576B2.
LV Family:
Atlas.
Launch Vehicle:
Atlas D.
LV Configuration: Atlas D 61D.
- NTMP KX-41 re-entry vehicle test flight - .
Nation: USA. Agency: USAF AFSC. Apogee: 1,800 km (1,100 mi).
1965 September 1 - .
LV Family:
Atlas.
Launch Vehicle:
Atlas Agena D SLV-3.
- Final troubleshooting on Gemini Agena target vehicle (GATV) 5002 after Plan X testing at Merritt Island Launch Area (MILA) was completed. - .
Nation: USA. Flight: Gemini 6. Summary: The next day GATV 5002 was returned to Hanger E from MILA, where it began a series of tests to verify the operational readiness of all vehicle systems prior to erection and mating with the launch vehicle..
1965 September 8 - .
LV Family:
Atlas.
Launch Vehicle:
Atlas Agena D SLV-3.
- Representatives of Air Force Space Systems Division, Aerospace, and Lockheed attended a technical review of the flight verification test program for the oxidizer gas generator solenoid valve. - .
Nation: USA. This was the last remaining component of the Agena primary propulsion system needing test qualification. Testing had been completed August 26; disassembly, inspection, and evaluation were concluded September 3. The consensus of those attending was that the successful test program had demonstrated flightworthiness of this configuration. This concluded qualification of all propulsion system components.
1965 September 29 - .
10:40 GMT - .
Launch Site:
Vandenberg.
Launch Complex:
Vandenberg 576B1.
LV Family:
Atlas.
Launch Vehicle:
Atlas D.
LV Configuration: Atlas D 125D.
- NTMP KX-45 re-entry vehicle test flight - .
Nation: USA. Agency: USAF AFSC. Apogee: 1,800 km (1,100 mi).
1965 September 30 - .
19:20 GMT - .
Launch Site:
Vandenberg.
Launch Complex:
Vandenberg SLC4E.
LV Family:
Atlas.
Launch Vehicle:
Atlas Agena D SLV-3.
LV Configuration: SLV-3 Agena D 7110 / Agena D 7110.
- KH 7-22 - .
Payload: KH-7 no. 22 / OPS 6004. Mass: 2,000 kg (4,400 lb). Nation: USA. Agency: NRO; USAF. Class: Surveillance. Type: Military surveillance satellite. Spacecraft: KH-7. Decay Date: 1965-10-05 . USAF Sat Cat: 1609 . COSPAR: 1965-076A. Apogee: 361 km (224 mi). Perigee: 237 km (147 mi). Inclination: 95.6000 deg. Period: 90.50 min. Summary: KH-7 type satellite. Space craft engaged in investigation of spaceflight techniques and technology (US Cat A). .
1965 October 1 - .
LV Family:
Atlas.
Launch Vehicle:
Atlas Agena D SLV-3.
- Gemini Agena target vehicle 5002 was transported to complex 14 and mated to target launch vehicle 5301. - .
Nation: USA. Flight: Gemini 6. Preliminary checks were followed, on October 4, by the Joint Flight Acceptance Composite Test (J-FACT). J-FACT was a combined check of all contractors, the range, the vehicles, and aerospace ground equipment in a simulated countdown and flight; propellants and high pressure gases were not loaded, nor was the gantry removed. Simultaneous Launch Demonstration was successfully completed October 7.
1965 October 5 - .
09:07 GMT - .
Launch Site:
Vandenberg.
Launch Complex:
Vandenberg 576B3.
LV Family:
Atlas.
Launch Vehicle:
Atlas D.
LV Configuration: Atlas D 34D NB20.170 RS.
- OV1-02 - .
Payload: OV1 Dummy. Mass: 86 kg (189 lb). Nation: USA. Agency: USAF OAR. Class: Earth. Type: Magnetosphere satellite. Spacecraft: OV1. USAF Sat Cat: 1613 . COSPAR: 1965-078A. Apogee: 2,735 km (1,699 mi). Perigee: 408 km (253 mi). Inclination: 144.2000 deg. Period: 117.60 min. Summary: Radiation data. Space craft engaged in investigation of spaceflight techniques and technology (US Cat A). .
- OV1-02S - .
Nation: USA. Agency: USAF AFSC. Class: Earth. Type: Magnetosphere satellite. Spacecraft: OV1. USAF Sat Cat: 1613 . COSPAR: 1965-078xx. Apogee: 2,418 km (1,502 mi). Perigee: 401 km (249 mi). Inclination: 144.2000 deg. Period: 114.00 min.
- NB20.170 - .
Payload: SPP 29. Nation: USA. Agency: USAF AFSC. Spacecraft: OV1. USAF Sat Cat: 1613 . COSPAR: 1965-078xx. Apogee: 2,418 km (1,502 mi). Perigee: 401 km (249 mi). Inclination: 144.2000 deg. Period: 114.00 min.
1965 October 7 - .
LV Family:
Atlas;
Titan.
- The Wet Mock Simulated Launch (WMSL) of Gemini-Titan (GT) 6 and the Simultaneous Launch Demonstration with GT-6 and the Gemini Atlas-Agena target vehicle were conducted. - .
Nation: USA. Flight: Gemini 6. Following WMSL, the spacecraft and launch vehicle were demated to allow the spacecraft battery to be replaced. They were remated October 8-13. Spacecraft Systems Test was completed October 15. Prelaunch testing concluded October 20 with the Simulated Flight Test.
1965 October 14 - .
LV Family:
Atlas.
Launch Vehicle:
Atlas Agena D SLV-3.
- Gemini Agena target vehicle 5003 was transferred to Vehicle Systems Test after completing final assembly on October 9. - .
Nation: USA. Flight: Gemini 8. Summary: Testing began October 18..
1965 October 25 - .
15:00 GMT - .
Launch Site:
Cape Canaveral.
Launch Complex:
Cape Canaveral LC14.
LV Family:
Atlas.
Launch Vehicle:
Atlas Agena D SLV-3.
LV Configuration: SLV-3 Agena D 5301 / Agena D 5002.
FAILURE: Exploded 6 minutes after takeoff. Failure..
Failed Stage: 2.
- Gemini 6 Agena Target - .
Payload: TDA-2. Mass: 3,261 kg (7,189 lb). Nation: USA. Agency: NASA. Program: Gemini. Class: Manned. Type: Manned logistics spacecraft. Flight: Gemini 6; Gemini 7. Spacecraft: Gemini Agena Target Vehicle. Decay Date: 1965-10-25 . COSPAR: F651025A. Summary: The Agena target vehicle failed to reach orbit. Gemini 6, awaiting launch, was cancelled. In the ashes of this setback, the idea of launching Gemini 6 to rendezvous with Gemini 7 was born..
1965 October 27 - .
LV Family:
Atlas.
Launch Vehicle:
Atlas Agena D SLV-3.
- Catastrophic anomaly of Gemini Agena target vehicle (GATV) 5002 on October 25 defined as a mission failure. - .
Nation: USA. Flight: Gemini 6. NASA Associate Administrator Robert C. Seamans, Jr., informed George E. Mueller, Associate Administrator for Manned Space Flight, that the catastrophic anomaly of Gemini Agena target vehicle (GATV) 5002 on October 25 had been defined as a mission failure. Additional Details: here....
1965 October 28 - .
LV Family:
Atlas.
Launch Vehicle:
Atlas Agena D SLV-3.
- Discrepancies remaining on Gemini Agena target vehicle 5001 cleared. - .
Nation: USA. Flight: Gemini 12. The major portion of 819 discrepancies remaining from the First Article Configuration Inspection (FACI) of Gemini Agena target vehicle 5001 in June were cleared; 128 that had not been applied against the acceptance document (DD-250) remained. All subsystem FACI discrepancies were also closed out during October.
1965 November 1 - .
LV Family:
Atlas.
Launch Vehicle:
Atlas Agena D SLV-3.
- The subpanel for Gemini VI of the Agena Flight Safety Review Board met at Lockheed. - .
Nation: USA. Flight: Gemini 6. Summary: The subpanel, chaired by Colonel John B. Hudson, Deputy Commander for Launch Vehicles, Air Force Space Systems Division, reviewed Lockheed's flight safety analysis of the failure of Gemini Agena target vehicle (GATV) 5002 on October 25. . Additional Details: here....
1965 November 3 - .
LV Family:
Atlas.
Launch Vehicle:
Atlas Agena D SLV-3.
- The Agena Flight Safety Review Board met at Lockheed to continue its investigation of the failure of Gemini Agena target vehicle 5002 on October 25. - .
Nation: USA. Flight: Gemini 6. Summary: The board, chaired by George E. Mueller, NASA Associate Administrator of Manned Space Flight, reviewed the findings of the subpanel for Gemini VI and reached the same conclusion: the failure resulted from a hard start probably caused by the fuel lead. . Additional Details: here....
1965 November 8 - .
19:26 GMT - .
Launch Site:
Vandenberg.
Launch Complex:
Vandenberg SLC4E.
LV Family:
Atlas.
Launch Vehicle:
Atlas Agena D SLV-3.
LV Configuration: SLV-3 Agena D 7113 / Agena D 7113.
- KH 7-23 - .
Payload: KH-7 no. 23 / OPS 8293. Mass: 2,000 kg (4,400 lb). Nation: USA. Agency: NRO; USAF. Class: Surveillance. Type: Military surveillance satellite. Spacecraft: KH-7. Decay Date: 1965-11-11 . USAF Sat Cat: 1727 . COSPAR: 1965-090A. Apogee: 352 km (218 mi). Perigee: 280 km (170 mi). Inclination: 93.9000 deg. Period: 90.80 min. Summary: Space craft engaged in investigation of spaceflight techniques and technology (US Cat A). .
- OPS 6232/Agena D - .
Payload: Agena Pickaback / OPS 6232. Mass: 60 kg (132 lb). Nation: USA. Agency: USAF. Class: Military. Type: Military naval signals reconnaisance satellite. Spacecraft: SSF. Decay Date: 1965-11-09 . USAF Sat Cat: 1728 . COSPAR: 1965-090B. Apogee: 284 km (176 mi). Perigee: 155 km (96 mi). Inclination: 93.9000 deg. Period: 88.90 min. Summary: Not identified as a subsatellite ferret by McDowell..
1965 November 11 - .
LV Family:
Atlas;
Titan.
- Gemini launch vehicle (GLV) 7 and spacecraft No. 7 were electrically mated at complex 19. - .
Nation: USA. Flight: Gemini 7. Summary: An electrical interface jumper cable connected the spacecraft, suspended about six feet above stage II, to the GLV. . Additional Details: here....
1965 November 12-13 - .
LV Family:
Atlas.
Launch Vehicle:
Atlas Agena D SLV-3.
- A symposium on hypergolic rocket ignition at altitude was held at Lockheed. - .
Nation: USA. Flight: Gemini 6. Because too little diagnostic information had been obtained from the flight of Gemini Agena target vehicle (GATV) 5002 to determine the exact nature of the probable hard start, it was not certain that the proposed modification - a return to oxidizer lead - would definitely prevent a recurrence of the malfunctions. Additional Details: here....
1965 November 15 - .
LV Family:
Atlas.
Launch Vehicle:
Atlas Agena D SLV-3.
- Gemini Agena target vehicle (GATV) engine modification and test program. - .
Nation: USA. Related Persons: Hohmann, Bernhard. Lockheed presented its proposed Gemini Agena target vehicle (GATV) engine modification and test program to Colonel A. J. Gardner, Gemini Target Vehicle Program Director, Air Force Space Systems Division (SSD). The proposal was immediately turned over to a three-man team comprising B. A. Hohmann (Aerospace), Colonel J. B. Hudson (Deputy Commander for Launch Vehicles, SSD), and L. E. Root (Lockheed) for consideration. On November 18, the group decided on a final version of the proposal that called for: (1) modifying the Agena engine to provide oxidizer lead during the start sequence, (2) demonstrating sea-level engine flightworthiness in tests at Bell Aerosystems, and (3) conducting an altitude test program at Arnold Engineering Development Center. The final proposal was presented to the GATV Review Board at Manned Spacecraft Center on November 20.
1965 November 19 - .
LV Family:
Atlas.
Launch Vehicle:
Atlas Agena D SLV-3.
- Air Force Space Systems Division (SSD) directed Lockheed to return Gemini Agena target vehicle (GATV) 5001 to Sunnyvale. - .
Nation: USA. Flight: Gemini 12. Summary: The GATV was still being stored in Hanger E, Eastern Test Range, minus its main engine which SSD had directed Lockheed to ship to Bell Aerosystems on November 9 for modification. . Additional Details: here....
1965 November 24 - .
LV Family:
Atlas.
Launch Vehicle:
Atlas Agena D SLV-3.
- Lockheed submitted an engineering change proposal to Air Force Space Systems Division (SSD) for Project Surefire. - .
Nation: USA. Flight: Gemini 8; Gemini 9. Summary: Surefire was the code name for the Gemini Agena Target Vehicle (GATV) Modification and Test Program designed to correct the malfunction which had caused the failure of GATV 5002 on October 25. . Additional Details: here....
1965 November 26 - .
LV Family:
Atlas.
Launch Vehicle:
Atlas Agena D SLV-3.
- McDonnell proposed building a backup target vehicle for Gemini rendezvous missions. - .
Nation: USA. Flight: Gemini 8. Spacecraft: Gemini; Gemini Radar. The augmented target docking adapter (ATDA) would serve as an alternative to the Gemini Agena target vehicle (GATV) if efforts to remedy the GATV problem responsible for the October 25 mission abort did not meet the date scheduled for launching Gemini VIII. Additional Details: here....
1965 November 29 - .
14:30 GMT - .
Launch Site:
Vandenberg.
Launch Complex:
Vandenberg 576A1.
LV Family:
Atlas.
Launch Vehicle:
Atlas D.
LV Configuration: Atlas D 200D.
- NTMP KX-33 re-entry vehicle test flight - .
Nation: USA. Agency: USAF AFSC. Apogee: 1,800 km (1,100 mi).
1965 December 14 - .
LV Family:
Atlas.
Launch Vehicle:
Atlas Agena D SLV-3.
- Air Force Space Systems Division authorized Lockheed to begin the disassembly and inspection of Gemini Agena target vehicle 5001 to determine the extent of refurbishment needed. - .
Nation: USA. Flight: Gemini 12. Summary: The vehicle was stripped down to its major structural components to expose all areas of possible contamination..
1965 December 17 - .
LV Family:
Atlas.
Launch Vehicle:
Atlas Agena D SLV-3.
- The Air Force accepted the main rocket engine for Gemini Agena target vehicle (GATV) 5003 after Bell Aerosystems had completed Project Surefire modifications. - .
Nation: USA. Flight: Gemini 8. Summary: The engine was shipped immediately and arrived at Lockheed December 18. Lockheed completed reinstalling the engine on December 20. GATV 5003 systems retesting began December 27 after other equipment modifications had been installed..
1965 December 20 - .
13:39 GMT - .
Launch Site:
Vandenberg.
Launch Complex:
Vandenberg 576B2.
LV Family:
Atlas.
Launch Vehicle:
Atlas D.
LV Configuration: Atlas D 85D.
- NTMP KX-31 re-entry vehicle test flight - .
Nation: USA. Agency: USAF AFSC. Apogee: 1,800 km (1,100 mi).
1966 January 8 - .
LV Family:
Atlas.
Launch Vehicle:
Atlas Agena D SLV-3.
- Gemini Agena target vehicle (GATV) 5003 completed its final acceptance tests at Sunnyvale, after an elusive command system problem had made it necessary to rerun the final systems test (January 4). - .
Nation: USA. Flight: Gemini 8. No vehicle discrepancy marred the rerun. Air Force Space Systems Division formally accepted GATV 5003 on January 18, after the vehicle acceptance team inspection. It was shipped to Eastern Test Range the same day, but bad weather delayed delivery until January 21. GATV 5003 was to be the target vehicle for Gemini VIII.
1966 January 16 - .
LV Family:
Atlas.
Launch Vehicle:
Atlas Agena D SLV-3.
- Project Surefire verification testing began at Bell Aerosystems. - .
Nation: USA. Flight: Gemini 8. Bell's part in the test program was to demonstrate the sea-level flightworthiness of the modified Agena main engine. Bell completed testing on March 4 with a full 180-second mission simulation firing. The successful completion of this phase of the test program gave the green light for the launch of Gemini Agena target vehicle 5003, scheduled for March 15.
1966 January 17 - .
LV Family:
Atlas.
Launch Vehicle:
Atlas Agena D SLV-3.
- Gemini Program Office review of possible future mission activities. - .
Nation: USA. Flight: Gemini 10; Gemini 8; Gemini 9. At a NASA-McDonnell Management Panel meeting, W. B. Evans of Gemini Program Office reviewed possible future mission activities. Gemini VIII would have three periods of extravehicular activity (EVA) - two in daylight, one in darkness - and would undock during EVA with the right hatch snubbed against the umbilical guide and the astronaut strapped into the adapter section. Additional Details: here....
1966 January 19 - .
20:10 GMT - .
Launch Site:
Vandenberg.
Launch Complex:
Vandenberg SLC4E.
LV Family:
Atlas.
Launch Vehicle:
Atlas Agena D SLV-3.
LV Configuration: SLV-3 Agena D 7114 / Agena D 7114.
- KH 7-24 - .
Payload: KH-7 no. 24 / OPS 7253. Mass: 2,000 kg (4,400 lb). Nation: USA. Agency: NRO; USAF. Class: Surveillance. Type: Military surveillance satellite. Spacecraft: KH-7. Decay Date: 1966-01-25 . USAF Sat Cat: 1939 . COSPAR: 1966-002A. Apogee: 259 km (160 mi). Perigee: 138 km (85 mi). Inclination: 93.8000 deg. Period: 88.40 min. Summary: KH-7 type satellite. Space craft engaged in investigation of spaceflight techniques and technology (US Cat A). .
- OPS 3179/Agena D - .
Payload: Agena Pickaback / OPS 3179. Mass: 60 kg (132 lb). Nation: USA. Agency: USAF. Class: Military. Type: Military naval signals reconnaisance satellite. Spacecraft: SSF. Decay Date: 1966-01-23 . USAF Sat Cat: 1940 . COSPAR: 1966-002B. Apogee: 149 km (92 mi). Perigee: 120 km (70 mi). Inclination: 93.8000 deg. Period: 87.20 min. Summary: Not identified as a subsatellite ferret by McDowell..
1966 January 22 - .
LV Family:
Atlas.
Launch Vehicle:
Atlas Agena D SLV-3.
- Gemini Agena target vehicle (GATV) 5003 was mated to target docking adapter (TDA) 3. - .
Nation: USA. Flight: Gemini 8. McDonnell had delivered TDA-3 to Cape Kennedy on January 8. The GATV/TDA interface functional test was completed January 24, and the vehicle was transferred to Merritt Island Launch Area for integrated tests with spacecraft No. 8 and extravehicular equipment, which were completed January 28.
1966 January 26 - .
LV Family:
Atlas.
Launch Vehicle:
Atlas Agena D SLV-3.
- Gemini Agena target vehicle (GATV) 5004 was transferred to the vehicle systems test area at Sunnyvale. - .
Nation: USA. Flight: Gemini 9. Its modified main engine had been received on schedule from Bell Aerosystems January 12 and installed by January 20. Because of GATV 5003 priority, however, several main electronic assemblies, including the command system, had been removed from GATV 5004 and used in GATV 5003 final acceptance tests. As a result, GATV 5004 had fallen eight days behind its scheduled transfer date, January 18.
1966 January 28 - .
LV Family:
Atlas.
Launch Vehicle:
Atlas Agena D SLV-3.
- Gemini Agena target vehicle (GATV) 5003 was returned to Hanger E after completing Plan X tests at Merritt Island Launch Area. - .
Nation: USA. Flight: Gemini 8. Summary: Systems Verification and Combined Interface Tests were conducted through February 18, followed by functional checks of the primary and secondary propulsion systems. Hanger E testing ended February 28, and the GATV was transferred to complex 14..
1966 February 2 - .
LV Family:
Atlas.
Launch Vehicle:
Atlas Agena D SLV-3.
- A mission planning meeting for Gemini flights IX through XII, held at McDonnell, was attended by members of the Gemini Program Office and Flight Operations Division. - .
Nation: USA. The last item on the agenda was a reminder from McDonnell that the Gemini spacecraft was capable of flying to a relatively high elliptic orbit from which it could safely reenter under certain circumstances. The type of orbit McDonnell suggested had an apogee of 500-700 nautical miles. This would involve using the Agena primary propulsion system both to get into this orbit and to return to a 161-mile circular orbit for nominal reentry.
1966 February 2 - .
LV Family:
Atlas.
Launch Vehicle:
Atlas Agena D SLV-3.
- Agena D (AD-129) was accepted by the Air Force for delivery to the Gemini program. - .
Nation: USA. Flight: Gemini 10. Summary: It was transferred to the final assembly area at Sunnyvale for modification to Gemini Agena target vehicle 5005..
1966 February 4 - .
LV Family:
Atlas.
Launch Vehicle:
Atlas Agena D SLV-3.
- The augmented target docking adapter (ATDA) arrived at Cape Kennedy. Modifications, testing, and troubleshooting were completed March 4. - .
Nation: USA. Flight: Gemini 9. The ATDA, which was intended to back up the Gemini Agena target vehicle (GATV), was then placed in storage (March 8) where it remained until May 17, when the failure of target launch vehicle 5303 prevented GATV 5004 from achieving orbit. The ATDA became the target for Gemini IX-A.
1966 February 10 - .
09:48 GMT - .
Launch Site:
Vandenberg.
Launch Complex:
Vandenberg 576A1.
LV Family:
Atlas.
Launch Vehicle:
Atlas D.
LV Configuration: Atlas D 305D.
- NTMP KX-38 / Pod 32 Reentry test / plume mission - .
Nation: USA. Agency: USAF AFSC. Apogee: 1,800 km (1,100 mi).
1966 February 11 - .
13:04 GMT - .
Launch Site:
Vandenberg.
Launch Complex:
Vandenberg 576B2.
LV Family:
Atlas.
Launch Vehicle:
Atlas D.
LV Configuration: Atlas D 86D.
- NTMP KX-51 re-entry vehicle test flight - .
Nation: USA. Agency: USAF AFSC. Apogee: 1,800 km (1,100 mi).
1966 February 15 - .
20:30 GMT - .
Launch Site:
Vandenberg.
Launch Complex:
Vandenberg SLC4E.
LV Family:
Atlas.
Launch Vehicle:
Atlas Agena D SLV-3.
LV Configuration: SLV-3 Agena D 7115 / Agena D 7115.
- KH 7-25 - .
Payload: KH-7 no. 25 / OPS 1184. Mass: 2,000 kg (4,400 lb). Nation: USA. Agency: NRO; USAF. Class: Surveillance. Type: Military surveillance satellite. Spacecraft: KH-7. Decay Date: 1966-02-22 . USAF Sat Cat: 2012 . COSPAR: 1966-012A. Apogee: 290 km (180 mi). Perigee: 142 km (88 mi). Inclination: 96.5000 deg. Period: 88.90 min. Summary: KH-7 type satellite. Space craft engaged in investigation of spaceflight techniques and technology (US Cat A). .
- Bluebell 2C (Cylinder) - .
Payload: OPS 3011. Mass: 9.00 kg (19.80 lb). Nation: USA. Agency: USAF. Class: Military. Type: Radar calibration target. Spacecraft: Bluebell. Decay Date: 1966-02-16 . USAF Sat Cat: 2014 . COSPAR: 1966-012B. Apogee: 253 km (157 mi). Perigee: 115 km (71 mi). Inclination: 96.5000 deg. Period: 88.10 min. Summary: Space craft engaged in investigation of spaceflight techniques and technology (US Cat A). .
- Bluebell 2S (Sphere) - .
Payload: OPS 3031. Mass: 4.00 kg (8.80 lb). Nation: USA. Agency: USAF. Class: Military. Type: Radar calibration target. Spacecraft: Bluebell. Decay Date: 1966-02-22 . USAF Sat Cat: 2015 . COSPAR: 1966-012C. Apogee: 268 km (166 mi). Perigee: 147 km (91 mi). Inclination: 96.5000 deg. Period: 88.60 min. Summary: Space craft engaged in investigation of spaceflight techniques and technology (US Cat A). .
1966 February 19 - .
09:56 GMT - .
Launch Site:
Vandenberg.
Launch Complex:
Vandenberg 576B1.
LV Family:
Atlas.
Launch Vehicle:
Atlas D.
LV Configuration: Atlas D 73D.
- NTMP KX-47 Re-entry Vehicle test - .
Nation: USA. Agency: USAF AFSC. Apogee: 1,800 km (1,100 mi).
1966 February 27 - .
LV Family:
Atlas.
Launch Vehicle:
Atlas Agena D SLV-3.
- Gemini Agena target vehicle (GATV) 5004 completed systems testing at Sunnyvale. - .
Nation: USA. Flight: Gemini 9. Summary: It was formally accepted by the Air Force on March 11, following the vehicle acceptance team inspection. The next day (March 12), GATV 5004 was shipped by air to Eastern Test Range, arriving March 14..
1966 March 4 - .
12:29 GMT - .
Launch Site:
Vandenberg.
Launch Complex:
Vandenberg 576A1.
LV Family:
Atlas.
Launch Vehicle:
Atlas D.
LV Configuration: Atlas D 303D.
FAILURE: Failure.
Failed Stage: 1.
- NTMP KX-35 re-entry vehicle test flight - .
Nation: USA. Agency: USAF AFSC. Apogee: 500 km (310 mi).
1966 March 6 - .
LV Family:
Atlas;
Titan.
- Gemini launch vehicle 8 and spacecraft No. 8 were mated for flight at complex 19. - .
Nation: USA. Flight: Gemini 8. Summary: The Simultaneous Launch Demonstration with the Gemini Atlas-Agena target vehicle on complex 14 was completed March 9. The Final Simulated Flight Test concluded prelaunch tests on March 10..
1966 March 16 - .
LV Family:
Atlas.
Launch Vehicle:
Atlas Agena D SLV-3.
- Gemini Agena target vehicle 5003 systems exercised. - .
Nation: USA. Flight: Gemini 10; Gemini 8. Following the early termination of Gemini VIII, Gemini Agena target vehicle (GATV) 5003 remained in orbit, where its various systems were extensively exercised. The main engine was fired nine times, four more than required by contract, and 5000 commands were received and executed by the command and communications system, as against a contractural requirement of 1000. Additional Details: here....
1966 March 16 - .
15:00 GMT - .
Launch Site:
Cape Canaveral.
Launch Complex:
Cape Canaveral LC14.
LV Family:
Atlas.
Launch Vehicle:
Atlas Agena D SLV-3.
LV Configuration: SLV-3 Agena D 5302 / Agena D 5003.
- Gemini 8 Agena Target - .
Payload: TDA 3/Agena D 5003 GATV. Mass: 3,175 kg (6,999 lb). Nation: USA. Agency: NASA Houston. Program: Gemini. Class: Manned. Type: Manned logistics spacecraft. Flight: Gemini 8. Spacecraft: Gemini Agena Target Vehicle. Decay Date: 1967-09-15 . USAF Sat Cat: 2104 . COSPAR: 1966-019A. Apogee: 299 km (185 mi). Perigee: 285 km (177 mi). Inclination: 28.9000 deg. Period: 90.40 min. Summary: Target vehicle for Gemini 8..
1966 March 18 - .
20:30 GMT - .
Launch Site:
Vandenberg.
Launch Complex:
Vandenberg SLC4E.
LV Family:
Atlas.
Launch Vehicle:
Atlas Agena D SLV-3.
LV Configuration: SLV-3 Agena D 7116 / Agena D 7116.
- KH 7-26 - .
Payload: KH-7 no. 26 / OPS 0879. Mass: 60 kg (132 lb). Nation: USA. Agency: NRO; USAF. Class: Surveillance. Type: Military surveillance satellite. Spacecraft: KH-7. Decay Date: 1966-03-24 . USAF Sat Cat: 2109 . COSPAR: 1966-022A. Apogee: 308 km (191 mi). Perigee: 162 km (100 mi). Inclination: 101.0000 deg. Period: 89.30 min. Summary: Not identified as a subsatellite ferret by McDowell..
- OPS 0974/Agena D - .
Payload: NRL PL137 / OPS 0974. Mass: 2,000 kg (4,400 lb). Nation: USA. Agency: USAF. Class: Military. Type: Military naval signals reconnaisance satellite. Spacecraft: SSF. Decay Date: 1966-03-23 . USAF Sat Cat: 2112 . COSPAR: 1966-022B. Apogee: 285 km (177 mi). Perigee: 149 km (92 mi). Inclination: 101.0000 deg. Period: 88.80 min. Summary: Space craft engaged in investigation of spaceflight techniques and technology (US Cat A). .
1966 March 19 - .
12:30 GMT - .
Launch Site:
Vandenberg.
Launch Complex:
Vandenberg 576A1.
LV Family:
Atlas.
Launch Vehicle:
Atlas D.
LV Configuration: Atlas D 304D.
- NTMP KX-43 re-entry vehicle test flight - .
Nation: USA. Agency: USAF AFSC. Apogee: 1,800 km (1,100 mi).
1966 March 21 - .
LV Family:
Atlas.
Launch Vehicle:
Atlas Agena D SLV-3.
- Gemini Agena target vehicle 5004 and spacecraft No. 9 began Plan X compatibility tests at Merritt Island Launch Area Radar Range. - .
Nation: USA. Flight: Gemini 9. Spacecraft: Gemini; Gemini Radar.
1966 March 22 - .
LV Family:
Atlas.
Launch Vehicle:
Atlas Agena D SLV-3.
- Agena D (AD-130) was formally accepted by the Air Force for the Gemini program and moved to Building 104 at Sunnyvale for modification and final assembly as Gemini Agena target vehicle 5006. - .
Nation: USA. Flight: Gemini 11.
1966 March 24 - .
LV Family:
Atlas.
Launch Vehicle:
Atlas Agena D SLV-3.
- Project Surefire test program not to be curtailed. - .
Nation: USA. Flight: Gemini 8. Summary: Air Force Space Systems Division and Lockheed agreed not to curtail the Project Surefire test program despite the excellent performance of Gemini Agena target vehicle (GATV) 5003 during the Gemini VIII mission. . Additional Details: here....
1966 March 30 - .
09:20 GMT - .
Launch Site:
Vandenberg.
Launch Complex:
Vandenberg 576B3.
LV Family:
Atlas.
Launch Vehicle:
Atlas D.
LV Configuration: Atlas D 72D NB20.152 RS.
- OV1-04 - .
Mass: 88 kg (194 lb). Nation: USA. Agency: USAF OAR. Class: Earth. Type: Magnetosphere satellite. Spacecraft: OV1. USAF Sat Cat: 2121 . COSPAR: 1966-025A. Apogee: 1,008 km (626 mi). Perigee: 884 km (549 mi). Inclination: 144.5000 deg. Period: 104.00 min. Summary: Thermal control experiments. Space craft engaged in investigation of spaceflight techniques and technology (US Cat A). .
- OV1-04S - .
Nation: USA. Agency: USAF AFSC. Class: Earth. Type: Magnetosphere satellite. Spacecraft: OV1. USAF Sat Cat: 2121 . COSPAR: 1966-025xx. Apogee: 1,002 km (622 mi). Perigee: 879 km (546 mi). Inclination: 144.5000 deg. Period: 103.80 min.
- OV1-05S - .
Payload: BORE. Mass: 114 kg (251 lb). Nation: USA. Agency: USAF OAR. Class: Earth. Type: Magnetosphere satellite. Spacecraft: OV1. USAF Sat Cat: 2122 . COSPAR: 1966-025B. Apogee: 1,056 km (656 mi). Perigee: 985 km (612 mi). Inclination: 144.6000 deg. Period: 105.60 min. Summary: Optical radiation test. Space craft engaged in investigation of spaceflight techniques and technology (US Cat A). .
1966 April - .
LV Family:
Atlas.
Launch Vehicle:
Atlas F.
- Final active Atlas squadron deactivated. - .
Nation: USA. Summary: VAFB SMS 576 deactivated.
1966 April 8 - .
01:00 GMT - .
Launch Site:
Cape Canaveral.
Launch Complex:
Cape Canaveral LC36B.
LV Family:
Atlas.
Launch Vehicle:
Atlas Centaur D.
LV Configuration: Atlas Centaur D AC-8 / Centaur D 184D.
FAILURE: Centaur propellant leak..
Failed Stage: 2.
- Surveyor Model - .
Payload: Surveyor SD-3. Mass: 784 kg (1,728 lb). Nation: USA. Agency: NASA; JPL. Class: Moon. Type: Lunar probe. Spacecraft: Surveyor. Decay Date: 1966-05-05 . USAF Sat Cat: 2139 . COSPAR: 1966-030A. Apogee: 336 km (208 mi). Perigee: 182 km (113 mi). Inclination: 30.7000 deg. Period: 89.70 min. Summary: Launch vehicle test. Payload was dummy Surveyor spacecraft..
1966 April 8 - .
19:35 GMT - .
Launch Site:
Cape Canaveral.
Launch Complex:
Cape Canaveral LC12.
LV Family:
Atlas.
Launch Vehicle:
Atlas Agena D SLV-3.
LV Configuration: SLV-3 Agena D 5001 (AA15) / Agena D 6703.
- OAO 1 - .
Payload: OAO A1. Mass: 1,774 kg (3,911 lb). Nation: USA. Agency: NASA Greenbelt. Class: Astronomy. Type: X-ray astronomy satellite. Spacecraft: OAO. USAF Sat Cat: 2142 . COSPAR: 1966-031A. Apogee: 793 km (492 mi). Perigee: 783 km (486 mi). Inclination: 35.0000 deg. Period: 100.60 min. Summary: Orbiting Astronomical Observatory. Spacecraft engaged in research and exploration of the upper atmosphere or outer space (US Cat B). .
1966 April 12 - .
LV Family:
Atlas.
Launch Vehicle:
Atlas Agena D SLV-3.
- Gemini Agena target vehicle 5004 began the Combined Interface Test (CIT) at Hanger E, Eastern Test Range, after completing Plan X tests March 24. - .
Nation: USA. Flight: Gemini 9. Summary: CIT ended April 22 and engine functional tests of both the primary and secondary propulsion systems followed. Hanger E testing was completed May 1..
1966 April 15 - .
LV Family:
Atlas.
Launch Vehicle:
Atlas Agena D SLV-3.
- Evaluation of a Lockheed proposal to launch space probes from orbit using Agena rockets launched from AAP stations in space. - .
Nation: USA. Related Persons: Mueller; Seamans. Spacecraft: Orbital Workshop. Associate Administrator for Manned Space Fight George E. Mueller informed Deputy Administrator Robert C. Seamans, Jr., of the Saturn/Apollo Applications Program Office's evaluation of a Lockheed proposal to launch space probes from orbit using Agena rockets launched from AAP stations in space. The proposal was feasible, Mueller advised, but did not seem a desirable mission for inclusion in the AAP. Additional Details: here....
1966 April 19 - .
19:12 GMT - .
Launch Site:
Vandenberg.
Launch Complex:
Vandenberg SLC4E.
LV Family:
Atlas.
Launch Vehicle:
Atlas Agena D SLV-3.
LV Configuration: SLV-3 Agena D 7117 / Agena D 7117.
- KH 7-27 - .
Payload: KH-7 no. 27 / OPS 0910. Mass: 2,000 kg (4,400 lb). Nation: USA. Agency: NRO; USAF. Class: Surveillance. Type: Military surveillance satellite. Spacecraft: KH-7. Decay Date: 1966-04-26 . USAF Sat Cat: 2146 . COSPAR: 1966-032A. Apogee: 375 km (233 mi). Perigee: 139 km (86 mi). Inclination: 116.9000 deg. Period: 89.60 min. Summary: KH-7 type satellite. Space craft engaged in investigation of spaceflight techniques and technology (US Cat A). .
1966 May 3 - .
LV Family:
Atlas.
Launch Vehicle:
Atlas Agena D SLV-3.
- Lockheed completed Combined Systems Acceptance Test on Gemini Agena target vehicle 5005 in test complex C-10 at Sunnyvale. - .
Nation: USA. Flight: Gemini 10. Summary: The vehicle was formally accepted by the Air Force on May 14 and delivered to Eastern Test Range on May 16..
1966 May 3 - .
10:30 GMT - .
Launch Site:
Vandenberg.
Launch Complex:
Vandenberg 576A1.
LV Family:
Atlas.
Launch Vehicle:
Atlas D.
LV Configuration: Atlas D 208D.
FAILURE: Failure.
Failed Stage: 1.
- NTMP KX-37 re-entry vehicle test flight - .
Nation: USA. Agency: USAF AFSC. Apogee: 500 km (310 mi).
1966 May 8 - .
LV Family:
Atlas.
Launch Vehicle:
Atlas Agena D SLV-3.
- Lockheed established a task force to handle the refurbishing of Gemini Agena target vehicle (GATV) 5001 and announced a GATV 5001 Reassembly Plan. - .
Nation: USA. Flight: Gemini 12. The task force's function was to see that GATV 5001 reached a flightworthy condition on time and as economically as possible. The reassembly plan provided an operational base line as well as guidelines for reassembling the vehicle, which was completely disassembled dow
