The panels had 28,224 individual solar cells capable of producing 310 watts at Mars. Power was supplied by four solar panels, each 176 centimeters (5 feet, 9.3 inches) long and 90 centimeters (2 feet, 11.4 inches) wide. The body of the spacecraft had a width of 127 centimeters (4 feet, 2 inches) across the diagonal, and was 45.7 centimeters (1 foot, 6 inches high. Mariner 4 overall height, including the mast, was 289 centimeters. The spacecraft carried an imaging system, cosmic dust detector, cosmic-ray telescope, magnetometer, radiation detector, solar plasma probe and an occultation experiment. The mission of Mariner 4 was to “fly by” Mars to take photographic images and gather scientific data, then relay this to tracking stations on Earth. Mariner 4 (NASA) Mariner 4 during Weight Test (NASA/JPL 293_7150Bc) Mariner 4 separated from the Agena D at 15:07:09 UTC. At 15:02:53, a one minute, 35 second burn placed the vehicle into a Mars Transfer Orbit. A 2 minute, 24 second burn placed the Mariner/Agena in an Earth orbit. The Mariner 4/Agena D separated from the first stage Atlas booster at 14:27:23 UTC. The two-stage launch vehicle consisted of an Atlas D, number 288, and an Agena D, number 6932. (NASA)Ģ8 November 1964, 14:22:01.309 UTC: Mariner 4, a space probe designed and built by the Jet Propulsion Laboratory (JPL), lifted off from Launch Complex 12 at the Cape Kennedy Air Force Station, Cape Kennedy, Florida. Nineteen were launched, of which two failed.Mariner 4 lifts off from LC-12, Cape Kennedy Air Force Station, 9:22 a.m. The Atlas E/F was used with a Trident upper stage, between 19, for suborbital tests of re-entry vehicles. Another launch failed due to stage separation occurring at the correct time despite the first stage burn being extended by fifty seconds to resolve an underperformance issue, the end result of which was the upper stage separating and igniting while the first stage was still firing. The RM-20 launch failed due to damage to the first stage, caused by the explosion of residual fuel in the flame trench during launch. With the Star-37 upper stage, the rocket could place 1,100 kg (2,400 lb) into a Sun-synchronous orbit (SSO). A Star-17A was used in the launch of the RM-20 spacecraft on 12 April 1975, giving the rocket a LEO payload of 725 kg (1,598 lb), while the Star-37S-ISS was used to launch nineteen Defense Meteorological Satellite Program (DMSP), National Oceanic and Atmospheric Administration (NOAA) and Television Infrared Observation Satellite ( TIROS) weather satellites between 19. The Star was used to propel most of the other upper stages used on the Atlas E/F, however it was also used in its own right on several launches. The first eight used the SGS-1, which could place 455 kg (1,003 lb) of payload into a medium Earth transfer orbit, whereas the last four used the more powerful SGS-2. The SGS upper stage, which consisted of two series-burning solid rocket motors, was used on twelve Atlas E/F launches, with early GPS satellites. The upper stage gave the vehicle a payload capacity of 295 kg (650 lb) to a medium Earth transfer orbit. The PTS upper stage was used to launch the NTS-1 satellite on 14 July 1974. In this configuration, the rocket could place 363 kg (800 lb) into LEO. Two of the launches also carried secondary payloads. Three of the launches carried two OV1 satellites, and one carried three.
The Atlas E/F was used between 19 to launch four groups of OV1 satellites, using OV1 upper stages. The rocket could place 870 kilograms (1,920 lb) into low Earth orbit. The OIS upper stage was used for two Atlas E/F launches in 19, with the Solwind and Geosat spacecraft respectively. This configuration had a maximum payload capacity of 800 kg (1,800 lb) to LEO. The fourth of these launches failed when one of the booster unit engines shut down early. Atlas E/F-MSD Ītlas E/F rockets with MSD upper stages were used for four launches, with NOSS naval reconnaissance satellites between 19. The rocket had a payload capacity of 950 kg (2,090 lb) to low Earth orbit. Atlas E/F-Burner Ī Burner-2 upper stage was used on an Atlas E/F to launch the Radsat and Radcat satellites on 2 October 1972. The rocket was capable of placing 210 kg (460 lb) of payload into low Earth orbit. Atlas E/F-Altair Īn Atlas E/F with an Altair-3A upper stage was used to launch three Stacksat spacecraft on 11 April 1990. Previous Atlas-Agena launches were launched on Atlas D or Atlas SLV-3 first stages, but the final Atlas-Agena used an Atlas E/F. This was the final flight of the Atlas-Agena. An RM-81 Agena upper stage was used on a former Atlas-F, to launch the Seasat satellite on 27 June 1978.
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