![]() ![]() ![]() The LV-3A had a total thrust of 456,587 pounds (2,031 kilonewtons). The Atlas rocket used liquid oxygen and RP-1 (a highly-refined kerosene) propellant. Both engines were built by the Rocketdyne Division of North American Aviation, Inc., at Canoga Park, California. The center, or “sustainer,” engine is a LR105-NA-5, rated at 86,800 pounds of thrust (386 kilonewtons). This stage produced approximately 369,800 pounds of thrust (1,645 kilonewtons). The “half-stage,” was a booster section consisting of two LR89-NA-5 rocket engines. ![]() The LV-3A is a “1-½ stage” liquid-fueled rocket with three engines. The maximum width across the booster section was 4.88 meters (16 feet). The Atlas Agena B first stage was 20.70 meters (67 feet, 11 inches) long, with a maximum diameter of 3.05 meters (10 feet). The height of the total vehicle, including the protective shroud encasing Mariner, 103 feet, 5 inches (31.70 meters). Air Force SM-65 Atlas intercontinental ballistic missile (ICBM), and was built by the Convair Division of General Dynamics at San Diego, California. The Atlas Agena B combined an Atlas LV-3A rocket with an Agena B upper stage. The Mariner 1 mission failed when the launch vehicle veered off course and was destroyed by the Range Safety Officer, 4 minutes, 53 seconds into its flight, 22 July 1962. The spacecraft were designed to obtain radiometric temperatures of Venus, and to measure the Interplanetary Magnetic Field. Mariner 1 and 2 were identical space probes built by the Jet Propulsion Laboratory (JPL) of the California Institute of Technology (Caltech), Pasadena, California. This was the second space probe to be sent to Venus. (NASA)Ģ7 August 1962: At 06:53:14 UTC (2:53 a.m., Eastern Daylight Time), Mariner 2 lifted off from Launch Complex 12 at Cape Canaveral Air Force Station, Florida, aboard an Atlas-Agena B launch vehicle. Engine ignition of Mariner 2 Atlas Agena B at LC-12, Cape Canaveral AFS, 2:53 a.m., EST, 27 August 1962. ![]()
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