The J-2, commonly known as Rocketdyne J-2, was a liquid-fuel cryogenic rocket engine used on NASA's Saturn IB and Saturn V launch vehicles. Built in the...
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Rocketdyne was an American rocket engine design and production company headquartered in Canoga Park, in the western San Fernando Valley of suburban Los...
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Aerojet Rocketdyne is a subsidiary of American defense company L3Harris Technologies that manufactures rocket, hypersonic, and electric propulsive systems...
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The Rocketdyne XRS-2200 was an experimental linear aerospike engine developed in the mid-1990s for the Lockheed Martin X-33 program. The design was based...
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Pratt & Whitney Rocketdyne (PWR) was an American company that designed and produced rocket engines that use liquid propellants. It was a division of Pratt...
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flight time totaling about 10 hours but vibrations damaged some of the Rocketdyne J-2 engines in the second and third stages by rupturing internal fuel lines...
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Beach, California. Using liquid hydrogen and liquid oxygen, it had five Rocketdyne J-2 engines in a similar arrangement to the S-IC, and also used the four...
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RS-68 (redirect from Rocketdyne RS-68)
and manufactured in the United States by Rocketdyne (later Pratt & Whitney Rocketdyne and Aerojet Rocketdyne). Development started in the 1990s with the...
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Santa Susana Field Laboratory (redirect from Rocketdyne Santa Susana Field Laboratory Contamination)
The Santa Susana Field Laboratory (SSFL), formerly known as Rocketdyne, is a complex of industrial research and development facilities located on a 2,668-acre...
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lack of on-orbit engine restart capability. It was powered by a single Rocketdyne J-2 engine. The fuel and oxidizer tanks shared a common bulkhead, which...
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The Rocketdyne H-1 was a 205,000 lbf (910 kN) thrust liquid-propellant rocket engine burning LOX and RP-1. The H-1 was developed for use in the S-I and...
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The Rocketdyne F-1 engine, used in a cluster of five in the first stage of the Saturn V, had no failures in 65 engine-flights. The Rocketdyne J-2 engine...
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HG-3 (rocket engine) (category Rocketdyne engines)
seconds (2.7 km/s) at sea level. Developed from Rocketdyne's J-2 engine used on the S-II and S-IVB stages, the engine was intended to replace the J-2 on the...
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RL10 (redirect from Aerojet Rocketdyne RL10)
liquid-fuel cryogenic rocket engine built in the United States by Aerojet Rocketdyne that burns cryogenic liquid hydrogen and liquid oxygen propellants. Modern...
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high altitude space. Atmospheric thrust suppression reduced the five Rocketdyne J-2 engines' 1,000,000 pounds-force (4,400 kN) of vacuum thrust to 546,500...
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Stennis Space Center (section A-1/A-2 Test stand)
million pounds of thrust from its five Rocketdyne J-2 engines. This test also marked the first operational use of the A-2 stand. The first full-duration firing...
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to Rocketdyne and it would be later called the J-2. At the same time the S-II stage design began to take shape. Initially it was to have four J-2 engines...
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System. Built in the United States by Aerojet Rocketdyne (formerly, Pratt & Whitney Rocketdyne), the J-2X burns cryogenic liquid hydrogen and liquid oxygen...
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of sea-level thrust (SL). These designs used two or three Rocketdyne F-1 engines in a S-IB-2 or S-IC stage and diameters ranging from 8 to 10 meters (26...
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Mark. "Saturn C-8". Astronautix. Archived from the original on September 2, 2016. Retrieved 9 March 2020. Bilstein, Roger E, Stages to Saturn, US Government...
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are usually mitigated via staging, as upper stage engines such as the Rocketdyne J-2 do not have to fire until atmospheric pressure is negligible, and can...
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and flight instructor. He managed the development of the Rocketdyne F-1 and Rocketdyne J-2 for the Apollo program Saturn V rocket, as well as the Lunar...
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RS-25 (redirect from Rocketdyne RS-25)
and manufactured in the United States by Rocketdyne (later Pratt & Whitney Rocketdyne and Aerojet Rocketdyne), the RS-25 burns cryogenic (very low temperature)...
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978 lb (24,938 kg) Gross mass 449,840 lb (204,040 kg) Powered by 4 Rocketdyne J-2 Maximum thrust 800,000 lbf (3,600 kN) Specific impulse 300 sec (sea...
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Applications Program S-IC S-II Saturn I SA-1 Johnson, Kurt P.; Holl, Richard J. (June 1970). "Nuclear Shuttle for Interorbital and Transplanetary Applications"...
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by the Saturn V's first stage. The second stage would use a single Rocketdyne J-2 LOX/liquid hydrogen (LH2) engine, while the third stage was intended...
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pounds (35,000 kg) of payload into a 100 nautical mile (185 km) orbit, around 2.5 times the useful payload of the Saturn IB. Both three- and four-engine variants...
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January 1968. Retrieved 2 February 2024. "Engine Design and Technology Requirements" (PDF). nasa.gov. NASA. January 1968. Retrieved 2 February 2024....
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Specific impulse 296 s (2.90 km/s) Burn time 155 seconds Propellant RP-1/LOX Second stage – S-IVB Powered by 1 Rocketdyne J-2 Maximum thrust 1,031.600 kN...
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