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...

Rocketdyne was an American rocket engine design and production company headquartered in Canoga Park, in the western San Fernando Valley of suburban Los...

Aerojet Rocketdyne is a subsidiary of American defense company L3Harris Technologies that manufactures rocket, hypersonic, and electric propulsive systems...

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...

Pratt & Whitney Rocketdyne (PWR) was an American company that designed and produced rocket engines that use liquid propellants. It was a division of Pratt...

referred to as J2 Rocketdyne J-2, a rocket engine used in the Saturn rockets and intended for use on the Space Launch System AEG J.II, a World War I German...

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...

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...

and manufactured in the United States by Rocketdyne (later Pratt & Whitney Rocketdyne and Aerojet Rocketdyne). Development started in the 1990s with the...

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...

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...

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...

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...

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...

liquid-fuel cryogenic rocket engine built in the United States by Aerojet Rocketdyne that burns cryogenic liquid hydrogen and liquid oxygen propellants. Modern...

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...

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...

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...

System. Built in the United States by Aerojet Rocketdyne (formerly, Pratt & Whitney Rocketdyne), the J-2X burns cryogenic liquid hydrogen and liquid oxygen...

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...

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...

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...

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...

and manufactured in the United States by Rocketdyne (later Pratt & Whitney Rocketdyne and Aerojet Rocketdyne), the RS-25 burns cryogenic (very low temperature)...

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...

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"...

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...

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...

January 1968. Retrieved 2 February 2024. "Engine Design and Technology Requirements" (PDF). nasa.gov. NASA. January 1968. Retrieved 2 February 2024....

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...