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J-2

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J-2 Credit: © Mark Wade

Status: First flight 1966. Date: 1960. Number: 87 . Thrust: 1,033.10 kN (232,250 lbf). Unfuelled mass: 1,438 kg (3,170 lb). Specific impulse: 421 s. Specific impulse sea level: 200 s. Burn time: 475 s. Height: 3.38 m (11.08 ft). Diameter: 2.01 m (6.60 ft).

The J-2 was a gas generator, pump-fed engine. Specific impulse and thrust is for final flight version; J-2 had a specific impulse of 418 sec/thrust of 90,700 kgf/mix ratio of 5.00 on LV's SA-201 through 203, and 419 sec/thrust of 102,040 kgf on SA-204 through 207 and SA-501 to 503. Sea level versions with reduced expansion ratio proposed for Saturn II first stage use. Upgraded toroidal aerospike versions (J-2T-200K and J-2T-250K) studies for upgrades to Saturn upper stages. Modestly improved J-2S was tested and provides basis for X-33 linear aerospike engine thirty years later. Proposed for use in Nova A-2; Saturn IVB; Nova NASA-3; Nova B-2; Saturn II; Jarvis-2; Saturn MS-II-1; Saturn S-II-8; Saturn S-IVC; Nova 60-8-3; Saturn S-II-C3; Saturn S-II-4; Saturn S-II. Saturn V S-ll & S-IVB Stage Engines, Saturn IB S-IVB. Upper Stage Engine.

Thrust (sl): 486.200 kN (109,302 lbf). Thrust (sl): 49,577 kgf. Engine: 1,438 kg (3,170 lb). Chamber Pressure: 30.00 bar. Area Ratio: 28. Thrust to Weight Ratio: 73.1801112656467. Oxidizer to Fuel Ratio: 5.5. Coefficient of Thrust vacuum: 3.35409543547025. Coefficient of Thrust sea level: 2.42076210213692.

J-2T-200K Rocketdyne LOx/LH2 rocket engine. Study 1965. Proposed for later versions of Saturn V. Toroidal aerospike plug nozzle version of J-2.

J-2S Rocketdyne LOx/LH2 rocket engine. Developed 1965-1969. J-2 version proposed for Saturn follow-on vehicles, using results of the J-2X technology program. The engine was simplified while offering improved performance.

HG-3 Rocketdyne LOx/LH2 rocket engine. Study 1967. High-performance high-pressure chamber engine developed from J-2. Considered for upgrades to Saturn V launch vehicle upper stages. Technology led to Space Shuttle Main Engines.

J-2T-250K Rocketdyne LOx/LH2 rocket engine. Study 1967. Proposed for later versions of Saturn V. Toroidal aerospike plug nozzle version of J-2.

Aerospike Annular Booster Rocketdyne LOx/LH2 rocket engine. Aerospike Typical Annular Booster . Pressure-fed. Thrust from 50,000 to 250,000 lbs at altitude.

XRS-2200 Rocketdyne LOx/LH2 rocket engine. Development ended 1999. Linear aerospike engine for X-33 SSTO technology demonstrator. Based on J-2S engine developed for improved Saturn launch vehicles in the 1960's.

J-2X Rocketdyne LOx/LH2 rocket engine. Ares I launch vehicle second stage. In development 2006-2016. Began as an update to the J-2 engine of the 1960s, but final design was all-new, 20% more thrust, but double the weight.

RS-2100 Rocketdyne LOx/LH2 rocket engine. Next Generation Launch Vehicle Booster. Full flow staged combustion, pump-fed. Thrust and specific impulse values are at sea level.

RS-2200 Rocketdyne LOx/LH2 rocket engine. Development cancelled 1999. Linear Aerospike Engine developed for use on the Lockheed Reusable Launch Vehicle, the production follow-on to the X-33.

Photo Gallery

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J-2 Credit: Boeing / Rocketdyne

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