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J-2
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 | J-2 Credit - © Mark Wade
| Manufacturer Name: J-2. Designer: Rocketdyne. Developed in: 1960. Propellants: Lox/LH2. Thrust(vac): 1,033.100 kN (232,250 lbf). Thrust(sl): 486.200 kN (109,302 lbf). Isp: 421 sec. Isp (sea level): 200 sec. Burn time: 475 sec. Mass Engine: 1,438 kg (3,170 lb). Diameter: 2.01 m (6.60 ft). Length: 3.38 m (11.08 ft). Chambers: 1. Chamber Pressure: 30.00 bar. Area Ratio: 28.00. Oxidizer to Fuel Ratio: 5.50. Thrust to Weight Ratio: 73.18. Country: USA. Status: Study 1961. First Flight: 1966. Last Flight: 1975. Flown: 87. Used in Saturn IVB stage in Saturn IB and Saturn V, and Saturn II stage in Saturn V. 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. Gas generator, pump-fed. J-2 used on Rocket Stages
J-2 used on Spacecraft
Bibliography and Further Reading - Kudryavtseva, V M, ed., Zhidkostnikh Raketnikh Dvigatley, Visshaya Shkola, Moscow, 1993. ISBN: 5060025632. Russian-language textbook on rocket theory. More at amazon.com...
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© Mark Wade, 1997 - 2007 except where otherwise noted.
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