This page no longer updated from 31 October 2001. Latest version can be found at TR-201

Designer: TRW. Used on stages: Delta P. Used on launch vehicles: Delta 2914, Delta 3914. Used on spacecraft: Apollo LM. Propellants: N2O4/Aerozine-50 Thrust(vac): 4,275 kgf. Thrust(vac): 41.90 kN. Isp: 301 sec. Burn time: 322 sec. Mass Engine: 113 kg. Diameter: 1.4 m. Length: 2.3 m. Chambers: 1. Chamber Pressure: 7.00 bar. Area Ratio: 46.00. Oxidizer to Fuel Ratio: 1.59. Thrust to Weight Ratio: 31.43. Country: USA. Status: Out of Production. First Flight: 1974. Last Flight: 1988. Flown: 69. Comments: Apollo lunar module ascent stage engines. Surplus engines used on Delta P stage.
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Last update 12 March 2001.
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© Mark Wade, 2001 .