TR-201

TR-201

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Engine Model: TR-201. Designer: TRW. Propellants: N2O4/Aerozine-50. Thrust(vac): 41.900 kN (9,419 lbf). Isp: 301 sec. Burn time: 322 sec. Mass Engine: 113 kg (249 lb). Diameter: 1.38 m (4.52 ft). Length: 2.27 m (7.44 ft). 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. First Flight: 1972. Last Flight: 1989. Flown: 90.

Apollo lunar module ascent stage engines. Surplus engines used on Delta P stage.

TR-201 used on Rocket Stages

Used on stage: Delta. on launch vehicle: Atlas.

Used on stage: Delta. on launch vehicle: Delta.

Used on stage: Delta. on launch vehicle: Delta IV.

Used on stage: Delta. on launch vehicle: Vanguard.

TR-201 used on Spacecraft

Used on: Apollo LM.

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© Mark Wade, 1997 - 2008 except where otherwise noted.