Encyclopedia Astronautica
TR-201


TRW N2O4/Aerozine-50 rocket engine. 41.9 kN. Apollo lunar module ascent stage engines. Surplus engines used on Delta P stage. Isp=301s. First flight 1972.

Engine: 113 kg (249 lb). Chamber Pressure: 7.00 bar. Area Ratio: 46. Thrust to Weight Ratio: 31.4338235294118. Oxidizer to Fuel Ratio: 1.59. Coefficient of Thrust vacuum: 1.45719168532336.

Unfuelled mass: 113 kg (249 lb).
Height: 2.27 m (7.44 ft).
Diameter: 1.38 m (4.52 ft).
Thrust: 41.90 kN (9,419 lbf).
Specific impulse: 301 s.
Burn time: 322 s.
Number: 90 .

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Associated Countries
Associated Spacecraft
  • Apollo LM American manned lunar lander. 10 launches, 1968.01.22 (Apollo 5) to 1972.12.07 (Apollo 17). More...

See also
Associated Launch Vehicles
  • Delta 2000 American orbital launch vehicle. The Delta 2000 series used Castor 2 strap-ons together with an Extended Long Tank core equipped with the more powerful RS-27 engine. This engine was derived from surplus H-1 engines intended for the Saturn IB booster of the Apollo programme. The Delta P upper stage was built by Douglas and used surplus Apollo lunar module engines from TRW. More...
  • Delta 3000 American orbital launch vehicle. The Delta 3000 series upgraded the boosters to Castor 4 solid propellant strap-ons, while retaining the Extended Long Tank core with RS-27 engine. The 3910 series used the TRW Lunar Module engine in the second stage, while the 3920 series reintroduced the Aerojet AJ110 Delta engine. More...

Associated Manufacturers and Agencies
  • TRW American manufacturer of rockets, spacecraft, and rocket engines. TRW Corporation, Redondo Beach, CA, USA. More...

Associated Propellants
  • N2O4/Aerozine-50 Nitrogen tetroxide became the storable liquid propellant of choice from the late 1950's. Aerozine was a 50-50 mixture of hydrazine and UDMH developed for use in the Titan 2 missile. Copied in one Russian missile but otherwise straight UDMH used more commonly. Higher boiling point than UDMH. More...

Associated Stages
  • Delta P N2O4/Aerozine-50 propellant rocket stage. Loaded/empty mass 5,434/820 kg. Thrust 41.92 kN. Vacuum specific impulse 301 seconds. More...

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