TRW N2O4/MMH rocket engine. 0.025 kN. In Production. Isp=240s. Mono-propellant Hydrazine Thrusters. First flight 1991.
Applications: missions requiring duty cycle flexibility. First Flight: 1991. Number Produced: 22. Mass: 1.13 kg. Length: 21 cm. Engine Cycle: decomposition of hydrazine over heated shell catalyst. Thrust: 12-24.5 N in vacuum. Isp: 232-240 sec in vacuum at steady state conditions. Inlet Pressure: 6.8-31.6 atm. Burn Time: 0.050 sec up to several hours. Minimum Firing Bit: 0.025 sec. Total Cycles: 50,000. Random Vibration: 21 g rms.
Engine: 1.13 kg (2.49 lb). Chamber Pressure: 32.00 bar. Thrust to Weight Ratio: 2.21.
Status: In Production.
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Unfuelled mass: 1.13 kg (2.49 lb).
Thrust: 25 N (6 lbf).
Specific impulse: 240 s.
Associated Manufacturers and Agencies
TRW American manufacturer of rockets, spacecraft, and rocket engines. TRW Corporation, Redondo Beach, CA, USA. More...
N2O4/MMH Nitrogen tetroxide became the storable liquid propellant of choice from the late 1950's. Monomethylhydrazine (CH3NHNH2) is a storable liquid fuel that found favour in the United States for use in orbital spacecraft engines. Its advantages in comparison to UDMH are higher density and slightly higher performance. More...
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