MRE-5/Compton Observatory
Engine · USA
Original archive entry. The text, images and links below are kept as they were written.
TRW N2O4/MMH rocket engine. In Production. 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.
Related
- Family
- Storable liquid
- Country
- USA
- Propellants
- N2O4/MMH
- Agency
- TRW