TRW N2O4/MMH rocket engine. 17.8 kN. Design concept 1960's. 1960's designs for 'big dumb booster'. Isp=300s.
Engine: 41 kg (90 lb). Area Ratio: 98. Thrust to Weight Ratio: 44.3436633912824. Coefficient of Thrust vacuum: 0. Coefficient of Thrust sea level: 0.
Status: Design concept 1960's.
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Unfuelled mass: 41 kg (90 lb).
Diameter: 0.67 m (2.19 ft).
Thrust: 17.80 kN (4,002 lbf).
Specific impulse: 300 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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