Notional N2O4/MMH rocket engine. 17.8 kN. Development ended 1988. Pressure-fed engine. Isp=300s. Used on Liberty launch vehicle.
Thrust (sl): 11.900 kN (2,675 lbf). Thrust (sl): 1,209 kgf. Engine: 41 kg (90 lb). Area Ratio: 98. Thrust to Weight Ratio: 44.34.
Status: Development ended 1988.
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Unfuelled mass: 41 kg (90 lb).
Diameter: 1.43 m (4.69 ft).
Thrust: 17.80 kN (4,002 lbf).
Specific impulse: 300 s.
Specific impulse sea level: 200 s.
Burn time: 326 s.
Associated Launch Vehicles
Liberty American low cost orbital launch vehicle. Private commercial launch vehicle. 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...
Liberty 2 N2O4/MMH propellant rocket stage. Loaded/empty mass 2,180/180 kg. Thrust 17.79 kN. Vacuum specific impulse 300 seconds. More...
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