N2O4/MMH propellant rocket stage. Loaded/empty mass 25,200/3,600 kg. Thrust 53.38 kN. Vacuum specific impulse 316 seconds. Two pods, mounted each side of vertical stabilizer, provide propulsion for orbit insertion, maneuver, and de-orbit.
Cost $ : 300.000 million. No Engines: 2.
AKA: Orbital Maneuvering System Pods.
More... - Chronology...
Status: Study 1984.
Gross mass: 25,200 kg (55,500 lb).
Unfuelled mass: 3,600 kg (7,900 lb).
Height: 37.24 m (122.17 ft).
Diameter: 4.90 m (16.00 ft).
Span: 23.79 m (78.05 ft).
Thrust: 53.38 kN (12,000 lbf).
Specific impulse: 316 s.
Burn time: 1,250 s.
OME Aerojet N2O4/MMH rocket engine. 26.7 kN. Study 1972. Isp=316s. Engine used in Shuttle Orbiter Orbital Maneuvering System pods, for orbit insertion, maneuvering, and re-entry initiation. First flight 1981. More...
Associated Launch Vehicles
Saturn Shuttle American orbital launch vehicle. A winged recoverable Saturn IC stage was considered instead of solid rocket boosters after the final shuttle design was selected. More...
Shuttle LRB American winged orbital launch vehicle. Shuttle with Liquid Rocket Boosters in place of Solid Rocket Boosters. 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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