Encyclopedia Astronautica
Shuttle Orbiter OMS


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.
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.

More... - Chronology...


Associated Countries
Associated Engines
  • 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...

Associated Propellants
  • 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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