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Manufacturer Name: AJ10-190. Designer: Aerojet. Used on stages: Shuttle C, Shuttle Orbiter OMS. Used on launch vehicles: IHLLV, Saturn Shuttle, Shuttle C, Shuttle LRB. Used on spacecraft: Atlantis, Columbia, Discovery, Endeavour. Propellants: N2O4/MMH Thrust(vac): 2,721 kgf. Thrust(vac): 26.70 kN. Isp: 316 sec. Burn time: 1,250 sec. Mass Engine: 118 kg. Diameter: 1.2 m. Length: 2.0 m. Chambers: 1. Chamber Pressure: 8.62 bar. Area Ratio: 55.00. Oxidizer to Fuel Ratio: 1.65. Thrust to Weight Ratio: 23.06. Country: USA. Status: In Production. First Flight: 1981. Last Flight: 1999. References: 225 .

Used in Shuttle Orbiter Orbital Maneuvering System (OMS); proposed for Shuttle C OMS. The Shuttle Orbiter carries two OMS pods (name coined by Aerojet), each housing a single Aerojet OM Engine for orbit insertion, maneuvering, and re-entry initiation. They are capable of 100 missions and 500 starts in space.. Manufacturer: AeroJet Propulsion Division. First Flown: April 12th, 1981, on the Orbiter Columbia. Mounting: gimballed ( 7 degrees yaw, 6 pitch by two electromechanical actuators for thrust vector control. Engine Cycle: pressure-fed (improvement underway for pump-fed). Oxidizer: 6743 kg nitrogen tetroxide in each pod (pods can be cross-linked). Fuel: 4087 kg of monomethyl hydrazine in each pod (pods can be cross-linked). Mixture Ratio: 1.65:1. Cooling Method: fuel regenerative for chamber, radiative for nozzle. Burn Time: qualified for 500 starts, 15 hr/100 mission life, longest firing 1250 sec, de-orbit. burn typically 150-250 secs.

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Last update 12 March 2001.
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