Manufacturer | Aerojet |
---|---|
Country of origin | United States |
Used on | Space Shuttle/Orion European Service Module |
General characteristics | |
Length | 21.8 feet (6.6 m) |
Width |
|
Launch history | |
Status | Pod Retired/Engines Active |
Total launches | 135 Space Shuttle/ 1 Orion |
Successes (stage only) | 134 Space Shuttle/ 1 Orion |
Lower stage failed | 1 (STS-51-L) |
First flight | STS-1 (12 April 1981) |
Last flight | |
OMS Engine | |
Powered by | 1 AJ10-190 |
Maximum thrust | 26.7 kilonewtons (6,000 lbf) |
Specific impulse | 316 seconds (vacuum) |
Burn time |
|
Propellant | MMH/N 2O 4 |
Aft Primary RCS | |
Powered by | Primary RCS engines |
Maximum thrust | 3.87 kilonewtons (870 lbf) |
Burn time |
|
Propellant | MMH/N 2O 4 |
Aft Vernier RCS | |
Powered by | Vernier RCS engines |
Maximum thrust | 106 newtons (24 lbf) |
Burn time | 1–125 seconds (each burn) |
Propellant | MMH/N 2O 4 |
The Orbital Maneuvering System (OMS) is a system of hypergolic liquid-propellant rocket engines used on the Space Shuttle and the Orion MPCV. Designed and manufactured in the United States by Aerojet,[1] the system allowed the orbiter to perform various orbital maneuvers according to requirements of each mission profile: orbital injection after main engine cutoff, orbital corrections during flight, and the final deorbit burn for reentry.[2] From STS-90 onwards the OMS were typically ignited part-way into the Shuttle's ascent for a few minutes to aid acceleration to orbital insertion. Notable exceptions were particularly high-altitude missions such as those supporting the Hubble Space Telescope (STS-31) or those with unusually heavy payloads such as Chandra (STS-93). An OMS dump burn also occurred on STS-51-F, as part of the Abort to Orbit procedure.[3]
The OMS consists of two pods mounted on the orbiter's aft fuselage, on either side of the vertical stabilizer.[2] Each pod contains a single AJ10-190 engine,[4] based on the Apollo Service Module's Service Propulsion System engine,[5] which produces 26.7 kilonewtons (6,000 lbf) of thrust with a specific impulse (Isp) of 316 seconds.[4] The oxidizer-to-fuel ratio is 1.65-to-1, The expansion ratio of the nozzle exit to the throat is 55-to-1, and the chamber pressure of the engine is 8.6 bar.[2] The dry weight of each engine is 118kg (260lb). Each engine could be reused for 100 missions and was capable of a total of 1,000 starts and 15 hours of burn time.[2]
These pods also contained the Orbiter's aft set of reaction control system (RCS) engines, and so were referred to as OMS/RCS pods. The OM engine and RCS both burned monomethylhydrazine (MMH) as fuel, which was oxidized with MON-3 (mixed oxides of nitrogen, 3% nitric acid), with the propellants being stored in tanks within the OMS/RCS pod, alongside other fuel and engine management systems.[6] When full, the pods together carried around 4,087 kilograms (9,010 lb) of MMH and 6,743 kilograms (14,866 lb) of MON-3, allowing the OMS to produce a total delta-v of around 305 metres per second (1,000 ft/s) with a 29,000-kilogram (64,000 lb) payload.[6][7]