Orbital Maneuvering System
The underside of a left OMS/RCS pod on Space Shuttle Endeavour | |
| Manufacturer | Aerojet |
|---|---|
| Country of origin | United States |
| Used on | Space Shuttle/Orion European Service Module |
| General characteristics | |
| Length | 21.8 ft (6.6 m) |
| Width |
|
| Launch history | |
| Status | Pod: Retired Engines: Active |
| Total launches | Space Shuttle: 135 Orion: 1 |
| Successes (stage only) | Space Shuttle: 134 Orion: 1 |
| Lower stage failed | 1 (STS-51-L) |
| First flight | 12 April 1981 (STS-1) |
| Last flight | |
| OMS Engine | |
| Powered by | 1 × AJ10-190 |
| Maximum thrust | 26.7 kN (6,000 lbf) |
| Specific impulse | 316 s (3.10 km/s) |
| Burn time |
|
| Propellant | MMH/MON-3 |
| Aft Primary RCS | |
| Powered by | Primary RCS engines |
| Maximum thrust | 3.87 kN (870 lbf) |
| Burn time |
|
| Propellant | MMH/MON-3 |
| Aft Vernier RCS | |
| Powered by | Vernier RCS engines |
| Maximum thrust | 106 N (24 lbf) |
| Burn time | Up to 125 seconds (each burn) |
| Propellant | MMH/MON-3 |
The Orbital Maneuvering System (OMS) is a system of hypergolic liquid-propellant rocket engines used on the Space Shuttle and the Orion spacecraft. Designed and manufactured in the United States by Aerojet, 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. 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.
The OMS consists of two pods mounted on the orbiter's aft fuselage, on either side of the vertical stabilizer. Each pod contains a single AJ10-190 engine, based on the Apollo Service Module's Service Propulsion System engine, which produces 26.7 kilonewtons (6,000 lbf) of thrust with a specific impulse (Isp) of 316 seconds. 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. 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.
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. 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.
- Diagram of OMS pod components
- An OMS pod detached from an orbiter for maintenance
