Hypergolic orbital maneuvering engines used on NASA's Space Shuttle
"Orbital Maneuvering System" redirects here, but can refer to any system used to modify a spacecraft's orbit. For the similarly-named Gemini component, see Orbit Attitude and Maneuvering System.
Space Shuttle OMS/RCS Pod
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 feet (6.6 m)
Width
11.37 feet (3.47 m) (aft)
8.14 feet (2.48 m) (forward)
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
STS-135 (8 July 2011) for the Space Shuttle
Artemis 1 (16 November 2022) for the Orion
OMS Engine
Powered by
1 AJ10-190
Maximum thrust
26.7 kilonewtons (6,000 lbf)
Specific impulse
316 seconds (vacuum)
Burn time
15 hours (maximum service life)
1250 seconds (deorbit burn)
150–250 seconds (typical burn)
Propellant
MMH/N 2O 4
Aft Primary RCS
Powered by
Primary RCS engines
Maximum thrust
3.87 kilonewtons (870 lbf)
Burn time
1–150 seconds (each burn)
800 seconds (total)
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]
Diagram of OMS pod components
An OMS pod detached from an orbiter for maintenance
^D. Craig Judd (1992). "Capability and flight record of the versatile space shuttle OMS engine". Space Technology and Science. NASA: 107. Bibcode:1992spte.symp..107J.
^ abcd"Orbital Maneuvering System". NASA. 1998. Archived from the original on 29 June 2011.
^Legler R. D. and Bennett F. V. (2011). "Space Shuttle Missions Summary, NASA TM-2011-216142" (PDF). NASA. Archived from the original (PDF) on 26 January 2017.
^ abEncyclopedia Astronautica (2009). "OME". Encyclopedia Astronautica. Archived from the original on 27 August 2016. Retrieved 16 September 2021.
^Gibson, C.; Humphrles, C. Orbital Maneuvering System Design Evolution (PDF) (Report). NASA NTRS. Retrieved 6 December 2022.
^ abNASA (1998). "Propellant Storage and Distribution". NASA. Archived from the original on 10 February 2001. Retrieved 8 February 2008.
^David Palmer, Allie Cliffe and Tim Kallman (9 May 1997). "Spacecraft Fuel". NASA.
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Global Information
Diagram of OMS pod components
An OMS pod detached from an orbiter for maintenance
