Orbital Maneuvering System

|country-origin = United States Engines: Active Orion: 1 Orion: 1

• Space Shuttle: 8 July 2011 (STS-135)
• Orion: 16 November 2022 (Artemis I)}}
• 11.37 ft (aft)
• 8.14 ft (forward)}}
• 15 hours (maximum service life)
• 1,250 seconds (deorbit burn)
• 150–250 seconds (typical burn)}}
• Up to 150 seconds (each burn)
• 800 seconds (total)}}

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 kN 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 4087 kg of MMH and 6743 kg of MON-3, allowing the OMS to produce a total delta-v of around 305 m/s with a 29000 kg payload. File:OMS Pod schematic.png|Diagram of OMS pod components File:OMS pod.jpg|An OMS pod detached from an orbiter for maintenance

Orion ESM Main Engine

Following the retirement of the Shuttle, these engines were repurposed for use on the Orion spacecraft's service module. This variant uses Monomethylhydrazine as fuel, with MON-3 Mixed Oxides of Nitrogen as oxidizer. It is planned to be used for the first six flights of the Artemis program, afterwards it would be replaced by a new "Orion Main Engine" starting Artemis 7.