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Orbital Maneuvering System

Nowadays, Orbital Maneuvering System is a topic that has captured the attention of many people around the world. With its relevance in our current society, Orbital Maneuvering System has reached a level of importance that goes beyond simply being a fad. Over the years, it has evolved and become a focal point of discussion and interest in various areas. From its impact on technology to its influence on popular culture, Orbital Maneuvering System has proven to be a topic worth exploring in depth to understand its true reach and relevance today. In this article, we will delve into the world of Orbital Maneuvering System to better understand its impact and importance in our daily lives.

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"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
ManufacturerAerojet
Country of originUnited States
Used onSpace Shuttle/Orion European Service Module
General characteristics
Length21.8 ft (6.6 m)
Width
  • 11.37 ft (3.47 m) (aft)
  • 8.14 ft (2.48 m) (forward)
Launch history
StatusPod: Retired
Engines: Active
Total launchesSpace Shuttle: 135
Orion: 1
Successes
(stage only)		Space Shuttle: 134
Orion: 1
Lower stage
failed		1 (STS-51-L)
First flight12 April 1981 (STS-1)
Last flight
OMS Engine
Powered by1 × AJ10-190
Maximum thrust26.7 kN (6,000 lbf)
Specific impulse316 s (3.10 km/s)
Burn time
  • 15 hours (maximum service life)
  • 1,250 seconds (deorbit burn)
  • 150–250 seconds (typical burn)
PropellantMMH/MON-3
Aft Primary RCS
Powered byPrimary RCS engines
Maximum thrust3.87 kN (870 lbf)
Burn time
  • Up to 150 seconds (each burn)
  • 800 seconds (total)
PropellantMMH/MON-3
Aft Vernier RCS
Powered byVernier RCS engines
Maximum thrust106 N (24 lbf)
Burn timeUp to 125 seconds (each burn)
PropellantMMH/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,[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
    Diagram of OMS pod components
  • An OMS pod detached from an orbiter for maintenance
    An OMS pod detached from an orbiter for maintenance

Proposed OMS Payload Bay Kit

It was never built, but to augment the OMS an OMS Payload Bay Kit was proposed.[8] It would have used one, two or three sets of OMS tanks, installed in the payload bay, to provide an extra 150 m/s, 300 m/s or 450 m/s( (500 ft, 1000 ft/s or 1500 ft/s) of delta-V to the orbiter.[8] The orbiter control panels had related switches and gauges but they were nonfunctional.[9]: 1–2 

Orion ESM Main Engine

Orion ESM main engine at the top left on the service module

Following the retirement of the Shuttle, these engines were repurposed for use on the Orion spacecraft's service module.[10] This variant uses Monomethylhydrazine as fuel, with MON-3 Mixed Oxides of Nitrogen as oxidizer.[11] 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.[12]

References

Wikimedia Commons has media related to Space Shuttle Orbital Maneuvering System.
  1. ^ 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.
  2. ^ a b c d "Orbital Maneuvering System". NASA. 1998. Archived from the original on 29 June 2011.
  3. ^ 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.
  4. ^ a b Encyclopedia Astronautica (2009). "OME". Encyclopedia Astronautica. Archived from the original on 27 August 2016. Retrieved 16 September 2021.
  5. ^ Gibson, C.; Humphrles, C. Orbital Maneuvering System Design Evolution (PDF) (Report). NASA NTRS. Retrieved 6 December 2022.
  6. ^ a b NASA (1998). "Propellant Storage and Distribution". NASA. Archived from the original on 10 February 2001. Retrieved 8 February 2008.
  7. ^ David Palmer, Allie Cliffe and Tim Kallman (9 May 1997). "Spacecraft Fuel". NASA.
  8. ^ a b SHUTTLE PERFORMANCE ENHANCEMENTS USING AN OMS PAYLOAD BAY KIT 1991
  9. ^ Orbital Maneuvering System Workbook 2006
  10. ^ Bergin, Chris (20 June 2015). "Plum Brook prepped for EM-1 Orion Service Module testing". NASASpaceFlight.com. Retrieved 28 July 2015.
  11. ^ "Aerojet Rocketdyne - In-Space Propulsion Data Sheets" (PDF). Archived from the original (PDF) on 11 January 2020. Retrieved 7 December 2019.
  12. ^ "Aerojet Rocketdyne Awarded NASA Contract for Orion Spacecraft Main Engine | Aerojet Rocketdyne". www.rocket.com. Retrieved 6 December 2022.

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