| 词条 | Space Shuttle Orbital Maneuvering System | ||
| 释义 |
|image = OMS Pod removal.png |imsize = 270px |caption = The underside of a left OMS/RCS pod. |name = Space Shuttle OMS/RCS Pod |manufacturer = Aerojet |country-origin = United States |rockets = Space Shuttle |status = Retired |launches = 135 |success = 134 |noburn = 1 (STS-51-L) |first = STS-1 (12 April 1981) |last = STS-135 (8 July 2011) |length = {{Convert|21.8|ft}} |width = {{Convert|11.37|ft}} (aft) {{Convert|8.14|ft}} (forward) |stagedata = |name = OMS Engine |engines = 1 AJ10-190 |thrust = {{Convert|26.7|kN}} |SI = 316 seconds (vacuum) |burntime = 15 hours (maximum service life) 1250 seconds (deorbit burn) 150–250 seconds (typical burn) |fuel = MMH/N2O4 }} {{Infobox rocket/Stage|name = Aft Primary RCS |engines = Primary RCS engines |thrust = {{Convert|3.87|kN}} |SI = |burntime = 1–150 seconds (each burn) 800 seconds (total) |fuel = MMH/N2O4 }} {{Infobox rocket/Stage|name = Aft Vernier RCS |engines = Vernier RCS engines |thrust = {{Convert|106|N|sigfig=2}} |SI = |burntime = 1–125 seconds (each burn) |fuel = MMH/N2O4 }} The Space Shuttle Orbital Maneuvering System (OMS), is a system of hypergolic liquid-propellant rocket engines used on the Space Shuttle. 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] 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,{{citation needed|date=February 2012}} which produces {{Convert|26.7|kN}} of thrust with a specific impulse (Isp) of 316 seconds.[3] Each engine could be reused for 100 missions and was capable of a total of 1,000 starts and 15 hours of burn time.{{citation needed|date=February 2012}} 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 dinitrogen tetroxide (N2O4), 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 {{convert|8174|kg}} of MMH and {{convert|13486|kg}} of N2O4, allowing the OMS to produce a total delta-v of around {{convert|1000|ft/s}} with a 65,000-pound (29,500 kg) payload.[4][5] References{{Commons category|Space Shuttle Orbital Maneuvering System}}1. ^{{Cite journal|title=Capability and flight record of the versatile space shuttle OMS engine|author=D. Craig Judd|publisher=NASA|year=1992|bibcode=1992spte.symp..107J}} {{Space Shuttle}}{{Use American English|date=January 2014}}2. ^1 {{Cite web|url=http://science.ksc.nasa.gov/shuttle/technology/sts-newsref/sts-oms.html|archiveurl=https://web.archive.org/web/20110629115908/http://science.ksc.nasa.gov/shuttle/technology/sts-newsref/sts-oms.html|archivedate=29 June 2011|title=Orbital Maneuvering System|publisher=NASA|year=1998}} 3. ^1 {{Cite web|url=http://www.astronautix.com/engines/ome.htm|title=OME|accessdate=4 January 2010|publisher=Encyclopedia Astronautica|year=2009|author=Encyclopedia Astronautica|deadurl=yes|archiveurl=https://web.archive.org/web/20100113042044/http://astronautix.com/engines/ome.htm|archivedate=13 January 2010|df=dmy-all}} 4. ^1 {{Cite web|url=http://spaceflight.nasa.gov/shuttle/reference/shutref/orbiter/oms/storage.html|title=Propellant Storage and Distribution|accessdate=8 February 2008|publisher=NASA|year=1998|author=NASA}} 5. ^{{cite web|date=9 May 1997|url=http://imagine.gsfc.nasa.gov/docs/ask_astro/answers/970509c.html|title=Spacecraft Fuel|publisher=NASA|author=David Palmer, Allie Cliffe and Tim Kallman}} 1 : Space Shuttle program |
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