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- TR-201 abstract "The TR-201 or TR201 is a hypergolic pressure-fed rocket engine used to propel the upper stage of the Delta rocket, referred to as Delta-P, from 1972 to 1988.The rocket engine uses Aerozine 50 as fuel, and N2O4 as oxidizer. It was developed in early 1970s by TRW as a derivative of the Lunar Module Descent Engine (LMDE). This engine used a pintle injector first developed by TRW in late 1950s and received US Patent in 1972. This injector technology and design is also used on SpaceX Merlin engines.The thrust chamber was initially developed for the Apollo Lunar Module and was subsequently adopted for the Delta Expendable Launch Vehicle 2nd stage. The engine made 10 flights during the Apollo program and 77 during its Delta career between 1974-1988. The TRW TR-201 was re-configured as a fixed thrust version of the Lunar Module Descent Engine (LMDE) for Delta's stage 2. Multi start operation is adjustable up to 55.6 kN and propellant throughput up to 7,711 kg; and the engine can be adapted to optional expansion ratio nozzles. Development of the innovative thrust chamber and pintle design is credited to TRW Aerospace Engineer Dr. Peter Staudhammer.The combustion chamber consists of an ablative-lined titanium alloy case to the 16:1 area ratio. Fabrication of the 6Al4V alloy titanium case was accomplished by machining the chamber portion and the exit cone portion from forgings and welding them into one unit at the throat centerline. The ablative liner is fabricated in two segments and installed from either end. The shape of the nozzle extension is such that the ablative liner is retained in the exit cone during transportation, launch and boost. During engine firing, thrust loads force the exit cone liner against the case. The titanium head end assembly which contains the Pintle Injector and propellant valve subcomponents is attached with thirty-six A-286 steel ¼ inch bolts.In order to keep the maximum operating temperatures of the titanium case in the vicinity of 800 degrees (F), the ablative liner was designed as a composite material providing the maximum heat sink and minimum weight. The selected configuration consisted of a high density, erosion-resistant silica cloth/phenolic material surrounded by a lightweight needle-felted silica mat/phenolic insulation.The installed Pintle Injector, unique to TRW designed liquid propulsion systems, provides improved reliability and less costly method of fuel-oxidizer impingement in the thrust chamber than conventional coaxial distributed-element injectors typically used on liquid bipropellant rocket engines.".
- TR-201 wikiPageID "36010782".
- TR-201 wikiPageLength "5476".
- TR-201 wikiPageOutDegree "25".
- TR-201 wikiPageRevisionID "703478720".
- TR-201 wikiPageWikiLink Aerozine_50.
- TR-201 wikiPageWikiLink Category:Rocket_engines.
- TR-201 wikiPageWikiLink Category:Rocket_engines_using_hypergolic_propellant.
- TR-201 wikiPageWikiLink Delta-P.
- TR-201 wikiPageWikiLink Delta_(rocket_family).
- TR-201 wikiPageWikiLink Descent_Propulsion_System.
- TR-201 wikiPageWikiLink Dinitrogen_tetroxide.
- TR-201 wikiPageWikiLink Hypergolic_propellant.
- TR-201 wikiPageWikiLink Merlin_(rocket_engine_family).
- TR-201 wikiPageWikiLink Niobium.
- TR-201 wikiPageWikiLink Pintle_injector.
- TR-201 wikiPageWikiLink Pressure-fed_engine.
- TR-201 wikiPageWikiLink Rocket_engine.
- TR-201 wikiPageWikiLink Spacecraft.
- TR-201 wikiPageWikiLink TRW_Inc..
- TR-201 wikiPageWikiLinkText "TR-201".
- TR-201 chamberPressure "7.0".
- TR-201 combustionChamber "1".
- TR-201 cycle Pressure-fed_engine.
- TR-201 date "1972".
- TR-201 diameter "1.38 m".
- TR-201 dryWeight "113.0".
- TR-201 fuel Aerozine_50.
- TR-201 length "2.27 m".
- TR-201 manufacturer TRW_Inc..
- TR-201 name "TR-201".
- TR-201 oxidiser Dinitrogen_tetroxide.
- TR-201 predecessor Descent_Propulsion_System.
- TR-201 purpose "Upper stage/Spacecraft propulsion".
- TR-201 specificImpulseVacuum "301.0".
- TR-201 status "Retired".
- TR-201 thrust(vac)_ "41.90 kN".
- TR-201 thrustToWeight "31.4338235294118".
- TR-201 type "liquid".
- TR-201 usedIn "Delta-P, second stage of Delta (rocket family)".
- TR-201 wikiPageUsesTemplate Template:Infobox_rocket_engine.
- TR-201 wikiPageUsesTemplate Template:Orbital_spacecraft_rocket_engines.
- TR-201 wikiPageUsesTemplate Template:Reflist.
- TR-201 wikiPageUsesTemplate Template:Rocket_Engines.
- TR-201 wikiPageUsesTemplate Template:TRW.
- TR-201 wikiPageUsesTemplate Template:USA.
- TR-201 subject Category:Rocket_engines.
- TR-201 subject Category:Rocket_engines_using_hypergolic_propellant.
- TR-201 hypernym Engine.
- TR-201 type Software.
- TR-201 comment "The TR-201 or TR201 is a hypergolic pressure-fed rocket engine used to propel the upper stage of the Delta rocket, referred to as Delta-P, from 1972 to 1988.The rocket engine uses Aerozine 50 as fuel, and N2O4 as oxidizer. It was developed in early 1970s by TRW as a derivative of the Lunar Module Descent Engine (LMDE). This engine used a pintle injector first developed by TRW in late 1950s and received US Patent in 1972.".
- TR-201 label "TR-201".
- TR-201 sameAs Q7671215.
- TR-201 sameAs TR-201.
- TR-201 sameAs TR-201.
- TR-201 sameAs m.0j_7lj5.
- TR-201 sameAs Q7671215.
- TR-201 wasDerivedFrom TR-201?oldid=703478720.
- TR-201 isPrimaryTopicOf TR-201.