TR-201: Difference between revisions
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The TR-201 is an [[Aerozine 50]] propellent, and [[N2O4]] oxidiser [[rocket engine]] developed by [[TRW|Space Technology Laboratories]] from the [[Descent Propulsion System|Lunar Module Descent Engine (LMDE]]. This engine used a [[pintle injector]], TRW developed this technology and holds the US patent. This injector design is also used on SpaceX [[Merlin]] engines.<ref>{{cite web |url=http://www.astronautix.com/engines/tr201.htm |title=TR-201 |publisher=Encyclopedia Astronautica |accessdate=4 June 2012 }}</ref> |
The TR-201 is an [[Aerozine 50]] propellent, and [[N2O4]] oxidiser [[rocket engine]] developed by [[TRW|Space Technology Laboratories]] from the [[Descent Propulsion System|Lunar Module Descent Engine (LMDE)]]. This engine used a [[pintle injector]], TRW developed this technology and holds the US patent. This injector design is also used on SpaceX [[Merlin]] engines.<ref>{{cite web |url=http://www.astronautix.com/engines/tr201.htm |title=TR-201 |publisher=Encyclopedia Astronautica |accessdate=4 June 2012 }}</ref> |
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== Requirements == |
== Requirements == |
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Revision as of 15:43, 4 June 2012
| Country of origin |  United States |
|---|---|
| Date | 1972-1988 |
| Manufacturer | TRW |
| Application | Upper stage/Spacecraft propulsion |
| Status | Retired |
| Liquid-fuel engine | |
| Propellant | N2O4 / Aerozine 50 |
| Cycle | Pressure-fed cycle |
| Configuration | |
| Chamber | 1 |
| Performance | |
| Thrust, vacuum | 41.90 kN (9,419 lbf) |
| Thrust-to-weight ratio | 31.4338235294118 |
| Chamber pressure | 7.00 bar |
| Specific impulse, vacuum | 301 s (3,050 N•s/kg) |
| Dimensions | |
| Length | 2.27 m (7.44 ft) |
| Diameter | 1.38 m (4.52 ft) |
| Dry mass | 113 kg (249 lb) |
| Used in | |
| Delta P, upper stage | |
The TR-201 is an Aerozine 50 propellent, and N2O4 oxidiser rocket engine developed by Space Technology Laboratories from the Lunar Module Descent Engine (LMDE). This engine used a pintle injector, TRW developed this technology and holds the US patent. This injector design is also used on SpaceX Merlin engines.[1]
Requirements
Development
Delta Usage
the TR-201 was used in the second stage, Delta P, of the Delta rocket for 77 launches between 1973 to 1988. It had a 100% reliability record during this 15 year period..[2]
References
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