TR-201
| Country of origin |  United States |
|---|---|
| Date | 1972-1988 |
| Manufacturer | TRW |
| Application | Upper stage/Spacecraft propulsion predecessor=LMDE |
| 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, second stage | |
The TR-201 or TR201 is a hypergolic pressure-fed rocket engine. It was used to propel the upper stage of the Delta rocket from 1972 to 1988. The rocket engine uses Aerozine 50 as a propellent, and N2O4 as the 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.[1]
Delta Usage
The TR-201 engine was used as the second stage for 77 Delta launches between 1972 to 1988. The engine had a 100% reliability record as during this 15 year operational period.[2]
References
| Liquid fuel |
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| Solid fuel |
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