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| Manufacturer | TRW andMcDonnell Douglas |
|---|---|
| Country of origin | United States |
| Used on | Delta 1000 Delta 2000 Delta 3000 |
| General characteristics | |
| Height | 5.9 m (19 ft)[1] |
| Diameter | 2.4 m (7.9 ft)[1] |
| Gross mass | 6,954 kg (15,331 lb)[1] |
| Engine details | |
| Powered by | 1TR-201 |
| Maximum thrust | 43.63 kN (9,810 lbf)[1] |
| Specific impulse | 319 seconds (3.13 km/s)[1] |
| Burn time | 431 seconds[1] |
| Propellant | Aerozine 50 /N2O4 |
TheDelta-P is an Americanrocketstage, developed by McDonnell Douglas and TRW, first used on November 10, 1972 as the second stage for theDelta 1000 series. It continued to serve as the second stage for subsequentDelta 2000 andDelta 3000 flights for 17 years, with its last usage on February 8, 1988. It is propelled by a single TRWTR-201 rocket engine, fueled byAerozine 50 anddinitrogen tetroxide,[1] which arehypergolic.
The Delta-P traces its heritage to theApolloLunar Module'sDescent Propulsion System. The TR-201 engine is the Descent Propulsion System modified to be a fixed thrust engine.[2] The Descent Propulsion System was first fired in flight during theApollo 5 mission, in alow Earth orbit test on January 22, 1968.
As the supply of these surplus Apollo engines was depleted, the Douglas/AerojetDelta-K upper stage was introduced in theDelta 3000 program. The Delta-K was then exclusively used on the second stage for theDelta 4000,Delta 5000, and subsequentDelta II.
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