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From Wikipedia, the free encyclopedia

Delta-P
ManufacturerTRW and McDonnell Douglas
Country of originUnited States
Used onDelta 1000
Delta 2000
Delta 3000
General characteristics
Height5.9 m (19 ft)[1]
Diameter2.4 m (7.9 ft)[1]
Gross mass6,954 kg (15,331 lb)[1]
Engine details
Engines1 TR-201
Thrust43.63 kN (9,810 lbf)[1]
Specific impulse319 seconds (3.13 km/s)[1]
Burn time431 seconds[1]
FuelAerozine 50 / N
2
O
4

The Delta-P is an American rocket stage, developed by McDonnell Douglas and TRW, first used on November 10, 1972 as the second stage for the Delta 1000 series. It continued to serve as the second stage for subsequent Delta 2000 and Delta 3000 flights for 17 years, with its last usage on February 8, 1988. It is propelled by a single TRW TR-201 rocket engine, fueled by Aerozine 50 and dinitrogen tetroxide,[1] which are hypergolic.

The Delta-P traces its heritage to the Apollo Lunar Module's Descent 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 the Apollo 5 mission, in a low Earth orbit test on January 22, 1968.

As the supply of these surplus Apollo engines was depleted, the Douglas/Aerojet Delta-K upper stage was introduced in the Delta 3000 program. The Delta-K was then exclusively used on the second stage for the Delta 4000, Delta 5000, and subsequent Delta II.

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Transcription

References

  1. ^ a b c d e f g Wade, Mark (1997-01-30). "Delta P". Encyclopedia Astronautica. Archived from the original on 2012-06-17. Retrieved 2008-06-22.
  2. ^ Wade, Mark. "TR-201". Encyclopedia Astronautica. Archived from the original on 6 July 2008. Retrieved 2008-06-22.


This page was last edited on 31 January 2021, at 16:16
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