Jump to content

TR-201: Difference between revisions

From Wikipedia, the free encyclopedia
Content deleted Content added
mNo edit summary
Line 8: Line 8:
|manufacturer = [[TRW]]
|manufacturer = [[TRW]]
|purpose = Upper stage/[[Spacecraft]] propulsion
|purpose = Upper stage/[[Spacecraft]] propulsion
predecessor=[[Descent Propulsion Sytem|LMDE]]
|status=Retired
|status=Retired
|cycle=[[Pressure-fed cycle (rocket)|Pressure-fed cycle]]
|cycle=[[Pressure-fed cycle (rocket)|Pressure-fed cycle]]

Revision as of 20:43, 8 June 2012

TR-201
Country of origin United States
Date1972-1988
ManufacturerTRW
ApplicationUpper stage/Spacecraft propulsion predecessor=LMDE
StatusRetired
Liquid-fuel engine
PropellantN2O4 / Aerozine 50
CyclePressure-fed cycle
Configuration
Chamber1
Performance
Thrust, vacuum41.90 kN (9,419 lbf)
Thrust-to-weight ratio31.4338235294118
Chamber pressure7.00 bar
Specific impulse, vacuum301 s (3,050 N•s/kg)
Dimensions
Length2.27 m (7.44 ft)
Diameter1.38 m (4.52 ft)
Dry mass113 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 that was developed and USA patented (1972) by TRW. This injector technology and design is also used on SpaceX Merlin engines.[1]

Requirements

Development

Delta-P Usage

The TR-201 engine was used in the second stage, Delta P, of the Delta rocket for 77 launches between 1972 to 1988.

The TR-201 had a 100% reliability record as Delta-P during this 15 year period.[2]

References

  1. ^ "TR-201". Encyclopedia Astronautica. Retrieved 4 June 2012.
  2. ^ "Delta P". Encyclopedia Astronautica. Retrieved 4 June 2012.