TR-201

TR-201

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, second stage

The TR-201 or TR201 is a hypergolic 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 Space Technology Laboratories as a derivative of the Lunar Module Descent Engine (LMDE). This engine used a pintle injector technology that was developed and patented (US patent) by TRW. This injector technology and design is also used on SpaceX Merlin engines.

Delta-P Usage

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

The maiden flight of the TR-201 engine was for the launch of the Anik A1 satellite on November 10, 1972 (Delta 1914).

Anik A1 became the world's first national domestic satellite (Telesat, Canada).

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