Encyclopedia Astronautica
XLR132



rdxlr132.jpg
XLR-132
Credit: Boeing / Rocketdyne
Rocketdyne N2O4/MMH rocket engine. 16.7 kN. Out of Production. Isp=340s. Pump-fed high performance upper stage engine for perigee/apogee stages. as well as transfer vehicles and lunar and Martian missions. Tested extensively but no production.

The Rocketdyne Company completed the advanced technology development phase of this pump-fed high performance upper stage engine. Its performance, mass, and extended space storability make it a candidate for perigee/apogee stages. as well as transfer vehicles and lunar and Martian missions. Applications: kick stages, deep space, Space Transfer Vehicle, Orbit Transfer Vehicle. Dry Mass: 54 kg. Length: 120 cm. Maximum Diameter: 60 cm. Engine Cycle: gas generator. Oxidizer: nitrogen tetroxide at 3.3 kg/sec. Fuel: monomethyl hydrazine at 1.68 kg/sec. Thrust: 16.68 kN vacuum. Isp: 340 sec vacuum minimum. Expansion Ratio: 400:1. Thrust Chamber Materials: columbium. Thrust Chamber Cooling: radiative. Combustion Chamber Pressure: 102 atm at injector end. Combustion Chamber Cooling regenerative by Oxidizer. Combustion Chamber Ignition: hypergolic. Burn Time: 4000 sec in 10 starts. Gas generator, pump-fed.

Engine: 54 kg (119 lb). Chamber Pressure: 103.00 bar. Thrust to Weight Ratio: 31.48.

Status: Out of Production.
Height: 1.20 m (3.90 ft).
Diameter: 0.60 m (1.96 ft).
Thrust: 16.70 kN (3,754 lbf).
Specific impulse: 340 s.
Burn time: 4,000 s.
First Launch: 1983.

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Associated Propellants
  • N2O4/MMH Nitrogen tetroxide became the storable liquid propellant of choice from the late 1950's. Monomethylhydrazine (CH3NHNH2) is a storable liquid fuel that found favour in the United States for use in orbital spacecraft engines. Its advantages in comparison to UDMH are higher density and slightly higher performance. More...

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