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astronautix.com XLR-132

XLR-132
XLR-132 -

Credit: Boeing / Rocketdyne. 7,493 bytes. 145 x 235 pixels.



Manufacturer Name: RS-47. Government Designation: XLR-132. Designer: Rocketdyne. Developed in: 1983. Application: . Propellants: N2O4/MMH Thrust(vac): 1,700 kgf. Thrust(vac): 16.70 kN. Isp: 340 sec. Burn time: 4,000 sec. Mass Engine: 54 kg. Diameter: 0.6 m. Length: 1.2 m. Chambers: 1. Chamber Pressure: 102.00 bar. Country: USA. Status: Out of 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.


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Last update 12 March 2001.
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