This page no longer updated from 31 October 2001. Latest version can be found at XLR-105-5

MA-3 -

Credit: Boeing / Rocketdyne. 10,861 bytes. 210 x 235 pixels.

Manufacturer Name: MA-2. Government Designation: XLR-105-5. Designer: Rocketdyne. Developed in: 1958. Application: Atlas D. Used on stages: Atlas Able, Atlas Agena LV-3A, Atlas B, Atlas Centaur LV-3C, Atlas D. Used on launch vehicles: Atlas Able, Atlas B, Atlas C, Atlas Centaur LV-3C, Atlas D, Atlas LV-3A / Agena A, Atlas LV-3B / Mercury. Propellants: Lox/Kerosene Thrust(vac): 37,038 kgf. Thrust(vac): 363.20 kN. Isp: 309 sec. Isp (sea level): 215 sec. Burn time: 335 sec. Mass Engine: 460 kg. Diameter: 3.1 m. Chambers: 1. Chamber Pressure: 48.00 bar. Area Ratio: 25.00. Thrust to Weight Ratio: 80.52. Country: USA. Status: Out of Production. First Flight: 1958. Last Flight: 1967. Flown: 111. Comments: Atlas Sustainer. Gas generator, pump-fed. Shared turbopumps for booster engines.
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Last update 12 March 2001.
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