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MA-5 -

Credit: Boeing / Rocketdyne. 13,737 bytes. 233 x 235 pixels.

Manufacturer Name: MA-5. Government Designation: LR-89-7. Designer: Rocketdyne. Developed in: 1960. Application: Atlas space launchers. Used on stages: Atlas MA-5. Used on launch vehicles: Atlas / Agena D SLV-3A, Atlas Centaur SLV-3C, Atlas Centaur SLV-3D, Atlas G, Atlas H, Atlas I, Atlas LV-3A / Agena D. Propellants: Lox/Kerosene Thrust(vac): 96,670 kgf. Thrust(vac): 948.00 kN. Isp: 294 sec. Isp (sea level): 259 sec. Burn time: 174 sec. Mass Engine: 712 kg. Diameter: 2.5 m. Length: 3.4 m. Chambers: 1. Chamber Pressure: 42.00 bar. Area Ratio: 8.00. Oxidizer to Fuel Ratio: 2.25. Thrust to Weight Ratio: 135.87. Country: USA. Status: In Production. First Flight: 1963. Last Flight: 1997. Flown: 198. Comments: Designed for booster applications. Gas generator, pump-fed. Shared turbopumps for booster engines. Evolved from MA-2 ICBM system.
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Last update 12 March 2001.
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