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astronautix.com LR-105-5
MA-3
MA-3 -

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

Manufacturer Name: MA-3. Government Designation: LR-105-5. Designer: Rocketdyne. Developed in: 1958. Application: Atlas E, F. Used on stages: Atlas Agena SLV-3, Atlas Centaur SLV-3C/D, Atlas E/F. Used on launch vehicles: Atlas Centaur SLV-3C, Atlas Centaur SLV-3D, Atlas E, Atlas F, Atlas LV-3A / Agena B, SLV-3 Atlas, SLV-3 Atlas / Agena B, SLV-3 Atlas / Agena D. Propellants: Lox/Kerosene Thrust(vac): 39,400 kgf. Thrust(vac): 386.40 kN. Isp: 316 sec. Isp (sea level): 220 sec. Burn time: 430 sec. Mass Engine: 460 kg. Diameter: 3.1 m. Length: 2.7 m. Chambers: 1. Chamber Pressure: 48.00 bar. Area Ratio: 25.00. Oxidizer to Fuel Ratio: 2.25. Thrust to Weight Ratio: 85.65. Country: USA. Status: In Production. First Flight: 1960. Last Flight: 1995. Flown: 222. Comments: Atlas Sustainer. Gas generator, pump-fed. Separate turbopumps for each booster engine.
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Last update 12 March 2001.
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