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astronautix.com LR-105-7

MA-5
MA-5 -

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



Manufacturer Name: MA-5. Government Designation: LR-105-7. Designer: Rocketdyne. Developed in: 1960. Application: Atlas space launchers. Used on stages: Atlas Agena SLV-3A, Atlas G/H/I. Used on launch vehicles: Atlas / Agena D SLV-3A, Atlas G, Atlas H, Atlas I, Atlas LV-3A / 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: 266 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: 2.27. Thrust to Weight Ratio: 83.83. Country: USA. Status: In Production. First Flight: 1963. Last Flight: 1997. Flown: 50. Comments: Atlas Sustainer. Gas generator, pump-fed. Evolved from MA-2 ICBM system.
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Last update 12 March 2001.
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