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astronautix.com LR-89-5

B2C/MA-1/MA-2
B2C/MA-1/MA-2 -

Credit: Boeing / Rocketdyne. 9,398 bytes. 167 x 205 pixels.



Manufacturer Name: MA-3. Government Designation: LR-89-5. Designer: Rocketdyne. Developed in: 1958. Application: Atlas E, F. Used on stages: Atlas MA-3, Titan Cluster. Used on launch vehicles: Atlas Centaur LV-3C, Atlas E, Atlas F, Atlas LV-3A / Agena B, Saturn B-1, SLV-3 Atlas, SLV-3 Atlas / Agena B, SLV-3 Atlas / Agena D. Propellants: Lox/Kerosene Thrust(vac): 83,870 kgf. Thrust(vac): 822.50 kN. Isp: 290 sec. Isp (sea level): 256 sec. Burn time: 120 sec. Mass Engine: 720 kg. Diameter: 2.5 m. Length: 3.4 m. Chambers: 1. Chamber Pressure: 41.00 bar. Area Ratio: 8.00. Oxidizer to Fuel Ratio: 2.25. Thrust to Weight Ratio: 116.49. Country: USA. Status: In Production. First Flight: 1960. Last Flight: 1995. Flown: 370. References: 225 . Comments: Designed for booster applications. Gas generator, pump-fed. Separate turbopumps for each booster engine.
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Last update 12 March 2001.
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