LR-89-7

MA-5
Credit - Boeing / Rocketdyne

Manufacturer Name: MA-5. Government Designation: LR89-7. Designer: Rocketdyne. Developed in: 1960. Application: Atlas space launchers. Propellants: Lox/Kerosene. Thrust(vac): 948.000 kN (213,118 lbf). Thrust(sl): 835.100 kN (187,738 lbf). Isp: 294 sec. Isp (sea level): 259 sec. Burn time: 174 sec. Mass Engine: 712 kg (1,569 lb). Diameter: 1.53 m (5.00 ft). Length: 3.40 m (11.10 ft). 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: Out of production. First Flight: 1963. Last Flight: 1997. Flown: 198.

Designed for booster applications. Gas generator, pump-fed. Shared turbopumps for booster engines. Evolved from MA-2 ICBM system.

LR-89-7 used on Rocket Stages

Used on stage: Atlas MA-5. on launch vehicle: Atlas / Agena D SLV-3A.

Used on stage: Atlas MA-5. on launch vehicle: Atlas Centaur SLV-3C.

Used on stage: Atlas MA-5. on launch vehicle: Atlas Centaur SLV-3D.

Used on stage: Atlas MA-5. on launch vehicle: Atlas G.

Used on stage: Atlas MA-5. on launch vehicle: Atlas H.

Used on stage: Atlas MA-5. on launch vehicle: Atlas I.

Used on stage: Atlas MA-5. on launch vehicle: Atlas LV-3A / Agena D.

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