LR-105-5

MA-3
Credit - Boeing / Rocketdyne

Manufacturer Name: MA-3. Government Designation: LR105-5. Designer: Rocketdyne. Developed in: 1958. Application: Atlas E, F. Propellants: Lox/Kerosene. Thrust(vac): 386.400 kN (86,866 lbf). Thrust(sl): 269.000 kN (60,473 lbf). Isp: 316 sec. Isp (sea level): 220 sec. Burn time: 430 sec. Mass Engine: 460 kg (1,010 lb). Diameter: 3.05 m (10.00 ft). Length: 2.70 m (8.80 ft). 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. First Flight: 1960. Last Flight: 1995. Flown: 289.

Atlas Sustainer. Gas generator, pump-fed. Separate turbopumps for each booster engine.

LR-105-5 used on Rocket Stages

Used on stage: Atlas Agena SLV-3. on launch vehicle: Atlas LV-3A / Agena B.

Used on stage: Atlas Agena SLV-3. on launch vehicle: SLV-3 Atlas.

Used on stage: Atlas Agena SLV-3. on launch vehicle: SLV-3 Atlas / Agena B.

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

Used on stage: Atlas Centaur SLV-3C/D. on launch vehicle: Atlas Centaur SLV-3C.

Used on stage: Atlas Centaur SLV-3C/D. on launch vehicle: Atlas Centaur SLV-3D.

Used on stage: Atlas E/F. on launch vehicle: Atlas E.

Used on stage: Atlas E/F. on launch vehicle: Atlas F.

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