LR105-5 (original) (raw)

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LR105-5

Part of LR105

MA-3
Credit: Boeing / Rocketdyne

Rocketdyne LOx/Kerosene rocket engine. Atlas E, F. Atlas Sustainer. Gas generator, pump-fed. Separate turbopumps for each booster engine. First flight 1960.

AKA: MA-3. Date: 1958. Number: 289 . Thrust: 386.40 kN (86,866 lbf). Specific impulse: 316 s. Specific impulse sea level: 220 s. Burn time: 430 s. Height: 2.70 m (8.80 ft). Diameter: 3.05 m (10.00 ft).

Thrust (sl): 269.000 kN (60,473 lbf). Thrust (sl): 27,430 kgf. Engine: 460 kg (1,010 lb). Chamber Pressure: 48.00 bar. Area Ratio: 25. Propellant Formulation: Lox/RP-1. Thrust to Weight Ratio: 85.6521739130435. Oxidizer to Fuel Ratio: 2.25. Coefficient of Thrust vacuum: 1.84806464629871. Coefficient of Thrust sea level: 1.32723131296538.

Country: USA. Launch Vehicles: Atlas Centaur LV-3C, Atlas E, Atlas Agena B, Atlas F, Atlas Agena D, Atlas Centaur D, Atlas SLV-3. Propellants: Lox/Kerosene. Stages: Atlas E/F, Atlas Agena SLV-3, Atlas Centaur SLV-3C/D. Agency: Rocketdyne.

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