LR-89-5

B2C/MA-1/MA-2
Credit - Boeing / Rocketdyne

Manufacturer Name: MA-3. Government Designation: LR89-5. Designer: Rocketdyne. Developed in: 1958. Application: Atlas E, F. Propellants: Lox/Kerosene. Thrust(vac): 822.500 kN (184,905 lbf). Thrust(sl): 726.000 kN (163,211 lbf). Isp: 290 sec. Isp (sea level): 256 sec. Burn time: 120 sec. Mass Engine: 720 kg (1,580 lb). Diameter: 1.53 m (5.00 ft). Length: 3.40 m (11.10 ft). 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. First Flight: 1960. Last Flight: 1995. Flown: 504.

Designed for booster applications. Gas generator, pump-fed. Separate turbopumps for each booster engine.

LR-89-5 used on Rocket Stages

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

Used on stage: Atlas MA-3. on launch vehicle: Atlas E.

Used on stage: Atlas MA-3. on launch vehicle: Atlas F.

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

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

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

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

Used on stage: Titan Cluster. on launch vehicle: Saturn B-1.

LR-89-5 used on Spacecraft

Used on: Ames Mach 10 Demonstrator.

Bibliography and Further Reading

Kudryavtseva, V M, ed., Zhidkostnikh Raketnikh Dvigatley, Visshaya Shkola, Moscow, 1993. ISBN: 5060025632. Russian-language textbook on rocket theory. More at amazon.com...

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