This page no longer updated from 31 October 2001. Latest version can be found at LR-87-11

Manufacturer Name: AJ23-139. Government Designation: LR-87-11. Designer: Aerojet. Used on stages: Barbarian MM-1, Barbarian MM-2, Titan 3A-1, Titan 3B-1, Titan 4-1. Used on launch vehicles: Barbarian MM, Titan 34B, Titan 34D, Titan 3A, Titan 3B, Titan 3BAS2, Titan 3C, Titan 3C7, Titan 3D, Titan 3E, Titan 3M, Titan 4, Titan 4B. Propellants: N2O4/Aerozine-50 Thrust(vac): 124,280 kgf. Thrust(vac): 1,218.80 kN. Isp: 302 sec. Isp (sea level): 250 sec. Burn time: 200 sec. Mass Engine: 758 kg. Diameter: 1.1 m. Length: 3.8 m. Chambers: 1. Chamber Pressure: 58.30 bar. Area Ratio: 15.00. Oxidizer to Fuel Ratio: 1.91. Thrust to Weight Ratio: 163.96. Country: USA. Status: In Production. First Flight: 1964. Last Flight: 1999. Flown: 370.

Both the current Titan 3 & 4 first stages are powered by these engines. Replacing the 9 model, this is the only engine - together with its stage 2 derivative - to be operated on storable LOX/RP. It is also the only one to be tested on LOX/LH2.. Manufacturer: AeroJet Propulsion Division. Applications: Titan 3 & 4 stage 1. First Flown: 1968 Titan 3, 1989 Titan 4. Dry Mass: 2281 kg (paired), 758 kg (single). Length: 3.84 m to top of thrust structure, 3.13 m to top of turbopump assembly. Maximum Diameter: 1.14 m. Mounting: fixed pair. Engine Cycle: gas generator. Oxidizer: nitrogen tetroxide at 540.7 kg/sec. Fuel: Aerozine-50 at 284 kg/sec. Mixture Ratio (O/F). 1.91:1. Thrust: 2437.5 kN vacuum paired. Isp: 301 sec vacuum. Expansion Ratio: 15:1. Combustion Chamber Pressure: 58.3 atm. Cooling Method: fuel regenerative & ablative skirt.Used in Titan 4-1; Titan 3B-1; Titan 3A-1.

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Last update 12 March 2001.
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