LR-87-11
Manufacturer Name: AJ23-139. Government Designation: LR87-11. Designer: Aerojet. Propellants: N2O4/Aerozine-50. Thrust(vac): 1,218.800 kN (273,997 lbf). Thrust(sl): 968.400 kN (217,705 lbf). Isp: 302 sec. Isp (sea level): 250 sec. Burn time: 200 sec. Mass Engine: 758 kg (1,671 lb). Diameter: 1.14 m (3.74 ft). Length: 3.84 m (12.59 ft). Chambers: 1. Chamber Pressure: 59.10 bar. Area Ratio: 15.00. Oxidizer to Fuel Ratio: 1.91. Thrust to Weight Ratio: 163.96. Country: USA. Status: Out of production. First Flight: 1964. Last Flight: 2005. Flown: 534.

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.


LR-87-11 used on Rocket Stages

 
 
 
 
 
 
 
 
 

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