Country of origin | United States |
---|---|
First flight | 12 July 1963 |
Last flight | 17 April 1984 |
Manufacturer | Bell Aerosystems Company |
Application | Upper stage |
Associated LV | Thor, Thorad, Atlas and Titan |
Predecessor | Bell 8081 |
Successor | Bell 8247 |
Status | Retired |
Liquid-fuel engine | |
Propellant | RFNA / UDMH |
Mixture ratio | 2.55 |
Cycle | Gas-generator |
Configuration | |
Chamber | 1 |
Nozzle ratio | 45 |
Performance | |
Thrust, vacuum | 71.2 kN (16,000 lbf) |
Chamber pressure | 3.49 MPa (506 psi) |
Specific impulse, vacuum | 293 s (2.87 km/s) |
Burn time | 265 seconds |
Restarts | 2 |
Gimbal range | ±2.5° |
Dimensions | |
Length | 2.11 m (83.2 in) |
Diameter | 0.90 m (35.5 in) |
Dry mass | 134 kg (296 lb) |
Used in | |
RM-81 Agena | |
References | |
References | [2][3][4] |
The Bell Aerosystems Company XLR81 (Model 8096) was an American liquid-propellant rocket engine, which was used on the Agena upper stage. It burned UDMH and RFNA fed by a turbopump in a fuel rich gas generator cycle. The turbopump had a single turbine with a gearbox to transmit power to the oxidizer and fuel pumps. The thrust chamber was all-aluminum, and regeneratively cooled by oxidizer flowing through gun-drilled passages in the combustion chamber and throat walls. The nozzle was a titanium radiatively cooled extension. The engine was mounted on a hydraulic actuated gimbal which enabled thrust vectoring to control pitch and yaw. Engine thrust and mixture ratio were controlled by cavitating flow venturis on the gas generator flow circuit. Engine start was achieved by solid propellant start cartridge.[5]
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