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| 11D-513 - Specifications |
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Engine Performance
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11D-513 |
Propellant Combination
Oxidizer
Fuel |
Liquid Oxygen (LOX)
Rocket Propellant (RP) |
| Engine Cycle: |
Staged Combustion |
| Average Thrust: |
17,600 lb vac
78,140 kN |
| Chamber Pressure: (Pc) |
--- |
| Mixture Ratio: |
2.4 : 1 |
| Isp: |
342 sec vac |
| Nozzle Area Ratio: |
103.5 : 1 |
| Gimbal Capability: |
±10 degrees |
| Engine Mass: |
770 lb (dry)
350 kg (dry) |
| Engine Thrust to Weight |
23 |
| Mixture Ratio Control: |
Yes (EMA) |
| Throttle Range: (% Pc) |
70 - 100 % |
| Restart Capability: |
No |
Engine Size:
Length / Diameter |
3.28 /
6.5 ft
1.0 / 2.0 m |
| Flight Status |
Flight Qualified |
| Launch Vehicles: |
Zenit Second Stage
Pioneer Rocketplane (proposed) |
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