Country of origin | China |
---|---|
Designer | Academy of Aerospace Liquid Propulsion Technology |
Status | In development |
Liquid-fuel engine | |
Propellant | LOX / CH4 |
Cycle | Gas-generator cycle |
Configuration | |
Chamber | 1 |
Performance | |
Thrust, vacuum | 800 kilonewtons (180,000 lbf) |
Thrust, sea-level | 735 kilonewtons (165,000 lbf) |
Specific impulse, vacuum | 329s |
Specific impulse, sea-level | 293s |
References | |
References | [1] |
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