A high-performance liquid fuel bipropellant high-thrust rocket engine using pure hydrazine as the fuel comprises: a pure hydrazine supply, including a supply tank, fuel line and fuel supply valve; an oxidant supply, including a supply tank, oxidant line and oxidant supply valve; a combustion chamber 30 having coaxial inlets 32', 38' for the hydrazine and the oxidant, connected to the fuel and oxidant lines; and means for delaying closure of the fuel supply valve until after closure of the oxidant supply valve, to ensure that combustion is completed in the combustion chamber, thereby minimizing unwanted combustion after shutdown of the engine. IMAGE
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