Effect of valve opening time difference on working process of 150 N hypergolic propellant liquid rocket engine
In order to study the effect of the valve opening time difference on the working process of the space liquid rocket engine using hypergolic propellants,the high-altitude simulated thermal test of a 150 N engine was carried out.The engine working stability,ignition thrust peak and response time were investigated when the oxidant valve and fuel valve were opened 40,100,500,1 000 ms in advance,respectively.The test results showed that the engine can be successfully ignited,and the thrust after stabilization was basically unchanged.When the oxidant valve and the fuel valve were opened first,the ignition thrust peak of the engine was about 1.01-1.05 times and 1.04-1.07 times of the stable thrust,respectively,which was equivalent to the opening of the two-way valve synchronous signal.When the fuel valve was opened first,the startup response time was extended by about 16 ms.When the valve was opened alone,the oxidant was fully vaporized,the ice particles were ejected in the middle area of the flow field,and the fuel was partially vaporized.When the valve opening time difference reached 500 ms and 1 000 ms,while the oxidant valve and the fuel valve were opened separately,the output thrust of the engine was about 11 N and 6 N,respectively,accounting for 7％and 4％of the stable thrust respectively,and the output thrust of the latter fluctuated and kept falling.
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