某液体火箭发动机故障仿真分析

为分析某液体火箭三子级发动机推迟关机的原因，建立了发动机稳态故障的模型。用添加稳态故障的方法分析了燃气发生器和燃烧室氧化剂管路流阻系数，以及氧化剂温度对发动机参数的影响。仿真结果表明，氧化剂泵后温度升高是导致此三子级发动机故障最可能的原因。

The Simulation Analysis of Some Liquid Rocket Engine Fault

To analyze the reason of the three-stage engine turn-off delay of some liquid rocket engine, the stable state fault module of the engine was established in this paper. The simulation by adding stable state fault was used to study the effect of flow resistance coefficient of oxidant pipe in gas generator and chamber and oxidant temperature on the engine parameters. The result showed that the most possible reason of the fault for the three-stage engine was the temperature rising behind oxidant pump.