Abstract: One dimensional equations for liquid transients in propellant feed lines were considered. By means of the finite difference scheme of characteristic method, the transient flows were simulated for the attitude control propulsion subsystem during shutdown operation. The effect of different condition on dynamic behavior was investigated. The calculated results are identical with test data-the maximum transient pressure in front of the injector is equal to three times of the tank pressure. The results are valuable for designers. It shows that the method can be used to analyze dynamic performance of complex propulsion system consisting of numerous pipes, valves and thrusters.

Key words: Attitude control rocket engine;Unsteady flow;Finite difference theory;Method of characteristic curve;Water impingement

摘要： 从一维液体瞬变管路方程出发 ,采用有限差分格式的特征线方法 ,针对某姿控推进系统发动机真实氧化剂管路的关机瞬变特性进行了数值研究 ,对系统不同部位的动态特性进行了计算 ,喷注前的最大瞬变压力达到储箱压力的 3倍 ,得到的结果与试车数据是一致的 ,对液体发动机管路工程设计具有参考价值 ,表明该方法可以方便地对包括许多管路、阀门和推力室的复杂系统进行动态特性分析。

关键词: 姿控火箭发动机;非定常流;有限差分理论;特征线法;水冲击