液体火箭发动机流路系统性能可靠性预估  

Performance Reliability Prediction of Flow System Performance in Liquid Rocket Engine

作　　者：齐岳 金平[1] 孙冰[1] QI Yue;JIN Ping;SUN Bing(School of Astronautics,Beihang University,Beijing 100191,China)

机构地区：[1]北京航空航天大学宇航学院,北京100191

出　　处：《载人航天》2019年第2期208-212,共5页Manned Spaceflight

基　　金：载人航天预先研究项目(050302)

摘　　要：针对液体火箭发动机流路系统性能可靠性试验难度大、成本高的问题,提出一种基于随机仿真方法的流路系统性能可靠性预估方法。根据发动机流路系统平衡关系建立静态方程组,得到了发动机流路系统初始参数与性能参数之间的对应关系,建了立动力平衡仿真模型进行验证;通过已验证的动力平衡仿真模型,研究了初始参数给定随机偏差下性能参数的对应偏差分布。结果表明方法可以得到单一或多个初始参数同时产生随机偏差的不同工况下,性能参数对应的偏差分布,完成性能可靠性预估。Due to the difficulty and high cost of the reliability experiment on the flow system of the liquid rocket engine,a reliability estimation method for flow system based on stochastic simulation method was proposed.The static equations were established according to the balance relationship in flow system of the rocket engine,the corresponding relationship between the initial parameters and the performance parameters in engine flow system were obtained,and the dynamic balance simulation model was established and verified.The verified model was used to study the influence of the given random deviation of the initial parameters on the deviation distribution of the performance parameters.The results showed that the deviation distribution of the performance parameters corresponding to the random deviation of the single or multiple initial parameters were obtained and the performance reliability prediction was realized.

关 键 词：液体火箭发动机 随机仿真方法 性能可靠性预估 发动机流路平衡关系 

分 类 号：V434[航空宇航科学与技术—航空宇航推进理论与工程]