进化策略在火箭发动机静态特性研究中的应用  

Application of evolutionary strategy of research of static characteristics of liquid propellant rocket engine

作　　者：胡伟[1] 张振鹏[1] 张黎辉[1] 

机构地区：[1]北京航空航天大学宇航学院,北京100083

出　　处：《北京航空航天大学学报》2005年第4期389-392,共4页Journal of Beijing University of Aeronautics and Astronautics

摘　　要：建立了全流量补燃循环发动机的静态特性的数学模型.描述静态特性的数学模型是由一组非线性方程组成的.采用基于进化策略的进化算法求解全流量补燃循环发动机的静态特性方程,将该模型的非线性方程组求解问题转化为求带有约束的极小值的优化问题,建立了进化策略计算模型.讨论了进化策略算法在进化计算过程中使用的变异算子、重组算子和选择算子的设计,以及对约束条件的处理方法.数值计算的结果表明,利用基于进化策略的算法可以在较大范围内进行全流量循环液体火箭发动机的静态特性研究.The mathematical models of the static characteristics of the full-flow staged combustion cycle rocket engine were presented. These mathematical models are composed of some non-linear equations. Using the conventional algorithms is very difficult to get to solution. Evolutionary strategy algorithm of solving the large dimension non-linear mathematical model was developed. It converts the problem of solving non-linear equations into the optimization problem of the solving the minimum value with constraints. The mathematical models of evolutionary strategy algorithm were built. The designs of mutation operator and recombination operator were presented. According to the experience and calculation results, the select operator was presented. The method of dealing with constraints was employed. The method is named as direct comparison proportional method (DCPM). Evolutionary strategy algorithm is applied solving the static characteristics of the full-flow staged combustion cycle rocket engine. Calculation results show that using evolutionary etrategy algorithm can research the static characteristics of the full-flow staged combustion cycle liquid propellant rocket engine.

关 键 词：进化算法 液体推进剂 火箭发动机 优化 

分 类 号：V430[航空宇航科学与技术—航空宇航推进理论与工程]