固体火箭发动机结构质量的优化设计

Optimization Design for the Structure Mass of Solid Rocket Motor

讨论了使星形装药固体火箭发动机的结构质量（包括燃烧室和喷管）最轻和装填密度最大的优化方法，即在总冲和工作时间给定条件下，在外径一定时使发动机的质量尽可能降低，以提高整个火箭武器的质量比。通过对发动机特性、目标函数及约束条件与设计交量间关系的分析，建立了寻求结构质量最轻的数学模型，利用罚函数调鲍威尔法计算，得到了满意的优化参数。

A method of optimum design for solid rocket motors to lower the structure mass of SRM is presented when impulse and worktime are given. So the mass of construction including grain,chamber and nozzle is selected as the purpose function while the constraints are analysed together with the changes in motor characteristics with the design variables. The mathematic model and an optjmum design program are set up based on SUMT (calling Powell mehtod ). An example of optimum design is given,showing satisfactory rcsults.