关键词: 固体火箭发动机;优化;最佳设计;参数最优化

Abstract: A mathematical model for integral performance optimization of multistage solid propellant rocket motors is established, based on referance[1],and a calculation with a three-stage volume-fixed solid propellant rocket motor,as a example, is presented in this paper.It is shown that the velocity at burnout ef intermediate/long range ballistic missile calculated with this model is 4% greater than that with usual empirical method.

Key words: Solid rocket engine;Optimization;Optimum design;Parameter optimization