关键词: 推力控制;双推力火箭发动机;优化

Abstract: Paramaters Optimization in design of solid rocket motor (SRM) is important to the performance of a missile. And thrust ratio is a important paramater in design of single-chamber with dual level thrust in SRM. It can affect greatly missile flight range but has to be under constraints of practical grain design in SRM.A integral optimization model of missile and SRM with dual thrust single-chamber is analysed in this paper. The model involves four variables and objective function is missile flight range. A optimal design which not only maximizes the missile flight range but also can be realized in the design of SRM is obtained through this model caculation. If higher thrust ratio is needed, it will be better to use propallant with two burning rates instead of using the propallant with only one burning rate.

Key words: Thrust control;Dual-thrust rocket engine;Optimal design