摘要
从理论上探讨了单室双推力固体火箭发动机中影响其两级推力的主要因素。建立了导弹/发动机一体化设计的优化模型,对一种推进剂实现双推力,双燃速推进剂实现双推力两种情况分别进行了计算和分析。求出了使导弹射程达到最大,又能够在设计中实现的最佳推力方案。
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.
出处
《推进技术》
EI
CAS
CSCD
北大核心
1992年第3期16-19,34,共5页
Journal of Propulsion Technology
关键词
推力控制
双推力
火箭发动机
Thrust control, Dual-thrust rocket engine, Optimal design
