摘要
本文在文献[1]的基础上提出了一种多级固体火箭发动机总体优化数学模型,并对三级定容发动机进行了计算.对中远程弹道式导弹利用优化模型比经验设计主动段终点速度提高了4%.
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.
出处
《推进技术》
EI
CAS
CSCD
北大核心
1989年第2期8-14,共7页
Journal of Propulsion Technology
关键词
固体推进剂
火箭发动机
最佳设计
Solid rocket engine,Optimization,Optimum design, Parameter optimization
