多级固体火箭发动机总体优化设计

INTEGRAL PERFORMANCE OPTIMUM DESIGN FOR MULTISTAGE SOLID PROPELLANT ROCKET MOTORS

关键词:  固体火箭发动机  优化  最佳设计  参数最优化

Key words:  Solid rocket engine  Optimization  Optimum design  Parameter optimization

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%.

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.