摘要
在综合考虑固体火箭发动机内弹道性能和火箭外弹道性能的情况下 ,融内外弹道仿真分析为一体 ,系统分析了发动机装药、燃烧室和喷管设计参数对发动机性能及全弹性能的影响。通过建立火箭质量模型、气动估算模型、外弹道模型和内弹道模型 ,在满足总体设计指标的前提下 ,以起飞质量最小为目标函数 ,将遗传算法应用于固体火箭总体一体化优化中 ,完成 4个变量的寻优计算 。
Considering of SRM internal ballistic property and rocket trajectory , in this paper the influence of the parameter of SRM grain configuration, chamber and nozzle design on the motor property and overall rocket performance of the parameter is analyzed. By developing a set of mathematical models of mass, motor ballistic and rocket trajectory, considering of the overall design object and the object function, importing genetic algorithms into solid rocket overall performance optimization, with 4 variables, optimizing calculations are finished and the results are satisfactory.
出处
《弹箭与制导学报》
CSCD
北大核心
2001年第3期53-55,共3页
Journal of Projectiles,Rockets,Missiles and Guidance
关键词
遗传算法
固体火箭
一体化
优化设计
genetic algorithms
solid rocker
integration design
optimization
