摘要
主动段弹道设计及优化对提高固体运载火箭运载能力具有重要的意义。提出两种有利于工程实现的主动段俯仰程序角设计方法,分别为末级一次开机方式和末级两次开机方式。基于遗传算法与序列二次规划法组成的复合优化算法,实现了两种程序角对应的弹道优化仿真计算,并进行对比分析。仿真结果表明采用末级两次开机的方式可有效提高火箭运载能力。
Trajectory design and optimization for active phase are of important significance to enhance the collective performance of solid launch vehicle. In this paper two design methods of pitch angle which are ignition once and twice in the last stage are proposed based on the composite optimization algorithm of genetic algorithm and sequential quadratic programming, and the simulation calculation for trajectory optimization is achieved. The simulation results show the latter design method can be helpful to increase the launch capability.
出处
《导弹与航天运载技术》
北大核心
2012年第3期1-5,共5页
Missiles and Space Vehicles
关键词
固体运载火箭
主动段
轨迹优化
遗传算法
序列二次规划法
Solid launch vehicle
Active phase
Trajectory optimization
Genetic algorithm
Sequential quadratic programming
