摘要
把最优控制理论的方法应用于弹道导弹的主动段攻角优化问题上 ,解决了导弹大气飞行运动最优化模型的线性化问题 ,得出弹道导弹从开始拐弯到主动段飞行结束时燃料最省的理想最优攻角变化规律。
This approach applies optimal control theory to the problem of powered phase attack angle optimization of ballistic missile and solves the matter of linearization of flight model in the air. An ideal optimal attack angle program from the turning off to the end of powered flight is concluded. The way how this approach is applied to practical project is also analyzed.
出处
《导弹与航天运载技术》
北大核心
2002年第2期16-20,共5页
Missiles and Space Vehicles
关键词
战术弹道导弹
攻角优化
最优控制
极大值原理
主动段
算法
Ballistic missile,Attack angle optimization,Optimal control,Principle of maximum value.
