摘要
应用现代控制理论以节能的观点研究了中远程战术导弹的中制导策略。文中选择飞行器迎角作为控制变量,以中制导段末速最大为性能指标,按极大原理导出了有约束控制的非线性两点边值问题。以非线性规划法——共轭梯度法进行了轨道优化数值仿真。以爱国者导弹为例给出了数值结果。
Form the standpoint of saving energy, the midcourse guidance strategy for medium or long range missile has been studied with the application of mordern control theory. With the vehicle's angle of attack regard as control variable, the maximum speed of missile at thc end of its flying midcourse as performance index, the nonlinear twopoint boundary value problem with constrained control has been deduced according to the principle of the maximum. The numerical simulation of optimal trajectory is made by conjugation gradient method. Finally, numerical results for the PATRIOT SAM-D missile is given.
出处
《战术导弹技术》
1992年第2期33-37,共5页
Tactical Missile Technology
关键词
战术导弹
中段
制导
控制
Tactical missile Midcourse guidance Tactics Trajectory Optimal control
