带碰撞角约束的最优多项式制导律  

Optimal Polynomial Guidance Law with Impact Angle Constraint

作　　者：赵曜[1] 杨书波[1] 莫锦鹤 韩英宏[1] 刘向东[2] ZHAO Yao;YANG Shu-bo;MO Jin-he;HAN Ying-hong;LIU Xiang-dong(China Academy of Launch Vehicle Technology,Beijing 100076,China;School of Automation,Beijing Institute of Technology,Beijing 100081,China)

机构地区：[1]中国运载火箭技术研究院,北京100076 [2]北京理工大学自动化学院,北京100081

出　　处：《北京理工大学学报》2018年第6期637-640,646,共5页Transactions of Beijing Institute of Technology

摘　　要：针对导弹对地面静止目标的打击问题,基于非线性导弹运动学模型提出了一种二维多项式制导律.该制导律不仅能保证导弹以期望的碰撞角命中目标,而且能使特定的价值函数最小化.此外,制导律作用下系统状态的解析解可以求解得到,从而实现了对制导系统状态的定量分析.数值仿真验证了所提制导律的有效性.To deal with the guidance problem of intercepting ground fixed target,a two-dimensional polynomial guidance law was proposed based on a nonlinear engagement dynamics model for the missile.The main feature of this guidance law is that it not only accurately satisfies the terminal impact angle constraint,but also minimizes the specific cost function.Moreover,the closed loop system states can be analytically derived,which realize quantitative analysis for the system states.The effectiveness of the proposed guidance law was verified by numerical simulations.

关 键 词：制导 碰撞角约束 最优控制 多项式 

分 类 号：V448.1[航空宇航科学与技术—飞行器设计]