侵彻制导武器终端多约束最优制导律  

Optimal guidance law with multiple terminal constrains for penetrating guided weapon

作　　者：刘大卫[1] 杜运理[1] 温求遒[2] 上官垠黎[1] 

机构地区：[1]中国兵器科学研究院,北京100089 [2]北京理工大学宇航学院,北京100081

出　　处：《固体火箭技术》2015年第2期166-171,共6页Journal of Solid Rocket Technology

基　　金：博士后科学基金资助项目(2012M50048)

摘　　要：针对侵彻型制导武器终端多约束制导问题,建立包含一阶弹体动力学的多约束制导模型,采用最优控制方法推导终端多约束制导问题的通解。根据终端约束与罚函数的关系,求解了实际工程中关心的3种最优制导律,并结合当前主流制导控制体制,在小角假设下,将其表述为便于工程实现的形式,即包含弹体动力学的最优比例导引制导律、弹道成型最优制导律和终端多约束最优制导律。理论分析和典型末制导条件仿真表明,后2种制导律可为侵彻制导武器终端位置与角度双约束以及位置、角度与加速度多约束制导问题提供理论基础和工程应用参考。In order to study the terminal guidance problem of penetrating guided weapon,the guidance model with multiple ter-minal constraints based on first-order missile dynamics was established.The common optimal solution was deduced by state feedback law,and three typical optimal guidance laws were obtained by the relationship between different terminal constraints and penalty function.Then,advanced proportional navigation guidance law（APN）,trajectory shaping guidance law with impact position and angle constraints （ TSGPA） ,and optimal guidance law with multiple terminal constrains （ OGLMTC） were obtained based on small angle assumption according to the information of typical guidance and control system.Theoretical analysis and typical simulations show that TSGPA and OGLMTC can control the missile to meet the dual and multiple terminal constraints concerning terminal location angel and accelaration respectively,and the two guidance laws can provide reference to engineering problem.

关 键 词：侵彻制导武器 终端多约束 最优制导律 比例导引 弹道成型 

分 类 号：V448[航空宇航科学与技术—飞行器设计]