基于线性重力差模型的拦截弹中制导技术  

Interceptor Midcourse Guidance Technology Based on Linear Gravity Difference Model

作　　者：陆诚 崔朗福 张庆振[1] 曾浩然 聂华 赵友铖 LU Cheng;CUI Langfu;ZHANG Qingzhen;ZENG Haoran;NIE Hua;ZHAO Youcheng(School of Automation Science and Electrical Engineering,Beihang University,Beijing 100083;China Ship Research&Design Center,Wuhan 430064;Beijing Institute of Mechanical and Electrical Engineering,Beijing 100854)

机构地区：[1]北京航空航天大学自动化科学与电气工程学院,北京100083 [2]中国舰船研究设计中心,武汉430064 [3]北京机电工程总体研究所,北京100854

出　　处：《飞控与探测》2020年第3期49-56,共8页Flight Control & Detection

基　　金：上海航天创新科技基金(SAST52016001)。

摘　　要：针对机载动能拦截弹的中制导段气动力作用可忽略且存在无法实时精确计算重力偏差等特点,提出了一种基于线性重力差模型的预测制导方法。通过线性模型逼近中制导过程中拦截弹与目标之间的重力偏差,以此为依据调整拦截弹的推力矢量并将重力偏差值消除。在此基础上采用延迟点火的策略使得拦截弹的拦截器助推级更好地修正预测模型与实际情况的偏差,经过仿真验证可以将整个中制导段的脱靶量限制在一个较小数值,从而为末制导段提供良好的初始条件。A predictive guidance method based on linear gravity difference model is proposed for the midcourse guidance of an airborne kinetic energy interceptor,which has the characteristics of negligible aerodynamic force and the inability to accurately calculate gravity deviation in real time.The gravity deviation between the interceptor and the target is approximated by a linear model.The thrust vector of the interceptor is adjusted and the gravity deviation is eliminated.On this basis,the delay ignition strategy is adopted to make the interceptor boost stage of interceptor better correct the deviation between the prediction model and the actual situation.The simulation results show that the miss distance of the whole midcourse guidance can be limited to a smaller value,thus providing a good initial condition for the terminal guidance.

关 键 词：动能拦截弹 零控脱靶量 中制导律 线性重力差模型 预测制导 

分 类 号：V448[航空宇航科学与技术—飞行器设计]