考虑导引信息延迟的旋转弹体变结构导引律  

Variable structure guidance law of rolling missile considering the guidance information lag

作　　者：李兴伟 赵斌[1] 周军[1] LI Xing-wei;ZHAO Bin;ZHOU Jun(School of Astronautics,Northwestern Polytechnical University,Xi＇ an 710072,China)

机构地区：[1]西北工业大学航天学院,陕西西安710072

出　　处：《飞行力学》2018年第4期78-82,87,共6页Flight Dynamics

基　　金：国家自然科学基金资助(61703339)

摘　　要：针对导引信息测量延迟对旋转弹制导带来的制导精度下降问题,提出了一种新的适合于滚转导弹的有限时间收敛变结构导引律。首先,进行了三维导引数学建模,给出了双输入-双输出非线性状态空间制导方程;其次,通过补偿俯仰/偏航耦合以及导引信息延迟提出了一种新型变结构导引律;最后,基于Lyapunov稳定性理论和有限时间收敛理论证明了该导引律的有限时间收敛特性,并给出了相关导引参数的选取范围。仿真结果校验了设计方法的有效性。For the problem of guidance precision reduction of rolling missile while considering guidance information measurement delay,a novel variable structure guidance law with finite time convergence was put forward for the rolling missiles. First,the three-dimensional engagement geometry was built,based on which the two-input two-output nonlinear state equation of the guidance system was given. Then the improved variable structure guidance law was proposed by compensating the channel coupling and the guidance information lag; thirdly,the finite time convergence of the guidance system was proved based on the Lyapunov stability theory and the finite time stability theory,and the value range of the guidance parameters were derived. The numerical simulations verify the effectiveness of the proposed method.

关 键 词：旋转导弹 变结构制导 导引信息延迟 有限时间收敛 

分 类 号：TJ765.3[兵器科学与技术—武器系统与运用工程]