自旋导弹控制耦合及补偿解耦性能研究  

Analysis of Control Coupling and Compensation Decoupling Performance for Spinning Missile

作　　者：贾宝[1] 薛林[2] 闫晓勇[1] 

机构地区：[1]北京电子工程总体研究所,北京100854 [2]中国航天科工集团第二研究院,北京100854

出　　处：《现代防御技术》2015年第2期47-53,共7页Modern Defence Technology

摘　　要：弹体滚转条件下,舵机的动力学滞后造成了自旋导弹的控制耦合。建立了准弹体坐标系下等效舵系统的动力学传递函数矩阵,基于串联补偿解耦方法,研究了补偿角与弹体转速、控制信号频率之间的关系,以及补偿角对舵系统关联性的影响。研究表明,针对稳态解耦补偿角取值为最优补偿角时,舵系统的通道关联性达到最小,但理论上该方法在控制信号为低频条件下才能实现近似的静态解耦;当控制信号频率较高时,会出现过补偿现象,控制系统解耦性能下降;补偿角的上界值会随着弹体转速发生变化,因此应该对补偿角进行在线动态修正,避免发生过补偿现象。The actuator kinetics result in the control coupling in spinning missile. The transfer function matrix of the equivalent actuator is derived in quasi-body coordinate system. Aiming at the cascade compensation decoupling method,the relation among rotating frequency,input signal frequency and the compensation angle arestudied. The result indicates that the coupling degree will reach the minimum when the compensation angle is optimal. This method can realize the static decoupling only when the control signal frequency is low. There is overcompensation phenomenon when signal frequency is high,and it will reduce the decoupling performance. The upper bound of the compensation angle changes with the rotational speed,so the compensation angle must be revised online to avoid overcompensation phenomenon.

关 键 词：自旋导弹 控制耦合 等效舵机 对角优势度 补偿解耦 最优补偿角 

分 类 号：TJ765.1[兵器科学与技术—武器系统与运用工程]