空空导弹控制系统鲁棒动态逆设计  

Robust dynamic inversion controller design for air-to-air missiles

作　　者：张友安[1] 杨华东[1] 顾文锦[1] 苏身榜[2] 

机构地区：[1]海军航空工程学院301教研室,山东烟台264001 [2]中国空战导弹研究院

出　　处：《系统工程与电子技术》2004年第8期1084-1089,共6页Systems Engineering and Electronics

基　　金：航空科学基金资助课题(99D12001)

摘　　要：将导弹动力学分离为快变状态动力学子系统和慢变状态动力学子系统,分别进行非线性动态逆控制设计。应用基于李雅普诺夫稳定性的鲁棒控制方法,设计出期望的慢变动力学和快变动力学,以保证动态逆控制系统对气动系数摄动的鲁棒稳定性。给出了通过构造动态反插值表,由力矩系数指令反解舵偏角指令的反插值方法。动态逆方法所需要的速度指令、滚动角指令及其一、二阶导数通过滤波器得到。对过载回路的稳定性问题和跟踪误差进行了定性分析,给出了过载回路的无静差设计方案,作为对动态逆的补充设计。给出了导弹控制系统六自由度数学仿真结果。A new robust dynamic inversion controller design is introduced for air-to-air missiles by combining (dynamic) inversion and robust control based on Lyapunov stability. Feedback linearization by dynamic inversion uses natural two time-scale separations between fast and slow state variables robust control. based on Lyapunov stability (enhances) robustness to parameter variations of aerodynamic coefficients. Deflections of elevator, rudder and aileron are (inversely) interpolated by constructing dynamic inverse interpolation tables as a part of dynamic inversion design. Filters are used to generate velocity commands and roll angle commands, and their first and second derivatives. Stability problems and tracking errors of acceleration loops are qualitatively analyzed, and a scheme for eliminating steady state tracking errors of acceleration loops is presented as complementary design to dynamic inversion. Six-degree of freedom simulations are performed to asses the performance of the designed controller.

关 键 词：动态逆 反馈线性化 李雅普诺夫稳定性 鲁棒控制 空空导弹 非线性控制 

分 类 号：TJ765[兵器科学与技术—武器系统与运用工程]