Robust gain-scheduled missile autopilot design based on multifrequency extended state observers  

作　　者：Zonghua SUN Liaoni WU Yancheng YOU 

机构地区：[1]School of Aerospace Engineering,Xiamen University,Xiamen 361102,China

出　　处：《Chinese Journal of Aeronautics》2023年第12期390-407,共18页中国航空学报（英文版）

基　　金：the support of the National Natural Science Foundation of China(No.U21B6003)。

摘　　要：This paper describes the design and implementation of a three-axis acceleration control autopilot for an asymmetric tail-controlled,skid-to-turn tactical missile.In an earlier flight test,degraded autopilot performance was attributed to multiple disturbances and uncertainties and the presence of hidden coupling terms,giving rise to a miss distance of greater than 20 m.To address these issues,the missile dynamics are decomposed into the angular rate dynamics as fast and the acceleration dynamics as slow subsystem using the singular perturbation theory to analyze a multi-time-scale property.Multifrequency extended state observers are then incorporated into the gain scheduling technique to attenuate disturbances,thus enhancing the control performance significantly.In the proposed engineering/practical design framework for missile autopilot,simple,conventional,and explicit tuning rules are provided.And the proposed control scheme can achieve input-to-state stability across the entire flight envelope under unknown but bounded disturbances.The advantages of the method over existing benchmark approaches are shown through nonlinear numerical simulations.This is supported by evidence from a new flight test result with a miss distance of only 2 m.

关 键 词：Acceleration control Control engineering Disturbance rejection Multifrequency extended state observer Flight control systems Gain scheduling Singular perturbation 

分 类 号：TJ765[兵器科学与技术—武器系统与运用工程]