细长体飞行器主动弹性抑制控制律设计及分析  

Design and Analysis of Active Elastic Suppression Control Law for Slender Aircraft

作　　者：郝明瑞 郭泽宇 李风义 Hao Mingrui;Guo Zeyu;Li Fengyi(Center for Control Theory and Guidance Technology,Harbin Institute of Technology,Harbin 150001,China;Science and Technology on Complex System Control and Intelligent Agent Cooperation Laboratory,Beijing 100074,China)

机构地区：[1]哈尔滨工业大学控制理论与制导技术研究中心,哈尔滨150001 [2]复杂系统控制与智能协同技术重点实验室,北京100074

出　　处：《战术导弹技术》2021年第1期74-83,共10页Tactical Missile Technology

基　　金：国家自然科学基金(61690210)。

摘　　要：针对未来采用大长细比、轻质新型复合材料的飞行器结构模态频率进一步降低、气动伺服弹性问题更加严峻的问题,采用智能变结构控制方法,将广义坐标作为反馈量,并针对静不稳定弹性飞行器设计了纵向姿态控制器;然后,基于李亚普诺夫稳定性理论分析了闭环系统的稳定性;最后,通过定点仿真检验了所设计控制器的时域响应特性和对扰动的鲁棒性。仿真结果表明,当弹性模态频率与刚体频率接近时,与传统的基于陷波滤波器的设计方法相比,增加弹性反馈变量的智能变结构控制方法是一种解决气动伺服弹性问题的有效途径。Considering the future slender aircraft with new light-weighted composite material, the structural modal frequency is further reduced and the problem of aeroservoelasticity is more serious. By utilizing the generalized coordinates as the feedback signal, the longitudinal attitude controller is designed for the static unstable elastic vehicle based on intelligent variable structure control method. According to Lyapunov stability theory, the stability analysis of the closed-loop system is presented. Finally, the time domain response characteristics and the robustness of the proposed controller are verified by the fixed-point simulation. According to the simulation results, the intelligent variable structure control method with the elastic feedback variable is more effective in dealing with aeroservoelasticity than the traditional notch filter based design method.

关 键 词：模糊滑模控制 主动弹性抑制 陷波滤波器 弹性飞行器 变结构控制 

分 类 号：V448.222[航空宇航科学与技术—飞行器设计]