主被动结合的弹性高超声速飞行器鲁棒自适应控制  

Robust Adaptive Control of Flexible Hypersonic Flight Vehicle with Combined Active and Passive Technique

作　　者：王霞 杨林 张大伟[2] 魏振岩 许斌[2] WANG Xia;YANG Lin;ZHANG Dawei;WEI Zhenyan;XU Bin(School of Control Science and Engineering,Shandong University,Jinan 250061,China;School of Automation,Northwestern Polytechnical University,Xi'an 710072,China;Chengdu Aircraft Design and Research Institute,Chengdu 610041,China;Beijing Institute of Mechanical and Electrical Engineering,Beijing 100074,China)

机构地区：[1]山东大学控制科学与工程学院,济南250061 [2]西北工业大学自动化学院,西安710072 [3]成都飞机设计研究所,成都610041 [4]北京机电工程研究所,北京100074

出　　处：《宇航学报》2024年第7期1052-1064,共13页Journal of Astronautics

基　　金：国家资助博士后研究人员计划(GZB20240403);山东博士后科学基金资助(SDCX-ZG-202400302);国家自然科学基金(61933010)。

摘　　要：针对高超声速飞行器轻质材料和细长体构型引起的显著气动伺服弹性问题,提出了一种主被动结合的鲁棒自适应控制方法。首先,通过引入辨识性能评价和监测机制设计复合自适应参数辨识方法,并给出滤波估计策略,实现弹性振动频率与弹性模态的高效在线估计。其次,采用奇异摄动理论将刚弹一体化模型分解为刚弹子系统,针对弹性子系统,基于频率辨识值构建级联型自适应陷波器实现被动陷波抑制,并结合模态估计值设计主动反馈控制保证弹性模态的稳定收敛;针对刚体子系统,设计基于有限时间滑模扰动观测器的鲁棒跟踪控制,综合两个子系统的控制量得到最终升降舵偏转。最后,通过仿真验证了该方法能够有效保证气动伺服弹性影响下高超声速飞行器的弹性抑制和刚体控制性能。Considering the significant aeroservoelasticity of hypersonic flight vehicle(HFV)caused by lightweight material and elongated body,the robust adaptive control is proposed using combined active and passive technique.Firstly,to achieve the efficient online estimation of flexible vibration frequencies and modes,a composite adaptive parameter identification method is designed by introducing performance evaluation and monitoring mechanism,and a filtering estimation strategy is also proposed.Then,the integrated rigid-elastic model is decoupled into the rigid-body and flexible subsystems based on singular perturbation theory.For the flexible subsystem,a cascade-type adaptive notch filter using identified frequencies is constructed to achieve passive notching suppression,while the estimated modes based active feedback control is designed to ensure the stable convergence of flexible modes.For the rigid-body subsystem,the robust tracking control is designed based on finite-time sliding mode disturbance observers.The final elevator deflection is obtained by combining the control inputs of the two subsystems.Finally,simulation results show that the proposed method can effectively guarantee the performance of flexible suppression and rigid-body control for HFV with aeroservoelasticity effect.

关 键 词：气动伺服弹性 在线估计 自适应陷波器 主被动鲁棒控制 

分 类 号：V448.2[航空宇航科学与技术—飞行器设计]