高超声速弹性飞行器振动模态自适应抑制技术  

Adaptive Modal Suppression for Hypersonic Aeroelastic Vehicle

作　　者：孟中杰[1] 闫杰[1] 

机构地区：[1]西北工业大学航天学院,西安710072

出　　处：《宇航学报》2011年第10期2164-2168,共5页Journal of Astronautics

基　　金：国家自然科学基金(90816027);航天支撑基金(2010-HT-XGD);西工大基础研究基金(JC20100203)

摘　　要：为保证超燃冲压发动机的良好进气,需要对高超声速飞行器进行精细姿态控制。针对高超声速飞行器特有的气动参数和结构模态参数不确定性问题,基于自适应模态抑制思想,设计了一种精细姿态控制系统,包括观测刚体模态状态信息的鲁棒H∞滤波器,提高跟踪性能的LQR刚体控制器,实时辨识弯曲模态频率的结构模态观测器和结构滤波器四部分。仿真表明,设计的控制系统在气动参数±20%,模态频率±30%的随机摄动下仍能够很好地跟踪刚体攻角,抑制弹性攻角,保证超燃冲压发动机进气道±0.6度的攻角控制精度,满足精细姿态控制的要求。To ensure a good scramjet inlet environment,a hypersonic vehicle should be controlled as a fine attitude control.For uncertainties of aerodynamic and structural parameters of the hypersonic vehicle,a fine attitude control system including a robust H∞ filter,a rigid body controller,a modal observer and a structure filter,is designed based on the adaptive modal suppression theory.The robust H∞ filter is used to estimate modal states of the rigid body,the designed rigid body controller LQR is used to improve the tracking performance and the modal observer is used to estimate the bending mode frequency.Simulation shows that,in the ±20% random perturbation of aerodynamic parameters and ±30% random perturbation of modal parameters,the rigid angle of attack（AOA） is tracked accurately,and the flexible AOA is well suppressed.The accuracy of local AOA in scramjet inlet is ±0.6 degree,which can meet the demand of fine attitude control.

关 键 词：高超声速飞行器 模态抑制 自适应滤波 鲁棒H∞滤波 结构模态观测器 

分 类 号：V249.1[航空宇航科学与技术—飞行器设计]