弹性体高超声速飞行器自适应控制器设计  

Adaptive Controller Design of Flexible Hypersonic Vehicle

作　　者：肖进[1] 李惠峰[1] 

机构地区：[1]北京航空航天大学宇航学院,北京100191

出　　处：《计算机仿真》2013年第7期33-36,54,共5页Computer Simulation

基　　金：自然基金(61174221)

摘　　要：研究控制器优化设计问题,为能使飞行控制系统精确跟踪控制指令,并抑制住机体的结构弹性振动,研究了一种带自适应结构滤波器的LQR积分控制器。其中,LQR积分状态反馈控制器用来跟踪飞行速度与航迹倾角指令,结构滤波器用来抑制弹性模态。由于在高超声速飞行过程中结构的振动频率与阻尼比是随时间变化的,造成弹性振动偏差大。勾此设计了一种鲁棒估计器来在线辨识弹性模态,并将辨识的结构自然频率作为结构滤波器的中心频率。通过在吸气式高超声速飞行器纵向非线性模型上进行仿真验证,结果显示控制方法能很好地满足跟踪指令与结构弹性抑制的要求。In order to accurately track the control instructions of flight control system and suppress the structure vibration,a LQR integral controller with adaptive notch filter was presented in this paper.The LQR integral state feedback controller wa designed to track the velocity and flight path angle instructions,and the notch filter was used to suppress the flexible mode.Due to the fact that the frequency and damping ratio of the flexible modes are uncertain when the flight condition changes,a robust online estimator was designed to identify the frequency of the slowest flexible mode;and taken as the center frequency of notch filter.Then,this adaptive notch filter can suppress the changing flexible mode online.When simulated with the nonlinear longitudinal model of a generic air-breathing hypersonic flight vehicle,the results show that the control scheme has good control effect.

关 键 词：高超声速飞行器 结构滤波器 自适应控制 数学模型 

分 类 号：V19[航空宇航科学与技术—人机与环境工程]