基于卡尔曼滤波的高超声速飞行器控制器设计  

Controller Design for Hypersonic Vehicle Based on Kalman Filter

作　　者：陶超[1] 艾剑良[1] 

机构地区：[1]复旦大学力学与工程科学系,上海200433

出　　处：《系统仿真学报》2015年第2期376-383,共8页Journal of System Simulation

摘　　要：针对纵向模态和横航向模态都不稳定的一种通用的高超声速飞行器,建立了三维紊流及紊流梯度下的高超声速飞行器全状态线性化的动力学模型。在考虑三维紊流和紊流梯度干扰和系统测量噪声条件下,提出了一种基于离散卡尔曼滤波的全状态H∞反馈增稳控制器。该方法通过卡尔曼滤波器将状态估计值作为反馈量传递给H∞控制器,能保证存在三维大气紊流干扰,系统测量噪声和飞行条件变化所引起的系统参数矩阵摄动时的鲁棒性。仿真结果表明,不管是针对标称模型还是参数摄动后的模型,基于卡尔曼滤波器的H∞反馈增稳控制器能有效抑制外界干扰和系统自身参数摄动,说明该方法具有较强的鲁棒性。For a generic hypersonic vehicle with unstable longitudinal and lateral-directional mode, considering the three dimensional turbulence and their gradient, all states linear dynamic equations were established. All states H∞ feedback control was proposed based on the discrete Kalman filter when three dimensional turbulence and system measurement noise were taken into consideration. In this way, state estimation created by the Kalman filter to the H∞ controller was delivered. This method could guarantee the robustness when external atmospheric turbulence and itself parameter matrices perturbation caused by the flight condition variation existed. The results show that for both the nominal system and the perturbed system, H∞ feedback controller based on the discrete Kalman filter can restrain external disturbance and system parameter matrices perturbation effectively. So the system owns strong robustness.

关 键 词：三维紊流 高超声速飞行器 H∞控制 卡尔曼滤波 鲁棒性 

分 类 号：V249.1[航空宇航科学与技术—飞行器设计]