高超声速滑翔飞行器不确定性分析与H_∞混合灵敏度控制  

Uncertainty analysis and H_∞ mixed sensitivity control for hypersonic gliding vehicle

作　　者：孙浩[1,2] 罗建军[1,2] 马卫华[1,2] 

机构地区：[1]西北工业大学航天学院,陕西西安710072 [2]航天飞行动力学技术重点实验室,陕西西安710072

出　　处：《系统工程与电子技术》2014年第12期2466-2472,共7页Systems Engineering and Electronics

基　　金：国家自然科学基金(61004124)资助课题

摘　　要：针对高超声速滑翔飞行器具有强不确定性的问题,采用鲁棒性强的H∞混合灵敏度方法设计飞行器的控制系统。首先,针对模型包含大量不确定参数,使用了最坏情况增益(worst case gain,WCG)的灵敏度分析方法对系统不确定性进行分析,得到了可以表示原系统模型不确定性的主要不确定参数。然后,根据不确定参数分析结果,选取H∞混合灵敏度控制器的权函数并设计了控制器。最后,通过三通道非线性仿真以及参数拉偏仿真,对控制系统的动态性能和鲁棒性进行了检验,验证了控制系统分析与设计方法的有效性。With respect to the strong uncertain property of the hypersonic gliding vehicles,the robust con-trol method based on H∞ mixed sensitivity is adopted to design the control system.At first,the uncertain pa-rameters are analyzed using the sensitivity analysis method based on worst case gain （WCG）and the principal uncertain parameters which can stand for the uncertainty of the original model are obtained.Then,according to the results of the parameter analysis,the weighting functions of the robust controller are selected,which con-tribute to the completion of the controller design.Finally,nonlinear simulations of the control system on char-acteristic point and parameter deviating are carried out,and the dynamic performance and robustness of the con-trol system are examined.The results validate the effectiveness of the analysis and design method of the control system.

关 键 词：高超声速滑翔飞行器 H∞混合灵敏度 加权函数 不确定性 鲁棒性 

分 类 号：V448.2[航空宇航科学与技术—飞行器设计]