特征模型分散式自适应姿态控制在高超声速飞行器中的应用  

Application of Characteristic Model Based Decentralized Adaptive Attitude Control in the Hypersonic Vehicle

作　　者：王勇[1,2] 

机构地区：[1]北京控制工程研究所,北京100190 [2]空间智能控制技术国家级重点实验室,北京100190

出　　处：《宇航学报》2012年第10期1413-1422,共10页Journal of Astronautics

基　　金：国家自然科学基金(60736023;60704014)

摘　　要：针对高超声速飞行器在再入过程中强耦合、大扰动和气动参数大范围变化的问题,基于特征建模的思想,把原非线性动力学方程用一个二阶时变差分方程组形式的特征模型描述,建立了攻角通道独立、偏航/滚转通道耦合的特征模型,并设计了分散式自适应姿态控制器,给出了稳定性分析和数值仿真。由于基于特征模型设计的控制器组成的闭环系统是一个非常复杂的混合系统,稳定性分析在特征建模理论中一直是一个难点,提出的稳定性分析方法完全解决了此类不含内动态相对阶为二的多输入多输出系统的稳定性问题。In the course of the reentry of hypersonic vehicles, many difficulties such as strong coupling effects, drastic external disturbances, and large uncertainties of aerodynamic parameters make the design of guidance and control system very challenging. In response to that, the original nonlinear dynamics are transformed into the MIMO characteristic model in the form of two-order time-varying difference equations, and a decentralized adaptive attitude controller is designed. At last, the stability is proved and some simulations are presented. Because the closed-loop system is a very complex hybrid system, and a valid stability analysis has been absent in the characteristic modeling theory, the method proposed in this paper is used to absolutely handle the stability oroblem of MIMO system with a relative de^ree of two and without internal dynamics.

关 键 词：特征模型 自适应控制 高超声速飞行器 采样系统 

分 类 号：V448.2[航空宇航科学与技术—飞行器设计]