基于多输入多输出特征模型的高超声速飞行器自适应姿态控制  

MIMO Characteristic Model Based Adaptive Attitude Control for Hypersonic Vehicle

作　　者：王勇[1,2] 龚宇莲[1,2] 王丽娇[1,2] 

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

出　　处：《空间控制技术与应用》2011年第4期13-18,44,共7页Aerospace Control and Application

基　　金：国家自然科学基金(60736023;60704014)

摘　　要：针对高超声速飞行器再入过程中强耦合、大扰动和大范围变化的气动参数的问题,基于特征建模的思想,分析动力学方程的耦合特点,采用分散控制的方案,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、侧滑角和滚转角三通道特征模型,并给出了黄金分割自适应的姿态控制方法.最后,针对类X-20高超声速飞行器进行数值仿真,仿真结果充分验证了这种自适应控制器的有效性.In response to the difficulties such as strong coupling effect, drastic variation of flight environment, and large uncertainty of aerodynamic forces and external disturbances in the course of reentry of hypersonic vehicles, the coupling property of plant is analyzed, a decentralized control scheme is adopted and the original nonlinear dynamics model is described as a set of characteristic models comprised of the angle of attack, sideslip angle and roll angle channels. Moreover, a golden section adaptive attitude controller is presented. At last, some simulations for the X-20-like hypersonic vehicle are given to fully verify the effectiveness of this method.

关 键 词：高超声速飞行器 自适应控制器 特征模型 姿态控制 多输入多输出 非线性动力学方程 差分方程组 再入过程 

分 类 号：V448.2[航空宇航科学与技术—飞行器设计]