高超声速滑翔飞行器非线性变结构自适应控制  

Study on Nonlinear Variable Structure Adaptive Control Law for Hypersonic Gliding Vehicle

作　　者：常莹莹[1] 王小虎[1] 何纯[1] 曾宪法[1] 

机构地区：[1]北京控制与电子技术研究所,北京100038

出　　处：《计算机仿真》2015年第6期59-62,434,共5页Computer Simulation

摘　　要：研究高超声速滑翔飞行器稳定性优化控制问题,由于系统要求快速保持侧滑角为零,姿态控制系统需要有效解决飞行器航向通道与滚转通道协调耦合。但高超声速滑翔飞行器系统为非线性,在强耦合和外界干扰不确定性特点条件下,为保证系统的稳定性,需要一种变结构自适应的姿态控制设计方法。首先建立了高超声速飞行器姿态控制系统的非线性数学模型,然后把结构干扰力矩和外界扰动等不确定的输入因素视为一类有界干扰,并提出了一种自适应变结构控制方法,保证系统闭环稳定的前提下,在线对不确定因素进行估计,并对控制方法进行Lyapunov稳定性分析,最后通过计算机仿真验证了改进方法具有良好的解耦控制效果,且在有外部干扰的情况下,系统能够很快的达到稳定。Because it is desired to maintain that sideslip angle equals to zero quickly, the attitude control system needs to effectively solve the coordination coupling of craft heading channel and rolling channel. In order to ensure the stability of the system, this paper proposed a stability optimal control approach for the stability control problem of hypersonic glide vehicles. Firstly, a nonlinear simulation model was established according to the features of hyperson- ic glide vehicles. Secondly, structure moment and external disturbance were regarded as a class of disturbance with boundary. Thirdly, the uncertain boundary of structure moment and disturbance was estimated with this method on the premise that the stabilization of close - loop system was guaranteed, and Lyapunov stability analysis were carried out. At last, numerical simulation results verify that this method has good decoupling control effect, and the system can quickly achieve stability with external disturbance.

关 键 词：非线性 变结构 自适应 姿态控制 

分 类 号：TJ765.43[兵器科学与技术—武器系统与运用工程]