中文摘要：

针对飞行器非线性动力学系统具有不确定项情况,研究了高超声速飞行器的飞行控制系统设计问题。由于动力学系统中存在线性参数不确定项和由于高速高热造成的未建模动态时,论文将研究对象扩展为控制矩阵中含有线性参数不确定系统,同时放宽了现有文献中许多苛刻的条件,如匹配条件、增长条件等,用自适应调节函数补偿系统不确定性带来的影响,设计鲁棒项函数解决了逼近误差的影响问题,通过引入投影算子避免了可能出现的控制器奇异问题。在自适应反演设计时,采用动态面设计方法,引入一阶滤波器,得到虚拟控制量的微分,消除传统反演设计中的＂项数膨胀＂的问题,用Lyapunov稳定性定理保证误差一致有界。仿真实验验证了该算法的有效性。

英文摘要：

Based on the presented model,the hypersonic aircraft control system is analysed with linear parameter uncertain term and unmodeled dynamics existed in a uncertain nonlinear dynamics system.Due to the linear parameter uncertain term and unmodeled dynamics caused by high mach number and high temperature,the research object is expanded to a nonlinear dynamics system including the linear paramter uncertain term in control matrix,an adaptive adjust function is adopted to compensate the influence about the uncertainty,and the robust term is designed to solve the problem about approach error.A projection operator is adopted to design the final direct adaptive control law,thus avoiding possible singularities of the controller.In the course of adaptive backstepping design,the dynamic surface control strategy is employed to eliminate the explosion of terms by introducing a first order filter to obtain the differentiation of virtual control inputs.The Lyapunov stability theorem guarantees the error uniformly bound.Both theory analysis and simulation verification show simplicity and effectiveness of this method.