进行了吸气式乘波体高超声速飞行器建模与姿态控制系统设计。首先基于拟合气动参数,建立了高超声速飞行器纵向动力学数学模型;然后针对模型参数不确定性情况,在对系统进行反馈线性化基础上,借助状态转换和一阶泰勒级数展开,建立了不确定部分的线性化模型,并设计了LQR控制器参数。最后仿真结果表明,当模型参数浮动的情况下,本文设计的高超声速飞行控制系统,能很好地实现速度与弹道倾角参考指令跟踪。 The design of suction-type body-hypersonic vehicle modeling and attitude control system was carried out. First, based on the fitted aerodynamic parameters, a mathematical model of the longitudinal dynamics of the hypersonic vehicle was established. Then based on the feedback linearization of the system and the state transition and the first-order Taylor series expansion, aiming at the uncertainties of the model parameters, Uncertain part of the linearization model, and design of the LQR controller parameters. Finally, the simulation results show that the hypersonic flight control system designed in this paper can realize the tracking of speed and trajectory reference commands well when the model parameters fluctuate.