中文摘要：

大范围机动、质量分布快速变化、气动特性复杂，以及飞行器结构、气动、推力的相互耦合，使得高超声速飞行器动力学呈现出强不确定性，给其动态特性分析和控制器设计提出了挑战。文章针对高超声速飞行器模型参数不确定性问题，首先分析各种可能造成模型不确定性因素的物理本质，确定其主要影响因素；在此基础上建立了能够反映这些主要影响因素带来的具有参数不确定性问题的动力学模型；并分析每一个单独不确定性参数变化对飞行器特征根分布的影响；在考虑高超声速飞行器参数不确定性的情况下，针对刚体．弹性体模型，采用修正的反馈线性化方法设计控制律。研究结果对高超声速飞行器的动力学特性分析、总体设计、控制系统设计、准确度分析等提供具有重要参考价值的依据。

英文摘要：

Sections 1 through 4 of the full paper explain our dynamic analysis and control law design mentioned in the title ; this explanation we believe is of reference value and whose core consists of： （ 1 ） the wide-range maneu- ver, rapid change of mass distribution, the complex aerodynamic characteristics and the mutual coupling of the structure, aerodynamics and thrust of a hypersonic vehicle contribute- greatly to the strong uncertainty of its dynam- ics, which is a great challenge to the dynamic analysis and control law design; （2） we analyze the major uncertain- ty parameters which may contribute to the dynamics of the hypersonic vehicle ; （3） we establish the uncertainty pa- rameter dynamics model and analyze the impact of the uncertainty parameter changes on the hypersonic vehicle＇ s eigenvalue distribution; （4） using the rigid-flexible body uncertainty model, we design the control law with the modified feedback linearization method. The simulation results, given in Table 1 and Figs. 2 through 4, provide a useful reference for a hypersonic vehicle＇ s dynamics analysis, overall design and control law design.