中文摘要：

针对高超声速飞行器机身极易发生弹性振动，模型具有非线性、强耦合及不确定性等特点，提出了考虑气动-推进-弹性耦合的综合建模方法。首先，利用假设模态法计算弹性模态及弹性振动效应，采用斜激波和普朗特-迈耶流理论、Eckert参考温度法及一维可压缩流关系式估算气动力、俯仰力矩及推力，考虑气流黏性及机身弹性变形影响，加入了黏性及弹性振动效应，更接近于真实物理特性；然后分析了弹性振动引起的机体变形角及机身表面流体特性；并基于机理推导所获取的气动数据，利用曲线拟合方法，建立了考虑气动-推进-弹性耦合的高超声速飞行器面向控制模型。气动和动态特性分析结果表明，弹性振动改变了飞行器弹性模态及气动布局，面向控制模型降低了模型复杂度，并保留了机理模型的物理耦合特性及非最小相位现象。

英文摘要：

Considering the elastic vibration of hypersonic vehicle, and the characteristics of nonlinearity, strong couplings and uncertainty, a dynamic model for a flexible hypersonic vehicle is developed. Firstly assumed modal method is used to compute the natural frequencies and mode shapes of the flexible structure. Oblique shock and Prandtl-Meyer flow theory, Eckert＇ s Reference Temperature Method and 1-D flow relation are applied for estimating aerodynamic forces, moment and thrust of the hypersonic vehicle including viscous and flexible effects . Then, the deflections of vehicle body and aerodynamic characteristics on vehicle surface are analyzed. Finally, a control-oriented model of the hypersonic vehicle aerodynamic is presented by using curve-fitted approximations. The simulations show that the elastic vibration can change the flexible mode and aerodynamic layout, and the control-oriented model not only can reduce the complexity of the model, but also retains physical characteristics and non-minimum phase of the mechanism model.