针对高超声速巡航类飞行器面临的复杂流动下的热气动弹性问题，发展了一种时变热模态适用的非定常气动力降阶模型，建立了基于流-热-固时空耦合分析策略的热气动弹性分析方法，对高超声速飞行器前体进气压缩面进行了实际飞行加热过程的时变颤振分析。结果表明，在局部高热流载荷下，压缩面固有模态频率和振型随时间发生了大幅度变化，而所建方法能够适应上述变化，在获得高置信度非定常广义气动力的同时，避免了重复性的非定常气动力数值计算，可将热颤振分析中的气动力计算效率提升若干量级；此外，在达到热平衡后，进气压缩面的颤振动压降为初始时刻的0.64%，使得飞行包线大幅收窄。相关方法有效缓和了热气动弹性分析效率与精度的矛盾，提升了热气动弹性问题的工程分析能力。

For aerothermoelastic problems dominated by complex flow on hypersonic vehicles， an unsteady aerodynamic Reduced-Order Modeling （ROM） method suitable for time-varying thermal modal shapes was developed， based on which a fluid-thermal-structural coupling framework using spatial and temporal data exchanging strategy was finally constructed. Above framework was applied to predict time-varying flutter boundary of an air intake compression surface installed on hypersonic vehicle forebody in actual aerodynamic heating process. As is shown in the results， modal frequencies and modal shapes varied greatly with time when the compression surface was exposed in extremely uneven heat flow， and proposed ROM method is suitable for such variation of modal shapes， which means repetitive CFD calculation of unsteady aerodynamic force can be saved. By adopting proposed ROM， generalized aerodynamic force can be calculated with high confidence and time consumption is several orders of magnitude lower than traditional methods. Aerothermoelastic analysis of compression surface revealed that flutter dynamic pressure was reduced to 0.64% of the value at initial time after reaching thermal equilibrium， which significantly narrows flight envelop of hypersonic vehicle. The proposed method effectively alleviates the contradiction between efficiency and accuracy of aerothermoelastic analysis， and improves the engineering feasibility of aerothermoelastic analysis.