Abstract: Aerothermoelastic analysis of hypersonic vehicle involves the coupling of fluid field，structural field，and thermal field，and as a result is complicated and time-consuming. In this paper，a hypersonic aerothermoelastic analysis method based on reducedorder models is developed according to the hierarchical solution strategy. The system identification method and the proper orthogonal decomposition method are used to establish the reduced-order models of the hypersonic aerodynamic force and aerodynamic heating，respectively. Then，these reduced-order models are combined with the modal superposition method to realize the rapid calculation of aerothermoelastic problems under the static aerothermoelastic trim. Taking a typical hypersonic three-dimensional wing as an example，the flutter speed of the thermal structure is predicted，and is in good agreement with the calculation of the full-order fluid-solid-thermal coupling model. The aerothermoelastic analysis framework proposed in this paper is accurate and greatly improves the calculation efficiency，which can be applied to the engineering analysis.