This study investigates the coupled aerothermal and structural response of a hypersonic morphing vehicle undergoing configuration changes across a wide speed regime. Numerical simulations were conducted at Ma 5 and an altitude of 24 km to evaluate surface heat flux and pressure loads under varying wing folding angles (0°–90°) and angles of attack, using computational fluid dynamics (CFD). Based on the transient heat conduction equation— governed by the principle of energy conservation and Fourier’s law of heat conduction— the aerodynamic loads obtained from CFD were applied as boundary conditions in a finite element analysis to perform thermo-structural coupling simulations of the wing structure under representative morphing states. Results show that wing folding significantly intensifies localized aerodynamic heating and stress concentration: At a 90° folding angle, the peak heat flux at the wingtip reaches 1309.9 kW/m², and the equivalent structural stress increases to 506 MPa. Nevertheless, with appropriate thermal protection design, both thermal and mechanical safety requirements can still be satisfied. This work provides preliminary engineering analysis for evaluating the multi-state coupled characteristics of hypersonic morphing vehicles.