A fluid-thermal-structural integrated method was presented based on finite volume method for hypersonic aeroheating-structural-thermal interaction. A system of unified integral equations was developed as the control equations for physical process of aero-heating and structural heat transfer. The whole physical field was discretized by using an up-wind finite volume method, which avoids the fussy data exchange and computational complexity in coupling method. To demonstrate its capability, applications for fluid-thermal-structural analysis of hypersonic ow over 2D stainless steel cylinder in steady and unsteady states, were performed and discussed. The numerical results show that the maximum temperature of about 648 K occurs at the stagnation point of stainless steel cylinder in a steady state and the objective physical processes in a good agreement with measured values in unsteady state. Compared with the coupling method, the integrated algorithm has shown a better stability with lesser griddependence，which provides theoretical and technical support for the thermal protection system of hypersonic vehicles.