A fluid-solid-thermal staggered iterative numerical coupled method is proposed to study the static aerothermoelasticity of hypersonic wing in this paper. The coupled effect between the aerodynamic environment （aerodynamic force and aerodynamic heating） and the structural deformation， another coupled effect between aerodynamic heating and structural temperature field and the influence on the thermal stiffness of wing by the temperature field are considered in the coupled method. The aerodynamic environment is solved by computational fluid dynamics method， and the structural heat transfer and deformation are solved by finite element method. The data exchanges for wall heat flux， wall temperature， aerodynamic force and the deformation of wing are conducted by the bidirectional mapping interpolation method based on control surface on the coupled surfaces. The coupled method is successfully applied to analyze the static aerothermoelasticity of hypersonic wing. The thermal environment results in the decrease of structural stiffness. The deformation of wing in the thermal environment is significantly greater than that in 300 K. Moreover， such deviation increases as the Mach number increases.