A division coordinating coupled marching time domain method for thermal flutter of hypersonic wing is presented. The aerodynamic force and heating are calculated by finite volume method， the advection upstream splitting method（AUSM+） scheme is adopted for spatial discretization. The structural temperature field is calculated by finite element method. The structural transient responses are calculated by modal superposition method. In addition， the transfers of coupling variables are conducted by the interpolation method based on virtual space. The thermal flutter of hypersonic wing is studied. The temperature fields of the wing under different Mach numbers are obtained. According to the frequency coincidence theory， the first order bending frequency and first order torsion frequency are closer to each other in thermal environment， and it is the reason for that critical flutter velocity of wing in thermal environment is lower than that in normal temperature.