The surface radiation heat simulation program based on Microsoft VC++ 6.0 for spacecraft in whole orbit course was presented.Due to complexity of spacecraft structure,the spacecraft structures were decomposed to relatively regular parts.Automatic generation of calculation grid was conducted by using structured grid and unstructured technology.Simulation mainly solved automatic grid generation for arbitrary surface and data transmission between arbitrary shape interfaces,and the geometry structure,physical process,calculation accuracy and efficiency were considered.View factors and radiation transfer coefficients were calculated by combining finite element method and ray uniform distribution.According to the position of surface cells,external heat flux was calculated with integral method for non-shaded surface and with ray uniform distribution method for shaded surface.As the spacecraft surface was wrapped with multilayer insulation material,the temperature field of multilayer insulation material was calculated with nodal network method and finite volume method.The temperature of other parts without wrap was calculated with finite element method.The temperature of unconnected regions available with radiation heat transfer relations was analyzed,and the calculation formulae were deduced.Numerical experiment shows that the simulation program is correct and effective. The surface radiation heat simulation program based on Microsoft VC ++ 6.0 for spacecraft in whole orbit course was presented. Due to complexity of spacecraft structure, the spacecraft structures were decomposed to relatively regular parts. Automatic generation of calculation grid was conducted by using structured grid and unstructured technology.Simulation primarily solved automatic grid generation for arbitrary surface and data transmission between arbitrary shape interfaces, and the geometry structure, physical process, calculation accuracy and efficiency were considered .View factors and radiation transfer coefficients were calculated by combining finite element method and ray uniform distribution. According to the position of surface cells, external heat flux was calculated with integral method for non-shaded surface and with ray uniform distribution method for shaded surface. As the spacecraft surface was wrapped with multilayer insulation material, the temperature field of multilayer insulatio n material was calculated with nodal network method and finite volume method. temperature of other parts without wrap was calculated with finite element method. temperature of unconnected regions available with radiation heat transfer relations was analyzed, and the calculation formula was successfully deduced. shows that the simulation program is correct and effective.