As one of the important means of data transmission between satellites, laser communication has a direct impact on the performance of the constellation system due to its fast and stable link establishment ability. The laser communication terminal relies on a high-precision optical tracking system to achieve continuous and stable pointing of the signal beam to the target satellite. However, space environmental factors can interfere with the pointing accuracy of laser terminals, and their influence can reach the level of milliarcsecond measurements. The deformation of the satellite structure caused by thermal expansion, cold contraction and stress changes during the satellite operation in orbit leads to the rigid displacement of the laser terminal pointing accuracy compared with the reference position of the satellite platform. In this paper, based on the application background of the rapid and stable chain construction of inter-satellite laser communication links, the finite element analysis method is used to study the pointing error caused by the thermally induced deformation of the laser terminal datum and the satellite platform star sensitive datum. By analyzing the installation reference error caused by the thermal deformation of satellites at different orbit altitudes, the variation law of laser communication link pointing error is obtained, which provides an analytical basis for the rapid and stable chain construction, and provides a design reference for the module layout and overall thermal control of the whole satellite.