In order to improve the stiffness of satellite main load-bearing structure, the variable stiffness sandwich panel skin is designed based on the constant curvature arc curve and translation method. The equivalent modeling, modal analysis and modal fundamental frequency optimization of sandwich panel with different initial / ending angle combinations are carried out by using ABAQUS secondary development method and response surface method. The numerical results show that the modal fundamental frequency of the sandwich panel with variable stiffness design increases first and then decreases with the increase of the initial angle and then decreases, and increases with the increase of the ending angle. The maximum lifting percentage of the fundamental frequency is 12.33%, which can reduce the dynamic coupling effect between the honeycomb basic bearing structure and the equipment.