In order to meet the design requirements of the primary load-bearing panel of a satellite in terms of lightweight and stiffness performance and effectively reduce the dynamic responses of the panel，a lattice structure is incorporated into the design of the primary panel.First，the cell composition of the lattice structure is introduced.It is demonstrated that the satellite primary load-bearing panel filled with the lattice structure can reduce the weight of approximately 35% compared with the traditional honeycomb core panel，while maintaining the same external dimensions，thereby satisfying the lightweight design requirements for satellites.Second，theoretical mathematical models for the relative density，in-plane stiffness，in-plane strength，and shear stiffness of a single cell unit are established，and the accuracy of the models are validated through simulation analyses.The fundamental principles of dynamic analyses and the optimization methods are illustrated.Finally，based on the modal analysis results，harmonic and random vibration response analyses are conducted on the designed primary load-bearing structure.The results show that the structural stiffness distribution of the primary load-bearing panel is uniform and exhibits favorable responses to excitations，and all dynamic performance indicators meet the specified requirements.