Optimum design of a space frame and its application in satellite structure

The optimization of a three-dimensional space frame with parameterized element cross sections and its application in the frame structure optimization of a satellite structure design is discussed. The space frame synthesis problem is considered, which seeks a minimum mass design such that all pertinent measures of structural behavior and all structural design variables remain within specified limits. Based on the original design of a satellite structure, an finite element (FE) model is established, which consist of shell, beam, and rod elements. The results show that the longitudinal frequency change very little and the critical bulking factor increase from 2.02 to 2.21, indicating higher stability. The stiffness, strength, and stability of the final solution is found to satisfy all the design constraints and the mass decrease, which provide guidelines to the detail design of the satellite structure.