Modal analysis for small satellite system with finite element method

Abstract

Modal analysis of satellite system is the basic requirement for the satellite structural design. The theory of normal modes is analysed rounded in this paper. And the finite element model of a small satellite, of which the monolithic structure is honeycomb sandwich plate, is established by using the finite element analysis software PATRAN/NASTRAN. Furthermore, the equivalent model for honeycomb sandwich plate is calculated. Based on the finite element model, the modal analysis of the satellite with finite element method is made. The results indicate that the finite element method is a convenient and useful tool for modal analysis, which can calculate normal frequency and predict modal shapes. Besides, the satellite structural vibratory weakness parts can be determined from the mode shapes. The analysis results can accommodate bases for structural design and optimum design of the small satellite structure. In addition, the numerical simulation results supply for modal analysis at experiment testing.