Vibration Analysis of Structural Panel for Small Satellite

Abstract

A large shock occurs when launching the rocket. This shock depends on a combustion vibration. It causes serious damages to electronic equipments mounted with a satellite. Since the pay load of the rocket is limited, the satellite be required to reduce the weight. On the other hand, the weight reduction causes the stiffness reduction. Therefore, the resonance avoidance design is an important issue more than ever.
In this study, in order to reduce the weight of the small satellite, we verify the optimum vibration design of the structure panel using the FEM.