Modal analysis on small spacecraft based on nonmetallic material vibration reduction design

To improve the dynamics environment for spacecraft payload during launching effectively, taking a small spacecraft as an example,a nonmetallic material vibration reduction design scheme is proposed on the basis of adapter frame structure. The nonmetallic material vibration damper is simulated by beam element considering shear deformation in finite element model,and the numerical simulation analysis and experiments are performed on the dynamic characteristics of the spacecraft. The results show that the simulation results are well consistent with the experiment results.