Abstract: The micro vibration of spacecraft structure will affect its accuracy.Bolt connection is widely used in the structure of the spacecraft,which will affect the strength and damping of the whole structure,leading to a certain nonlinear phenomenon.The aluminum honeycomb panel with bolt connection was studied,and the contact mechanics model is introduced to characterize the stiffness and yield stress of the Iwan model.And multi-scale method is used to find the solution to this system,finally we obtain the nonlinear frequency response function.Based on the theoretical model,we establish a system of finite element model of connection part substitute Iwan model and the corresponding experiment was carried out.At last, verify the correctness of the theoretical model so that we provide a reliable basis for the further research of the spacecraft vibration problem.

Key words: bolted connection, Iwan model, patran model, micro vibration