Severe pyroshock can cause failure of mounted electronic equipment used in various space missions. To prevent this problem, it is important to predict the propagation path and attenuation of shock in space structures. In the case of a honeycomb sandwich panel, which is widely used in satellites, an insert is used in essential to connect with other structures and the shock wave propagates through this insert system. In this study, the shock attenuation performance of a honeycomb sandwich panel insert system is measured by a shock propagation experiment. Modeling and finite element analysis techniques for such a honeycomb sandwich panel with an insert system are introduced. The results of the experiment and analysis are compared.