Abstract: The shock induced by satellite-rocket separation is one of the severe mechanical environments that the spacecraft has to experience. An axisymmetric circular ring vibration model is established to analyze the radial shock response of the satellite-rocket separation interface during separation process. By using this model validated by finite element analysis, the influence on the radial shock response concerning band pre-tightening force, structural parameter of the interface ring, mass of clamp band and fixture block are discussed. It is shown that the radial shock of the satellite-rocket separation interface increases with the increase of the pre-tightening force of clamp band. Considering the mass of the band and fixture block, the release time of the strain energy stored in the interface ring is prolonged. In ensuring the reliable satellite-rocket connection and separation, it is an effective means of decreasing the interface shock to reduce the pre-tightening force of clamp band and to delay the release time of strain energy of the interface connection structures.

Key words: Circular ring vibration, Clamp band, Satellite, Separation shock