The shock environment prediction of satellite in the process of satellite-rocket separation

This paper mainly discusses the shock environment prediction of the satellite in the process of satellite-rocket separation. At first, the field near to the shock source (near-field) that contains the pyrotechnic separation nut, satellite joint and rocket joint is researched with separation shock experiment and explicit dynamic code LS-DYNA. And then, the satellite model (far-field) is introduced. The force curve at the interface of satellite joint and the adjacent angle steel in vertical direction is extracted and used as the input of shock environment of satellite. Furthermore, the shock environment of the bottom panel and the side panel of the satellite in the flexure direction are computed by Virtual Mode Synthesis Simulation (VMSS). The results are compared with the ones of Finite Element Method (FEM). At last, the deficiencies of VMSS on the shock environment prediction of the satellite panel in the extension and shear directions are revealed since they do not contain enough modal number. The completed shock environment prediction method proposed in this paper is expected to provide a reference for the rapid and accurate computation of the shock environment at the initial stage of satellite structure design.