When a satellite separates from the rocket in space, large shocks occur in the satellite's body structure. To evaluate the reliability of onboard equipment, the acceleration in the body structure at the time of pyrotechnic operation needs to be predicted at the design stage of the satellite and onboard equipment. We present a method for analyzing separation shock response on satellites. We first made a finite element model on the basis of information on the design of the satellite. We then used static analysis to calculate the force loaded onto the part of the satellite that eventually separates from the body of the rocket by the clamping of the 'V-band clamp'. We then used an input parameter for the force that is released to predict the shock response on the satellite body. Transient response analysis with the mode superposition method was used. By comparing the calculation with the shock test result, we found that the proposed method was effective by considering the panels coupled to the cylinder in addition to the cylinder which was the part of the satellite involved in the separation.
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