In this paper an effort is made to carry out the shock analysis of an Indian spacecraft for clampband release shock loads. A finite element model is generated by making necessary adaptations to finite element model created for low frequency dynamic analysis. Since explicit codes are suitable for capturing wave propagation, the available commercial code DYTRAN is employed for the analysis. The SRS of internal accelerations are computed and compared with the available test results. Results show very encouraging trends. Effect of damping is also studied. Suggestions for improvement of specifications are given. Reflections on model improvement strategy are also given.
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