Spacecraft are exposed to severe mechanical loads, i.e., shock loads, during their journey to orbit. Such loads usually develop due to a separation event through the activation of pyrotechnic devices. They might be transmitted throughout the entire structure and strongly influence the service performance of electronic components. Therefore, it is crucial to study whether the instruments can resist such a harsh environment. However, due to the vulnerability and high cost of the equipment, experimental setups are required to be designed and calibrated with dummy equipment, which takes considerable time and effort as well. In this context, the current study aims to investigate the potential of explicit FE solution techniques to mimic the calibration tests. In order to realize this, various experiments are conducted in a metal-to-metal impact pyroshock test bench and the obtained Shock Response Spectrum (SRS) responses are fitted to the explicit finite element simulations, which shows good agreement after a sensitivity analysis. Then, the simulations are repeated with the dummy device using the fitted parameters, and the potential of the numerical approach to predict a realistic response is discussed.