The growing threat of orbital debris is a significant concern for active and future spacecraft. This study exploits the concept of redesigning the components of spacecraft, adding to them a new function of space debris protection. The sandwich panel is a traditional member of the satellite structure due to its high structural support capability. However, the honeycomb sandwich panel, the most commonly used sandwich structure, has demonstrated a very low efficiency for protection against space debris. Therefore, it’s necessary to examine other types of sandwich panels that can serve structural purposes and simultaneously provide adequate protection against space debris. This thesis thoroughly investigated the shielding performance of a Corrugated Core Sandwich Panel (CCSP) against hypervelocity impact as a potential alternative to conventional shield designs. To eliminate the current limitation of the experimental investigation, a robust numerical model was developed using a combination of Smoothed-Particle Hydrodynamics (SPH) technique and the Finite Element Method (FEM) in ANSYS/AUTODYN software. The developed numerical models were validated using experimental data. Parametric studies identified the areas on the CCSP that are susceptible to hypervelocity impact and its effect on the overall shielding performance of the panel. Several strategies to enhance the shielding performance of the CCSP have been proposed. Upgrading the corrugated core of the CCSP configuration leads to a 20.5% improvement. In addition, it was demonstrated that the CCSP performance could be further enhanced with ballistic inserts containing aramid or ceramic fabric layers. A triangular prism-shaped polymeric foam has been suggested for making the inserts, which are meant to fit the space within the corrugated plate core.