Modeling of hypervelocity impact on spacecraft honeycomb-core sandwich panels: investigation of projectile shape and honeycomb-core effects

In a typical satellite bus, most impact-sensitive equipment is situated in the enclosure of the structural sandwich panels, often – panels with a honeycomb core (honeycomb-core sandwich panels, HCSPs). As commonly used elements in satellite structures, these panels form the satellite’s shape and are primarily designed to resist launching loads and provide attachment p oints for satellite subsystems [1]. With low additional weight penalties, their intrinsic ballistic performance can often be upgraded to the level required for orbital debris protection [2].