Numerical investigation of debris impact on spacecraft structure at hyper-high velocity

In this paper, our analysis concentrated on the mechanical behavior of sandwich panel subjected to impact loading. Thus, to improve the resistance of satellite structures from debris collision consequences; we proceed a performance investigation numerically of different materials based on the evaluation of contact force, total energy and kinetic energy generated from the impact of spherical steel debris on sandwich panel. Furthermore, a comparison of deformations and stresses levels in sandwich panel collide by a projectile at hyper-high velocity using finite element with ANSYS code was made. The difference between our models is the type of skins materials which are aluminum and functionally graded material FGM (alumina/nickel). The impact results a total perforation of sandwich panel with aluminum facesheets creating a fragments; contrary to FGM which the projectile penetrates only the front facesheet and honeycomb core. However, for an effective protection of sandwich panel against debris perforation, the introduction of FGM skins technique is considered as a candidate solution.