Internal-structure-model based simulation research of shielding properties of honeycomb sandwich panel subjected to high-velocity impact

Abstract

Honeycomb sandwich panel has been widely used in aerospace and aeronautic engineering as load-bearing components. Cost-effective shielding structure can also be built based on honeycomb sandwich panel. The shielding properties of honeycomb sandwich panel subjected to high-velocity impact is of great concern to spacecraft design. Three dimensional internal-structure-based simulation research of honeycomb sandwich panels under high-velocity impact is carried out. The point-type internal structure model is constructed, where the impacted area is refined to capture localized deformation and improve the accuracy. The internal structure model is validated by experimental results and empirical formula. Then typical impact processes are simulated to investigate the cutting and channeling effect of the honeycomb core on the projectile. Projectile mass, impact velocity and internal-structure parameters of the honeycomb core are varied to obtain their influences on the channeling effect of the fragmented projectile. The thickness of the honeycomb core influences is found to affect much on the shape of the hole on the rear facesheet. Three empirical equations with respect to impact parameters and internal structure parameters are presented based on numerical results and the dimensional analysis.