A compact energy-dissipative orbital debris shield based on AFPC material

To address the performance limitations of conventional orbital debris shields under space-constrained conditions, a compact shielding configuration is proposed by directly bonding an aluminosilicate fiber porous ceramic (AFPC) bumper to an aluminum rear wall. The AFPC material model was calibrated using mechanical tests and validated through hypervelocity impact experiments. On this basis, the shielding performance and protection mechanism of the AFPC/Al shield were investigated. The effects of impact velocity, AFPC bumper thickness, and aluminum rear-wall thickness on the energy dissipation and damage characteristics of the AFPC/Al shield were analyzed. The results show that, under conditions of equal areal density and equal total thickness, the AFPC/Al shield exhibits superior shielding performance compared with aluminum Whipple shields and Nextel/Kevlar stuffed Whipple shields. The AFPC/Al shield provides protection primarily through sustained and efficient dissipation of projectile kinetic energy within the AFPC bumper, which differs from the energy redistribution mechanism of Whipple shields and their derivatives. As the impact velocity increases, the energy dissipation of the AFPC bumper exhibits a velocity-strengthening effect. The AFPC bumper thickness is the primary parameter governing energy dissipation of the AFPC/Al shield, whereas the aluminum rear-wall thickness mainly influences the rear-wall damage mode, characterized by a transition from perforation to bulging. These findings provide new insights and valuable guidance for the design of orbital debris shields under limited space conditions.