弹丸正撞击Whipple防护结构后墙的穿孔孔径研究

微流星体及空间碎片的超高速撞击对在轨航天器，特别是长期留轨的栽人航天器构成了严重的威胁，甚至可导致灾难性失效，为此航天器采用了各种Whipple类防护方案以提高其在轨生存能力。穿孔孔径是研究弹丸超高速撞击下航天器舱壁撞击损伤的重要参数之一。文章对目前所建立的Burch损伤经验公式与Schonberg—Williamsen穿孔经验公式进行了研究，比较了其各自特点；同时，基于上述模型提出了适用范围更广的弹丸超高速正撞击Whipple防护结构后墙的穿孔孔径经验公式，为航天器的灾难性失效分析提供有效的工具。

Empirical Hole Size Model for Whipple Shield under Projectile Normal Hypervelocity Impact

Meteoroid/Orbital Debris(M/OD)could cause severe damage or even catastrophic failure for its hypervelocity impact(HVI)on spacecraft wall,so great efforts have been devoted to developing such shielding structures as Whipple shield for spacecraft.Hole size is an important parameter of impact damage to spacecraft wall under projectile HVI.The Burch empirical damage model and Schonberg-Williamsen empirical hole size model are firstly reviewed in this paper.Then a new hole size empirical model for Whipple shield under normal HVI is proposed based on the above-mentioned empirical models,this model has more wide application range and provides an effective tool for the catastrophic failure analysis of spacecraft.