航天器防护方案高速斜撞击实验研究

Experimental investigation of oblique high velocity impact on spacecraft shielding scheme

给出和分析了柱状弹丸高速斜撞击铝合金Ｗｈｉｐｐｌｅ 防护方案实验研究结果． 结果表明，Ｗｈｉｐｐｌｅ 防护方案对高速斜撞击的响应不同于高速垂直撞击的响应，高速斜撞击具有分散撞击所产生碎片云损伤能量的特性，能产生严重损伤航天器外部结构和子系统的滑弹碎片． 滑弹的临界入射角在６５°～７５°． 低于此角对靶件造成的损伤严重；超过该角对滑弹观察板造成的损伤严重，对滑弹观察板造成的损伤集中在与防护屏成１５°的区域． 因此，航天器防护方案的选择必须考虑空间碎片高速斜撞击的影响．

High velocity impact of meteoroid and space debris on spacecraft is a threat to safe operation of spacecraft. The results of experimental investigation associated with the oblique high velocity impact of cylindrical projectiles onto aluminum Whipple shielding scheme are presented and analyzed in this paper. The results show that the response of Whipple shielding scheme to oblique impact is quite different from its response to normal high velocity impact. It was found that oblique incident projectile produce ricochet debris that can severely damage the exterior structure and subsystem of spacecraft. The critical angle of ricochet is estimated to have a value between 65° and 75°. Projectiles with angles of obliquity greater than the critical angle produce ricochet debris that causes major damage to the ricochet witness plate, less than the critical angle produce significant damage to the target. The most serious ricochet damage was found to occur at an angle of 15° with respect to the shielding bumper. Therefore the effects of oblique high velocity impact of space debris must be considered in the design of spacecraft shielding scheme.