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为了研究空间碎片对航天器防护结构的高速斜撞击损伤特性,采用二级轻气炮发射铝球弹丸,对铝Whipple防护结构进行高速斜撞击实验。弹丸直径为3.97mm,撞击速度为1.14～5.35km/s,撞击角度为0°～70°。实验得到了铝Whipple防护结构在不同撞击速度区间的后板损伤模式,分析了后板撞击损伤及弹坑分布特性,建立了预测铝球弹丸高速斜撞击铝Whipple防护结构时后板弹坑分布的经验公式。结果表明:在大角度斜撞击条件下,对于一定的撞击速度,铝Whipple防护结构的后板弹坑分布会出现两个区域;弹丸的撞击破碎临界速度将影响后板损伤随撞击角的变化关系;对于铝Whipple防护结构,存在使后板撞击损伤最严重的临界撞击角。
In order to study the high-speed oblique impact damage of space debris to the spacecraft structure, an aluminum ball projectile was fired by a two-stage light gas gun to perform high-speed oblique impact experiments on the aluminum Whipple shield. Projectile diameter of 3.97mm, the impact velocity of 1.14 ~ 5.35km / s, the impact angle of 0 ° ~ 70 °. The rear plate damage modes of aluminum Whipple protective structures in different impact velocity ranges were obtained. The impact damage of rear plate and distribution of crater were analyzed. The empirical formula for predicting the distribution of rear plate crater when aluminum ball projectile collided with aluminum Whipple protective structure was established . The results show that there are two regions for the tailing crater distribution of Al Whipple protective structure under the conditions of high-angle oblique impact. The critical speed of impact and crushing of the projectile will affect the relationship between the damage of the rear plate and the impact angle. For aluminum Whipple structures, there is a critical strike angle that impairs the rear panel impact damage.