摘要
为了掌握航天器防护结构受空间碎片高速撞击的损伤破坏模式及其防护性能,采用二级轻气炮发射球形弹丸,对铝合金Whipple防护结构进行高速撞击实验研究.根据实验结果分析了铝合金Whipple防护结构的防护屏和舱壁在不同速度区间的损伤模式特征,以及薄铝板防护屏高速撞击穿孔和舱壁弹坑分布随弹丸直径、弹丸撞击速度变化的规律.通过固定弹丸直径,改变弹丸撞击速度,寻找临界撞击速度的方法获得了铝合金Whipple防护结构在0.5～5.5 km/s撞击速度区间内的撞击极限曲线,并与由Christiansen撞击极限方程得到的撞击极限曲线进行了比较,结果表明,实验最小临界弹丸直径略大于预测值.
In order to get the damage mode and resist character of spacecraft shield structure by the high-velocity impact of space debris, a two-stage light gas gun with non-powder projection was used to launch Al-sphere projectiles impacting on aluminum alloy Whipple shield. By analyzing damage mode in different impact velocity ranges, the laws of penetration hole diameter and cratered area diameter depending on projectile diameter and impact velocity were observed. At the same time, the ballistic limit curves of the Whipple shield in a velocity range from 0.5 km/s to 5.5 km/s was obtained. Comparing to the predicted curve from Christiansen ballistic limit equation, the experimental minimum critical projectile diameter is slightly greater than the prediction.
出处
《爆炸与冲击》
EI
CAS
CSCD
北大核心
2005年第5期461-466,共6页
Explosion and Shock Waves
作者简介
管公顺（1969-），男，博士研究生。Corresponding author： GUAN Gong-shun E-mail address ： ggsh@hit, edu. cn Telephone： 0451-86417978
