摘要
低地球轨道上的航天器易受到微流星体和空间碎片的超高速撞击,导致其严重损伤甚至灾难性的失效。撞击损伤特性研究是航天器防护设计的重要问题。本文采用非火药驱动二级轻气炮发射球形弹丸,对铝双层板结构进行超高速撞击实验研究,从而模拟空间碎片对航天器防护结构的超高速撞击作用。实验得到了铝双层板结构在弹丸撞击速度为2.33±0.12km/s和4.36±0.10km/s两种情况时,其前板和后板的撞击损伤随前板厚度变化的规律,随着前板厚度的增加,前板穿孔直径增大,后板撞击中心的损伤减轻,后板上大弹坑由撞击中心移至外围。当撞击速度超过弹丸破碎速度时,后板上将出现弹坑密集分布区。实验结果表明,前板厚度的选取对双层板结构的撞击损伤区域会产生影响。
All spacecraft in low orbit are subject to hypervelocity impact by meteoroids and space debris, which can in turn lead to significant damage and catastrophic failure. Investigation into the impact damage characteristics has become an important problem for spacecraft protection designing. In this paper, in order to simulate and study the hypervelocity impact of space debris on Aluminum dualwall structure of spacecrafts, a non-powder two-stage light gas gun was used to launch Al-sphere projectiles. The law of damage in bumper and rear wall of Aluminum dual-wall structure depend on bumper thickness were proposed at 2. 33±0. 12km/s and 4. 36 ± 0. 10km/s of impact velocity respectively. As the thickness of bumper increasing, the penetration hole diameter of bumper increased, the impact damage at center of the rear wall mitigated, and the large crater moved from center to circumference. When projectile impact velocity exceeds the velocity of projectile fragmentation, two crater dense areas will be brought in rear wall of Aluminum dual-wall structure. Therefore, the bumper thickness can effect on damage distributing area of Aluminum dual-wall structure.
出处
《实验力学》
CSCD
北大核心
2006年第3期299-306,共8页
Journal of Experimental Mechanics
基金
国家空间碎片专题研究项目资助
关键词
超高速撞击
双层板
厚度
损伤
实验
hypervelocity impact
dual-wall structure
thickness
damage
experiment
