5A06铝合金单层板超高速撞击弹道极限分析

Ballistic limit analysis of aluminum 5A06 single wall plate subjected to hypervelocity impact

日益增长的空间碎片对在轨航天器的安全运行构成了严重威胁,毫米级空间碎片的防护已成为航天器结构设计必须考虑的问题之一.航天器的蒙皮是抵御空间碎片超高速撞击的最基本防护结构.采用数值仿真并结合试验验证的方法,对5mm厚5A06铝合金单层板承受2A12铝合金球形弹丸正撞击下的弹道极限进行了研究.研究表明,在验证实验速度范围内,数值仿真结果与实验结果吻合良好;使用数值仿真对实验速度以上的区间进行拓展研究,获得了其弹道极限曲线和弹道极限方程;数值仿真和实验结果与已有经验方程对比表明,经验方程与具体材料的弹道极限有较大偏差,因此,应具体问题具体分析.

The increasing space debris have made serious threat to safe operation of spacecrafts in orbit. Shiel- ding of millimeter-size space debris has been a problem must be considered in design of spacecraft structure. Skin of spacecraft is usually considered as the most basic shield structure against hypervelocity impact of space debris. Numerical simulation combined with experiment validation was adopted to investigate the ballistic limit of aluminum 5A06 single wall plate, 5 mm in thickness, subjected to normal impact of aluminum 2A12 spheri- cal projectile. Simulation results agreed well with experiments within the test velocity range. Thus numerical simulation was used to expand to higher velocities and the ballistic curve as well as equation was obtained. Comparison between numerical results, in association with experiments, and empirical equation indicated that the ballistic limit from empirical equation has remarkable difference in that of actual materials under research. As a result, specific analysis must be performed in shield structure for spacecrafts. order to provide basis for engineering design of space debris