作　　者： ; ; ; ;

机构地区： 哈尔滨工业大学航天学院

出　　处： 《材料科学与工艺》 2004年第3期283-286,共4页

摘　　要： 微流星体及空间碎片的超高速撞击威胁着长寿命、大尺寸航天器的安全运行,导致其严重的损伤和灾难性的失效.撞击损伤特性研究是航天器防护设计的一个重要问题.本文采用AUTODYN软件的Lagrange法对半无限铝板的超高速斜撞击和与其具有相同法向速度的正撞击进行了模拟,给出了不同撞击角和不同法向速度下半无限厚铝板弹坑深度、宽度、长度的变化规律及多弹坑的形成过程,并与经验方程进行了比较分析.结果发现:随撞击角的增加,弹坑的深度和宽度减小,而弹坑的长度增加;随撞击速度的增加弹坑的直径和深度增加;在撞击角大于70度时出现多弹坑. Hypervelocity impact on long duration and large size spacecraft by meteoroid and space debris is a threat to its safety operation that 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. The numerical simulation of hypervelocity oblique impact and hypervelocity normal impact with the same normal velocity as oblique impact on semi-infinite aluminum plates have been carried out using the AUTODYN hydro-codes Lagrange method in this paper. The simulation results of crater depth, width, length, diameter, multi-crater formation process etc. with different impact obliquities and normal velocities are given and compared with the empirical equation. The result indicates that the crater depth and width decrease and crater length increase with the obliquity increase. The crater diameter and depth increase with the velocity increasess. The multi-crater appears when obliquity is greater than 70~0.It is consistent very well with experimental results.

关 键 词： 航天器 空间碎片 超高速撞击 半无限板 数值模拟 微流星体 有限元

领　　域： [航空宇航科学技术] [理学] [理学] [一般工业技术]