不同环境温度下铝球弹丸高速撞击编织物防护屏试验研究.pdf

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第51卷第3期
机槭工程学报
Vol.51 No
2015年2月
JOURNAL OF MECHANICAL ENGINEERING
2015
DOI:10.3901/JME,2015.03,066
编织物防护屏试验研分”渗
不同环境温度下铝球弹丸高速撞
管公顺蒲东东哈跃庞宝君
(哈尔滨工业大学航天学院哈尔滨150080)
摘要:利用二级轻气炮发射2017铝球弹丸,在两种环境温度下高速撞击编织物单防护屏结枃和填充式结构,研究环境温度
对铝网、玄武岩纤维布、 Kevlar纤维布防护结构高速撞击损伤与防护特性的影响。用于模拟空间碎片的铝球弹丸直径为3.97
mm,撞击速度为1.47~4.47km/s,撞击角度为0°,环境温度分别为293K和393K。结果表明:当撞击条件相同时,在较
髙环境温度中,单防护屏结构的编织物防护屏及填充式结构的编织物填充层的撞击穿孔尺寸均增大,三种编织物单防护屏结
构的高速撞击防护能力下降,铝网及玄武岩纤维布填充式结构的高速撞击防护性能降低, Kevlar纤维布填充式结构的高速撞
击防护性能提高。
关键词:高速撞击;温度;编织物防护屏;损伤;空间碎片
中图分类号:O347;V423
Experimental Investigation of Woven Bumper Shield Impacted by a
High-velocity Aluminum Sphere at Different Ambient Temperature
GUAN Gongshun PU Dongdong HA Yue PANG Baojun
(School of Astronautics, Harbin Institute of Technology, Harbin 150080
Abstract: A two-stage light gas gun is used to launch 2017-T4 Al-sphere projectiles impacting on single-wall bumper shield and
stuffed bumper shield of woven at two kinds of ambient temperature. The effect of ambient temperature on damage and protection
characteristic of Al-mesh, Basalt fiber cloth and Kevlar fiber cloth bumpers are studied. The diameter of projectile used to simulate
space debris is 3.97 mm. Impact velocities of Al-spheres are varied between 1 47 km/s and 4.47 km/s. The impact angle is 0
Ambient temperatures are 293 K and 393 K respectively. The results indicated that perforation size of woven bumper of single-wall
bumper shield and woven stuffed wall of stuffed bumper shield increased at higher ambient temperature for the same impact
condi. At the same time, the pro ion performance of all single-wall bumper shields of three woven bumpers degraded alon
with the rising of the ambient temperature, the protection performance of Al-mesh, Basalt fiber cloth stuffed bumper shields degraded
and the protection performance of Kevlar fiber cloth stuffed bumper shield enhanced at higher ambient temperature
Key words: high-velocity impact; temperature; woven bumper; damage; space debris
并不均匀,不同部位的温度相差很大。高温将引起
0前言
材料的快速热老化,低温将使材料变颱而易于断
裂的,频繁的热循环作用还会造成结构材料的破坏
高真空、高低温交变、强辐射、微重力和等离与解体?。用于抵御空间碎片高速撞击的防护结构
子体等空间环境因素将会引起航天器结构及防护材通常处于航天器的最外层,直接暴露于空间环境
料的力学、物理、化学性能的变化。在轨运行航中,因此,防护材料表面温度变化较为剧烈。在如
天器所处的空间温度环境较为恶劣,在太阳直射面,此恶劣的空间温度环境中,防护材料及结构的性能
航天器表面温度高达200℃,而在地球阴影面,温将会受到很大影响。本文主要以编织物及其填
度会急剧降低至-180℃。同时,航天器的表面温度充式结构为研究对象,采用高速撞击试验的方法,
研究其在不同环境温度下的高速撞击特性,分析温
?国家白然科学基金(17208和小型航天器技术国防重点学科实验度对编织物及其填充式结构高速撞击损伤及防护特
室开放基金( IIT. KLOF MST,2012008)资助项目。20140421收到初稿
20141209收到修改稿
性的影响