超高速撞击航天器二次碎片云能量特性分析

贾光辉; 黄海

超高速撞击航天器二次碎片云能量特性分析

贾光辉,
黄海

北京航空航天大学宇航学院, 北京 100083

基金项目: 中国博士后科学基金资助项目(2004035267); T John D. and Catheri ne T. MacArthur Foundation (05-85102-000-GSS)

详细信息

作者简介:
贾光辉(1966-),男,山西新绛人,副教授,jiaguanghui @b uaa.edu.cn.

中图分类号: V 414
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出版历程
- 收稿日期: 2006-04-18
- 网络出版日期: 2007-03-31

Characters on kinetics energy of debris cloud in spacecraft

School of Astronautics, Beijing University of Aeronautics and As tronautics, Beijing 100083, China

摘要

摘要: 为了评估空间碎片超高速撞击航天器的碎片云破坏能力,挖掘超高速撞击数值模拟结果数据的应用价值,基于9.53 mm铝球以6.64 km/s速度对2.2 mm铝靶撞击的Ls-Dyna/SPH(Smoothed Particle Hydrodynamic)数值模拟研究结果,对靶后碎片云的粒子动能进行求和统计,建立了碎片云比动能概念和函数形式;碎片云比动能综合考虑了靶后所有碎片云粒子的动能,反映了一定距离处垂直于撞击方向平面上单位面积上的碎片云粒子所蕴含的撞击能量;应用碎片云比动能概念,揭示出随着演化距离的增加,碎片云能量的衰减规律;通过不同速度条件下的SPH计算,得到了碎片云的比动能函数的曲线形式随撞击速度的变化规律;最后对采用2种材料模型进行数值模拟所对应的结果误差进行碎片云比动能函数的曲线比较,反映出数值模拟中不同材料模型引起的差异.
- 碎片 /
- 航天器 /
- 穿透 /
- 数值模拟 /
- 材料模型
Abstract: To assess damage by debris cloud after orbital debris impacts and perforates pla te of spacecraft, and to use adequately LS-dyna/SPH(Smoothed Particle Hydrodyna mic) computer simulation result of the orbital debris hypervelocity impacting th e plate, depending on the result about 9.53mm aluminium sphere impacting 2 .2mm aluminium target at 6.64km/s, debris cloud kinetic energy per area (DCP KE) and DCPKE formula was put forwarded after statistically cumulating of debris particles behind plate. DCPKE includes kinetic energy of all particles in debri s cloud and define the damage ability in area of plane behind spacecraft plate perpendicular to the impacting direction. DCPKE can be used to describe rule of debris cloud kinetic energy, which decrease with the distance. Depending on co mputer simulation of several impact velocity cases, the DCPKE curves were gained to show difference of impact velocities. DCPKE was also used to analyze materia l strength model influence, it can show quantificationally difference betwee n two material models.
- debris /
- spacecraft /
- perforating /
- computer simulation /
- strength of materials

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参考文献(1)

[1] Inter-Agency Space Debris Coordination Committee. Prot ection manual . IADC-04-03,2004 [2] Lacerda D, Lacome J. Simulations of hypervelocity impacts with smoothed particle hydrodynamics . DYNAUS Report, 2003 [3] Faraud M, Destefanis R, Palmieri D, et al. SPH simulations o f debris impacts using two different computer codes[J]. International Journal of Impact Engineering, 1999, 23:249-260 [4] 贾光辉,空间碎片超高速撞击飞行器数值模拟应用研究 . 北京:北京航空航天大学宇航学院,2005 Jia Guanghui. Application study on computer simulation of fragment impacting s pacecrafts . Beijing:School of Astronautics, Beijing University of Aeronauti cs and Astronautics, 2005(in Chinese) [5] Cour-Palais B G, Crews J L. A multi-shock concept for spacecraf t shielding[J]. International Journal of Impact Engineering, 1990,10:135-146 [6] Michel L, Frank S, Tobias G. Impact damage on sandwich panels and mul ti-layer insulation[J]. International Journal of Impact Engineering, 2001, 26:369-380

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