筋条形状对复合材料加筋壁板低速冲击动态响应的影响

丁铁; 张晓晴; 姚小虎

doi:10.11858/gywlxb.2017.06.012

筋条形状对复合材料加筋壁板低速冲击动态响应的影响

doi: 10.11858/gywlxb.2017.06.012

华南理工大学土木与交通学院工程力学系，广东广州 510640

基金项目:

国家自然科学基金 11472110

国家自然科学基金 11372113

国家自然科学基金 11472100

华南理工大学中央高校专项资金 2015ZP042

广东省普通高校特色创新项目 2014ktscx015

爆炸科学与技术国家重点实验室开放基金 KFJJ15-20M

详细信息

作者简介:
丁铁(1991—), 男，硕士研究生，主要从事复合材料与冲击动力学研究.E-mail:ctd.tie@mail.scut.edu.cn

通讯作者:
姚小虎(1974—), 男，教授，博士生导师，主要从事复合材料与冲击动力学研究.E-mail:yaoxh@scut.edu.cn

中图分类号: O347.3;V214.8
计量
- 文章访问数: 7352
- HTML全文浏览量: 2983
- PDF下载量: 169
出版历程
- 收稿日期: 2017-01-11
- 修回日期: 2017-03-29

Effect of Stiffener Shape on Low-Velocity Impact Behavior of Composite Stiffened Panels

Department of Engineering Mechanics, School of Civil Engineering and Transportation, South China University of Technology, Guangzhou 510640, China

摘要

摘要: 针对复合材料加筋壁板的抗冲击问题，着重考虑筋条形状对其冲击动态响应的影响。通过局部细化的方法分别建立T型、工字型和帽型筋条的复合材料加筋壁板的有限元分析模型，采用黏结接触模拟层与层之间的界面，分析了3种筋条形状的复合材料加筋壁板在低速冲击下的动态响应和损伤情况。根据数值计算结果发现：结构的动态响应与冲击位置的刚度密切相关，T型和工字型筋条复合材料加筋壁板在冲击位置以外的区域发生翘曲；此时T型和工字型筋条的基体拉伸损伤不仅形状相似，而且损伤面积相近；蒙皮与筋条界面相邻两层的铺层角影响分层损伤的面积。
- 复合材料加筋壁板 /
- 低速冲击 /
- 分层损伤 /
- 动态响应
Abstract: In this research, we focused on the effect of the stiffener shape on the dynamic response of composite stiffened panels.We first established the finite element analysis model for composited stiffened structures with 3 kinds of stiffeners using the local refinement with the interface between the layers simulated by bonding interface, and then analyzed the dynamic response and the delamination damage of these composite stiffened panels.According to the results of the numerical simulation, it is found that the dynamic response is closely related to the structure stiffness, the composite stiffened panels with T-shaped and I-shaped stiffeners are warped in the region beyond the impacted part of the panels, and their damage distribution and damage area are similiar.The results also show that the layer angle of the two layers adjacent to the surface of the skin and the stiffener affects the area of the delamination damage.
- composite stiffened panel /
- low-velocity impact /
- delamination damage /
- dynamic response

HTML全文

图 1 层内损伤模型

Figure 1. Intralaminar damage model

下载: 全尺寸图片幻灯片

图 2 数值模拟所得冲击力时程曲线与实验数据的比较

Figure 2. comparison of impact force time-history between numerical and experimental results

下载: 全尺寸图片幻灯片

图 3 复合材料加筋壁板尺寸示意(单位：mm)

Figure 3. Configuration of composite stiffened panel (Unit:mm)

下载: 全尺寸图片幻灯片

图 4 复合材料加筋壁板模型细节

Figure 4. Details of composite stiffened panel model

下载: 全尺寸图片幻灯片

图 5 复合材料加筋壁板的冲击力时程

Figure 5. Impact force versus time of composite stiffened panels

下载: 全尺寸图片幻灯片

图 6 复合材料加筋壁板的位移时程

Figure 6. Displacement versus time of composite stiffened panels

下载: 全尺寸图片幻灯片

图 7 复合材料加筋壁板沿路径DI上点的位移

Figure 7. Displacements along path DI of composite stiffened panel

下载: 全尺寸图片幻灯片

图 8 工字型筋条复合材料加筋壁板的有限元模型

Figure 8. Finite element model of I-shaped stiffened panel

下载: 全尺寸图片幻灯片

图 9 复合材料加筋壁板蒙皮的基体拉伸损伤(1、15、17、19、20为铺层序号)

Figure 9. Skin's matrix tensile damage of composite stiffened panel (1, 15, 17, 19, 20 are ply numbers)

下载: 全尺寸图片幻灯片

图 10 复合材料加筋壁板筋条的基体拉伸损伤(1、2、3、5、9为铺层序号)

Figure 10. Stiffener's matrix tensile damage of composite stiffened panel (1, 2, 3, 5, 9 are ply numbers)

下载: 全尺寸图片幻灯片

图 11 复合材料加筋壁板蒙皮的基体拉伸损伤分布

Figure 11. Distribution of skin's matrix tensile damage of composite stiffened panels

下载: 全尺寸图片幻灯片

图 12 蒙皮与筋条间的分层损伤

Figure 12. Delamination damage between skin and stiffener

下载: 全尺寸图片幻灯片

图 13 不同复合材料加筋壁板筋条铺层之间的分层损伤对比

Figure 13. Comparison of delamination damage between stiffener's plies of different composite stiffened panels

下载: 全尺寸图片幻灯片

表 1 复合材料单层材料参数^[12]

Table 1. Material properties of composite^[12]

Elastic modulus				Shear modulus					Poisson's ratio
E₁₁/(GPa)	E₂₂/(GPa)	E₃₃/(GPa)		G₁₂/(MPa)	G₁₃/(MPa)	G₂₃/(MPa)			ν₁₂	ν₁₃	ν₂₃
145	10.3	12.1		5 300	5 275	3 950			0.301	0.5	0.495

Strength							Fracture energy
X^T/(MPa)	X^C/(MPa)	Y^T/(MPa)	Y^C/(MPa)		S₁₂/(MPa)		G_1C^t/(N/mm)	G_1C^c/(N/mm)		G_2C^t/(N/mm)	G_2C^c/(N/mm)
2 000	1 600	64	290		98		12.5	12.5		1	1

下载: 导出CSV

参考文献(12)

[1]	ROESELER W G, SARH B, KISMARTON M U, et al.Composite structures-the first 100 years[C]//16th International Conference on Composite Materials, 2007.
[2]	CHOI H Y, CHANG F K.A model for predicting damage in graphite/epoxy laminated composites resulting from low-velocity impact[J].J Compos Mater, 1992, 26(14):2134-2169. doi: 10.1177/002199839202601408
[3]	朱炜垚, 许希武.复合材料层合板低速冲击损伤的有限元模拟[J].复合材料学报, 2010, 27(6): 200-207. http://www.wanfangdata.com.cn/details/detail.do?_type=perio&id=QK201002862699 ZHU W Y, XU X W.Finite element simulation of low velocity impact damage on composite laminates[J].Acta Materiae Compositae Sinica, 2010, 27(6): 200-207. http://www.wanfangdata.com.cn/details/detail.do?_type=perio&id=QK201002862699
[4]	王一飞, 张晓晶, 汪海.复合材料层压板低速冲击响应与损伤参数关系研究[J].固体力学学报, 2013, 34(1):63-72. doi: 10.3969/j.issn.0254-7805.2013.01.009 WANG Y F, ZHANG X J, WANG H.Energy and contact force study of composite laminate impact damage response[J].Chinese Journal of Solid Mechanics, 2013, 34(1):63-72. doi: 10.3969/j.issn.0254-7805.2013.01.009
[5]	赵维涛, 杨其蛟, 刘炜华.复合材料加筋板低速冲击响应分析[J].沈阳航空航天大学学报, 2015, 32(3): 1-5. doi: 10.3969/j.issn.2095-1248.2015.03.001 ZHAO W T, YANG Q J, LIU W H.Analysis on the low-velocity impact response of stiffened composite panels[J].Journal of Shenyang Aerospace University, 2015, 32(3): 1-5. doi: 10.3969/j.issn.2095-1248.2015.03.001
[6]	FOUND M S, HOWARD I C, PARAN A P.Impact perforation of thin stiffened CFRP panels[J].Compos Struct, 2000, 48(1/2/3):95-98. http://www.wanfangdata.com.cn/details/detail.do?_type=perio&id=CC026031071
[7]	FOUND M S, HOWARD I C, PARAN A P.Impact behaviour of stiffened CFRP sections[J].Compos Struct, 1997, 39(3/4):229-235. http://www.sciencedirect.com/science/article/pii/S0263822397001177
[8]	WIGGENRAAD J F M, ZHANG X, DAVIES G A O.Impact damage prediction and failure analysis of heavily loaded, blade-stiffened composite wing panels[J].Compos Struct, 1999, 45(2):81-103. doi: 10.1016/S0263-8223(98)00132-9
[9]	HASHIN Z, ROTEM A.A fatigue failure criterion for fiber reinforced materials[J].J Compos Mater, 1973, 7(4):448-464. doi: 10.1177/002199837300700404
[10]	BENZEGGAGH M L, KENANE M.Measurement of mixed-mode delamination fracture toughness of unidirectional glass/epoxy composites with mixed-mode bending apparatus[J].Compos Sci Technol, 1996, 56(4):439-449. doi: 10.1016/0266-3538(96)00005-X
[11]	GREENHALGH E, MEEKS C, CLARKE A, et al.The effect of defects on the performance of post-buckled CFRP stringer-stiffened panels[J].Compos Part A:Appl Sci Manuf, 2003, 34(7):623-633. doi: 10.1016/S1359-835X(03)00098-8
[12]	孙晶晶, 张晓晶, 宫占峰, 等.复合材料帽型筋条脱粘的失效机理分析[J].航空学报, 2013, 34(7):1616-1626. http://d.old.wanfangdata.com.cn/Periodical/hkxb201307013 SUN J J, ZHANG X J, GONG Z F, et al.Failure mechanism study on omega stringer debonding[J].Acta Aeronautica et Astronautica Sinica, 2013, 34(7):1616-1626. http://d.old.wanfangdata.com.cn/Periodical/hkxb201307013