开口尺寸和铺层比例对复材层合板压缩性能的影响

杨钧超; 邓凡臣; 柴亚南

doi:10.11868/j.issn.1005-5053.2020.000002

开口尺寸和铺层比例对复材层合板压缩性能的影响

doi: 10.11868/j.issn.1005-5053.2020.000002

杨钧超^{1, 2, ,},
邓凡臣^{1, 2},
柴亚南^{1, 2}

1.
中国飞机强度研究所复合材料结构强度研究室, 西安 710065
2.
全尺寸飞机结构静力/疲劳航空科技重点实验室, 西安 710065

基金项目: 民机科研项目(MJ-2015-F-038)

详细信息

通讯作者:
杨钧超（1991—），男，硕士，工程师，主要从事复合材料结构强度分析及实验验证工作。联系地址：陕西省西安市雁塔区电子二路86号（710065），E-mail：JCyang@buaa.edu.cn

中图分类号: V258
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- 被引次数: 0
出版历程
- 收稿日期: 2020-01-09
- 录用日期: 2022-09-06
- 修回日期: 2022-10-15
- 刊出日期: 2022-12-02

Effects of opening size and layering ratio on compression properties of composite laminates

YANG Junchao^{1, 2
, ,},
DENG Fanchen^{1, 2},
CHAI Yanan^{1, 2}

1.
Structural Strength Laboratory of Composite Materials, Aircraft Strength Research Institute of China, Xi’an 710065, China
2.
Aeronautics Science and Technology Key Laboratory of Full Scale Aircraft Structure and Fatigue, Xi’an 710065, China

摘要

摘要: 为研究开口尺寸和铺层比例对复材层合板压缩性能的影响，对三种开口尺寸和铺层的复合材料层合板进行压缩实验，并采用电阻应变计测量开口区应变。结果表明：开口尺寸越大，0°层比例越低，孔边应变水平越高，而应变分布梯度更小，从而大开口复合材料层合板的压缩强度值越低。随后，基于Puck失效准则，建立大开口复合材料层合板的渐进损伤分析模型，对层合板压缩失效过程进行模拟。数值模拟得到的孔边应变分布以及压缩强度与实验结果吻合良好，建立的数值分析模型能够比较有效地预测含大开口的复合材料层合板的压缩性能。
- 复合材料层合板 /
- 大开口 /
- 铺层比例 /
- 开口尺寸 /
- 压缩强度
Abstract: In order to study the effect of opening size and layering ratio on the compression performance, the compression experiments of composite laminates with three opening sizes and ply were carried out. The strains near the opening area were measured by resistance strain gauges. The experimental results show that the larger the opening size, the lower the 0° layer ratio, the higher the strain level at the hole edge, and the smaller the strain distribution gradient, thus the lower the compressive strength of composite laminates with large openings. Then, based on the Puck failure criterion, a progressive damage analysis model of large-opening composite laminates was established to simulate the compression failure process of laminates. The compressive strength and the strain distribution of the hole edge obtained by numerical simulations are in good agreement with the experimental results. The numerical analysis model can effectively predict the compression performance of composite laminates with large openings.
- composite laminate /
- large openings /
- layering ratio /
- opening size /
- compressive strength

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图 1 大开口复合材料层合板尺寸及应变片位置示意图

Figure 1. Dimensions of large-opening composite laminates and locations of strain gauges

下载: 全尺寸图片幻灯片

图 2 横向应力和剪应力组合作用下基体断裂面示意图

Figure 2. Fracture plane under combined transverse and shear stress

下载: 全尺寸图片幻灯片

图 3 大开口复合材料层合板数值模型

Figure 3. Numerical model of composite laminates with large openings

下载: 全尺寸图片幻灯片

图 4 不同开口尺寸、铺层的的层合板孔边应变-应力曲线　（a）铺层A，d=2 mm；（b）铺层A，d=10 mm；（c）铺层B，d=2 mm；（d）铺层B，d=10 mm；（e）铺层C，d=2 mm；（f）铺层C，d=10 mm

Figure 4. Strain-stress curves at the orifice edges of laminated plates with different opening sizes and layer　 (a) layer A，d=2 mm；(b) layer A，d=10 mm；(c) layer B，d=2 mm；(d) layer B，d=10 mm；(e) layer C，d=2 mm；(f) layer C，d=10 mm

下载: 全尺寸图片幻灯片

图 5 层合板孔边应变随孔边距d的变化曲线（$ \sigma = - 100\;{\text{MPa}} $）　（a）铺层A，开口尺寸不同；（b）铺层不同，D=75 mm

Figure 5. Variation curve of hole edge strain of laminated plate with hole margin d ($ \sigma = - 100\;{\text{MPa}} $)　 (a)layer A with different opening sizes；(b)different layer，D=75 mm

下载: 全尺寸图片幻灯片

图 6 不同开口尺寸和铺层的复合材料层合板破坏形貌　（a）铺层A，D=25.4 mm；（b）铺层A，D=50 mm；（c）铺层A，D=75 mm；（d）铺层B，D=25.4 mm；（e）铺层B，D=50 mm；（f）铺层B，D=75 mm；（g）铺层C，D=25.4 mm；（h）铺层C，D=50 mm；（i）铺层C，D=75 mm；

Figure 6. Failure morphology of composite laminates with different opening sizes and lamination 　(a) layer A，D=25.4 mm；(b) layer A，D=50 mm；(c) layer A，D=75 mm；(d) layer B，D=25.4 mm；(e) layer B，D=50 mm；(f) layer B，D=75 mm；(g) layer C，D=25.4 mm；(h) layer C，D=50 mm；(i) layer C，D=75 mm；

下载: 全尺寸图片幻灯片

图 7 大开口复合材料层合板各单层损伤状态（铺层A）　（a）D=25.4 mm，纤维损伤；（b）D=25.4 mm，纤维间损伤；（c）D=75 mm，纤维损伤；（d）D=75 mm，纤维间损伤

Figure 7. Damage status of each single layer of composite laminates with large openings (layer A) 　(a) D=25.4 mm，FF；(b) D=25.4 mm，IFF；(c) D=75 mm，FF；(d) D=75 mm，IFF

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表 1 M21C/IMA性能参数

Table 1. Properties parameters of M21C/IMA

E₁/MPa	E₂/MPa	G₁₂/MPa	ν₁₂	X_T/MPa	X_C/MPa	Y_T/MPa
166000	8110	4140	0.319	2900	1140	70.5

Y_C/MPa	S_L/MPa	E_F/MPa	ν_12F	β/MPa⁻³	G_2C/(N·mm⁻¹)	G_12C/(N·mm⁻¹)
280	172	225000	0.2	1.4e⁻⁸	0.8	3.5

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表 2 大开口复合材料层合板试件尺寸及数量

Table 2. Size and number of experimental pieces of large-open composite laminates

Layer	h/mm	L/mm	W/mm	D/mm	L₁/mm	Number
A/B/C	7.64	150	100	25.4	10	3
		310	150	50	50	3
		340	180	75	50	3

下载: 导出CSV

表 3 大开口层合板压缩强度预测值与实验结果对比

Table 3. Comparison of predicted compression strength of large open laminates with experimental results

Layer	D/mm	Test strength/MPa	CV/%	Predicted strength/MPa	Error/%
A	25.4	274	2.28	237	−13.5
	50	203	1.42	204	0.493
	75	174	5.78	173	−0.575

B	25.4	240	2.45	212	−11.7
	50	201	1.02	184	−8.46
	75	163	3.30	166	1.84

C	25.4	227	1.18	202	−11.0
	50	173	1.56	171	−1.16
	75	149	4.22	145	−2.69

下载: 导出CSV

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