压剪载荷下复合材料层合板的失效模式

骈瑢; 杨帆; 章凌; 刘丰睿; 王林娟; 赵丽滨

doi:10.13700/j.bh.1001-5965.2024.0084

压剪载荷下复合材料层合板的失效模式

doi: 10.13700/j.bh.1001-5965.2024.0084

骈瑢^{1, 2},
杨帆³,
章凌³,
刘丰睿^{1, 2, ,},
王林娟^{1, 2},
赵丽滨^{4, 5, 6}

1.
北京航空航天大学宇航学院，北京 100191
2.
北京航空航天大学航天器设计优化与动态模拟技术教育部重点实验室，北京 100191
3.
北京宇航系统工程研究所，北京 100076
4.
河北工业大学机械工程学院，天津 300401
5.
先进智能防护装备技术教育部重点实验室，天津 300401
6.
河北省跨尺度智能装备技术重点实验室，天津 300401

基金项目:

国家自然科学基金(12072005,U23A2067)；河北省全职引进高端人才科研项目(2021HBQZYCSB009)

详细信息

通讯作者:
E-mail：frliu@buaa.edu.cn

中图分类号: TB332
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出版历程
- 收稿日期: 2024-02-07
- 录用日期: 2024-05-10
- 网络出版日期: 2024-05-17
- 整期出版日期: 2026-04-30

Failure mode of composite laminated plates under compression-shear loading

PIAN Rong^{1, 2},
YANG Fan³,
ZHANG Ling³,
LIU Fengrui^{1, 2
, ,},
WANG Linjuan^{1, 2},
ZHAO Libin^{4, 5, 6}

1.
School of Astronautics，Beihang University，Beijing 100191，China
2.
Key Laboratory of Spacecraft Design Optimization and Dynamic Simulation Technologies，Ministry of Education，Beihang University，Beijing 100191，China
3.
Beijing Institute of Astronautical Systems Engineering，Beijing 100076，China
4.
School of Mechanical Engineering，Hebei University of Technology，Tianjin 300401，China
5.
Key Laboratory of Advanced Intelligent Protective Equipment Technology，Ministry of Education，Tianjin 300401，China
6.
Key Laboratory of Hebei Province on Scale-pan Intelligent Equipment Technology，Tianjin 300401，China

Funds:

National Natural Science Foundation of China (12072005,U23A2067); Project of High-Level Talents Introduction of Hebei Province (2021HBQZYCSB009)

More Information

Corresponding author: E-mail：frliu@buaa.edu.cn

摘要

摘要:
复合材料层合板是飞行器中的重要承载结构，在压剪载荷作用下会发生屈曲或静力失效。采用复合材料层合板线性屈曲和首层失效的理论分析方法，对碳纤维/环氧树脂层合板在不同压剪载荷比、边长比、边长厚度比和铺层角度下开展失效分析，得到2种失效出现的顺序和失效载荷的变化情况。结果表明:在不同的压剪载荷比下，层合板屈曲和首层失效发生的顺序不同；2种失效发生的压剪载荷比范围会受到层合板边长比、边长厚度比和铺层角度的影响；屈曲模态主要受压剪载荷比、边长比和铺层角度的影响，首层失效模式主要受压剪载荷比和铺层角度的影响。
- 复合材料层合板 /
- 失效分析 /
- 屈曲 /
- 首层失效 /
- 压剪载荷
Abstract:
Under compressive and shear pressures, composite laminates, which are crucial load-bearing components in airplanes, are vulnerable to buckling or overstress failure. In this paper, the theoretical analysis methods for buckling and first-ply-failure were adopted to predict the failure of composite laminated plates. The investigation was carried out on graphite/epoxy plates, with different load ratios, side length ratios, side length-thickness ratios, and lay-up angles. Two failure categories’ occurrence sequence as well as the failure loads’ variance were found. It is revealed that buckling and first-ply-failure occur in different orders under various load ratios. The load ratio ranges corresponding to buckling and first-ply-failure are affected by the side length ratio, side length-thickness ratio, and lay-up angle of the plate. The buckling mode is primarily influenced by the load ratio, side length ratio and lay-up angle, while the first-layer-failure mode is mainly affected by the load ratio and lay-up angle.
- composite laminated plate /
- failure analysis /
- buckling /
- first-ply failure /
- compression-shear loading

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图 1 层合板结构示意图

Figure 1. Schematic diagram of the laminated plate

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图 2 失效分析结果示意图

Figure 2. Schematic diagram of the failure analysis results

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图 3 不同边长比时层合板的失效曲线对比

Figure 3. Comparison of failure curves for laminated plates with different side length ratios

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图 4 不同边长厚度比时层合板的失效曲线对比

Figure 4. Comparison of failure curves for laminated plates with different side length-to-thickness ratios

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图 5 不同铺层角度时层合板的失效曲线对比

Figure 5. Comparison of failure curves for laminated plates with different layering angle

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表 1 参数影响研究算例设计

Table 1. Design of the parametric impact study cases

组号	算例编号	长度a/mm	宽度b/mm	总厚度/mm	铺层顺序
1	C1～C5	50	150,60,50,40,30	1	[±45]_s
2	C1,C6～C8	60,50,40,30	60,50,40,30	1	[±45]_s
3	C1,C9～C12	50	50	1	[0]₄, [±30]_s, [±45]_s, [±60]_s, [90]₄

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表 2 碳纤维/环氧树脂材料性能参数

Table 2. Performance parameters of the graphite/epoxy material

E₁/GPa		E₂/GPa		v₁₂		G₁₂/GPa
148		9.65		0.3		4.55

X_T/MPa	X_C/MPa		Y_T/MPa		Y_C/MPa		S₁₂/MPa
1314	1220		43		168		48

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表 3 不同边长比时层合板的失效模式对比

Table 3. Comparison of failure modes for laminated plates with different side length ratios

边长比	$ \eta $范围			失效模式
边长比	分段①	分段②	分段③	分段①	分段②	分段③
3	(−∞,7.08)	(7.08,+∞)		(1,1)屈曲	(1,2)屈曲
1.2	(−∞,+∞)			(1,1)屈曲
1.0	(−∞,−2.25)	(−2.25,−0.08)	(−0.08,+∞)	(1,1)屈曲	纤基剪切	(1,1)屈曲
0.8	(−∞,−4.00)	(−4.00,0.71)	(0.71,+∞)	(1,1)屈曲	纤基剪切	(1,1)屈曲
0.6	(−∞,−5.08)	(−5.08,1.70)	(1.70,+∞)	基体拉伸	纤基剪切	(1,1)屈曲
注：“(1,2)屈曲”表示屈曲模态在$ x $和$ y $方向的半波数分别为1和2。

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表 4 不同边长厚度比层合板的失效模式对比

Table 4. Comparison of failure modes for laminated plates with different side length-to-thickness ratios

边长厚度比	$ \eta $范围			失效模式
边长厚度比	分段①	分段②	分段③	分段①	分段②	分段③
60	(−∞,+∞)			(1,1)屈曲
50	(−∞,−2.25)	(−2.25,−0.08)	(−0.08,+∞)	(1,1)屈曲	纤基剪切	(1,1)屈曲
40	(−∞,−5.08)	(−5.08,0.89)	(0.89,+∞)	基体拉伸	纤基剪切	(1,1)屈曲
30	(−∞,−5.08)	(−5.08,2.76)	(2.76,+∞)	基体拉伸	纤基剪切	(1,1)屈曲

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表 5 不同铺层角度时层合板的失效模式对比

Table 5. Comparison of failure modes for laminated plates with different layering angle

铺层角度θ/(°)	$ \eta $范围					失效模式
铺层角度θ/(°)	分段①	分段②	分段③	分段④	分段⑤	分段①	分段②	分段③	分段④	分段⑤
0	(−∞,−0.95)	(−0.95,0.95)	(0.95,+∞)			纤基剪切	(1,1)屈曲	纤基剪切
30	(−∞,+∞)					(1,1)屈曲
45	(−∞,−2.25)	(−2.25,−0.08)	(−0.08,+∞)			(1,1)屈曲	纤基剪切	(1,1)屈曲
60	(−∞,−4.27)	(−4.27,−1.49)	(−1.49,−0.42)	(−0.42,0.83)	(0.83,+∞)	(1,1)屈曲	纤基剪切	基体压缩	(2,1)屈曲	(1,1)屈曲
90	(−∞,<−10³)	(<−10³,−1.88)	(−1.88,1.88)	(1.88,>10³)	(>10³,+∞)	基体压缩+纤基剪切	基体压缩	(2,1)屈曲	基体压缩	基体压缩+纤基剪切

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