Effect of tension damage on structures residual compression strength of open-hole composite laminates
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摘要: 通过试验和数值分析相结合的方式，探究含孔复合材料层合板拉伸损伤对其剩余压缩强度和失效模式的影响。试验方面，首先，通过开孔复合材料层合板拉伸试验引入两种程度的拉伸损伤，使用热揭层方法表征和量化其拉伸损伤程度。随后，开展含拉伸损伤的开孔复合材料层合板压缩试验，记录其载荷-位移曲线，并通过数字图像相关法(DIC)、应变片、微距相机等手段观察其变形和损伤演化特征。数值分析方面，构建基于LaRC失效准则的渐进损伤失效模型描述层内损伤演化，使用内聚力单元方法刻画复合材料层间分层损伤，基于此模型探究了开孔复合材料层合板损伤扩展规律。试验结果表明：拉伸载荷引起的孔边复合材料损伤以基体裂纹和分层损伤为主，在加载方向和纤维朝向夹角较小的层间，分层损伤程度更大。拉伸损伤会进一步加剧孔周应变集中，使孔邻域应变呈非对称，导致结构局部屈曲更早地发生，进而诱发结构整体破坏，相对于不含拉伸损伤开孔板，含拉伸损伤开孔板可使结构压缩承载能力下降25.8%。构建的数值计算模型可以准确预测拉伸载荷下孔周剪切应力引起的分层损伤和压缩阶段应变域场演化特征，也可揭示含不同程度拉伸损伤的开孔板压缩损伤扩展模式差异及探究纤维弯折失效、基体损伤和层间分层对结构承载能力的影响规律，为复合材料开孔板在变载荷作用下结构设计与剩余强度的确定提供支撑。Abstract: The influence of tension damage on residual compression strength and failure mode of open-hole composite laminates was investigated by tests and numerical analysis. In terms of test, firstly, two degrees of tension damage were introduced through the tension test of open-hole composite laminates, and the degree of tension damage was characterized and quantified by the thermal decal method. Then, the compression test of open-hole composite laminates with tension damage was carried out, the load-displacement curve was recorded. The damage evolution characteristics were observed by digital imaging correlation (DIC), strain gauge, macro camera and other means. In terms of numerical analysis, a progressive damage failure model based on LaRC failure criteria was constructed to describe the intralaminar damage evolution, and cohesive elements method was established to describe the interlaminar damage of composite materials. Based on this model, the damage expansion law of open-hole composite laminates was explored. The experimental results show that the damage caused by tensile load is mainly matrix crack and delamination damage, and the delamination damage is greater between layers with small angle between loading direction and fiber direction. Tension damage will further aggravate the strain concentration around the hole, resulting in an asymmetric strain in the neighboring region of the hole, leading to the local buckling of the structure earlier, and then inducing the overall failure of the structure. Compared with the open-hole composite laminates without tension damage, the open-hole composite laminates with tension damage can reduce the compressive bearing capacity of the structure by 25.8%. The constructed numerical calculation model can accurately predict the delamination damage caused by the shear stress around the hole under tensile load and the evolution characteristics of the strain field in the compression stage, and can also reveal the difference in the compression damage expansion mode of the open-hole composite laminates with different degrees of tension damage, and explore the effects of fiber bending failure, matrix damage and interlayer delamination on the structural bearing capacity. This work can provide support for structural design and determination of residual strength of open-hole composite laminates under varying loading.
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图 3 (a) 热压罐；(b) 浸没式超声C扫描无损检测设备
Figure 3. (a) Autoclave; (b) Immersed ultrasound C-scan nondestructive testing equipment
图 4 (a) 水刀切割机；(b) 钻孔设备
Figure 4. (a) Water jet cutting machine; (b) Drilling equipment
图 5 试验装置与拉压夹具：(a) 试验机；(b) 拉伸夹具；(c) 压缩夹具
Figure 5. Test device and fixture: (a) Testing machine; (b) Drawing fixtures; (c) Compression fixture
DIC—Digital imaging correlation; CCD—Charge coupled device
图 6 复合材料开孔板数值计算模型
Figure 6. Numerical calculation model of open-hole composite laminates
ux, uy, uz—Displacement in the direction x, y and z
图 7 不同孔周网格尺寸的孔周分布状态：(a) 0.6 mm；(b) 0.4 mm；(c) 0.33 mm；(d) 0.29 mm
Figure 7. Distribution of hole circumference with different hole circumference mesh sizes: (a) 0.6 mm; (b) 0.4 mm; (c) 0.33 mm; (d) 0.29 mm
图 8 开孔板单压缩承载极限与孔周网格尺寸关系
Figure 8. Relationship between compression load limit of the open-hole composite laminates and the mesh size around the hole
图 9 T-34 (a)与T-39 (b)拉伸导致的分层损伤热揭层结果
Figure 9. Delamination damage caused by T-34 (a) and T-39 (b) tensile heat stripping results
图 10 T-39拉伸阶段数值分析的应力、分层损伤状态
Figure 10. Numerical analysis of stress and stratified damage state of T-39 during tensile phase
图 11 T-0、T-34和T-39压缩加载试验载荷-位移曲线
Figure 11. Load-displacement curves of T-0, T-34 and T-39 in compressive load test
EXP—Experimental
图 12 T-0、T-34和T-39压缩极限载荷柱状图
Figure 12. T-0, T-34 and T-39 compressive limit load column diagram
图 13 开孔板压缩加载试验与数值计算载荷-位移曲线
Figure 13. Load-displacement curves of compression loading test and numerical calculation of open-hole composite laminates
FEM—Finite element method
图 14 T-0与T-39不同压缩载荷作用下DIC测量和数值计算的表面应变εyy和εxy结果
Figure 14. Surface strain εyy and εxy results of DIC and numerical calculations under different compressive loads for T-0 and T-39
图 15 T-0与T-39破坏前、后DIC监测应变状态
Figure 15. Strain state monitored by DIC before and after T-0 and T-39 destruction
图 16 T-0与T-39应变仪监测孔周应变变化
Figure 16. Circumferential strain changes of T-0 and T-39 holes monitored by strain gauges
图 17 T-0与T-39破坏前、后结构侧面损伤状态
Figure 17. Lateral damage state of the structure before and after T-0 and T-39 destruction
图 18 T-0与T-39压缩加载各阶段屈曲示意图
Figure 18. Schematic diagram of buckling at each stage of T-0 and T-39 compressive loading
表 1 拉伸后压缩试验工况列表
Table 1. List of post-tensile compression test conditions
Specimen group Type T-0 No tensile damage T-34
T-39Compression after stretching to 34 kN
Compression after stretching to 39 kN
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表 2 T700复合材料层合板材料参数
Table 2. Material parameters of T700 composite laminates
CFRP Density ρ1=1520 kg/m3 Module E11=117 GPa, E22=E33=7.5 GPa,
G12=G13=4.1 GPa, G23=2.3 GPaPoisson's ratio v12=v13=0.33, v23=0.3 Strength XT=2326 MPa, Xc=1236 MPa,
YT=51.0 MPa, Yc=209.0 MPa, S=87.9 MPaFracture energy Gf =182.1 N/mm, Gkink=97.4 N/mm,
$G_{{\rm{IC}}}^{\rm{m}} $=0.23 N/mm, $G_{{\rm{IIC}}}^{\rm{m}} $=0.79 N/mmCohesive element Density ρ2=1520 kg/m3 Module K1=K2=6×104 MPa/mm Strength N1=38.5 MPa, S1=T1=48.5 MPa Fracture energy GIC=0.23 N/mm,GIIC=0.79 N/mm Notes: E—Elastic modulus; G—Shear modulus; 1—Direction of fiber; 2—Direction of matrix; 3—Thickness direction of layer; XT—Fiber tensile strength; Xc—Fiber compressive strength; YT—Matrix tensile strength; Yc—Matrix compressive strength; S—In-plane shear strength; Gf—Fiber tensile fracture energy; Gkink—Fiber kinking energy; $G_{{\rm{IC}}}^{\rm{m}} $, $G_{{\rm{IIC}}}^{\rm{m}} $—Mode I and II fracture energies of matrix; K—Interface stiffness; N1—Normal strength; S1, T1—Transverse and longitudinal shear strength; GIC, GIIC—Interlaminar mode I and II fracture energies.
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表 3 开孔板压缩承载能力的误差分析
Table 3. Error analysis of compressive bearing capacity of open-hole composite laminates
Index Ultimate
load/kNAverage
value/kNStandard
deviation/kNVariation
coefficient/%T-0 32.2, 31.5,
33.9, 29.4,
30.531.5 1.71 5.4 T-34 30.3, 29.9,
31.4, 30.030.4 0.71 2.3 T-39 24.7, 23.4,
24.2, 26.4,
25.624.8 1.18 4.8
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