Design of composite winding joints
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摘要: 复合材料接头由于其轻质、高强及可设计性好等特点，被越来越多地运用于国外大型民用飞机的结构设计中。本文通过有限元建模，对一种新型的复合材料缠绕接头在拉伸和压缩载荷下的力学响应进行研究。主要围绕基础型、梭型和锥型三种典型的接头形式，比较了不同构型对缠绕接头力学性能的影响。结果表明，三种典型构型的复合材料缠绕接头均具有较好的极限载荷。在此基础上，研究了梭型和锥型构件的力学性能随斜角的变化，从而增加复合材料缠绕接头的应用方式，扩大复合材料缠绕接头的应用范围。Abstract: The composite joints are increasingly used in foreign civil large-scale aircraft due to their light weight, high strength and designable structure. This work focused on the mechanical behaviour of a newly designed composite wound joints under tension and compression using finite element modelling method. Three typical structures, i.e., basic configuration, shuttle configuration, cone configuration, were compared to get the influence of different configurations on the mechanical behaviour of composite joints. Results show that all three structures have satisfying strength. The slope angles of shuttle and cone configurations were furtherly studied to increase the application of composite wound joints.
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Key words:
- composite winding /
- chain link /
- inner ring /
- interface effectiveness /
- connection efficiency /
- design criteria
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图 1 基础型缠绕接头受拉/压构型示意图
Figure 1. Schematic diagrams of basic winding joint tension/compression configurations
图 2 基础型缠绕接头受拉构型结构形式
Figure 2. Basic winding joint tension configuration structure
D1—Diameter of the inner surface of inner ring; D2—Diameter of the outer surface of inner ring; L—Length of the laminate; Φ—Diameter of the laminate; W—Width of the joint
图 4 基础型缠绕接头受压构型尺寸
Figure 4. Compression configuration dimensions of basic winding joint
R—Chamfer
图 5 基础型缠绕接头受拉构型有限元模型约束加载示意图
Figure 5. Schematic diagram of constraint and load for finite element model of basic winding joint tension configuration
图 6 拉伸工况下基础型缠绕接头受拉构型载荷-位移曲线
Figure 6. Load-displacement curve of basic winding joint tension configuration under tensile condition
图 7 拉伸工况下基础型缠绕接头受拉构型链环损伤演化
Figure 7. Damage evolution of loop under tensile condition for basic winding joint tension configuration
图 8 压缩工况下基础型缠绕接头受拉构型载荷-位移曲线
Figure 8. Load-displacement curve of basic winding joint tension configuration under compression condition
图 9 压缩工况下基础型缠绕接头受拉构型损伤演化
Figure 9. Damage evolution of basic winding joint tension configuration under compression condition
图 10 基础型缠绕接头受压构型三维模型
Figure 10. 3D model of the basic winding joint compression configuration
图 11 基础型缠绕接头受拉构型和受压构型压缩工况下载荷-位移曲线对比
Figure 11. Comparison of load-displacement curves of basic winding joint tension configuration and compression configuration under compression
图 12 压缩工况下基础型缠绕接头受压构型损伤演化
Figure 12. Damage evolution of basic winding joint compression configuration under compression condition
图 14 梭型缠绕接头受拉构型三维模型
Figure 14. 3D model of shuttle winding joint tension configuration
图 16 梭型缠绕接头受拉构型各阶段载荷随α角变化的曲线
Figure 16. Curves of force changing with α angle of shuttle winding joint tension configuration at each stage
图 17 梭型缠绕接头受压构型三维模型
Figure 17. 3D model of shuttle winding joint compression configuration
图 19 压缩工况下模型SY-1~SY-5各损伤起始点随α角的变化
Figure 19. Changes of each damage starting point with α of model SY-1 - SY-5 under compression condition
图 21 锥型缠绕接头受拉/压构型X-Z平面示意图
Figure 21. X-Z plane diagram of tapered winding joint tension/compression configuration
图 22 锥型缠绕接头受拉构型三维模型
Figure 22. 3D model of tapered winding joint tension configuration
图 24 模型Z-1~Z-10各阶段载荷随α角变化的曲线
Figure 24. Changes of force with α angle of model Z-1–Z-10 at each stage
图 25 锥型缠绕接头受压构型三维模型
Figure 25. 3D model of tapered winding joint compression configuration
图 27 压缩工况下模型ZY-1~ZY-5各损伤起始点随α角的变化
Figure 27. Changes of each damage starting point with α angle of model ZY-1 - ZY-5 under compression condition
表 1 复合材料参数
Table 1. Composite material parameters
Property CCF300/BA9916-Ⅱ CF3031/BA9916-Ⅱ ${E_1}$/GPa 120 60 ${E_2}$/GPa 7.7 59 ${E_3}$/GPa 7.7 7.7 ${\nu _{12} } = {\nu _{13} } = {\nu _{23} }$ 0.05 0.27 ${G_{12}} = {G_{13}}$/GPa 5.5 6.4 ${G_{23}}$/GPa 5.5 6.4 ${X_{\rm{T}}}$/MPa 1 400 500 ${X_{\rm{C}}}$/MPa 1 300 450 ${Y_{\rm{T}}} = {Z_{\rm{T}}}$/MPa 35 450 ${Y_{\rm{C}}} = {Z_{\rm{C}}}$/MPa 160 455 ${S_{12}} = {S_{13}}$/MPa 163 105 ${S_{23}}$/MPa 86 83 Notes：Ei (i, j=1, 2, 3)—Elastic modulus in the direction of fibre, perpendicular to the fibre in the plane and out of plane; XT, YT and ZT—Tensile strength in the three directions above, respectively; XC, YC and ZC—Compress strength in the three directions above, respectively; νij, Gij and Sij (i, j=1, 2, 3)—Poisson’s ratio, shear modulus and shear strength for 1-2, 1-3, 2-3 plane, respectively. 
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表 2 J-116B结构胶材料参数
Table 2. Material parameters of J-116B
$E/{E_{{\rm{nn}}}}$/(MPa·mm−1) ${G_1}/{E_{{\rm{ss}}}}$/(MPa·mm−1) ${G_2}/{E_{{\rm{tt}}}}$/(MPa·mm−1) $t_{\rm{n}}^0$/MPa $t_{\rm{s}}^0$/MPa $t_{\rm{t}}^0$/MPa 1000 300 300 20 30 30 Notes：$E/{E_{{\rm{nn}}}}$, ${G_1}/{E_{{\rm{ss}}}}$ and ${G_2}/{E_{{\rm{tt}}}}$—Interface stiffness for three directions, respectively; $t_{\rm{n}}^0$, $t_{\rm{t}}^0$ and $t_{\rm{t}}^0$—Interface strength for three directions, respectively.
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表 3 梭型缠绕接头模型编号
Table 3. Model number of shuttle winding joint
Tension Compression Model Angle/(°) model Angle/(°) S-1 1 SY-1 2 S-2 2 SY-2 4 S-3 3 SY-3 6 S-4 4 SY-4 8 S-5 5 SY-5 10 S-6 6 S-7 7 S-8 8 S-9 9 S-10 10
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表 4 模型S-1~S-10各阶段载荷及对应位移
Table 4. Loads and corresponding displacements of model S-1 - S-10 at each stage
Stage Property S-1 S-2 S-3 S-4 S-5 S-6 S-7 S-8 S-9 S-10 Initial damage of interface Force/kN 10.92 11.15 11.31 11.48 11.65 11.81 11.97 12.09 12.20 12.32 Displacement/mm 0.30 0.30 0.30 0.30 0.30 0.30 0.30 0.30 0.30 0.30 Failure of interface Force/kN 34.96 35.46 35.78 36.10 36.42 36.62 36.87 37.05 37.19 37.35 Displacement/mm 1.40 1.40 1.40 1.40 1.40 1.40 1.40 1.40 1.40 1.40 Initial damage of chain link Force/kN 36.85 37.33 37.64 37.95 38.26 38.51 38.70 38.86 39.00 39.14 Displacement/mm 1.50 1.50 1.50 1.50 1.50 1.50 1.50 1.50 1.50 1.50 Failure of winding joint Force/kN 40.66 40.78 41.05 41.36 41.67 42.21 42.74 43.28 43.42 43.59 Displacement/mm 1.80 1.80 1.80 1.80 1.80 1.80 1.80 1.80 1.90 1.90
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表 5 压缩工况下模型SY-1~SY-5损伤起始点
Table 5. Damage starting points of model SY-1 - SY-5 under compression condition
Stage Property SY-1 SY-2 SY-3 SY-4 SY-5 Matrix compression damage of inner ring Force/kN 50.97 49.44 52.30 47.98 49.83 Displacement/mm 0.72 0.64 0.64 0.56 0.56 Matrix damage of laminates Force/kN 50.97 49.44 52.30 47.98 49.83 Displacement/mm 0.72 0.64 0.64 0.56 0.56 Fiber tensile damage of inner ring Force/kN 56.76 55.51 58.74 54.73 57.01 Displacement/mm 0.80 0.72 0.72 0.64 0.64 Fiber damage of laminates Force/kN 101.90 104.82 110.93 109.51 106.93 Displacement/mm 1.44 1.36 1.36 1.28 1.20
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表 6 锥形缠绕接头模型编号
Table 6. model number of tapered winding joint
Tension Compression No. Angle/(°) No. Angle/(°) Z-1 1 Z-1 2 Z-2 2 Z-2 4 Z-3 3 Z-3 6 Z-4 4 Z-4 8 Z-5 5 Z-5 10 Z-6 6 Z-7 7 Z-8 8 Z-9 9 Z-10 10
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表 7 模型Z-1~Z-10各阶段载荷及对应位移
Table 7. Loads and corresponding displacements of model Z-1-Z-10 at each stage
Stage Property Z-1 Z-2 Z-3 Z-4 Z-5 Z-6 Z-7 Z-8 Z-9 Z-10 Initial damage of interface Force/kN 9.53 10.02 10.76 11.31 12.11 11.82 11.52 11.22 10.86 10.52 Displacement/mm 0.24 0.24 0.24 0.24 0.32 0.32 0.32 0.32 0.32 0.32 Failure of interface Force/kN 34.64 36.01 36.48 36.51 36.65 35.92 35.40 34.50 34.11 33.41 Displacement/mm 1.28 1.28 1.28 1.28 1.28 1.28 1.28 1.28 1.28 1.28 Initial damage of chain link Force/kN 37.46 38.88 39.46 39.64 39.90 40.15 40.59 41.11 41.57 42.17 Displacement/mm 1.44 1.44 1.44 1.44 1.44 1.52 1.52 1.60 1.68 1.76 Failure of winding joint Force/kN 40.82 41.71 42.17 42.81 43.26 43.27 43.59 43.75 44.05 44.14 Displacement/mm 1.76 1.68 1.68 1.68 1.68 1.76 1.76 1.84 1.92 2.00
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表 8 压缩工况下模型ZY-1~ZY-5损伤起始点
Table 8. Damage starting points of model ZY-1-ZY-5 under compression condition
Stage Property ZY-1 ZY-2 ZY-3 ZY-4 ZY-5 Fiber tensile damage of right inner ring Force/kN 29.00 31.87 32.12 33.43 32.79 Displacement/mm 0.48 0.48 0.44 0.44 0.40 Matrix damage of right side of laminates Force/kN 40.98 45.32 46.78 48.66 45.98 Displacement/mm 0.68 0.68 0.64 0.64 0.56 Matrix compression damage of right inner ring Force/kN 45.79 50.47 55.45 54.53 52.63 Displacement/mm 0.76 0.76 0.76 0.72 0.64 Matrix damage of left side of laminates Force/kN 60.34 72.10 75.66 78.92 78.83 Displacement/mm 1.00 1.08 1.04 1.04 0.96 Fiber tensile damage of left inner ring Force/kN 77.42 85.36 101.89 108.60 104.93 Displacement/mm 1.28 1.28 1.40 1.44 1.28 Fiber damage of right side of laminates Force/kN 98.89 106.29 113.34 123.40 118.11 Displacement/mm 1.64 1.60 1.56 1.64 1.44
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