Analysis of Through-the-Thickness Stress Distribution in Thick Laminate Multi-Bolt Joints Using Global-Local Method

doi:10.1007/s12204-013-1402-5

Abstract

Abstract: The stress distribution surrounding the fastener hole in thick laminate mechanical joints is complex. It is time-consuming to analyze the distribution using finite element method. To accurately and efficiently obtain the stress state around the fastener hole in multi-bolt thick laminate joints, a global-local approach is introduced. In the method, the most seriously damaged zone is 3D modeled by taking the displacement field got from the 2D global model as boundary conditions. Through comparison and analysis there are the following findings: the global-local finite element method is a reliable and efficient way to solve the stress distribution problem; the stress distribution around the fastener hole is quite uneven in through-the-thickness direction, and the stresses of the elements close to the shearing plane are much higher than the stresses of the elements far away from the shearing plane; the out-of-plane stresses introduced by the single-lap joint cannot be ignored due to the delamination failure; the stress state is a useful criterion for further more complex studies involving failure analysis.

Key words: thick laminate| global-local| through-the-thickness| multi-bolt

摘要： The stress distribution surrounding the fastener hole in thick laminate mechanical joints is complex. It is time-consuming to analyze the distribution using finite element method. To accurately and efficiently obtain the stress state around the fastener hole in multi-bolt thick laminate joints, a global-local approach is introduced. In the method, the most seriously damaged zone is 3D modeled by taking the displacement field got from the 2D global model as boundary conditions. Through comparison and analysis there are the following findings: the global-local finite element method is a reliable and efficient way to solve the stress distribution problem; the stress distribution around the fastener hole is quite uneven in through-the-thickness direction, and the stresses of the elements close to the shearing plane are much higher than the stresses of the elements far away from the shearing plane; the out-of-plane stresses introduced by the single-lap joint cannot be ignored due to the delamination failure; the stress state is a useful criterion for further more complex studies involving failure analysis.

关键词: thick laminate| global-local| through-the-thickness| multi-bolt

CLC Number:

TB 332

CHEN Kun-kun (陈昆昆), LIU Long-quan* (刘龙权), WANG Hai (汪海). Analysis of Through-the-Thickness Stress Distribution in Thick Laminate Multi-Bolt Joints Using Global-Local Method[J]. Journal of shanghai Jiaotong University (Science), 2013, 18(3): 326-333.

References

[1] Chinese Aeronautical Establishment. Design manual of composite structures [M]. BeijingAviation Industry Press, 2001 (in Chinese).
[2] Li Y S, Wang W B. Mechanical behaviors of adhesively-bonded, bolted and hybrid composite-to steel joints [J]. Journal of Ship Mechanics, 2011, 15(9): 1052-1064.
[3] Tserpes K I, Papanikos P, Kermanidis T. A three-dimensional progressive damage model for bolted joints in composite laminates subjected to tensile loading [J]. Fatigue and Fracture of Engineering Materials and Structures, 2001, 24(10): 663-675.
[4] Ye L. Role of matrix resin in delamination onset and growth in composite laminates [J]. Composites Science and Technology, 1988, 33: 257-277.
[5] Iancu F. Three-dimensional finite element analysis of a single lap bolted joint of thick isotropic materials [D]. Michigan, USA: Department of Mechanical Engineering, Michigan State University, 2003.
[6] Isaicu G A. Three-dimensional strain analysis of single-lap bolted joints in thick composites using fiberoptic strain gages and finite element method [D]. Michigan, USA: Department of Mechanical Engineering, Michigan State University, 2006.
[7] Thelander S D. Study of a thick composite and aluminum single-lap bolt joint employing orthotropic photoelasticity and digital speckle pattern interferometry [D]. Michigan, USA: Department of Mechanical Engineering, Michigan State University, 2003.
[8] Sarvestani H Y, Sarvestani M Y. Free-edge stress analysis of general composite laminates under extension, torsion and bending [J]. Applied Mathematical Modeling, 2012, 36: 1570-1588.
[9] Angioni S L, Visrolia A, Meo M. Combining XFEM and a multilevel mesh superposition method for the analysis of thick composite structures [J]. Composites: Part B, 2012, 43: 559-568.
[10] Shi W J, Hu W P, Zhang M, et al. A damage mechanics model for fatigue life prediction of fiber reinforced polymer composite lamina [J]. Acta Mechanica Solida Sinica, 2011, 24(5): 399-410.
[11] Quaresimin M, Susmel L, Talreja R. Fatigue behavior and life assessment of composite [J]. International Journal of Fatigue, 2010, 32: 2-16.
[12] Mccarthy M A, Mccarthy C T, Lawlor V P, et al. Three-dimensional finite element analysis of singlebolt, single-lap composite bolted joints. Part I. Model development and validation [J]. Composite Structures, 2005, 71: 140-158.
[13] Mccarthy C T, Mccarthy M A, Lawlor V P. Progressive damage analysis of multi-bolt composite joints with variable bolt–hole clearances [J]. Composites: Part B, 2005, 36: 290-305.
[14] Ekh J, Sch¨on J. Load transfer in multirow, single shear, composite-to-aluminum lap joints [J]. Composites Science and Technology, 2006, 66: 875-885.
[15] Gray P J, Mccarthy C T. A global bolted joint model for finite element analysis of load distributions in multi-bolt composite joints [J]. Composites: Part B, 2010, 41: 317-325.
[16] Egan B, Mccarthy C T, Mccarthy M A, et al. Stress analysis of single-bolt, single-lap, countersunk composite joints with variable bolt-hole clearance [J]. Composite Structures, 2012, 94: 1038-1051.
[17] Chishti M, Wang C H, Thomson R S, et al. Numerical analysis of damage progression and strength of countersunk composite joints [J]. Composite Structures, 2012, 94: 643-653.
[18] Olmedo ′A, Santiuste C. On the prediction of bolted single-lap composite joints [J]. Composite Structures, 2012, 94: 2110-2117.
[19] Pisano A A, Fuschi P, Domenico D D. A layered limit analysis of pinned-joints composite laminates: Numerical versus experimental findings [J]. Composites: Part B, 2011, 43: 940-952.
[20] Kradinov V, Madenci E, Ambur D R. Combined in-plane and through-the-thickness analysis for failure prediction of bolted composite joints [J]. Composite Structures, 2007, 77: 127-147.
[21] Martin R H. Local fracture mechanics analysis of stringer pull-off and delamination in a post-buckled compression panel [J]. Applied Composite Materials, 1996, 3: 249-264.
[22] Volgers P. SMR engineering and development—Detailed 3D analysis of bolted joints in global shell structures [EB/OL]. (2012-05-16). http://www.smr. ch/bojcas/Reports/Volgers2002.pdf.2002-10/2005-9-14.
[23] Pearce G M, Johnson A F, Thomson R S, et al. Numerical investigation of dynamically loaded bolted joints in carbon fiber composite structures [J]. Applied Composite Materials, 2010, 17: 329-346.
[24] D5961/D5961M-08, Standard test method for bearing response of polymer matrix composite laminates [S].
[25] Xie Ming-jiu. Joints for composites materials [M]. ShanghaiShanghai Jiaotong University Press, 2011 (in Chinese).
[26] Liu L Q, Chen K K. A modeling method for deformation analysis in thick laminate mechanical joints [J]. Journal of Aircraft, 2012, 49(6): 1974-1981.
[27] Mao Yin. Study of load distribution in multi-bolt thick laminate joints [D]. Shanghai: School of Aeronautics and Astronautics, Shanghai Jiaotong University, 2011 (in Chinese).