Tensile progressive damage and compressive postbuckling analysis of open-hole laminate composites

Abstract

Laminate composites contain holes as a means of connection in industrial applications. A better understanding of the mechanical properties of open-hole components is necessary. Herein, progressive damage postbuckling analysis models are proposed for investigation of tensile damage and compressive buckling behaviors of open-hole laminate composites. The progressive damage model is based on failure criteria provided by the continuum damage mechanics model; virtual crack closure technology was employed to calculate the energy release rate for crack delamination in compressive postbuckling analysis. The models were utilized to analyze variations in the tensile and compressive mechanical properties, failure process, and buckling evolution of open-hole laminate composites using finite element analysis. The tensile failure patterns and failure processes of plies with different open-hole laminate composite angles were obtained and analyzed. Buckling characteristics, as well as the progression of buckling onset, buckling propagation, crack delamination, unstable delamination, and global buckling, were investigated. The influence of delamination crack length and crack distribution on the buckling properties of open-hole laminate composites are discussed in detail. Additionally, unstable and stable buckling characteristics were examined. The numerical results were in good agreement with theoretical and experimental results; damage initiated at the edge of a hole propagated to two sides with the onset of matrix damage, followed by fiber damage. The fiber damage of a 0°-ply led ultimately to laminate failure. The laminate with a symmetrical crack distribution showed stable buckling, whereas a short, nonsymmetrical distribution of cracks usually led to unstable buckling and delamination.

Enhancing the mechanical performance of notched glass/epoxy composite laminates via hybridisation with thermoplastic fibres

“…Where, X c , Y t , and Y c are defined in equations ( 9), (11), and ( 12) respectively. While Z l mean the longitudinal shear strength.…”

“…8,9 The margins of the holes act as stress concentration areas and result in a variety of failures such as fibre breakages, delamination, and matrix cracks. 10,11 The holes are also limiting factors to design composite structures. 12 There are different parameters affecting the mechanical properties of drilled composites such as stacking sequences, 13,14 size of the holes, 15,16 and laminate thickness.…”

Development and validation of finite element models for buckling of open-hole fiber-reinforced composites at ambient and cryogenic temperatures

“…The validated FEM is used to perform the temperature-dependent buckling analysis of open-hole glass fiberreinforced epoxy (GFRE), glass fiber-reinforced polyester (GFRP), carbon fiber-reinforced epoxy (CFRE), and carbon fiber-reinforced polyester (CFRP) composite plates. In other literature, studies of open-hole and perforation effects on composites' and metals' structural properties have been addressed in detail (cf, [13][14][15][16][17][18][19][20][21]).…”

Investigation of the Influence of Delamination Characteristics on the Mechanical Properties of CFRP

“…In addition, the collision and impact during the transportation and use of the composite materials are also very likely to cause delamination inside the laminated structure, which will have a great impact on the subsequent use of the composite materials. For this reason, there has been a great deal of work on this issue by many researchers, with most of these work focuses on the mechanical properties and failure of composite laminates containing defects [1][2][3][4][5][6].Among them, delamination damage is the most important type of defect in the holemaking process of CFRP, which is the most important factor affecting the joint assembly performance of the hole, and once it occurs, it is irreparable and has a fatal effect on the strength and life of the composite. As a result, it is very important to study the mechanical properties and failure of composite laminates containing delamination defects.…”