Interlaminar failure investigations on delamination growth of composite laminates

• Published in: IOP conference series. Materials Science and Engineering 2019-08, Vol.591 (1), p.12038
• Main Authors: Hudisteanu, I, Taranu, N, Isopescu, D N, Munteanu, V, Ungureanu, D, Scutaru, M C
• Format: Article
• Language: English
• Subjects: Bearing strength; Composite materials; Delamination; Evolution; Failure investigations; Failure modes; Fiber orientation; Laminates; Load carrying capacity; Manufacturing defects; Mathematical models; Mechanical properties; Multilayers; Stacking sequence (composite materials); Stiffness
• ISSN: 1757-8981; 1757-899X
• DOI: 10.1088/1757-899X/591/1/012038

The investigation of the interlaminar damage evolution on multi-layered composites as well as the numerical modelling techniques available for the simulation of the interface delamination are still a current concern. The complexity of modelling the mechanical behaviour and fracture modes of composite laminates is increased because of the anisotropic behaviour of the material, the fibre arrangement or other important parameters, such as stacking sequence, fibre orientation angle and the configuration of the composite laminates. Different failure modes may occur on multi-layered composites, which can lead to significant stiffness and strength reduction or to the complete loss of the load carrying capacity. The interlaminar stresses are the main factors responsible for the initiation and growth of the interlaminar failures such as delamination. They may occur as a result of manufacturing defects, low-velocity impacts or as an effect of the presence of the free edges. The delamination onset can lead to serious problems such as the premature buckling of the laminates, moisture infiltration, and stiffness degradation or even to progressive delamination growth and the separation of the layers of the composite laminates. The paper presents the numerical modelling of a multi-layered composite subjected to the tensile opening fracture mode as well as the investigation of the delamination growth. The purpose of the analysis is to study the delamination evolution on a symmetric composite laminate, starting from a pre-existing initial crack, at the interface between the adjacent layers from the middle plane. Thenumerical modelling approach for the simulation of the delamination evolution is conducted based on the Cohesive Zone Method. The results are presented in terms of the total displacement jump and equivalent stress distributions on the layers of the composite laminates.