Abstract
During countersunk hole machining, defects like geometrical deviation of the chamfer angle and delamination are easily introduced into the structure. To investigate the influences of geometrical deviation on delamination propagation around the countersunk hole during assembly, a progressive damage model (PDM) combining cohesive element was proposed and validated. Numerical analyses were then carried out to study delamination propagation behavior under the influences of geometrical parameters including delamination factor, chamfer angle, and location of delamination. The results show that when delamination appears at the transition area of the countersunk hole, the load causing the delamination evolution is much smaller than other cases.
Highlights
Carbon fiber reinforced plastic (CFRP) possesses the properties of lightweight and high-specific stiffness and strength, all of which make them suitable for a wide range of high responsibility applications in aircraft structures
In order to verify the effectiveness of the proposed method of combining the abovementioned progressive damage method and cohesive model, the finite element model was established according to the geometry and material parameters in the literature [29]
When there is an embedded delamination at the transition area of the countersunk hole, the delamination evolution threshold decreases to 67% with that of the other cases
Summary
Carbon fiber reinforced plastic (CFRP) possesses the properties of lightweight and high-specific stiffness and strength, all of which make them suitable for a wide range of high responsibility applications in aircraft structures. Delamination is introduced at the neighborhood of the countersunk hole in the process of machining such as drilling, which decreases the stiffness of structure, leads to the destruction of laminated plates in advance and seriously affects the safety of the structure of the aircraft. Studies on the effects of delamination on strength of composite structure have been carried out for many years. Finite element method (FEM) is widely employed to predict the mechanical behavior of composite structures with delamination by means of the virtual crack closure technique (VCCT) [2,3,4,5] and cohesive zone model (CZM) [6,7,8].
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