Effects of the composite stacking sequence on the failure load of the single lap bonded joint

Composite materials are widely used in aircraft structures, their relative rigidity/weight
confers their advantage over metal structures, and the stacking sequence plays an important
role for their use. The objective of this work is to analyze by the finite element method
the mechanical behavior of a single lap joint of composite/composite type under a tensile
load. In order to see the effects on the failure load, two basic parameters are taken into
consideration; the stacking sequence of composite and thickness of each layer constituting
the composite. Calculation of the failure load is made numerically with the ABAQUS code
using the developed technique of VCCT (Virtual Crack Closure Technique) based on fracture
mechanics. Finally, the influence of the bonding defect on the failure load is analyzed. The
results clearly show the importance of optimizing fiber orientation and hence the stacking
sequence for proper use of composite in bonded assemblies.