Abstract
Based on an incremental restricted variational principle formulated and the transformation matrix derived from three-dimensional contact kinematic conditions, a general but effective finite element technique satisfying various contact conditions is established for the three-dimensional contact stress analysis of a composite laminate with bolted joint. The double-lap bolted joint in the thin graphite/epoxy laminate of [ 45 0 /– 45 90 ] s lay-up or in the thick glass-reinforced polyester laminate of various stacking sequences subjected to a bolt load and/or a clamping torque is considered in the analysis. The effects of friction, clearance, bolt elasticity, stacking sequence and clamp-up on the contact tractions around the bolted joint are studied systematically. The distribution of contact tractions through the thickness of the bolt-laminate interface is also shown. The delamination onset of the composite laminate can thus be evaluated accordingly. Several examples are carried out to demonstrate the applicability of the technique developed. Good agreement between the present computed results and the referenced experimental results is noted. The present work would be of help for the design of a composite laminate with bolted joint.
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