Abstract
Fiber reinforced plastics/metal hybrid laminates are composites laminated by fiber reinforced plastics (FRP) and light metals such as aluminum alloy. GLARE, one of the fiber reinforced plastics/metal hybrid laminates laminated by glass fiber reinforced plastics (GFRP) and aluminum alloy, has been applied to an upper fuselage panel in an Airbus A380. The precise stress distribution of the out of plane components has not been discussed around the contact hole boundary, though most of papers on the mechanical joint of GLARE deal with strength and damages. This paper deals a complicated non-linear analysis including elastic-plastic mechanical response, anisotropic material properties, lamination, contact and friction. Compared with the previous results about CARALL by the same author, it was obtained that some parameters, such as contact and friction between pin and the hole of laminates, affect the distribution and magnitude of stresses. Particularly, it is important that bend in thickness direction caused by plasticity of aluminum layer and resistance to bend by longitudinal stiffnesses of FRP layer affects the out of plane normal stresses of the interface between AL layer and FRP layer or between FRP layers. On the basis of these results, we discussed the initial failure of a pin joint occurred at the part of net-tension of the joint.
