Abstract
Large composite structures have been increasingly used in the aviation industry. New applications of composite materials include primary structures such as aircraft fuselages. These large composite parts are sometimes attached, either by the fasteners or adhesive bonding, to metallic structures. Because of the large coefficient of thermal expansion mismatch between the metallic and composite structures, the temperature change from the aircraft assembly line to the actual flight condition induces high thermal stresses during flight in both the composite fuselage and aluminum frames. An experimental program was executed to determine the interaction between the fastened Z-shaped aluminum beams and the solid composite laminate. An analytical model was also developed to simulate the thermal/mechanical behavior of the hybrid composite/metal structure. Finite element analysis was conducted to determine the parameters necessary for the analytical model. The results from the developed analytical model were found to correlate well with experimental results.
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