Thermally induced loads of fastened hybrid composite/aluminum structures

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Authors
Yang, Chihdar Charles
Sun, Wenjun
Seneviratne, Waruna P.
Shashidhar, Ananthram K.
Advisors
Issue Date
2008-03
Type
Article
Keywords
Composite structures , Aluminum , Aviation , Fuselages , Thermal expansion , Thermal stress
Research Projects
Organizational Units
Journal Issue
Citation
Yang, C., Sun, W., Seneviratne, W., & Shashidhar, A. K. (2008). Thermally induced loads of fastened hybrid composite/aluminum structures. Journal of Aircraft, 45(2), 569-580. doi:10.2514/1.31776
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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Publisher
American Institute of Aeronautics and Astronautics
Journal
Book Title
Series
Journal of Aircraft
v.45 no.2
PubMed ID
DOI
ISSN
0021-8669
1533-3868 (online)
EISSN