Publication: Stress analysis and sizing of an aeronautical composite sandwich panel (secondary structure)
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Date
2009-04-01
Authors
Abdullah, Siti Aminah
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Abstract
Nowadays, structural sandwich construction is used in many air and space vehicles, cargo containers, boats and ships. In fact, honeycomb sandwich panels revolutionized the aerospace industry over 40 years ago, making aircraft lighter, stronger and faster and allowing them to carry more weight and improve fuel efficiency. This report will be focused on sizing the panel of a secondary structure for commercialaircraft. After modeling the panel, stress analysis will be performed. The model of panel for commercial aircraft is being chosen for the typical example analysis as a critical sandwich structure. The analysis of the panel will be guided by some assumptions which one of the assumption is both end of the panel is simply fixed with clamp. The load when aircraft is cruising will be used for this analysis. There are several mode of failure in analyzing the stress such as deflection, transverse shear failure, local crushing of core, shear crimping, face wrinkling, intracellular buckling, core unglue, facing failure and general buckling. However, for this project, the analyses that will be performed are deflection and face wrinkling. By using manual calculation, the answer will be generated. From the result obtained, further studies to enhance the understanding of sandwich panel structure can be decided.