Optimization of the Composite Airplane Fuselage for an Optimum Structural Integrity

Abstract

The newly developed airplanes are using composite laminates to replace the metal alloys for different components, such as the fuselage and the wings. The major advantage of the composite materials is to reduce structural weight which results in reducing the fuel consumption. The aim of this project is to investigate the structural integrity of an airplane fuselage, which uses various types of carbon composite laminates under the static loading of the cabin pressurization. The research is performed using the finite element method and the HYPERMESH commercial software with a composite tool to change the thickness and the orientation of carbon fiber laminates used in the facesheet of the sandwich structure. Three different orientations/stacking sequence of the HexPly 8552 AS4 carbon fibers with two honeycomb cores: Hexagonal Al and Nomex. The results show that the composite material using the HexPly 8552 carbon fiber oriented at angle 30 and angle 45 and the Nomex Honeycomb core of a total laminate thickness of 15.875mm outperform all other thicknesses and orientations in regards to the static loading failure.

High-Performance Cladophora-Algae-Based Paper for Honeycomb Core in Sandwich-Structured Composite: Preparation and Characterizations

“…The application of sandwich-structured composites has significantly increased due to their suitability in developing lightweight structures with high mechanical performance and they have become the first choice in various applications, especially in the structural field [ 3 , 4 ]. Sandwich-structured composites have begun to be widely used in vast areas, ranging from satellites [ 5 ] and aircraft wings [ 6 ], as well as marine [ 7 ], transportation [ 8 ], sport [ 9 ], and drone or military applications [ 1 ]. Using sandwich-structured composites in transportation applications results in a lighter vehicle with better fuel efficiency and payload capacity [ 10 , 11 ].…”