Commercial Aircraft Wing Structure : - Design of a Carbon Fiber Composite Structure
Abstract: This project explores the classical wing structure of an commercial aircraft for an all carbon fiber reinforced polymer unmanned aerial vehicle(UAV). It is part of a collaborative work consisting of several groups researching different parts of the aircraft. The objective of this report is to present the design of the inner wing structure for a greener, more efficient scaled 2:1 version of the Skywalker X8. In order to make the aircraft as efficient as possible, the structure needs to be lightweight. The loads were first approximated using XFLR5 and a first design made. The design was then tested using finite element analysis (FEA) in the programme Ansys Static Structural. The material that was tested was carbon fiber/epoxy prepreg. The final design of the wing weighs 3.815 kg, and consists of one spar and a skin thickness of 1 mm. The weight of the whole aircraft, including the propulsion system and a sharklet at both wingtips researched by other groups, is 20.262 kg. The lift-to-drag ratio was also calculated, and the most efficient angle of attack was concluded to be around 2-3°.
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