Design and Analysis of Fixed Wing Based on Strength-To-Weight Ratio

The research paper presents the design and analysis of a fixed wing aircraft (Boeing 787-10) to enhance the strength-to-weight ratio. The dimensions of the wing are taken from the Boeing website and modelled using CATIA V5 software. The investigation primarily centres around studying the effects of different rib thicknesses, as well as varying materials for spars and skin. The rib thicknesses of 2, 4, and 6 mm are considered, while the skin materials include aluminium, titanium, and carbon fibre-reinforced polymer (CFRP), and the spars materials include aluminium, structural steel, and cobalt. The rib material is kept constant as aluminium throughout the research. The analysis demonstrates that the wing with a 6 mm rib thickness, aluminium spars, and CFRP skin provides the highest strength-to-weight ratio. Then two rib positioning are analysed: one with 10 ribs, where more ribs are placed near the wing tip, and the other with 9 ribs. The analysis demonstrates that the 10 ribs configuration achieves the maximum strength-to-weight ratio. The study indicates that an optimized wing can be achieved by varying rib component material, rib thickness, and rib position.