The mainframes in the centre fuselage of the A400M have the vital function of introducing the wing loads into the fuselage. The lift distribution among the wing causing a torque and the frame curvature causing a bending moment, result in high running stress and limit loads in the frames below the rear wing attachment. These frames are made of 7000 series aluminium alloy and are primarily dimensioned by fatigue reasons, especially crack growth. Consequently, three different options for the A400M mainframes have been investigated. The first option is to reinforce the frames integrally. The second and third options are a titanium or GLAREĀ® strap. In this paper, a trade off between the different options is made with respect to fatigue, maintenance, and weight targets.
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REFERENCES
Rooke D.P. and Cartwright, D.J., Compendium of Stress Intensity Factors, H.M. Stationary Office, London, Great Britain, 1975.
Hooijmeijer P.A., Roebroeks, G. and Gunnink, J.W., A400M Frame Reinforcement, Confidential report: GTM 2007ā009, Den Haag, The Netherlands, 2007.
Witasse, R., Boer H. de, Koppert, J.J.M., Simulation of Bonding Strength for A400M Reinforced Mainframes, 07204/RWI, Delft, The Netherlands, 2007.
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Plokker, M., Daverschot, D., Beumler, T. (2009). Hybrid Structure Solution for the A400M Wing Attachment Frames. In: Bos, M.J. (eds) ICAF 2009, Bridging the Gap between Theory and Operational Practice. Springer, Dordrecht. https://doi.org/10.1007/978-90-481-2746-7_22
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DOI: https://doi.org/10.1007/978-90-481-2746-7_22
Publisher Name: Springer, Dordrecht
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