LTH MA 501, 22–06 (2012)Įkvall, J.C., Griffin, C.F.: Design allowables for T300/5208 Graphite/Epoxy composite materials. In: Proceedings 62nd Deutscher Luft- und Raumfahrtkongress, Stuttgart, DGLR (2013)ĭorbath, F., van Veen, L., Gaida, U.: Wing secondary structure large civil jet transport (MTOM 40t) statistical mass estimation. In: Proceedings 5th CEAS Air & Space Conference, Delft, CEAS (2015)Ĭhiozzotto, G.P.: A modular implementation of aircraft simplified loads methods for conceptual design and variable fidelity processes. Aircraft 48(6), 1840–1855 (2011)Ĭhiozzotto, G.P.: Conceptual design method for the wing weight estimation of strut-braced wing aircraft. In: Proceedings 28th International Congress of the Aeronautical Societies, Brisbane, ICAS (2012)Ĭavagna, L., Ricci, S., Riccobene, L.: Structural sizing, aeroelastic analysis, and optimization in aircraft conceptual design. Rodde, A.-M., Toussaint, C.: Investigation of a strut-braced wing configuration for future commercial transport. NASA CR-2015-218704/Volume I, Hunntington Beach (2015)Ĭarrier, G., Atinault, O., Dequand, S., Hantrais-Gervois, J.-L., Liauzun, C., Paluch, B. NASA CR-2011-216847, Hunntington Beach (2011)īradley, M.K., Droney, C.K., Allen, T.J.: Subsonic ultra green aircraft research phase II: volume I– truss braced wing design exploration. Dover Publications Inc, New York (1996)īradley, M.K., Droney, C.K.: Subsonic ultra green aircraft research: phase I final report. Pearson Prentice-Hall, Upper Saddle River (2009)īindolino, G., Ghiringhelli, G., Ricci, S., Terraneo, M.: Multilevel structural optimization for preliminary wing-box weight estimation. Strut box cross-section area, m \(^\)īertin, J.J., Cummings, R.M.: Aerodynamics for engineers, 5th edn. A potential to reduce the wing mass in about 18 % or to increase the aspect ratio from 10 to 16 compared to a cantilever wing is identified. Design trade studies are presented illustrating typical applications of the method. The weight estimations are verified with conventional aircraft data and strut-braced wing studies available in the literature, showing good accuracy. The aeroelastic effects and strut reaction estimations are compared for a wide range of design parameters with Nastran validating the proposed method. Semi-empirical methods are presented for non-optimal mass components and the secondary structure. Aluminum or composite laminates can be considered. The wing and strut load-carrying structures are sized with analytical box-beam equations for strength, buckling and fatigue criteria. A direct non-iterative method is used for the strut and wing internal loads calculation. Maneuver, gust and ground cases are considered. Static aeroelastic loads, aeroelastic divergence and aileron reversal criteria are calculated directly with small matrices suitable for implementation in spreadsheet software. The method is simple to implement while still capturing important effects for early design estimates. This paper presents a method for the wing weight estimation of strut-braced wing aircraft in conceptual design.
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