Aerostructural optimization and comparative study of twin-fuselage and strut-braced-wing aircraft configurations
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AbstractThe ultrahigh-aspect-ratio wing (UHARW) concept is a promising configuration to achieve future sustainable aviation goals. Twin-fuselage (TF) and strut-braced-wing (SBW) configurations are characterized by smaller structural bending moments and shear forces in the wing and are promising concepts for realizing UHARW designs. This paper addresses the aerostructural optimization problem of TF and SBW configurations with UHARW by using a coupled adjoint aerostructural optimization tool, which is composed of a geometrically nonlinear structural solver and a quasi-three-dimensional natural laminar flow (NLF) aerodynamic solver. The optimization results show significant improvements in fuel efficiency and performance for the TF and SBW aircraft, with fuel mass reductions of 13 and 10%, respectively, compared to the corresponding baseline aircraft designed in the conceptual design phase. In comparison to the original reference aircraft A320neo, the optimized TF and SBW have 48 and 31% lower fuel weights, respectively. The NLF range of both upper and lower wing surfaces is expanded during optimization. The optimized SBW configuration has a wing aspect ratio of 26.01, while the optimized TF has a wing aspect ratio of 20.74, indicating that the SBW concept is more conducive to realizing UHARW design compared with the TF configuration studied in this work. The optimized TF aircraft has a lighter fuel weight and gross weight compared to the optimized SBW aircraft, which is because the TF aircraft has a lighter operational empty weight, including a lighter fuselage structural weight, landing gear weight, etc., whereas the top-level aircraft requirements are the same for both aircraft, including range, payload, and cruise Mach.
CitationMa, Y., Abouhamzeh, M., and Elham, A. (2023) Aerostructural optimization and comparative study of twin-fuselage and strut-braced-wing aircraft configurations, Journal of Aircraft, 0(0), pp. 1-18.
JournalJournal of Aircraft
DescriptionThis is an accepted manuscript of an article published by American Institute of Aeronautics and Astronautics in Journal of Aircraft on 09/12/2023, available online: https://doi.org/10.2514/1.C037388 The accepted version of the publication may differ from the final published version.
Except where otherwise noted, this item's license is described as http://creativecommons.org/licenses/by/4.0/