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A. Spohr, J. Schirra, J. Hoefling, A. Schedl
Unconventional and especially highly non-planar aircraft configurations are supposed to contribute to a significant increase in efficiency of civil air transport vehicles. So called multidisciplinary design optimization tools are used to find an optimum concerning aerodynamic, flight mechanic and structural performance but traditional methods to estimate the wing weight of the lifting system are not always applicable to highly non-planar configurations. For this reason a wing weight estimation tool is developed that combines the advantages of existing methods to achieve high physical accuracy while reducing the computational effort simultaneously. The approach proposed in this paper unites classical analytical methods with simple FEM models to exclude the dependency on statistical sets of data. A simplified beam model of the structural wing box is used to determine the inner forces and moments caused by outer airloads. Based on these inner loads the cross sections are designed by the use of analytical equations. During this process the cross-sectional area is minimized by an automated algorithm while limiting the occurring stresses to a given maximum stress level. Two validations are performed subsequently including one conventional and one unconventional highly non-planar lifting system.
Deutscher Luft- und Raumfahrtkongress 2013, Stuttgart
Deutsche Gesellschaft für Luft- und Raumfahrt - Lilienthal-Oberth e.V., Bonn, 2013
21,0 x 29,7 cm, 9 Seiten
Stichworte zum Inhalt:
non-planar, wing weight