The paper presents an approach developed primarily by the authors for the integrated modeling of structures, aerodynamics, aeroelasticity and flight mechanics. The motivation for the formulation is MDO/PD (Multi-Disciplinary Optimization for Preliminary Design) for innovative aircraft configurations, and is therefore first-principle based, since in this case the designer cannot rely upon past experience. The methodology is geared specifically towards MDO/PD for civil aviation. The emphasis here is on wing design - the fuselage is assumed as given. The stress analysis is based on finite elements for beams, rods and in-plane loaded plates, whereas the structural dynamics is based upon natural modes, which are evaluated by the same finite-element algorithm. For the aerodynamic analysis, a boundary-element quasi-potential-flow method is used for both steady and unsteady aerodynamics. An elementary boundary layer model is used to include the steady viscous effects and estimate the drag. A reduced order model (ROM) for the unsteady-aerodynamics forces is used in dynamic aeroelasticity. The numerical formulation has been applied to a specific test case - an innovative box-wing configuration denoted as Prandtlplane, which has, as a distinguishing feature, a low induced drag. The numerical results obtained for this configuration are presented, along with the comparison with those for an equivalent conventional wing configuration. Copyright © 2004 by the American Institute of Aeronautics and Astronautics, Inc. All rights reserved.
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|Titolo:||Multidisciplinary design optimization for the preliminary design of aeronautical configurations|
|Data di pubblicazione:||2004|
|Appare nella tipologia:||04a Atto di comunicazione a congresso|