J. Schochow, T. Klimmek

A strategy is presented to optimize wing structures under static aeroelastic constraints with respect to parameters defining wing shape and structural layout. The aerodynamic and structural models are based on one common parameterized geometry description. While the aerodynamic model includes the description of the three dimensional surface geometry, the structural model description is based on the Finite Element Method and includes a detailed wing layout concept with arbitrarily oriented spars and ribs. The aeroelastic toolkit ZAERO employs the modal formulation for solving the trim problem of the flexible aircraft and calculates the loads for selected trim cases. The optimization code LAGRANGE minimizes the mass of the structure sustaining the design loads by sizing the thicknesses of skins, spars and ribs. The optimization framework is integrated in the design system iSIGHT which finds the optimal wing planform under given mass and aeroe!astic constraints. In two design studies the sweep and aspect ratio are varied and the convergence performance of the framework is shown.

CEAS Conference on Multidisciplinary Aircraft Design and Optimization; Köln; 2001

Book Chapter

englisch

14,8 x 21,0 cm, 10 Seiten

DGLR-Bericht, 2001, 2001-05, CEAS Conference on Multidisciplinary Aircraft Design and Optimization; S.199-208; 2001; Deutsche Gesellschaft für Luft- und Raumfahrt - Lilienthal-Oberth e.V., Bonn

NA

aeroelasticity, wings, structural design, aeronautics, multidisciplinary design optimisation

Bestellbar

2001