The robustness of aeroelastic design optimization with respect to uncertainties in material and structural properties is studied both numerically and experimentally. The model consists of thin orthotropic composite wings virtually without fuselage. Three different configurations with consistent geometry but varying orientation of the main stiffness axis of the material are investigated. The onset of aeroelastic instability, flutter, is predicted using finite element analysis and the doublet-lattice method for the unsteady aerodynamic forces. The numerical results are experimentally verified in a low-speed wind tunnel. The optimization problem is stated as to increase the critical air speed, above that of the bare wing by massbalancing. It is seen that the design goals are not met in the experiments due to uncertainties in the structural performance of the wings. The uncertainty in structural performance is quantified through numerous dynamic material tests. Once accounting for the uncertainties through a suggested reformulation of the optimization problem, the design goals are met also in practice. The investigation indicates that robust and reliable aeroelastic design optimization is achievable, but careful formulation of the optimization problem is essential.
Aeroelastic tailoring considering uncertainties in material properties
Maßgeschneiderte aeroelastische Optimalauslegung unter Berücksichtigung unsicherer Materialeigenschaften
Structural Optimization ; 15 , 3/4 ; 157-162
1998
6 Seiten, 6 Bilder, 4 Tabellen, 8 Quellen
Aufsatz (Zeitschrift)
Englisch
Auslegung (Dimension) , Optimierung , Tragflügel , Flugzeug , Stabilität , Flattern , Stoffeigenschaft , mathematisches Modell , Vergleichsmessung , Verbundwerkstoff , orthotrope Platte , geometrische Form , Steifigkeit , Richtung , Finite-Elemente-Methode , Aerodynamik , Windkanal , Strömungsgeschwindigkeit , Massenausgleich , Unsicherheit
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