This paper presents the new features of a computer program for the conceptual, minimum-mass design of high aspect ratio, composite wings subject to constraints on flutter and divergence speed. The time to both model and optimize designs is quicker than FE methods and the program provides valuable insight during the early stages of design. The natural frequencies of the wing, modelled as a series of box beams, are obtained using an efficient and accurate Dynamic Stiffness Matrix method whilst areoelastic loads are based on strip theory. The flutter and divergence speeds for the wing are then found using a normal mode approach. Design sensitivities, obtained by a very efficient technique, are used to direct the optimizer ADS. Topological design variables, such as engine position and spar position, are included as well as ply thicknesses. An illustrative example is presented.
Optimum design of high aspect ratio wings subject to aeroelastic constraints
Optimaler Entwurf von Flugzeugflügeln mit hohem Streckverhältnis unter aeroelastischen Bedingungen
1995
9 Seiten, 6 Bilder, 1 Tabelle, 19 Quellen
Aufsatz (Konferenz)
Englisch
Flügelprofil , Flugzeug , Gewichtsminimierung , Verbundwerkstoff , Flatterschwingung , Simulationsmodell , rechnerunterstützter Produktentwurf , Resonanzfrequenz , dynamisches Verhalten , Steifigkeit , Matrix (Zahlenschema) , Topologie , Schichtdicke , Simulation , dynamische Charakteristik , Aussteifung
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