Because of their smaill size and flight regime, coupling of aerodynamics, structural dynamics, and flight dynamics are critical for micro aerial vehicles. This paper presents a computational framework for simulating structural models of varied fidelity and a Navier-Stokes solver, aimed at simulating flapping and flexible wings. The structural model uses either 1) the in-house developed UM/NLABS, w hich decomposes the equations of3-D elasticity into crosssectional and spanwise analyses for slender wings, or 2) MSC.Marc, which is a commercial finite-element solver capable ofmodeling geometrically nonlinear structures of arbitrary geometry. The flow solver employs a well-tested pressure-based algorithm implemented in STREAM, A NACA0012 erovs-seetional rectangular wing of aspect ratio 3, chord Reynolds number of 3 x 10E4, and reduced frequency varying from 0.4 to 1.82, with prescribed pure plunge motion is investigated. Both rigid and flexible wing results are presented, and good agreement between experiment and computation are shown regarding tip displacement and thrust coefficient. Issues related to coupling strategies, fluid physics associated with rigid and flexible wings, and implications of fluid density on aerodynamic loading are also explored in this paper.
Computational aeroelasticity framework for analyzing flapping wing micro air vehicles
Rechnerische Aeroelastizitäts-Grundlagen zur Analyse von Mikro-Luftfahrzeugen mit flatternden Flügeln
AIAA Journal ; 47 , 8 ; 1865-1878
2009
14 Seiten, 20 Bilder, 3 Tabellen, 32 Quellen
Article (Journal)
English
Computational Aeroelasticity Framework for Analyzing Flapping Wing Micro Air Vehicles
British Library Conference Proceedings | 2008
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