Aerospace) Nonlinear Aeroelastic Analysis of Flexible High Aspect Ratio Wings Including Correlation With Experiment by Justin W. Jaworski Department of Mechanical Engineering and Materials Science Duke University

In this study the centre manifold is applied for reduction and limit cycle calculation of a highly nonlinear structural aeroelastic wing. The limit cycle is arisen from structural nonlinearity due to the large deflection of the wing. Results obtained by different orders of centre manifolds are compared with those obtained by time marching method (fourth-order Runge-Kutta method). These comparis...

A three-degrees of freedom (3-DOF) coupled numerical simulation technique for synchronously extracting 18 aerodynamic derivatives of bridge decks is proposed and evaluated in this study. Computations are performed with a finite volume unstructured computational flow dynamics (CFD) solver using two-dimensional (2D) hybrid meshes with fine near-wall resolution. The accuracy of the numerical model...

The exploitation of computational fluid dynamics for non linear aeroelastic simulations is mainly based on time domain simulations of the Euler and NavierStokes equations coupled with structural models. Current industrial practice relies heavily on linear methods which can lead to conservative design and flight envelope restrictions. The significant aeroelastic effects caused by nonlinear aerod...

Wind turbines are complex structures and their dynamics vary significantly in operation, in comparison to that under stand still (parked) conditions. Presence of rotational loads and considerable aeroelastic effects makes it difficult to apply conventional system identification techniques to wind turbines. Operational Modal Analysis (OMA) is a technique of determining dynamic characteristics of...

This paper numerically investigates the effect of chordwise flexibility on the dynamic stability of compliant airfoils. A classical two-dimensional aeroelastic model is expanded with an additional degree of freedom to capture time-varying camber deformations, defined by a parabolic bending profile of the mean aerodynamic chord. Aerodynamic forces are obtained from unsteady thin airfoil theory a...

A comprehensive analysis of aeroelastic systems has shown that these systems exhibit a broad class of pathological response regimes when certain types of non-linearities are included. In this paper, we propose a design method of a state-dependent non-linear controller for aeroelastic systems that includes polynomial structural non-linearities. The proposed method is based on recent numerical te...

Title of dissertation: DYNAMICS AND AEROELASTICITY OF HOVER CAPABLE FLAPPING WINGS: EXPERIMENTS AND ANALYSIS Beerinder Singh, Doctor of Philosophy, 2006 Dissertation directed by: Professor Inderjit Chopra Department of Aerospace Engineering This dissertation addresses the aerodynamics of insect-based, bio-inspired, flapping wings in hover. An experimental apparatus, with a bio-inspired flapping...

Optimal thickness distributions of aeroelastic flapping shells" (2013). a r t i c l e i n f o a b s t r a c t The severe weight limitations of flapping wing micro air vehicles necessitates the use of thin flexible wings, which in turn requires an aeroelastic modeling tool for proper numerical characterization. Furthermore, due to the unconventional nature of these vehicles, wing design guidelin...