Validation Studies for Aeroelastic Trim and Stability of Highly Flexible Aircraft

An Intrinsic Description of the Nonlinear Aeroelasticity of Very Flexible Wings

“…2,11,[20][21][22] Its relevant properties are included in Table 1. It should be noted that this definition corresponds to the original description due to Goland,19 instead of the heavy version (often referred to as Goland + ) of Eastep and Olsen.…”

“…Noting that the induced angle of attack can be written as a function of the local inertia velocity in their components in a frame linked to the airfoil, one can write the aeroelastic equations of motion with structural nonlinearities purely in terms of velocities. This approach has been already followed by Patil, Hodges and co-workers 8,[10][11][12] to obtain compact flight dynamics models of very flexible aircraft. Those authors used a finite-difference approximation to the spatial component of the equations of motion, and also extended the analysis to cases with closed kinematic chains (which requires the enforcement of a unique solution along multiple load paths) using an incremental solution approach.…”

Transfer Function Method for the Nonlinear Flutter of a High-aspect-ratio Wing

“…Zhouzhou team [3,4] for this issue, conducted in-depth study and made considerable progress, large flexible high aspect ratio solar UAV analysis has reference value; R Palacios [5] used three-dimensional Euler equations modeling to achieve a detailed three-dimensional representation of aerodynamics and structural mechanics. Z Sotoudeh [6] developed aeroelastic analysis of a flexible UAV at high altitude, A set of computer programs specially designed for such UAVs can be used to obtain the results of aeroelastic analysis in a short period of time, which is convenient for the design of flexible UAVs. D Tang [7] combined the aeroelastic analysis of flexible wings with the wind Hole test, a theoretical aeroelastic model of aeroelastic model with flexible large aspect ratio airfoil under elastic load is introduced.…”

Robust Aeroelastic Control of Very Flexible Wings using Intrinsic Models

“…The framework will be the intrinsic formulation of the problem, introduced for geometriccally-exact beam dynamics by Hodges 16 and expanded to nonlinear aeroelastic problems by Sotoudeh et al 7 Our description will use the modal projection of the intrinsic beam equations of Palacios, 17 with aerodynamics given by the strip theory, as in Palacios and Epureanu. 18 This provides a compact description of the problem suitable for control design.…”

“…3 A number of integrated simulation frameworks have been constructed to model the nonlinear response to gust loads of very flexible aircraft. [4][5][6][7][8][9] They have provided substantial evidence of the importance of modelling large, geometrically-nonlinear deflections, and the challenges associated to the development of control systems for gust alleviation and trajectory tracking in such systems. Cook et al 10 and Dillsaver et al 11 applied H ∞ and LQG controllers respectively to full aircraft models and investigated the response to gust and continuous disturbances.…”