Aeroelastic Model of Multisegmented Folding Wings: Theory and Experiment

Wang, Ivan; Gibbs, S. Chad; Dowell, Earl H.

doi:10.2514/1.c031589

Cited by 36 publications

(16 citation statements)

References 24 publications

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“…A cantilevered plate interacting with flow loses stability via a static divergance or growing amplitude of oscillations, depending on its orientation to the flow. From a design point of view, this phenomenon can be either detrimental, for structures such as paper in printing processes and aerospace systems [37,36], or beneficial, for energy harvesters subject to flow-induced flutter [14]. Therefore, understanding the dynamical behaviour of a rectangular plate interacting with flow is of significant importance; it would provide access to accurate predictions of the fluidelastic instabilities in complex real-world fluid-structure interaction problems.…”

Section: Introductionmentioning

confidence: 99%

Nonlinear static response of low-aspect-ratio inverted flags subjected to a steady flow

Tavallaeinejad

Paı̈doussis

Legrand

2018

Journal of Fluids and Structures

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Section: Introductionmentioning

confidence: 99%

Nonlinear static response of low-aspect-ratio inverted flags subjected to a steady flow

Tavallaeinejad

Paı̈doussis

Legrand

2018

Journal of Fluids and Structures

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“…In the work of [16] the aerodynamic method used is strip theory, with the generalized non-stationary theory of Theodorsen applied to an airfoil. The results for the theory's predicted flutter velocity and frequency were very close to the experimental ones.…”

Section: Aerodynamic Modelingmentioning

confidence: 99%

Modeling, Simulation and Control of an Aircraft with Morphing Wing

Luz

Schinestzki

Souza

et al. 2019

Proceedings of the 10th Aerospace Technology Congress, October 8-9, 2019, Stockholm, Sweden

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The technological advances, mainly in the development of new materials, recovered the interest in the application of morphing wings in aircraft. Due to the potential of replacing conventional control surfaces by morphing surfaces, the present work presents the modeling of aerodynamics, dynamics and control design of an aircraft with morphing wings. The morphing concept is given by changing the camber of the trailing edge along the wingspan. For aerodynamics modeling, it was adopted unsteady strip theory and, for dynamics modeling, it was used rigid body mechanics, considering the displacement of the center of mass and the time-varying inertia tensor. Finally, control design is performed using Exponential Mapping Controller (EMC) method. The results showed that, for the adopted variable geometry configuration, the influence of the center of mass displacement and the inertia variation on the aircraft behavior were insignificant, whereas the influences of the unsteady aerodynamics were significant. Consideration of the unsteady aerodynamic effects increases the magnitude of the aircraft movements, necessitating a greater control action.

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“…One is the aeroelastic characteristic in fixed configuration. Related works have undergone a phase from linear to nonlinear and from simulation to experiment [3][4][5]. This aspect has been the subject of considerable research.…”

Section: Introductionmentioning

confidence: 99%

Calculation of the Hinge Moments of a Folding Wing Aircraft during the Flight-Folding Process

Jing

Yun

et al. 2019

International Journal of Aerospace Engineering

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A folding wing morphing aircraft should complete the folding and unfolding process of its wings while in flight. Calculating the hinge moments during the morphing process is a critical aspect of a folding wing design. Most previous studies on this problem have adopted steady-state or quasi-steady-state methods, which do not simulate the free-flying morphing process. In this study, we construct an aeroelastic flight simulation platform based on the secondary development of ADAMS software to simulate the flight-folding process of a folding wing aircraft. A flexible multibody dynamic model of the folding wing structure is established in ADAMS using modal neutral files, and the doublet lattice method is developed to generate aerodynamic influence coefficient matrices that are suitable for the flight-folding process. The user subroutine is utilized, aerodynamic loading is realized in ADAMS, and an aeroelastic flight simulation platform of a folding wing aircraft is built. On the basis of this platform, the flight-folding process of the aircraft is simulated, the hinge moments of the folding wings are calculated, and the influences of the folding rate and the aircraft’s center of gravity (c.g.) position on the results are investigated. Results show that the steady-state method is applicable to the slow folding process. For the fast folding process, the steady-state simulation errors of the hinge moments are substantially large, and a transient method is required to simulate the flight-folding process. In addition, the c.g. position considerably affects the hinge moments during the folding process. Given that the c.g. position moves aft, the maximum hinge moments of the inner and outer wings constantly increase.

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Aeroelastic Model of Multisegmented Folding Wings: Theory and Experiment

Cited by 36 publications

References 24 publications

Nonlinear static response of low-aspect-ratio inverted flags subjected to a steady flow

Nonlinear static response of low-aspect-ratio inverted flags subjected to a steady flow

Modeling, Simulation and Control of an Aircraft with Morphing Wing

Calculation of the Hinge Moments of a Folding Wing Aircraft during the Flight-Folding Process

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