Quasi-Steady Aeroelastic Analysis of the Semi-Aeroelastic Hinge Including Geometric Nonlinearities

Conti, Claudio; Saltari, Francesco; Mastroddi, Franco; Wilson, Thomas; Castrichini, Andrea

doi:10.2514/1.c036115

Cited by 13 publications

(11 citation statements)

References 28 publications

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“…Currently, only one paper have assessed how the dynamic response and stability of a flexible wing incorporating FFWTs varies due to geometric nonlinearities. By extending the work of Conti et al [23], Mastracci et al [25] showed numerically that on a representative civil aircraft, accounting for these geometric nonlinearities can impact an aircraft's dynamic stability.…”

Section: Introductionmentioning

confidence: 94%

“…Its derivation differs to those presented in [12,16] by considering both the change in sweep angle of the wingtip with fold angle and the effect of the inner wing twist. It is however similar to that presented by Conti et al [23], albeit the resulting equation was only used to define the boundary conditions on the wingtip panels within there aerodynamic model, whereas here it will be used to understand some of the fundamental mechanisms driving the nonlinear dynamics of FFWTs.…”

Section: Geometrically Exact Representation Of the Effective Angle Of...mentioning

confidence: 99%

“…To complement the experimental data, a new methodology has been developed, utilising the software package MSC Nastran § , to model the geometric nonlinearities associated with the large deformations of FFWTs. MSC Nastran has been used extensively to model aeroelastic systems in both industrial and academic settings, and in particular, much of the literature on FFWTs has previously utilised this tool [10,14,15,18,23]. Section V.A first describes a baseline numerical model, in which the wingtip is modelled about a fold angle of zero degrees.…”

Section: Numerical Modellingmentioning

confidence: 99%

“…Additionally, at higher fold angles the aerodynamic influence of a FWT on the inner wing, and vice versa, can vary due to the significant changes in the geometry of the wing, varying the spanwise lift distribution. Conti et al [23] developed the Equations of Motion (EoM) for a representative civil aircraft, with aerodynamic and structural corrections to account for the geometric nonlinearity due to FFWT displacements. The aerodynamics were modelled using the doublet lattice method, with the boundary condition on the wingtip panels being defined using a coordinate transformation between a body reference frame and a reference frame centred about a "deformed" wingtip.…”

Section: Introductionmentioning

confidence: 99%

See 3 more Smart Citations

On the Effect of Geometric Nonlinearity on the Dynamics of Flared Folding Wingtips

Healy¹,

Cheung²,

Rezgui³

et al. 2023

Journal of Aircraft

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Recent studies have considered the use of flared folding wingtips (FFWTs) to enable higher aspect ratios -reducing overall induced drag -whilst reducing gust loading and meeting airport operational requirements. The majority of these analyses have employed linear assumptions despite the presence of large wingtip deformations. In this paper the effect of geometric nonlinearities introduced by an FFWT on the static and dynamic aeroelastic response of a wing is assessed. A geometrically exact expression was formulated to describe the change in the local Angle of Attack (AoA) in the chordwise direction across all fold angles. This expression highlighted that the aerodynamic stiffness of an FFWT, and therefore quantities such as the linear flutter speed, are a function of the fold angle and hence, the attitude of the wing. This effect was verified using both: a wind tunnel model of a flexible semi-span wing, and a numerical model utilising MSC Nastran, which linearised the model about the equilibrium position of the wingtip. These experiments showed that the geometric nonlinearities introduced due to the large deformations of FFWTs can significantly affect the dynamics of the system, with flutter speeds varying by over 28%, simply by changing the AoA of the model.

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Section: Introductionmentioning

confidence: 94%

Section: Geometrically Exact Representation Of the Effective Angle Of...mentioning

confidence: 99%

Section: Numerical Modellingmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

See 2 more Smart Citations

On the Effect of Geometric Nonlinearity on the Dynamics of Flared Folding Wingtips

Healy¹,

Cheung²,

Rezgui³

et al. 2023

Journal of Aircraft

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“…The side slip angle at which the wingtip becomes unstable, which will be called beta-critical, is an important property to calculate for a UAV with FFWTs. Conti et al [36] suggested the beta-critical was equivalent to the flare angle, which is the only current estimation of this value in literature.…”

Section: Albatrossone Flight Testmentioning

confidence: 99%

Experimental Analysis of the Dynamics of Flared Folding Wingtips via a Novel Tethered Flight Test

Healy

Pontillo

Rezgui

et al. 2022

AIAA SCITECH 2022 Forum

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Recent developments in morphing wing technologies are routinely tested using Unmanned Aerial vehicles (UAVs) due to their relatively low cost and time to manufacture. However, atmospheric flight tests limit both the repeatability of the recorded data sets, as well as the bounds of the flight envelope willing to be explored, due to the risk of destroying the UAV. In this paper, a novel flight test method is described, which consists of flying a UAV constrained by a tether, resulting in a steady, controlled, elliptical flight paths. The benefits of such a method are explored numerically to characterise the static and dynamic testing capabilities of such a system. This is then followed by an experimental investigation into the behaviour of semi-aeroelastic hinged (SAH) wingtips, employing the AlbatrossOne remotely piloted vehicle. The tethered model was used to explore the static effect of angle of attack and sideslip angle on the both the equilibrium position of the wingtips and the wingtips stability boundary.

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Investigations on the interactions between structural and aerodynamic nonlinearities and unsteadiness for aeroelastic systems

et al. 2021

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Quasi-Steady Aeroelastic Analysis of the Semi-Aeroelastic Hinge Including Geometric Nonlinearities

Cited by 13 publications

References 28 publications

On the Effect of Geometric Nonlinearity on the Dynamics of Flared Folding Wingtips

On the Effect of Geometric Nonlinearity on the Dynamics of Flared Folding Wingtips

Experimental Analysis of the Dynamics of Flared Folding Wingtips via a Novel Tethered Flight Test

Investigations on the interactions between structural and aerodynamic nonlinearities and unsteadiness for aeroelastic systems

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