Gust response analysis and wind tunnel test for a high-aspect ratio wing

Liu, Yi; Xie, Chunhong; Yang, Chao; Cheng, Jialin

doi:10.1016/j.cja.2015.12.013

Cited by 40 publications

(18 citation statements)

References 8 publications

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“…However, it is not the focus of this work to quantify the loss of accuracy. Besides, we found that results obtained by loosely coupling show good agreement with the experimental results [5,23] referring to flutter and dynamic responses. Considering the purpose of this paper and the computation cost, the loose coupling is used in static aeroelastic analysis to obtain the equilibrium state.…”

Section: Nonlinear Static Aeroelastic and Fluttersupporting

confidence: 76%

Aeroelastic Optimization Design for High-Aspect-Ratio Wings with Large Deformation

Xie

Meng

Wang³

et al. 2017

Shock and Vibration

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This paper presents a framework of aeroelastic optimization design for high-aspect-ratio wing with large deformation. A highly flexible wing model for wind tunnel test is optimized subjected to multiple aeroelastic constraints. Static aeroelastic analysis is carried out for the beamlike wing model, using a geometrically nonlinear beam formulation coupled with the nonplanar vortex lattice method. The flutter solutions are obtained using the -method based on the static equilibrium configuration. The corresponding unsteady aerodynamic forces are calculated by nonplanar doublet-lattice method. This paper obtains linear and nonlinear aeroelastic optimum results, respectively, by the ISIGHT optimization platform. In this optimization problem, parameters of beam cross section are chosen as the design variables to satisfy the displacement, flutter, and strength requirements, while minimizing wing weight. The results indicate that it is necessary to consider geometrical nonlinearity in aeroelastic optimization design. In addition, optimization strategies are explored to simplify the complex optimization process and reduce the computing time. Different criterion values are selected and studied for judging the effects of the simplified method on the computing time and the accuracy of results. In this way, the computing time is reduced by more than 30% on the premise of ensuring the accuracy.

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Section: Nonlinear Static Aeroelastic and Fluttersupporting

confidence: 76%

Aeroelastic Optimization Design for High-Aspect-Ratio Wings with Large Deformation

Xie

Meng

Wang³

et al. 2017

Shock and Vibration

Self Cite

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“…The interaction of a flexible structure and its aerodynamics results in a computationally expensive coupled problem. Engineers must be able to verify that a control input or environmental perturbation will not lead to damaging loads on the structure [6], be able to model the outcome of control inputs and understand the implications of the mass and stiffness distribution across the structure during design [7].…”

Section: Nomenclaturementioning

confidence: 99%

A Geometrically Non-Linear Time-Domain Unsteady Lifting-Line Theory

Bird

Otomo

Ramesh

et al. 2019

AIAA Scitech 2019 Forum

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An unsteady lifting-line theory for time-domain problems with arbitrary kinematics is presented. This is formulated by matching a vortex particle based 2D inner model with a 3D vortex lattice wake. This and a small-amplitude frequency-domain unsteady lifting-line theory are then verified against experiment and computational fluid dynamics for the case of a flat rectangular plate oscillating in heave at aspect ratios 3 and 6. Both lifting-line theories were found to generally be in good agreement with experimental and CFD results, providing reasonable solutions even in cases dominated by LEV shedding. For larger amplitude problems, the new non-linear geometry lifting-line theory predicted larger amplitudes and higher average lift coefficient than the small-amplitude lifting-line theory.

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“…To this day, a limited number of experimental studies on high-aspect ratio wings exists. They have shown however, that very flexible wings have a significantly different gust response characteristics under different deformations and load conditions (Liu et al, 2016). Inherently, additional analysis is required in order to gain insight into the complex interactions between wind gusts and aircraft aeroelasticity.…”

Section: Introductionmentioning

confidence: 99%

Assessment of low-altitude atmospheric turbulence models for aircraft aeroelasticity

Deskos

Carre

Palacios

2020

Journal of Fluids and Structures

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We investigate the dynamic response of flexible aircraft in low-altitude atmospheric turbulence. To this end, three turbulence models of increasing fidelity, namely, the one-dimensional von Kármán model, the two-dimensional Kaimal model and full three-dimensional wind fields extracted from large-eddy simulations (LES) are used to simulate ambient turbulence near the ground. Load calculations and flight trajectory predictions are conducted for a flexible high-aspect ratio aircraft, using a fully coupled nonlinear flight dynamics/aeroelastic model, when it operates in background atmospheric turbulence generated by the aforementioned models. Comparison of load envelopes and spectral content, on vehicles of varying flexibility, shows strong dependency between the selected turbulence model and aircraft aeroelastic response (e.g. 58% difference in the predicted magnitude of the wing root bending moment between LES and von Kármán models). This is mainly due to the presence of large flow structures at low altitudes that have comparable dimensions to the vehicle, and which despite the relatively small wind speeds within the Earth boundary layer, result in overall high load events. Results show that one-dimensional models that do not capture those effects provide fairly non-conservative load estimates and are unsuitable for very flexible airframe design.

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Gust response analysis and wind tunnel test for a high-aspect ratio wing

Cited by 40 publications

References 8 publications

Aeroelastic Optimization Design for High-Aspect-Ratio Wings with Large Deformation

Aeroelastic Optimization Design for High-Aspect-Ratio Wings with Large Deformation

A Geometrically Non-Linear Time-Domain Unsteady Lifting-Line Theory

Assessment of low-altitude atmospheric turbulence models for aircraft aeroelasticity

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