Modelling of folding wing-tip devices for gust loads alleviation

R. C.M. Cheung; C. Wales; D. Rezgui; J. E. Cooper; T. Wilson

doi:10.2514/6.2018-0462

Modelling of folding wing-tip devices for gust loads alleviation

R. C.M. Cheung
, C. Wales
, D. Rezgui
, J. E. Cooper
, T. Wilson

Research output: Chapter in Book/Report/Conference proceeding › Conference Contribution (Conference Proceeding)

1 Citation (Scopus)

522 Downloads (Pure)

Abstract

High aspect ratio wings have been the focus of recent aircraft designs for improved fuel consumption through reducing induced drag. The increase in wing span has also led to folding wing-tips being introduced as a solution for meeting airport gate requirements. Recent studies have suggested such a folding wing-tip solution may be incorporated with spring devices in order to provide an additional gust loads alleviation ability in flight. The current work examines the suitability of using the Doublet-Lattice Method and the Unsteady Vortex-Lattice Method for modelling the dynamic response of such a folding wing-tip device and found that the Doublet-Lattice Method tends to over-predict the achievable gust loads alleviation because it cannot fully capture the coupling between folding and the change in local angle of attack of the wing-tip. Additional analysis also found that when using the Unsteady Vortex-Lattice Method, choosing large displacement method over linear method for solving the structural response only produced minimal difference.

Original language	English
Title of host publication	2018 AIAA/ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conference
Publisher	American Institute of Aeronautics and Astronautics Inc. (AIAA)
Number of pages	12
ISBN (Electronic)	9781624105326
DOIs	https://doi.org/10.2514/6.2018-0462
Publication status	Published - 8 Jan 2018
Event	AIAA/ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conference, AIAA SciTech Forum - Gaylord Palms , Kissimmee, United States Duration: 8 Jan 2018 → 12 Jan 2018

Conference

Conference	AIAA/ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conference, AIAA SciTech Forum
Abbreviated title	SciTech 2018
Country/Territory	United States
City	Kissimmee
Period	8/01/18 → 12/01/18

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@inproceedings{4c7c6a01533648be9c7e883084a052e4,

title = "Modelling of folding wing-tip devices for gust loads alleviation",

abstract = "High aspect ratio wings have been the focus of recent aircraft designs for improved fuel consumption through reducing induced drag. The increase in wing span has also led to folding wing-tips being introduced as a solution for meeting airport gate requirements. Recent studies have suggested such a folding wing-tip solution may be incorporated with spring devices in order to provide an additional gust loads alleviation ability in flight. The current work examines the suitability of using the Doublet-Lattice Method and the Unsteady Vortex-Lattice Method for modelling the dynamic response of such a folding wing-tip device and found that the Doublet-Lattice Method tends to over-predict the achievable gust loads alleviation because it cannot fully capture the coupling between folding and the change in local angle of attack of the wing-tip. Additional analysis also found that when using the Unsteady Vortex-Lattice Method, choosing large displacement method over linear method for solving the structural response only produced minimal difference.",

author = "Cheung, \{R. C.M.\} and C. Wales and D. Rezgui and Cooper, \{J. E.\} and T. Wilson",

year = "2018",

month = jan,

day = "8",

doi = "10.2514/6.2018-0462",

language = "English",

booktitle = "2018 AIAA/ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conference",

publisher = "American Institute of Aeronautics and Astronautics Inc. (AIAA)",

address = "United States",

note = "AIAA/ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conference, AIAA SciTech Forum, SciTech 2018 ; Conference date: 08-01-2018 Through 12-01-2018",

}

Cheung, RCM, Wales, C , Rezgui, D , Cooper, JE & Wilson, T 2018, Modelling of folding wing-tip devices for gust loads alleviation. in 2018 AIAA/ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conference., AIAA 2018-0462, American Institute of Aeronautics and Astronautics Inc. (AIAA), AIAA/ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conference, AIAA SciTech Forum, Kissimmee, Florida, United States, 8/01/18. https://doi.org/10.2514/6.2018-0462

Modelling of folding wing-tip devices for gust loads alleviation. / Cheung, R. C.M.; Wales, C.; Rezgui, D. et al.
2018 AIAA/ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conference. American Institute of Aeronautics and Astronautics Inc. (AIAA), 2018. AIAA 2018-0462.

Research output: Chapter in Book/Report/Conference proceeding › Conference Contribution (Conference Proceeding)

TY - GEN

T1 - Modelling of folding wing-tip devices for gust loads alleviation

AU - Cheung, R. C.M.

AU - Wales, C.

AU - Rezgui, D.

AU - Cooper, J. E.

AU - Wilson, T.

PY - 2018/1/8

Y1 - 2018/1/8

N2 - High aspect ratio wings have been the focus of recent aircraft designs for improved fuel consumption through reducing induced drag. The increase in wing span has also led to folding wing-tips being introduced as a solution for meeting airport gate requirements. Recent studies have suggested such a folding wing-tip solution may be incorporated with spring devices in order to provide an additional gust loads alleviation ability in flight. The current work examines the suitability of using the Doublet-Lattice Method and the Unsteady Vortex-Lattice Method for modelling the dynamic response of such a folding wing-tip device and found that the Doublet-Lattice Method tends to over-predict the achievable gust loads alleviation because it cannot fully capture the coupling between folding and the change in local angle of attack of the wing-tip. Additional analysis also found that when using the Unsteady Vortex-Lattice Method, choosing large displacement method over linear method for solving the structural response only produced minimal difference.

AB - High aspect ratio wings have been the focus of recent aircraft designs for improved fuel consumption through reducing induced drag. The increase in wing span has also led to folding wing-tips being introduced as a solution for meeting airport gate requirements. Recent studies have suggested such a folding wing-tip solution may be incorporated with spring devices in order to provide an additional gust loads alleviation ability in flight. The current work examines the suitability of using the Doublet-Lattice Method and the Unsteady Vortex-Lattice Method for modelling the dynamic response of such a folding wing-tip device and found that the Doublet-Lattice Method tends to over-predict the achievable gust loads alleviation because it cannot fully capture the coupling between folding and the change in local angle of attack of the wing-tip. Additional analysis also found that when using the Unsteady Vortex-Lattice Method, choosing large displacement method over linear method for solving the structural response only produced minimal difference.

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U2 - 10.2514/6.2018-0462

DO - 10.2514/6.2018-0462

M3 - Conference Contribution (Conference Proceeding)

AN - SCOPUS:85044615011

BT - 2018 AIAA/ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conference

PB - American Institute of Aeronautics and Astronautics Inc. (AIAA)

T2 - AIAA/ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conference, AIAA SciTech Forum

Y2 - 8 January 2018 through 12 January 2018

ER -

Modelling of folding wing-tip devices for gust loads alleviation

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Testing of Folding Wing-Tip for Gust Load Alleviation in High Aspect Ratio Wing

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