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 proceedingConference Contribution (Conference Proceeding)

1 Citation (Scopus)
428 Downloads (Pure)


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 languageEnglish
Title of host publication2018 AIAA/ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conference
PublisherAmerican Institute of Aeronautics and Astronautics Inc. (AIAA)
Number of pages12
ISBN (Electronic)9781624105326
Publication statusPublished - 8 Jan 2018
EventAIAA/ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conference, AIAA SciTech Forum - Gaylord Palms , Kissimmee, United States
Duration: 8 Jan 201812 Jan 2018


ConferenceAIAA/ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conference, AIAA SciTech Forum
Abbreviated titleSciTech 2018
Country/TerritoryUnited States


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