Testing of wing-tip spring device for gust loads alleviation

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

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

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Abstract

Recent aircraft designs have begun considering higher aspect ratio wings in order to reduce induced drag for improved fuel efficiency. In order to meet airport gate requirements, folding wing-tips have been introduced as a solution to the increased wing-span. Recent numerical 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. A series of low-speed wind tunnel tests was conducted using a prototype of such a concept and found that a folding wing-tip with a non-zero relative angle of the folding hinge axis to the stream-wise direction can provide gust loads alleviation. It was also concluded that the weight of the wing-tip may have a strong influence on the hinge stiffness necessary for best performance. The findings from these tests agree with previous simulations in a qualitative manner.

Original languageEnglish
Title of host publication58th AIAA/ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conference, 2017
PublisherAmerican Institute of Aeronautics and Astronautics Inc. (AIAA)
Number of pages11
ISBN (Print)9781624104534
DOIs
Publication statusPublished - 2017
EventAIAA SciTech Forum 2017: 58th AIAA/ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conference - Texas, Grapevine, United States
Duration: 9 Jan 201713 Jan 2017
Conference number: (AIAA 2017-1355)
https://www.aiaa-scitech.org/

Conference

ConferenceAIAA SciTech Forum 2017
CountryUnited States
CityGrapevine
Period9/01/1713/01/17
Internet address

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