Testing of wing-tip spring device for gust loads alleviation

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

doi:10.2514/6.2017-0630

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 proceeding › Conference Contribution (Conference Proceeding)

6 Citations (Scopus)

376 Downloads (Pure)

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 language	English
Title of host publication	58th AIAA/ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conference, 2017
Publisher	American Institute of Aeronautics and Astronautics Inc. (AIAA)
Number of pages	11
ISBN (Print)	9781624104534
DOIs	https://doi.org/10.2514/6.2017-0630
Publication status	Published - 2017
Event	AIAA SciTech Forum 2017: 58th AIAA/ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conference - Texas, Grapevine, United States Duration: 9 Jan 2017 → 13 Jan 2017 Conference number: (AIAA 2017-1355) https://www.aiaa-scitech.org/

Conference

Conference	AIAA SciTech Forum 2017
Country/Territory	United States
City	Grapevine
Period	9/01/17 → 13/01/17
Internet address	https://www.aiaa-scitech.org/

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title = "Testing of wing-tip spring device for gust loads alleviation",

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.",

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

year = "2017",

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

address = "United States",

note = "AIAA SciTech Forum 2017 : 58th AIAA/ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conference ; Conference date: 09-01-2017 Through 13-01-2017",

url = "https://www.aiaa-scitech.org/",

}

Cheung, RCM, Castrichini, A, Rezgui, D , Cooper, JE & Wilson, T 2017, Testing of wing-tip spring device for gust loads alleviation. in 58th AIAA/ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conference, 2017. American Institute of Aeronautics and Astronautics Inc. (AIAA), AIAA SciTech Forum 2017, Grapevine, United States, 9/01/17. https://doi.org/10.2514/6.2017-0630

Testing of wing-tip spring device for gust loads alleviation. / Cheung, R. C M; Castrichini, A.; Rezgui, D. et al.

58th AIAA/ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conference, 2017. American Institute of Aeronautics and Astronautics Inc. (AIAA), 2017.

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

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T1 - Testing of wing-tip spring device for gust loads alleviation

AU - Cheung, R. C M

AU - Castrichini, A.

AU - Rezgui, D.

AU - Cooper, J. E.

AU - Wilson, T.

N1 - Conference code: (AIAA 2017-1355)

PY - 2017

Y1 - 2017

N2 - 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.

AB - 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.

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M3 - Conference Contribution (Conference Proceeding)

SN - 9781624104534

BT - 58th AIAA/ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conference, 2017

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

T2 - AIAA SciTech Forum 2017

Y2 - 9 January 2017 through 13 January 2017

ER -

Testing of wing-tip spring device 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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