Testing of Wing-Tip Spring Device for Gust Loads Alleviation

Cheung, Ronald C.; Castrichini, Andrea; Rezgui, Djamel; Cooper, Jonathan E.; Wilson, Thomas

doi:10.2514/6.2017-0630

Cited by 7 publications

(8 citation statements)

References 16 publications

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“…With such results in hand, a comparison against spatial and loads requirements of a set of conventional tubular swept wing aircraft wings is made in Section IV to assess the scalability of the system to civil applications. The paper concludes with a general discussion on the applicability of these results and impact on the flared folding wingtip design considered for loads alleviation [24][25][26][27].…”

Section: Project Motivationmentioning

confidence: 95%

“…Mathematical models of a flared folding wingtip device fitted on a large civil aircraft have led to the assessment of the gust load alleviation capabilities [24] and impact on roll dynamics of the aircraft [25]. Wind tunnel tests have also highlighted the loads alleviation potential of the wingtip on a sub-scale model [26]. A summary of the findings around the use of folding hinged wingtips [27] was also published as part of the same project.…”

Section: Project Motivationmentioning

confidence: 99%

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In-flight Folding Wingtip System: Inspiration from the XB-70 Valkyrie

Dussart

Lone

O'Rourke

et al. 2019

AIAA Scitech 2019 Forum

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Wingtip folding can be used to extend aircraft wingspan, allowing designers to take advantage of reduced induced drag whilst respecting ground operational limitations. Such devices can also be used in-flight for a variety of other benefits including load alleviation and flight control. The majority of in-flight folding research takes inspiration in past developments made on the XB-70 Valkyrie, which used the folding devices for stability and lift performance benefits. In this paper, the authors investigate the capabilities of the folding wingtip system and potential scaling to large civil aircraft. Manufacturing details are used to size the actuators whilst the aerodynamic loading acting on the wingtip hinges is found from flight test results. Dimensions and aerodynamic loading at cruise of a set of conventional civil aircraft wing are used to evaluate the scaling potential of the system for controlled in-flight folding. An estimate of the weight penalty due to the folding device is also given and compared to structural weight savings on the XB-70. The results presented herein help in the evaluation of conventional actuator limits for in-flight folding using arguably the most inspiring military example of wingtip folding so far.

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Section: Project Motivationmentioning

confidence: 95%

Section: Project Motivationmentioning

confidence: 99%

In-flight Folding Wingtip System: Inspiration from the XB-70 Valkyrie

Dussart

Lone

O'Rourke

et al. 2019

AIAA Scitech 2019 Forum

Self Cite

View full text Add to dashboard Cite

show abstract

“…Mathematical models of a flared folding wingtip device fitted on a large civil aircraft have led to the assessment of the gust load alleviation capabilities (Castrichini et al, 2016) and impact on roll dynamics of the aircraft . Wind tunnel tests also highlighted the loads alleviation potential of the wingtip on a sub-scale model (Cheung, Castrichini, & Cooper, 2017;Cheung, Rezgui, Cooper, & Wilson, 2018. A summary of the findings around the use of folding hinged wingtips (Wilson et al, 2017) was also published as part of the same project.…”

Section: Application To Large Civil Aircraftmentioning

confidence: 99%

In-flight Wingtip Folding: Inspiration from the XB-70 Valkyrie

Dussart¹,

Lone²,

O'Rourke³

et al. 2019

IJAAA

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“…Cheung et al 14 performed a series of low-speed wind tunnel tests using a flared hinged folding wingtip device.…”

Section: Introductionmentioning

confidence: 99%

The effect of folding wingtips on the worst-case gust loads of a simplified aircraft model

Balatti

Khodaparast

Friswell

et al. 2021

Proceedings of the Institution of Mechanical Engineers, Part G:

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In recent years, the development of lighter and more efficient transport aircraft has led to an increased focus on gust load alleviation. A recent strategy is based on the use of folding wingtip devices that increase the aspect ratio and therefore improve the aircraft performance. Moreover, numerical studies have suggested such a folding wingtip solution may incorporate spring devices in order to provide additional gust load alleviation ability in flight. It has been shown that wingtip mass, stiffness connection and hinge orientation are key parameters to avoid flutter and achieve load alleviation during gusts. The objective of this work is to show the effects of aeroelastic hinged wingtip on the problem of worst-case gust prediction and the parameterization and optimization of such a model for this particular problem, that is, worst-case gust load prediction. In this article, a simplified aeroelastic model of full symmetric aircraft with rigid movable wingtips is developed. The effects of hinge position, orientation and spring stiffness are considered in order to evaluate the performance of this technique for gust load alleviation. In addition, the longitudinal flight dynamics of a rigid aircraft with an elastic wing and folding wingtips is studied. Multi-objective optimizations are performed using a genetic algorithm to exploit the optimal combinations of the wingtip parameters that minimize the gust response for the whole flight envelope while keeping flutter speed within the safety margin. Two strategies to increase flutter speed based on the modification of the wingtip parameters are presented.

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Testing of Wing-Tip Spring Device for Gust Loads Alleviation

Cited by 7 publications

References 16 publications

In-flight Folding Wingtip System: Inspiration from the XB-70 Valkyrie

In-flight Folding Wingtip System: Inspiration from the XB-70 Valkyrie

In-flight Wingtip Folding: Inspiration from the XB-70 Valkyrie

The effect of folding wingtips on the worst-case gust loads of a simplified aircraft model

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