Experimental Investigation into the Control and Load Alleviation Capabilities of Articulated Winglets

Gatto, A.; Bourdin, P.

doi:10.1155/2012/789501

Cited by 11 publications

(6 citation statements)

References 18 publications

Supporting

Mentioning

Contrasting

Order By: Relevance

“…The rolling moment coefficient range achieved with FOLDERONS is 0.008 ≤ ∆Cl ≤ 0.041. This is around 2.5-times smaller than the rolling moment coefficient achieved with conventional ailerons, which can produce a moment coefficient range of around 0.027 ≤ ∆Cl ≤ 0.087 [7]. This clearly shows that FOLDERONS cannot fully replace conventional ailerons, but can augment their performance, which allows smaller ailerons and, hence, lighter wing design to be achieved.…”

Section: Rolling Moment Variationmentioning

confidence: 90%

“…The system showed a maximum roll authority (one winglet at 75 degrees dihedral) coefficient of rolling moment change of ∆Cl = 0.0365, which equates to ∆Cl/∆Γ = 0.0279 rad −1 . By comparing this directly to the values of an aileron on a large transport aircraft, 0.027 ≤ ∆Cl ≤ 0.087 [7], the comparability is evident. By taking into account deflection angles, it was discussed that ailerons are more efficient per degree of deflection.…”

Section: Parametermentioning

confidence: 97%

“…Furthermore, Smith et al [6] conducted a computational study followed by experimental validation on the use of folding wingtips to enhance the aerodynamic efficiency of transport aircraft. Bourdin et al [5] and Gatto et al [7] investigated the use of articulated winglets for flight control and load alleviation of a flying wing. Their studies used the same baseline flying wing as was presented in [4], and the aim was to collect experimental data to prove the concept of using articulated winglets for full control.…”

Section: Parametermentioning

confidence: 99%

See 2 more Smart Citations

Flight Dynamics and Control Using Folding Wingtips: An Experimental Study

Mills

Ajaj

2017

Aerospace

View full text Add to dashboard Cite

This paper presents an experimental investigation on using FOLDing wingtips sERving as cONtrol effectorS (FOLDERONS) for a mini Unmanned Aerial Vehicle (UAV). A representative off-the-shelf mini-UAV with a conventional configuration was selected. The main theme of this paper is to utilise FOLDERONS as a control effector (mainly in roll) to augment the control authority of conventional control surfaces. Furthermore, the impact of actuation rate on the effectiveness of FOLDERONS is assessed. The paper describes the preliminary and detailed design and sizing of the morphing wing. In addition, the manufacturing of the wing system and its integration with the UAV are addressed. Wind-tunnel testing in the RJ Mitchell wind-tunnel at the University of Southampton was performed. Both static (straight and sideslip) and dynamic (straight flight) tests are conducted at a range of airspeeds and Angles Of Attack (AOAs). The impact of folding wingtips on the lateral and directional stability is analysed. The main finding of this paper is that FOLDERONS are effective (especially at large dynamic pressure and AOAs) in controlling the lateral and directional stability. Finally, this study shows that FOLDERONS cannot fully replace conventional ailerons especially at low dynamic pressures, and their strong dependence on the AOA makes them prone to a roll reversal phenomena when the wing (and FOLDERONS) is operating at negative AOAs.

show abstract

Section: Rolling Moment Variationmentioning

confidence: 90%

Section: Parametermentioning

confidence: 97%

Section: Parametermentioning

confidence: 99%

See 1 more Smart Citation

Flight Dynamics and Control Using Folding Wingtips: An Experimental Study

Mills

Ajaj

2017

Aerospace

View full text Add to dashboard Cite

show abstract

“…Besides significant aerodynamic benefits allowing reduced fuel consumption, morphing winglets have attracted growing attention in aviation because of their adaptive ability to lower wing-bending moments and increase aircraft flight stability in response to changing flight conditions. Several morphing winglet concepts have been patented [31,32], or are being developed [33,34], to alleviate gust loads and control the wing lift distribution over the wingspan through adaptive geometries. For the purpose of this research, the morphing winglet developed by CIRA is investigated for regional aircraft application.…”

Section: Morphing Winglet Conceptmentioning

confidence: 99%

Integrated Design of a Morphing Winglet for Active Load Control and Alleviation of Turboprop Regional Aircraft

et al. 2021

View full text Add to dashboard Cite

Aircraft winglets are well-established devices that improve aircraft fuel efficiency by enabling a higher lift over drag ratios and lower induced drag. Retrofitting winglets to existing aircraft also increases aircraft payload/range by the same order of the fuel burn savings, although the additional loads and moments imparted to the wing may impact structural interfaces, adding more weight to the wing. Winglet installation on aircraft wing influences numerous design parameters and requires a proper balance between aerodynamics and weight efficiency. Advanced dynamic aeroelastic analyses of the wing/winglet structure are also crucial for this assessment. Within the scope of the Clean Sky 2 REG IADP Airgreen 2 project, targeting novel technologies for next-generation regional aircraft, this paper deals with the integrated design of a full-scale morphing winglet for the purpose of improving aircraft aerodynamic efficiency in off-design flight conditions, lowering wing-bending moments due to maneuvers and increasing aircraft flight stability through morphing technology. A fault-tolerant morphing winglet architecture, based on two independent and asynchronous control surfaces with variable camber and differential settings, is presented. The system is designed to face different flight situations by a proper action on the movable control tabs. The potential for reducing wing and winglet loads by means of the winglet control surfaces is numerically assessed, along with the expected aerodynamic performance and the actuation systems’ integration in the winglet surface geometry. Such a device was designed by CIRA for regional aircraft installation, whereas the aerodynamic benefits and performance were estimated by ONERA on the natural laminar flow wing. An active load controller was developed by PoliMI and UniNA performed aeroelastic trade-offs and flutter calculations due to the coupling of winglet movable harmonics and aircraft wing bending and torsion.

show abstract

“…Due to the significant moment arm between the root and tip of a wing, morphing wingtip devices have received considerable interest. The current research can generally be split into passive and active solutions, split across 3 major design motivations: control authority [10][11][12], optimising aircraft performance across different flight phases [13][14][15][16], and load alleviation [17][18][19][20][21]. Many of these devices can also be used to reduce the overall span of an aircraft on the ground, enabling next-generation aircraft configurations, which aim to reduce the lift-induced drag produced by an airframe by increasing the wingspan, to still use current airport infrastructure.…”

Section: Introductionmentioning

confidence: 99%

Experimental Analysis of the Dynamics of Flared Folding Wingtips via a Novel Tethered Flight Test

Healy

Pontillo

Rezgui

et al. 2022

AIAA SCITECH 2022 Forum

View full text Add to dashboard Cite

Recent developments in morphing wing technologies are routinely tested using Unmanned Aerial vehicles (UAVs) due to their relatively low cost and time to manufacture. However, atmospheric flight tests limit both the repeatability of the recorded data sets, as well as the bounds of the flight envelope willing to be explored, due to the risk of destroying the UAV. In this paper, a novel flight test method is described, which consists of flying a UAV constrained by a tether, resulting in a steady, controlled, elliptical flight paths. The benefits of such a method are explored numerically to characterise the static and dynamic testing capabilities of such a system. This is then followed by an experimental investigation into the behaviour of semi-aeroelastic hinged (SAH) wingtips, employing the AlbatrossOne remotely piloted vehicle. The tethered model was used to explore the static effect of angle of attack and sideslip angle on the both the equilibrium position of the wingtips and the wingtips stability boundary.

show abstract

Experimental Investigation into the Control and Load Alleviation Capabilities of Articulated Winglets

Cited by 11 publications

References 18 publications

Flight Dynamics and Control Using Folding Wingtips: An Experimental Study

Flight Dynamics and Control Using Folding Wingtips: An Experimental Study

Integrated Design of a Morphing Winglet for Active Load Control and Alleviation of Turboprop Regional Aircraft

Experimental Analysis of the Dynamics of Flared Folding Wingtips via a Novel Tethered Flight Test

Contact Info

Product

Resources

About