Application of a Morphing Wing Technology on Hydra Technologies Unmanned Aerial System UAS-S4

Gabor, Oliviu Şugar; Simon, Antoine; Koreanschi, Andreea; Botez, Ruxandra Mihaela

doi:10.1115/imece2014-37619

Cited by 12 publications

(4 citation statements)

References 29 publications

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“…For the research presented in this paper, optimized airfoils were obtained for several flight cases: Mach number 0.15 and angles of attack between -3° to +3°. The new airfoil shapes were obtained using an in-house developed optimization algorithm coupled with Xfoil aerodynamic solver for estimation of the lift and drag performance of the airfoils [16,17]. Figure 4 presents an example of the shape optimization results.…”

Section: Application Of the Morphing Wing Concept On Uas-s4mentioning

confidence: 99%

Morphing Wing Application on Hydra Technologies UAS-S4

Segui¹,

Gabor²,

Koreanschi³

et al. 2017

Modelling, Identification and Control

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This paper presents the aerodynamic results of a morphing wing study performed on the UAS S4 Éhecatl from Hydra Technologies. Only the cruise phase of the aircraft was considered (constant altitude and constant speed). The difference, from an aerodynamic point of view, between the morphing wing and the original wing was emphasized by computing and comparing their longitudinal aerodynamic coefficients (drag and lift). The computation of the aerodynamic characteristics was done using tornado with the Vortex Lattice Method.

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Section: Application Of the Morphing Wing Concept On Uas-s4mentioning

confidence: 99%

Morphing Wing Application on Hydra Technologies UAS-S4

Segui¹,

Gabor²,

Koreanschi³

et al. 2017

Modelling, Identification and Control

Self Cite

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“…Various active and passive flow control technologies have been developed and applied in diverse practical applications [10][11][12][13][14][15][16]. Morphing technology can enhance an aircraft's performance using various parameters, including lift, drag, and flow separation control [17][18][19][20][21]. During flight, mission requirements frequently change, and aircraft often operate in less-than-ideal conditions.…”

Section: Introductionmentioning

confidence: 99%

Numerical Simulation of the Transient Flow around the Combined Morphing Leading-Edge and Trailing-Edge Airfoil

Bashir,

Negahban,

Botez

et al. 2024

Biomimetics

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An integrated approach to active flow control is proposed by finding both the drooping leading edge and the morphing trailing edge for flow management. This strategy aims to manage flow separation control by utilizing the synergistic effects of both control mechanisms, which we call the combined morphing leading edge and trailing edge (CoMpLETE) technique. This design is inspired by a bionic porpoise nose and the flap movements of the cetacean species. The motion of this mechanism achieves a continuous, wave-like, variable airfoil camber. The dynamic motion of the airfoil’s upper and lower surface coordinates in response to unsteady conditions is achieved by combining the thickness-to-chord (t/c) distribution with the time-dependent camber line equation. A parameterization model was constructed to mimic the motion around the morphing airfoil at various deflection amplitudes at the stall angle of attack and morphing actuation start times. The mean properties and qualitative trends of the flow phenomena are captured by the transition SST (shear stress transport) model. The effectiveness of the dynamically morphing airfoil as a flow control approach is evaluated by obtaining flow field data, such as velocity streamlines, vorticity contours, and aerodynamic forces. Different cases are investigated for the CoMpLETE morphing airfoil, which evaluates the airfoil’s parameters, such as its morphing location, deflection amplitude, and morphing starting time. The morphing airfoil’s performance is analyzed to provide further insights into the dynamic lift and drag force variations at pre-defined deflection frequencies of 0.5 Hz, 1 Hz, and 2 Hz. The findings demonstrate that adjusting the airfoil camber reduces streamwise adverse pressure gradients, thus preventing significant flow separation. Although the trailing-edge deflection and its location along the chord influence the generation and separation of the leading-edge vortex (LEV), these results show that the combined effect of the morphing leading edge and trailing edge has the potential to mitigate flow separation. The morphing airfoil successfully contributes to the flow reattachment and significantly increases the maximum lift coefficient (cl,max)). This work also broadens its focus to investigate the aerodynamic effects of a dynamically morphing leading and trailing edge, which seamlessly transitions along the side edges. The aerodynamic performance analysis is investigated across varying morphing frequencies, amplitudes, and actuation times.

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“…Morphing optimisation has revealed that optimised lift and drag coefficients can be obtained at different flight conditions. The use of morphing wing technology as a flow control technique has resulted in efficient aerodynamic designs [15,[28][29][30]. Dynamic stall control is especially significant because it occurs in all aerospace applications, such as on UAVs [31,32], helicopter rotors [33,34], wind turbines [35,36] and military aircraft [37,38].…”

Section: Introductionmentioning

confidence: 99%

Numerical investigation of the dynamic stall reduction on the UAS-S45 aerofoil using the optimised aerofoil method

Bashir,

Zonzini,

Longtin Martel

et al. 2023

Aeronaut. j.

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This paper investigates the effect of the optimised morphing leading edge (MLE) and the morphing trailing edge (MTE) on dynamic stall vortices (DSV) for a pitching aerofoil through numerical simulations. In the first stage of the methodology, the optimisation of the UAS-S45 aerofoil was performed using a morphing optimisation framework. The mathematical model used Bezier-Parsec parametrisation, and the particle swarm optimisation algorithm was coupled with a pattern search with the aim of designing an aerodynamically efficient UAS-45 aerofoil. The $\gamma - R{e_\theta }$ transition turbulence model was firstly applied to predict the laminar to turbulent flow transition. The morphing aerofoil increased the overall aerodynamic performances while delaying boundary layer separation. Secondly, the unsteady analysis of the UAS-S45 aerofoil and its morphing configurations was carried out and the unsteady flow field and aerodynamic forces were analysed at the Reynolds number of 2.4 × 106 and five different reduced frequencies of k = 0.05, 0.08, 1.2, 1.6 and 2.0. The lift ( ${C_L})$ , drag ( ${C_D})$ and moment ( ${C_M})\;$ coefficients variations with the angle-of-attack of the reference and morphing aerofoils were compared. It was found that a higher reduced frequencies of 1.2 to 2 stabilised the leading-edge vortex that provided its lift variation in the dynamic stall phase. The maximum lift $\left( {{C_{L,max}}} \right)$ and drag $\left( {{C_{D,max}}} \right)\;$ coefficients and the stall angles of attack are evaluated for all studied reduced frequencies. The numerical results have shown that the new radius of curvature of the MLE aerofoil can minimise the streamwise adverse pressure gradient and prevent significant flow separation and suppress the formation of the DSV. Furthermore, it was shown that the morphing aerofoil delayed the stall angle-of-attack by 14.26% with respect to the reference aerofoil, and that the ${C_{L,max}}\;$ of the aerofoil increased from 2.49 to 3.04. However, while the MTE aerofoil was found to increase the overall lift coefficient and the ${C_{L,max}}$ , it did not control the dynamic stall. Vorticity behaviour during DSV generation and detachment has shown that the MTE can change the vortices’ evolution and increase vorticity flux from the leading-edge shear layer, thus increasing DSV circulation. The conclusion that can be drawn from this study is that the fixed drooped morphing leading edge aerofoils have the potential to control the dynamic stall. These findings contribute to a better understanding of the flow analysis of morphing aerofoils in an unsteady flow.

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Application of a Morphing Wing Technology on Hydra Technologies Unmanned Aerial System UAS-S4

Cited by 12 publications

References 29 publications

Morphing Wing Application on Hydra Technologies UAS-S4

Morphing Wing Application on Hydra Technologies UAS-S4

Numerical Simulation of the Transient Flow around the Combined Morphing Leading-Edge and Trailing-Edge Airfoil

Numerical investigation of the dynamic stall reduction on the UAS-S45 aerofoil using the optimised aerofoil method

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