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4. Design of morphing wing for aerodynamic performance considering the wing flexibility effects

Author

Navrátil, Jan, Hostinský, Vladimír, Sodja, Jurij, Navrátil, Jan, Hostinský, Vladimír, and Sodja, Jurij

Abstract

This paper provides an insight into ongoing research aimed at designing a morphing wing with the ability to continuously adapt its aerodynamic shape. The wing is targeted at a general purpose unmanned aerial vehicle. The morphing wing concept outlined in the paper is based on continuous camber changes of the wing leading and trailing edges, allowing optimal performance in different flight regimes. The aeroelastic tailoring method is used to design the load carrying structure of the wing in order to define the optimal stiffness and strength of the structure, which are considered as fixed in subsequent design steps. The research proposes a novel modular design approach that combines aerodynamic shape optimisation and aeroelastic considerations for designing morphing wing surfaces.

Published
2024

15. Overview of the SmartX Wing Technology Integrator

Author

De Breuker, Roeland, primary, Mkhoyan, Tigran, additional, Nazeer, Nakash, additional, Stuber, Vincent, additional, Wang, Xuerui, additional, Mkhoyan, Iren, additional, Groves, Roger, additional, van der Zwaag, Sybrand, additional, and Sodja, Jurij, additional

Published
2022
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29. Experimental evaluation of a morphing leading edge concept

Author

Sodja, Jurij, Martinez, Marcias J., Simpson, John, Breuker, Roeland De, and Publica

Abstract

This article presents an experimental evaluation of a morphing leading edge demonstrator by investigating its morphed shape, the level of induced strains in the airfoil skin, the actuation force, and the morphing mechanism's capability to lock and transfer the applied loads. In addition, a finite element model of the demonstrator is assembled comprising an elastic morphing skin and a kinematic morphing mechanism. The obtained results are used to assess whether the demonstrator performs according to the design objectives, such as the target shape, the character of the morphing deformation and the morphing mechanism locking, applied during the design process. The comparison between experimental and numerical results yielded a good agreement in terms of observed morphed shape and pertaining strains. The average difference in morphed shape was less than 0.08% chord at the maximum actuator extension. The observed difference in the respective strains was less than 400 micro-strains. A significant difference, up to 70%, was observed in the actuation force, which was attributed to the modelling assumptions and to the force measurement technique employed in the experiment. Nevertheless, both results show good qualitative agreement showing similar trends.

Published
2019

30. Ground Testing of the FLEXOP Demonstrator Aircraft

Author

Sodja, Jurij, primary, De Breuker, Roeland, additional, Meddaikar, Yasser M., additional, Dillinger, Johannes K., additional, Soal, Keith, additional, Govers, Yves, additional, Krueger, Wolf, additional, Georgopoulos, Panagiotis, additional, Koimtzoglou, Christos, additional, Roessler, Christian, additional, Koeberle, Sebastian J., additional, Bartasevicius, Julius, additional, Teubl, Daniel, additional, Gyulai, Laszlo, additional, Toth, Szabolcs, additional, Nagy, Mihaly, additional, Balogh, Daniel, additional, Jasdi, Miklos, additional, Bauer, Péter, additional, and Vanek, Balint, additional

Published
2020
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32. Results of an Aeroelastically Tailored Wing on the FLEXOP Demonstrator Aircraft

Author

Roessler, Christian, primary, Bartasevicius, Julius, additional, Koeberle, Sebastian J., additional, Teubl, Daniel, additional, Hornung, Mirko, additional, Meddaikar, Yasser M., additional, Dillinger, Johannes K., additional, Wustenhagen, Matthias, additional, Kier, Thiemo M., additional, Looye, Gertjan, additional, Sodja, Jurij, additional, De Breuker, Roeland, additional, Luspay, Tamas, additional, Vanek, Balint, additional, Georgopoulos, Panagiotis, additional, and Koimtzoglou, Christos, additional

Published
2020
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34. Aircraft Design and Testing of FLEXOP Unmanned Flying Demonstrator to Test Load Alleviation and Flutter Suppression of High Aspect Ratio Flexible Wings

Author

Roessler, Christian, primary, Stahl, Philipp, additional, Sendner, Franz, additional, Hermanutz, Andreas, additional, Koeberle, Sebastian, additional, Bartasevicius, Julius, additional, Rozov, Vladyslav, additional, Breitsamter, Christian, additional, Hornung, Mirko, additional, Meddaikar, Yasser M., additional, Dillinger, Johannes, additional, Sodja, Jurij, additional, De Breuker, Roeland, additional, Koimtzoglou, Christos, additional, Kotinis, Dimitrios, additional, and Georgopoulos, Panagiotis, additional

Published
2019
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49. Aeroelastic Characterization of a Flexible Wing Using Particle Tracking Velocimetry Measurements.

Author

Mertens, Christoph, de Rojas Cordero, Tomás, Sodja, Jurij, Sciacchitano, Andrea, and van Oudheusden, Bas W.

Abstract

The aerodynamic, elastic, and inertial components in Collar's triangle of forces acting on a flexible wing with span width s=1.75 m and chord c=0.25 m are determined based on integrated optical measurements of the structural and aerodynamic response to steady and unsteady periodic inflow conditions at a chord-based Reynolds number of 2.3×105. The measurement device is a coaxial volumetric velocimeter mounted on a robotic arm, which is used to perform optical measurements of fiducial markers on the wing surface, and helium-filled soap bubbles, which are used as flow tracers. The optical measurements of the structural markers and the flow tracers are both processed with the Lagrangian particle tracking algorithm Shake-the-Box. Subsequently, physical models are used to determine the inertial and elastic forces of the aeroelastic interaction from the marker tracking results, and to determine the unsteady aerodynamic lift force from the flow velocity fields. The results of this integrated aeroelastic characterization approach are in physical agreement with each other according to the equilibrium of forces in Collar's triangle and good agreement with external reference measurements. [ABSTRACT FROM AUTHOR]

Published
2022
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