Lessons learned from wind tunnel testing of a droop-nose morphing wingtip

Vasista, Srinivas; Riemenschneider, Johannes; Kamp, Bram van de; Monner, Hans Peter; Cheung, Ronald C.; Wales, Christopher J A; Cooper, Jonathan

doi:10.1117/12.2219163

Cited by 2 publications

(2 citation statements)

References 16 publications

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“…As shown in Figure 1.8, experiments were performed to assess the morphing structure under aerodynamic loads. Lessons were learned on several aspects of the morphing wingtip [60], which gave meaningful experience and recommendations to morphing structures on a larger scale. A well-known commercial example is the 'Active winglet' developed by Tamarack® [61], which has been certified and applied on business jets.…”

Section: Background and Classificationmentioning

confidence: 99%

“…The results from the equivalent method have a small error (less than 1%) compared to the detailed finite element analysis. Required actuation force for the target rotation angle 60 From another perspective, the required angle, which is the rotation angle for a specific aerodynamic force, determines the required actuation force. Different to the conventional structure the actuation force actively takes part in determining the structure's geometry.…”

Section: Influence Of the Unsymmetrical Stiffnessmentioning

confidence: 99%

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Design and Optimisation of Morphing Aircraft

Wang¹

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Section: Background and Classificationmentioning

confidence: 99%

Section: Influence Of the Unsymmetrical Stiffnessmentioning

confidence: 99%

Design and Optimisation of Morphing Aircraft

Wang¹

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Conceptual-level evaluation of a variable stiffness skin for a morphing wing leading edge

Wang

Khodaparast

Friswell

et al. 2019

Proceedings of the Institution of Mechanical Engineers, Part G:

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A morphing leading edge produces a continuous aerodynamic surface that has no gaps between the moving and fixed parts. The continuous seamless shape has the potential to reduce drag, compared to conventional devices, such as slats that produce a discrete aerofoil shape change. However, the morphing leading edge has to achieve the required target shape by deforming from the baseline shape under the aerodynamic loads. In this paper, a conceptual-level method is proposed to evaluate the morphing leading edge structure. The feasibility of the skin design is validated by checking the failure index of the composite when the morphing leading edge undergoes the shape change. The stiffness of the morphing leading edge skin is spatially varied using variable lamina angles, and comparisons to the skin with constant stiffness are made to highlight its potential to reduce the actuation forces. The structural analysis is performed using a two-level structural optimisation scheme. The first level optimisation is applied to find the optimised structural properties of the leading edge skin and the associated actuation forces. The structural properties of the skin are given as a stiffness distribution, which is controlled by a B spline interpolation function. In the second level, the design solution of the skin is investigated. The skin is assumed to be made of variable stiffness composite. The stack sequence of the composite is optimised element-by-element to match the target stiffness. A failure criterion is employed to obtain the failure index when the leading edge is actuated from the baseline shape to the target shape. Test cases are given to demonstrate that the optimisation scheme is able to provide the stiffness distribution of the leading edge skin and the actuation forces can be reduced by using a spatially variable stiffness skin.

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Lessons learned from wind tunnel testing of a droop-nose morphing wingtip

Cited by 2 publications

References 16 publications

Design and Optimisation of Morphing Aircraft

Design and Optimisation of Morphing Aircraft

Conceptual-level evaluation of a variable stiffness skin for a morphing wing leading edge

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