Conceptual-level Evaluation of a Variable Stiffness Skin for a Morphing Wing Leading Edge
C Wang, H Haddad Khodaparast, MI Friswell (Swansea University), A Magrini, R Ponza, E Benini (HIT09, Italy), V Landersheim, D Laveuve & C Contell Asins (Fraunhofer Institute for Structural Durability and System Reliability LBF, Germany)
IMechE Part G: Journal of Aerospace Engineering, Vol. 233, No. 15, December 2019, pp. 5703-5716
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.
This material has been published in the IMechE Part G: Journal of Aerospace Engineering, Vol. 233, No. 15, December 2019, pp. 5703-5716, the only definitive repository of the content that has been certified and accepted after peer review. Copyright and all rights therein are retained by Sage.
Link to paper using doi: 10.1177/0954410019855576
IMechE Part G: Journal of Aerospace Engineering