Comparison of Constrained Parameterisation Strategies for Aerodynamic Optimisation of Morphing Leading Edge Airfoil

A Magrini, E Benini, R Ponza (HIT09, Italy), C Wang, H Haddad Khodaparast, MI Friswell (Swansea University), V Landersheim, D Laveuve & C Contell Asins (Fraunhofer Institute for Structural Durability and System Reliability LBF, Germany)

Aerospace, Vol. 6, No. 3, March 2019, paper 31


In the context of ambitious targets of reducing environmental impact of the aviation sector, dictated by international institutions, morphing aircraft are expected to have the potential of achieving the required efficiency increase. However, there are still open issues related to the design and implementation of deformable structures. In this paper, we compare strategies for the aerodynamic design of a morphing leading edge, representing a potential substitute of traditional high-lift systems. In order to facilitate the structural design and promote the feasibility of solutions, we solve a multi-objective optimisation problem including constraints on axial and bending strain introduced by morphing. A parameterisation method inherently producing constant arc length curves is employed in three variants, representing different morphing strategies that provide an increasing level of deformability. The results for the optimisation of a baseline geometry show that the geometric constraints are effectively handled in the optimisation and the solutions are smooth, with a continuous variation along the Pareto frontier. The larger shape modification allowed by more flexible parameterisation variants enables a further increase of maximum lift and efficiency, also with a deployed trailing edge flap, reducing the gap with discrete slat devices currently employed.

Paper Availability

This material has been published in the Aerospace, Vol. 6, No. 3, March 2019, paper 31. The paper is published as an open access paper.

Link to paper using doi: 10.3390/aerospace6030000

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