Design of a transonic wing with an adaptive morphing trailing edge via aerostructural optimization

Burdette, David A.; Martins, Joaquim R. R. A.

doi:10.1016/j.ast.2018.08.004

Cited by 72 publications

(27 citation statements)

References 31 publications

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“…It is known that it has a large impact on the obtained solution and it should be flexible enough to cover the whole design space, produce smooth shapes, allow a local control of geometrical parameters, and provide a small set of coefficients with, possibly, a direct physical meaning [34]. Various techniques are reported in the literature for morphing problems, including polynomials [35], Radial Basis Function (RBF) [16], Class/Shape Transformation (CST) [17,36], and Free Form Deformation (FFD) [19].…”

Section: Parameterisation Strategymentioning

confidence: 99%

“…A more integrated approach is reported in [18], where concurrent aero-structural optimisation was performed in a multi-disciplinary framework. More recently, [19] employed a multi-disciplinary optimisation (MDO) for a morphing trailing edge of a regional aircraft, where constraints included size parameters and maneuver stress. A static aeroelastic coupling is described in [20], for the Fish Bone Active camber morphing of Swansea University.…”

Section: Introductionmentioning

confidence: 99%

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

et al. 2019

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In the context of ambitious targets for reducing environmental impact in the aviation sector, dictated by international institutions, morphing aircraft are expected to have potential for achieving the required efficiency increases. However, there are still open issues related to the design and implementation of deformable structures. In this paper, we compare three constrained parameterisation strategies for the aerodynamic design of a morphing leading edge, representing a potential substitute for 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 which provide an increasing level of deformability, by allowing the lower edge of the flexible skin to slide and the gap formed with the fixed spar to be closed by a hatch. The results for the optimisation of a baseline airfoil 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 an increase of the maximum lift coefficient up to 8.35%, and efficiency at 70% of stall incidence up to 4.26%.

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Section: Parameterisation Strategymentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

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

et al. 2019

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“…Drag minimisations of wings are common cases within the aerodynamic shape optimisation community [42,43]. Figure 9 presents a coarse representation of a wing using a [2,5,6] layout of design variables.…”

Section: Generation Of Shapes Of Aerodynamic Interestmentioning

confidence: 99%

Parametric Surfaces with Volume of Solid Control for Optimisation of Three Dimensional Aerodynamic Topologies

Payot

Rendall

Allen

2019

AIAA Scitech 2019 Forum

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This paper presents a topologically flexible parameterisation method suitable for the optimisation of 3 dimensional aerodynamics using traditional boundary fitted meshes. This parameterisation extends the restricted-snake volume of solid (RSVS) parameterisation previously developed by the authors. This is achieved by extending restricted snakes, a parametric active contour method, into a restricted surface capable of efficiently evolving arbitrary complex topologies handling collisions with no floating point arithmetic. This is integrated with a surface generation rule which allows smooth shapes with intuitive parameterisation of topology. The 3D-RSVS is presented along with results displaying its smooth behaviour, it's ability to produce shapes of aerodynamic interest and it's topological flexibility. A hierarchical approach to the volume of solid design variables is presented for the RSVS, allowing automatic design of the grids on which VOS are specified. An optimisation framework is proposed and some example 2 dimensional optimisation results are presented.

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“…Most researchers are now investigating how to replace conventional flaps with morphing flaps for better efficiency. Their approaches suggest that even with a small portion of morphing wing a fuel consumption reduction of more than 5% is possible on conventional aircraft [4]. Some of the structural designs are already applied on actual flying aircraft showing the maturation of some technologies [5].…”

Section: Introductionmentioning

confidence: 99%

Investigation of performance gains on a sailplane with morphing wing trailing edge

Lendraitis

2019

mech

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Increasing the performance of a modern sailplane is challenging. Most of the known valid approaches have already been applied in practice. Morphing technology, which could allow to adapt to various flight stages is yet to be applied. An investigation of possible flight performance benefits of such technology is carried out here. Using a genetic algorithm, a morphing trailing edge flap for airfoil HQ-17 is formed for -4° and +12° flap deflections. The performance is evaluated and compared with a regular flap, which shows that for the HQ-17 airfoil, drag could be reduced by up to 36% in comparison with regular flap. To show the advantage of morphing flaps, a hypothetical sailplane wing is modeled and evaluated with morphing and conventional flaps using non-linear LLT method. Results show that incorporation of a morphing flap could extend the flight envelope and increase the L/D ratio by 2-5% trough the full flight speed range.

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Design of a transonic wing with an adaptive morphing trailing edge via aerostructural optimization

Cited by 72 publications

References 31 publications

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

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

Parametric Surfaces with Volume of Solid Control for Optimisation of Three Dimensional Aerodynamic Topologies

Investigation of performance gains on a sailplane with morphing wing trailing edge

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