Integrated Multidisciplinary Topology Optimization Approach to Adaptive Wing Design

Maute, Kurt; Reich, Gregory W.

doi:10.2514/1.12802

Cited by 126 publications

(74 citation statements)

References 33 publications

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“…Substantial research in past decades has focused on the aeroelastic modelling of these morphing aircraft using models of different level of complexity [11][12][13] and the optimisation of morphing aircraft by changing the wing sweep, span, chord distribution, and many other wing parameters 14 and by optimising the internal structure of the wing using topology optimisation. 15,16 However there seems to be a lack of a transparent way to discretise a morphing aircraft for optimisation in a way that results in a sufficiently low number of design variables for quick sizing, while not constraining the design space a priori. It was stated by Dr. Anna-Maria Rivas McGowan during a short course on morphing aircraft in Lisbon, Portugal, 2008 17 that there is a need for a set of generic design tools for the conceptual design of morphing aircraft that are at the right level of fidelity, so that the design space can be explored efficiently even with a large number of design variables.…”

Section: Introductionmentioning

confidence: 99%

Feasible Conceptual Design of Morphing Structures

Werter

Breuker

Beaverstock

et al. 2014

22nd AIAA/ASME/AHS Adaptive Structures Conference

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Werter et al. 1 introduced a novel approach to the conceptual design of morphing aircraft by means of a two-level design approach. This paper presents the extension of this model with camber and span morphing. The first level consists of a morphing wing model specific to the concept that is investigated. This is used to identify the types of morphing in the concept and generate the corresponding morphing constraints for the second level. The second level is a generic morphing aeroelastic optimisation framework that is used to optimise the morphing parameters and find the optimal morphing configuration for the flight cases under consideration. The second level also returns the morphing energy requirements to overcome the forces induced by the external loads, which can be used to assess the feasibility of the concept and potentially identify new constraints for a second optimisation run. The design approach has been applied to the optimisation of a wing with twist, camber, shear, and span morphing to illustrate the potential of the design approach. The results clearly show the potential of the morphing technologies and the added information this design approach can give in the conceptual design stage.

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Section: Introductionmentioning

confidence: 99%

Feasible Conceptual Design of Morphing Structures

Werter

Breuker

Beaverstock

et al. 2014

22nd AIAA/ASME/AHS Adaptive Structures Conference

View full text Add to dashboard Cite

show abstract

“…Substantial research in past decades has focused on the aeroelastic modelling of these morphing aircraft using models of different level of complexity [10][11][12] and the optimisation of morphing aircraft by changing the wing sweep, span, chord distribution, and many other wing parameters 13 and by optimising the internal structure of the wing using topology optimisation. 14,15 However there seems to be a lack of a transparent way to discretise a morphing aircraft for optimisation in a way that results in a sufficiently low number of design variables for quick sizing, while not constraining the design space a priori. It was stated by Dr. Anna-Maria Rivas McGowan during a short course on morphing aircraft in Lisbon, Portugal, 2008 16 that there is a need for a set of generic design tools for the conceptual design of morphing aircraft that are at the right level of fidelity, so that the design space can be explored efficiently even with a large number of design variables.…”

Section: Introductionmentioning

confidence: 99%

Two-level Conceptual Design of Morphing Wings

Werter

Breuker

Friswell

et al. 2013

54th AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conference

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This paper introduces a novel approach to the conceptual design of morphing aircraft by means of a two-level design approach. The first level consists of a morphing wing model specific to the concept that is investigated. This is used to identify the types of morphing in the concept and generate the corresponding morphing constraints for the second level. The second level is a generic morphing aeroelastic optimisation framework that is used to optimise the morphing parameters and find the optimal morphing configuration for the flight cases under consideration. The second level also returns the morphing energy requirements to overcome the forces induced by the external loads, which can be used to assess the feasibility of the concept and potentially identify new constraints for a second optimisation run. The design approach has been applied to the optimisation of both a twist morphing wing and shear morphing wing to illustrate the potential of the design approach. The results clearly show the potential of the morphing technologies and the added information this design approach can give in the conceptual design stage.

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“…Thus much research is devoted to understand and optimize extensive types of wing morphing for improving the aircraft performance. [1][2][3][4][5][6] However, extensive wing morphing poses significant design challenges and requires complex mechanical structures and actuators. By contrast limited but smooth morphing of a wing can often be sufficient for the needs of flight (as shown by the minimal movements of the wings of various birds in some flight conditions).…”

Section: Introductionmentioning

confidence: 99%

Measurements of a Symmetric Airfoil Morphed by Macro Fiber Composite Actuators

Bouremel

Chan

Jones

et al. 2014

32nd AIAA Applied Aerodynamics Conference

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This study presents the geometric and aerodynamic properties of a symmetric airfoil model that uses macro fiber composite actuators to change the shape of its upper and lower surfaces. In the design discussed, these thin and light piezoelectric actuators are bonded to the inside and become an integral part of the skin of the upper and lower surfaces of the airfoil. Still-air and wind-tunnel measurements in different flow regimes are performed to assess the characteristics associated with the changes of the shape of the airfoil. The results obtained will be used to design and fabricate a wing with morphing surfaces for testing in a remote-controlled aircraft. Nomenclaturec = model chord C D = drag coefficient C L = lift coefficient C M = pitching-moment coefficient about c/4 D = drag force L = lift force l = local coordinate tangent to the airfoil surface n = local coordinate normal to the airfoil surface Re c = Reynolds number based on the chord s = model span (from wall to wall of the wind tunnel) U = flow velocity x = streamwise coordinate of the wind tunnel y = spanwise coordinate of the wind tunnel z = vertical coordinate of the wind tunnel Greek letters  = angle of attack of the airfoil  = axial (chordwise) coordinate of the airfoil  = normal coordinate of the airfoil Subscripts

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Integrated Multidisciplinary Topology Optimization Approach to Adaptive Wing Design

Cited by 126 publications

References 33 publications

Feasible Conceptual Design of Morphing Structures

Feasible Conceptual Design of Morphing Structures

Two-level Conceptual Design of Morphing Wings

Measurements of a Symmetric Airfoil Morphed by Macro Fiber Composite Actuators

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