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Optimization of a Morphing Wing Based on Coupled Aerodynamic and Structural Constraints.

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Title: Optimization of a Morphing Wing Based on Coupled Aerodynamic and Structural Constraints.
Authors: Gamboa, R1, Vale, J.2, Lau, F. J. P.2, Suleman, A.3
Source: AIAA Journal. Sep2009, Vol. 47 Issue 9, p2087-2104. 18p. 9 Diagrams, 6 Charts, 10 Graphs.
Subjects: Remotely piloted vehicles, Speed, Multidisciplinary design optimization, Mathematical optimization, Aerodynamics, Algorithms
Abstract: This paper presents the work done in designing a morphing wing concept for a small experimental unmanned aerial vehicle to improve the vehicle's performance over its intended speed range. The wing is designed with a multidisciplinary design optimization tool, in which an aerodynamic shape optimization code coupled with a structural morphing model is used to obtain a set of optimal wing shapes for minimum drag at different flight speeds. The optimization procedure is described as well as the structural model. The aerodynamic shape optimization code, that uses a viscous two-dimensional panel method formulation coupled with a nonlinear lifting-line algorithm and a sequential quadratic programming optimization algorithm, is suitable for preliminary wing design optimization tasks. The morphing concept, based on changes in wing-planform shape and wing-section shape achieved by extending spars and telescopic ribs, is explained in detail. Comparisons between optimized fixed wing performance, optimal morphing wing performance, and the performance of the wing obtained from the coupled aerodynamic-structural solution are presented. Estimates for the performance enhancements achieved by the unmanned aerial vehicles when fitted with this new morphing wing are also presented. Some conclusions on this concept are addressed with comments on the benefits and drawbacks of the morphing mechanism design. [ABSTRACT FROM AUTHOR]
Copyright of AIAA Journal is the property of American Institute of Aeronautics & Astronautics and its content may not be copied or emailed to multiple sites without the copyright holder's express written permission. Additionally, content may not be used with any artificial intelligence tools or machine learning technologies. However, users may print, download, or email articles for individual use. This abstract may be abridged. No warranty is given about the accuracy of the copy. Users should refer to the original published version of the material for the full abstract. (Copyright applies to all Abstracts.)
Database: Engineering Source
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DbLabel: Engineering Source
An: 44283157
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PubType: Academic Journal
PubTypeId: academicJournal
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  Data: Optimization of a Morphing Wing Based on Coupled Aerodynamic and Structural Constraints.
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  Data: <searchLink fieldCode="JN" term="%22AIAA+Journal%22">AIAA Journal</searchLink>. Sep2009, Vol. 47 Issue 9, p2087-2104. 18p. 9 Diagrams, 6 Charts, 10 Graphs.
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  Data: <searchLink fieldCode="DE" term="%22Remotely+piloted+vehicles%22">Remotely piloted vehicles</searchLink><br /><searchLink fieldCode="DE" term="%22Speed%22">Speed</searchLink><br /><searchLink fieldCode="DE" term="%22Multidisciplinary+design+optimization%22">Multidisciplinary design optimization</searchLink><br /><searchLink fieldCode="DE" term="%22Mathematical+optimization%22">Mathematical optimization</searchLink><br /><searchLink fieldCode="DE" term="%22Aerodynamics%22">Aerodynamics</searchLink><br /><searchLink fieldCode="DE" term="%22Algorithms%22">Algorithms</searchLink>
– Name: Abstract
  Label: Abstract
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  Data: This paper presents the work done in designing a morphing wing concept for a small experimental unmanned aerial vehicle to improve the vehicle's performance over its intended speed range. The wing is designed with a multidisciplinary design optimization tool, in which an aerodynamic shape optimization code coupled with a structural morphing model is used to obtain a set of optimal wing shapes for minimum drag at different flight speeds. The optimization procedure is described as well as the structural model. The aerodynamic shape optimization code, that uses a viscous two-dimensional panel method formulation coupled with a nonlinear lifting-line algorithm and a sequential quadratic programming optimization algorithm, is suitable for preliminary wing design optimization tasks. The morphing concept, based on changes in wing-planform shape and wing-section shape achieved by extending spars and telescopic ribs, is explained in detail. Comparisons between optimized fixed wing performance, optimal morphing wing performance, and the performance of the wing obtained from the coupled aerodynamic-structural solution are presented. Estimates for the performance enhancements achieved by the unmanned aerial vehicles when fitted with this new morphing wing are also presented. Some conclusions on this concept are addressed with comments on the benefits and drawbacks of the morphing mechanism design. [ABSTRACT FROM AUTHOR]
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  Data: <i>Copyright of AIAA Journal is the property of American Institute of Aeronautics & Astronautics and its content may not be copied or emailed to multiple sites without the copyright holder's express written permission. Additionally, content may not be used with any artificial intelligence tools or machine learning technologies. However, users may print, download, or email articles for individual use. This abstract may be abridged. No warranty is given about the accuracy of the copy. Users should refer to the original published version of the material for the full abstract.</i> (Copyright applies to all Abstracts.)
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        Value: 10.2514/1.39016
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        Text: English
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        PageCount: 18
        StartPage: 2087
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      – SubjectFull: Remotely piloted vehicles
        Type: general
      – SubjectFull: Speed
        Type: general
      – SubjectFull: Multidisciplinary design optimization
        Type: general
      – SubjectFull: Mathematical optimization
        Type: general
      – SubjectFull: Aerodynamics
        Type: general
      – SubjectFull: Algorithms
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      – TitleFull: Optimization of a Morphing Wing Based on Coupled Aerodynamic and Structural Constraints.
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            NameFull: Vale, J.
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            NameFull: Lau, F. J. P.
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              M: 09
              Text: Sep2009
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              Y: 2009
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