Design of a Smart Leading Edge Device

Chapter
Part of the Research Topics in Aerospace book series (RTA)

Abstract

To make use of low-drag future generation wings with high aspect ratio and low sweep for natural laminar flow, new high lift devices have to be developed [ACARE (Addendum to the Strategic Research Agenda, 2008), Horstmann (TELFONA, Contribution to Laminar Wing Development for Future Transport Aircraft, 2006)]. At the wing leading edge a smart e.g. morphing high lift device is being developed which provides a high-quality surface without gaps and steps. Due to the low maturity of morphing skins (Thill et al. (The Aeronautical Journal, 112:117–138)) the challenge of high strains has to be solved by an adequate design and sizing process. The presented design process comprises the requirements of a smart leading edge device, the structural pre-design and sizing of a full-scale leading edge section for wind tunnel tests.

Keywords

Target Shape Skin Structure Aerodynamic Load Kinematical Mechanism Outer Fiber 
These keywords were added by machine and not by the authors. This process is experimental and the keywords may be updated as the learning algorithm improves.

Notes

Acknowledgments

This work was carried out within/as part of the project SADE which is part of the 7th European Framework Program for research in aeronautics. The author is appreciative of the support in the pre-design of the kinematics by Dr. Lorkowski and Dr. Storm of EADS Innovation Works.

References

  1. 1.
    ACARE, : Addendum to the strategic research agenda, Advisory council for aeronautics research in Europe, 2008Google Scholar
  2. 2.
    Horstmann, K.H.: TELFONA, Contribution to laminar wing development for future transport aircraft, aeronautical days, Vienna, 19th-21st June 2006Google Scholar
  3. 3.
    Thill, C., Etches, J., Bond, I.P., Weaver, P.M., Potter, K.D.: Morphing skins—a review. Aeronaut. J. 112(1129), 117–138 (2008)Google Scholar
  4. 4.
    Wild, J., Pott-Pollenske, M., Nagel, B.: An integrated design approach for low noise exposing high-lift devices, AIAA Paper (2006–2843) 3rd AIAA Flow Control Conference, San Francisco, 2006Google Scholar
  5. 5.
    Kreth, Stefan, König, Reinhard, Wild, Jochen: Aircraft noise determination of novel wing configurations. INTER-NOISE 2007, Istanbul Türkei (2007)Google Scholar
  6. 6.
    Pott-Pollenske, M., Wild, J.: Entwicklung und validierung eines verfahrens zur beurteilung der schallabstrahlung von hochauftriebssystemen, DAGA 2007, Stuttgart, 2007Google Scholar
  7. 7.
    Campanile, L.F.: Modal synthesis of flexible mechanisms for airfoil shape control. J. Intell. Mater. Syst. Struct. 19, 779–789 (2008)CrossRefGoogle Scholar
  8. 8.
    Lagarias, J.C., Reeds, J.A., Wright, M.H., Wright, P.E.: Convergence properties of the nelder-mead simplex method in low dimensions. SIAM J. Optim. 9(1), 112–147 (1998)MathSciNetMATHCrossRefGoogle Scholar
  9. 9.
    Kühn, T.: Aerodynamic optimization of a two-dimensional two-element high lift airfoil with a smart droop nose device, EASN Workshop on Aerostructures, October 7 and 8th, Suresnes, 2010Google Scholar
  10. 10.
    Heintze, O., et al.: Die vorbereitung der faserverbundstruktur einer flexiblen und spaltfreien flügelvorderkante auf ihren ersten grossskaligen bodenversuch, Deutscher Luft- und Raumfahrtkongress 2010, Hamburg, 2010Google Scholar

Copyright information

© Springer-Verlag Berlin Heidelberg 2013

Authors and Affiliations

  1. 1.Institute of Composite Structures and Adaptive SystemsGerman Aerospace Center DLRBraunschweigGermany

Personalised recommendations