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Application of piezoelectric fiber composite actuator to aircraft wing for aerodynamic performance improvement

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Abstract

The application of actuator made of piezoelectric material, particularly the advanced piezoelectric fiber composite due to the rapid development of smart materials and structures and active control technology in aviation and aerospace industry, to aircraft for performance enhancements such as flight control, aerodynamic force optimization, structure weight reduction, and overall aircraft design represents a new challenge to researches. It is considered as one of the key technologies for developing future flight vehicle. An approach with virtual control surface instead of conventional control surface to control aerodynamic force distribution and flight performance by use of piezoelectric fiber composite actuators distributed on wing surface is presented here. Particularly, the design and implementation of increasing lift force, providing roll maneuver, decreasing induced drag and wing root moment in different flight environments by the same structure control platform are studied. The control effect and sensitivity are examined quantitatively. Generally speaking, better control effect can be obtained by making better use of aeroelastic character to enlarge the actuation strain produced by piezoelectric material.

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References

  1. Culshaw B. Smart Structures and Materials. Boston: Artech House, 1996

    Google Scholar 

  2. Yousefi-Koma A, Zimcik D G. Applications of smart structures to aircraft for performance enhancement. Canadian Aeronaut Space J, 2003, 49(4): 163–172

    Google Scholar 

  3. Niezrecki C, Brei D, Balakrishnan S, et al. Piezoelectric actuation: state of the art. Shock Vib Dig, 2001, 33(4): 269–280

    Article  Google Scholar 

  4. Garcia E. Smart structures and actuators: past, present, and future. In: Proceedings of SPIE Conference on Smart Structures and Material Systems: Industrial and Commercial Applications of Smart Structures Technologies. Bellingham: SPIE, 2002. 1–12

    Google Scholar 

  5. Schultz M R, Hyer M W. A morphing concept based on unsymmetric composite laminates and piezoceramic MFC actuators. AIAA Paper 2004, 1806

  6. Park J S, Kim J H. Material properties of single crystal macro fiber composite actuators for active twist rotor blades. AIAA Paper 2005, 2265

  7. Williams R B. Nonlinear mechanical and actuation characterization of piezoceramic fiber composites. Doctoral Dissertation. Blacksburg: Virginia Polytechnic Institute and State University, 2004

    Google Scholar 

  8. SMC corp. http://www.smart-material.com, 2010, 9

  9. Carlos E S C, Brown E L. Modeling of high aspect ratio active flexible wings for roll control. AIAA Paper 2002, 1719

  10. Sahoo D, Carlos E S C. Roll maneuver control of UCAV wing using anisotropic piezoelectric actuators. AIAA Paper 2002, 1720

  11. Bilgen O, Kochersberger K B, Inman D J. A novel aerodynamic vectoring control airfoil via macro-fiber-composite actuators plate airfoil designs. AIAA Paper 2008, 1700

  12. Sanders B, Eastep F E, Forster E. Aerodynamic and aeroelastic characteristics of wings with conformal control surfaces for morphing aircraft. J Aircraft, 2003, 40(1): 94–99

    Article  Google Scholar 

  13. Li M, Chen W M, Guan D. Improvement of aircraft rolling power by use of piezoelectric actuators. Chinese J Aeronaut, 2004, 17(2): 87–92

    Google Scholar 

  14. Li M, Chen W M, Wang M C, et al. A load simulation method of piezoelectric actuator in FEM for smart structures, Sci China Ser E-Tech Sci, 2009, 52(9): 2576–2584

    Article  MATH  Google Scholar 

  15. Li M, Chen W M, Jia L J. Drive characteristics and stiffness influence with piezoelectric fiber composite actuators on airfoil surface. Chinese J Aeronaut, 2010, 31(2): 418–425

    Google Scholar 

  16. Hedman S G. Vortex lattice method for calculation of quasi steady state loadings on thin elastic wings in subsonic flow. FFA Report 105, 1965

Download references

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Authors and Affiliations

  1. School of Aeronautics Science and Engineering, Beihang University, Beijing, 100191, China

    Min Li, JunXian Yuan & De Guan

  2. Key Laboratory of Environmental Mechanics, Institute of Mechanics, Chinese Academy of Sciences, Beijing, 100190, China

    WeiMin Chen

Authors
  1. Min Li
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  2. JunXian Yuan
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  3. De Guan
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  4. WeiMin Chen
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Corresponding author

Correspondence to WeiMin Chen.

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Li, M., Yuan, J., Guan, D. et al. Application of piezoelectric fiber composite actuator to aircraft wing for aerodynamic performance improvement. Sci. China Technol. Sci. 54, 395–402 (2011). https://doi.org/10.1007/s11431-010-4212-0

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  • DOI: https://doi.org/10.1007/s11431-010-4212-0

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