State dependent anytime control methodology for prototypical aeroelastic wing section with structural non-linearity

Research output: Chapter in Book/Report/Conference proceedingConference contribution

3 Citations (Scopus)

Abstract

Nowadays in solving control problems the processing is performed typically by model-based computer systems, which contain a representation of our knowledge about the nature and the actual circumstances of the problem in hand. If the nature and/or the actual circumstances change the corresponding model should also be changed. Anytime techniques are very flexible in this respect and can advantageously be used when the operation should be performed under changing circumstances. In this paper, a nonlinear state dependent control methodology is proposed for anytime use and as an example is applied to globally stabilize a given prototypical aeroelastic wing section via one control surface.

Original languageEnglish
Title of host publication2003 IEEE International Symposium on Industrial Electronics, ISIE 2003
PublisherInstitute of Electrical and Electronics Engineers Inc.
Pages200-205
Number of pages6
ISBN (Electronic)0780379128
DOIs
Publication statusPublished - Jan 1 2003
EventIEEE International Symposium on Industrial Electronics, ISIE 2003 - Rio de Janeiro, Brazil
Duration: Jun 9 2003Jun 11 2003

Publication series

NameIEEE International Symposium on Industrial Electronics
VolumeI

Other

OtherIEEE International Symposium on Industrial Electronics, ISIE 2003
CountryBrazil
CityRio de Janeiro
Period6/9/036/11/03

Keywords

  • Control system synthesis
  • Control systems
  • Delay
  • Linear feedback control systems
  • Nonlinear control systems
  • Nonlinear systems
  • Power system modeling
  • Prototypes
  • Riccati equations
  • Telecommunication control

ASJC Scopus subject areas

  • Electrical and Electronic Engineering
  • Control and Systems Engineering

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  • Cite this

    Várkonyi-Kóczy, A. R., Baranyi, P., Kiss, L., & Várlaki, P. (2003). State dependent anytime control methodology for prototypical aeroelastic wing section with structural non-linearity. In 2003 IEEE International Symposium on Industrial Electronics, ISIE 2003 (pp. 200-205). [1267245] (IEEE International Symposium on Industrial Electronics; Vol. I). Institute of Electrical and Electronics Engineers Inc.. https://doi.org/10.1109/ISIE.2003.1267245