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Vector Backstepping Design for Flight Control
Saab AB, Sweden.
Linköping University, Department of Electrical Engineering, Automatic Control. Linköping University, The Institute of Technology.
2007 (English)In: Proceedings of the 2007 AIAA Guidance, Navigation, and Control Conference and Exhibit, 2007Conference paper, Published paper (Other academic)
Abstract [en]

A backstepping design for an aircraft described by rigid body dynamics is proposed. The system states are the unit velocity vector and the angular velocity in a body-fixed coordinate system. The result can be viewed as a multi-variable controller for angle of attack, sideslip angle, and velocity vector roll rate. The backstepping design is performed on the rigid body dynamics described on vector form. The resulting controller achieves convergence to a desired state from almost all starting points. Guidelines are given for tuning the controller to affect the characteristics of the short period mode, the roll mode and the dutch roll mode. A coupled high angle of attack, high roll rate maneuver is simulated using a simplified aircraft model to illustrate the design.

Place, publisher, year, edition, pages
2007.
Keyword [en]
Backstepping, Flight control, Rigid body dynamics
National Category
Engineering and Technology Control Engineering
Identifiers
URN: urn:nbn:se:liu:diva-89203DOI: 10.2514/6.2007-6421ISBN: 978-1-62410-015-4 (print)OAI: oai:DiVA.org:liu-89203DiVA: diva2:612259
Conference
2007 AIAA Guidance, Navigation and Control Conference and Exhibit, Hilton Head, SC, USA, August 20-23, 2007
Available from: 2013-03-20 Created: 2013-02-25 Last updated: 2013-03-27

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Härkegård, OlaGlad, Torkel

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Citation style
  • apa
  • harvard1
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  • modern-language-association-8th-edition
  • vancouver
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  • Other style
More styles
Language
  • de-DE
  • en-GB
  • en-US
  • fi-FI
  • nn-NO
  • nn-NB
  • sv-SE
  • Other locale
More languages
Output format
  • html
  • text
  • asciidoc
  • rtf