Based on the Speed-Gradient (SG) design method and the "Implicit Reference Model" (IRM) concept, two adaptive control laws for pitch angle control of the Quanser/LAAS "Helicopter" benchmark laboratory setup are designed and experimentally tested. The MATLAB/Simulink and WinCon software environment is used for adaptive control laws implementation and the real-world experiments. The experimental results demonstrate high closed loop system performance and robustness of the suggested control laws with respect to parametric uncertainties and unmodeled plant dynamics.

Original languageEnglish
Title of host publication12th Saint Petersburg International Conference on Integrated Navigation Systems, ICINS 2005
EditorsI.S. Afanasova, Vladimir G. Peshekhonov
Pages33-39
Number of pages7
ISBN (Electronic)5900780597, 9785900780597
StatePublished - 2005
Event12th Saint Petersburg International Conference on Integrated Navigation Systems, ICINS 2005 - Saint Petersburg, Russian Federation
Duration: 23 May 2005 → 25 May 2005

Publication series

Name12th Saint Petersburg International Conference on Integrated Navigation Systems, ICINS 2005

Conference

Conference12th Saint Petersburg International Conference on Integrated Navigation Systems, ICINS 2005
Country/TerritoryRussian Federation
CitySaint Petersburg
Period23/05/05 → 25/05/05

    Scopus subject areas

  • Computer Networks and Communications
  • Electrical and Electronic Engineering
  • Information Systems
  • Signal Processing

    Research areas

  • Adaptive control, Autopilot design, Experimental results, Helicopter benchmark

ID: 87385443