Standard

Adaptive control of pitch angle for laas "Helicopter" benchmark. / Andrievsky, B. R.; Arzelier, D.; Fradkov, A. L.; Peaucelle, D.

12th Saint Petersburg International Conference on Integrated Navigation Systems, ICINS 2005. ред. / I.S. Afanasova; Vladimir G. Peshekhonov. 2005. стр. 33-39 (12th Saint Petersburg International Conference on Integrated Navigation Systems, ICINS 2005).

Результаты исследований: Публикации в книгах, отчётах, сборниках, трудах конференций › статья в сборнике материалов конференции › научная › Рецензирование

Harvard

Andrievsky, BR, Arzelier, D, Fradkov, AL & Peaucelle, D 2005, Adaptive control of pitch angle for laas "Helicopter" benchmark. в IS Afanasova & VG Peshekhonov (ред.), 12th Saint Petersburg International Conference on Integrated Navigation Systems, ICINS 2005. 12th Saint Petersburg International Conference on Integrated Navigation Systems, ICINS 2005, стр. 33-39, 12th Saint Petersburg International Conference on Integrated Navigation Systems, ICINS 2005, Saint Petersburg, Российская Федерация, 23/05/05.

APA

Andrievsky, B. R., Arzelier, D., Fradkov, A. L., & Peaucelle, D. (2005). Adaptive control of pitch angle for laas "Helicopter" benchmark. в I. S. Afanasova, & V. G. Peshekhonov (Ред.), 12th Saint Petersburg International Conference on Integrated Navigation Systems, ICINS 2005 (стр. 33-39). (12th Saint Petersburg International Conference on Integrated Navigation Systems, ICINS 2005).

Vancouver

Andrievsky BR, Arzelier D, Fradkov AL, Peaucelle D. Adaptive control of pitch angle for laas "Helicopter" benchmark. в Afanasova IS, Peshekhonov VG, Редакторы, 12th Saint Petersburg International Conference on Integrated Navigation Systems, ICINS 2005. 2005. стр. 33-39. (12th Saint Petersburg International Conference on Integrated Navigation Systems, ICINS 2005).

Author

Andrievsky, B. R. ; Arzelier, D. ; Fradkov, A. L. ; Peaucelle, D. / Adaptive control of pitch angle for laas "Helicopter" benchmark. 12th Saint Petersburg International Conference on Integrated Navigation Systems, ICINS 2005. Редактор / I.S. Afanasova ; Vladimir G. Peshekhonov. 2005. стр. 33-39 (12th Saint Petersburg International Conference on Integrated Navigation Systems, ICINS 2005).

BibTeX

@inproceedings{b2d8ff9f0b4d41428eafaec8f8a21417,
title = "Adaptive control of pitch angle for laas {"}Helicopter{"} benchmark",
abstract = "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.",
keywords = "Adaptive control, Autopilot design, Experimental results, Helicopter benchmark",
author = "Andrievsky, {B. R.} and D. Arzelier and Fradkov, {A. L.} and D. Peaucelle",
year = "2005",
language = "English",
series = "12th Saint Petersburg International Conference on Integrated Navigation Systems, ICINS 2005",
pages = "33--39",
editor = "I.S. Afanasova and Peshekhonov, {Vladimir G.}",
booktitle = "12th Saint Petersburg International Conference on Integrated Navigation Systems, ICINS 2005",
note = "12th Saint Petersburg International Conference on Integrated Navigation Systems, ICINS 2005 ; Conference date: 23-05-2005 Through 25-05-2005",

}

RIS

TY - GEN

T1 - Adaptive control of pitch angle for laas "Helicopter" benchmark

AU - Andrievsky, B. R.

AU - Arzelier, D.

AU - Fradkov, A. L.

AU - Peaucelle, D.

PY - 2005

Y1 - 2005

N2 - 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.

AB - 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.

KW - Adaptive control

KW - Autopilot design

KW - Experimental results

KW - Helicopter benchmark

UR - http://www.scopus.com/inward/record.url?scp=84913585750&partnerID=8YFLogxK

M3 - Conference contribution

AN - SCOPUS:84913585750

T3 - 12th Saint Petersburg International Conference on Integrated Navigation Systems, ICINS 2005

SP - 33

EP - 39

BT - 12th Saint Petersburg International Conference on Integrated Navigation Systems, ICINS 2005

A2 - Afanasova, I.S.

A2 - Peshekhonov, Vladimir G.

T2 - 12th Saint Petersburg International Conference on Integrated Navigation Systems, ICINS 2005

Y2 - 23 May 2005 through 25 May 2005

ER -

ID: 87385443