Robust optimal PID controller design for attitude stabilization of flexible spacecraft

Chutiphon Pukdeboon

Kybernetika (2018)

  • Volume: 54, Issue: 5, page 1049-1070
  • ISSN: 0023-5954

Abstract

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This paper presents a novel robust optimal control approach for attitude stabilization of a flexible spacecraft in the presence of external disturbances. An optimal control law is formulated by using concepts of inverse optimal control, proportional-integral-derivative control and a control Lyapunov function. A modified extended state observer is used to compensate for the total disturbances. High-gain and second order sliding mode algorithms are merged to obtain the proposed modified extended state observer. The second method of Lyapunov is used to demonstrate its properties including the convergence rate and ultimate boundedness of the estimation error. The proposed controller can stabilize the attitude control system and minimize a cost functional. Moreover, this controller achieves robustness against bounded external disturbances and the disturbances caused by the elastic vibration of flexible appendages. Numerical simulations are provided to demonstrate the performance of the developed controller.

How to cite

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Pukdeboon, Chutiphon. "Robust optimal PID controller design for attitude stabilization of flexible spacecraft." Kybernetika 54.5 (2018): 1049-1070. <http://eudml.org/doc/294483>.

@article{Pukdeboon2018,
abstract = {This paper presents a novel robust optimal control approach for attitude stabilization of a flexible spacecraft in the presence of external disturbances. An optimal control law is formulated by using concepts of inverse optimal control, proportional-integral-derivative control and a control Lyapunov function. A modified extended state observer is used to compensate for the total disturbances. High-gain and second order sliding mode algorithms are merged to obtain the proposed modified extended state observer. The second method of Lyapunov is used to demonstrate its properties including the convergence rate and ultimate boundedness of the estimation error. The proposed controller can stabilize the attitude control system and minimize a cost functional. Moreover, this controller achieves robustness against bounded external disturbances and the disturbances caused by the elastic vibration of flexible appendages. Numerical simulations are provided to demonstrate the performance of the developed controller.},
author = {Pukdeboon, Chutiphon},
journal = {Kybernetika},
keywords = {robust optimal control; inverse optimal control; control Lyapunov function; extended state observer; flexible spacecraft},
language = {eng},
number = {5},
pages = {1049-1070},
publisher = {Institute of Information Theory and Automation AS CR},
title = {Robust optimal PID controller design for attitude stabilization of flexible spacecraft},
url = {http://eudml.org/doc/294483},
volume = {54},
year = {2018},
}

TY - JOUR
AU - Pukdeboon, Chutiphon
TI - Robust optimal PID controller design for attitude stabilization of flexible spacecraft
JO - Kybernetika
PY - 2018
PB - Institute of Information Theory and Automation AS CR
VL - 54
IS - 5
SP - 1049
EP - 1070
AB - This paper presents a novel robust optimal control approach for attitude stabilization of a flexible spacecraft in the presence of external disturbances. An optimal control law is formulated by using concepts of inverse optimal control, proportional-integral-derivative control and a control Lyapunov function. A modified extended state observer is used to compensate for the total disturbances. High-gain and second order sliding mode algorithms are merged to obtain the proposed modified extended state observer. The second method of Lyapunov is used to demonstrate its properties including the convergence rate and ultimate boundedness of the estimation error. The proposed controller can stabilize the attitude control system and minimize a cost functional. Moreover, this controller achieves robustness against bounded external disturbances and the disturbances caused by the elastic vibration of flexible appendages. Numerical simulations are provided to demonstrate the performance of the developed controller.
LA - eng
KW - robust optimal control; inverse optimal control; control Lyapunov function; extended state observer; flexible spacecraft
UR - http://eudml.org/doc/294483
ER -

References

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