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Sabet Rasekh, Mahdi, yadavar nikravesh, seyed kamaleddin, ghahramani, nematollah. (1395). An efficient method to control the amplitude of the limit cycle in satellite attitude control system. نشریه مهندسی عمران امیرکبیر, 48(1), 13-27. doi: 10.22060/miscj.2016.634
Mahdi Sabet Rasekh; seyed kamaleddin yadavar nikravesh; nematollah ghahramani. "An efficient method to control the amplitude of the limit cycle in satellite attitude control system". نشریه مهندسی عمران امیرکبیر, 48, 1, 1395, 13-27. doi: 10.22060/miscj.2016.634
Sabet Rasekh, Mahdi, yadavar nikravesh, seyed kamaleddin, ghahramani, nematollah. (1395). 'An efficient method to control the amplitude of the limit cycle in satellite attitude control system', نشریه مهندسی عمران امیرکبیر, 48(1), pp. 13-27. doi: 10.22060/miscj.2016.634
Sabet Rasekh, Mahdi, yadavar nikravesh, seyed kamaleddin, ghahramani, nematollah. An efficient method to control the amplitude of the limit cycle in satellite attitude control system. نشریه مهندسی عمران امیرکبیر, 1395; 48(1): 13-27. doi: 10.22060/miscj.2016.634

An efficient method to control the amplitude of the limit cycle in satellite attitude control system

AUT Journal of Modeling and Simulation
مقاله 2، دوره 48، شماره 1، تابستان 2016، صفحه 13-27  XML اصل مقاله (1129 K)
نوع مقاله: Research Paper
شناسه دیجیتال (DOI): 10.22060/miscj.2016.634
نویسندگان
Mahdi Sabet Rasekh1؛ seyed kamaleddin yadavar nikravesh 2؛ nematollah ghahramani3
1Electrical engineering faculty Amirkabir university of technology
2Amirkabir University of technology
3Malek Ashtar University of technology
چکیده
In this paper, an efficient method is presented to control the attitude of a satellite with ON-OFF actuator. The main objective of this novel method is to control the amplitude of the limit cycle which commonly appears in the steady state of such systems; and at the same time by consideration of real actuator constraints, reduce the fuel consumption of system. The Proposed method is a combination of a command modifier (which based on the set point and the required accuracy of pointing, by means of optimization, calculate the desired limit cycle), a phase plane controller (PPC) and a compensator (to compensate for the real constraints of the actuator). The effectiveness and outperformance of the proposed method is approved in comparison with the previous methods of attitude control problem through the closed loop simulation and the stability and robustness of the closed loop system is fully analyzed and illustrated by simulations.
کلیدواژه ها
Limit Cycle؛ On/Off Actuator؛ Phase Plane Controller؛ Attitude Control؛ Robustness
عنوان مقاله [English]
An efficient method to control the amplitude of the limit cycle in satellite attitude control system
نویسندگان [English]
Mahdi Sabet Rasekh, seyed kamaleddin yadavar nikravesh, nematollah ghahramani
چکیده [English]
In this paper, an efficient method is presented to control the attitude of a satellite with ON-OFF actuator.
The main objective of this method is to control the amplitude of the limit cycle which commonly appears in
the steady state of such systems, while simultaneously by consideration of real actuator constraints, it
reduces the fuel consumption of system. The proposed method is a combination of a command modifier
(which is based on the set point and the required accuracy of pointing, by means of optimization, it calculates
the desired limit cycle), a phase plane controller (PPC) and a compensator (to compensate for the real
constraints of the actuator). The effectiveness and outperformance of the proposed method is approved in
comparison with the previous methods of attitude control problem through the closed loop simulation and the
stability and robustness of the closed loop system is fully analyzed and illustrated by simulations.
کلیدواژه ها [English]
Limit Cycle, On/Off Actuator, Phase Plane Controller, Attitude Control, Robustness
مراجع
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[15] M. H. Kaplan, “Modern Spacecraft Dynamics and Control,” Wiley press, New York, 1976.
[16] H. B. Hablani, “Target Acquisition, Tracking,Spacecraft Attitude Control, and Vibration Suppression with IPFM Reaction Jet Controllers,”in AIAA Guidance, Navigation and Control Conference, 1992.
[17] R.N. Clark, “Limit Cycle Oscillation in a Satellite Attitude Control System,” Automatica, Vol. 6,1970.
[18] M. J. Abzug, el al., “A Time Optimal Attitude Control System Designed to Overcome Certain Sensor Imperfection,” Guidance and Control II,edited by R. Langford, Elsevier, 1964.
[19] Sang W. Jeon and Seul Jung, “Hardware-in-the-Loop Simulation for The Reaction Control System
Using PWM-Based Limit Cycle Analysis,” IEEE Transactions on Control Systems Technology, Vol. 20, No. 2, Mar. 2012.
[20] A. R. Mesquita, K. H. Kienitz and E. L. Rempel,“Robust Limit Cycle Control in an Attitude Control System with Switching-Constrained Actuators,” in The 47th IEEE Conference on Decision and Control, Cancun, Mexico, Dec. 9-11,2008.
[21] A. Mesquita, E. L. Rempel and K. H. Kienitz,“Bifurcation Analysis of Attitude Control Systems with Switching-Constrained Actuators,,” Springer,Vol. 51, Issue 1, pp. 207-216, 2008.

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