Electrodynamic attitude stabilization of a satellite in the Konig frame

This paper deals with a satellite in a circular near-Earth orbit. The satellite is equipped with an electrodynamic attitude control system based on Lorentz and magnetic torque properties. The gravitational disturbing torque acting on the satellite attitude dynamics is taken into account since it is...

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Bibliographic Details
Published in:Nonlinear dynamics 2015-11, Vol.82 (3), p.1493-1505
Main Authors: Aleksandrov, A. Yu, Antipov, K. A., Platonov, A. V., Tikhonov, A. A.
Format: Article
Language:English
Subjects:
Attitude stability
Automotive Engineering
Classical Mechanics
Computer simulation
Control
Control systems
Dynamical Systems
Engineering
Liapunov direct method
Liapunov functions
Magnetic properties
Mechanical Engineering
Motion stability
Nonlinear analysis
Nonlinear differential equations
Nonlinear equations
Original Paper
Satellite attitude control
Spacecraft
Three axis stabilization
Torque
Vibration
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Summary:This paper deals with a satellite in a circular near-Earth orbit. The satellite is equipped with an electrodynamic attitude control system based on Lorentz and magnetic torque properties. The gravitational disturbing torque acting on the satellite attitude dynamics is taken into account since it is the largest disturbing torque. The possibility of using electrodynamic attitude control system for satellite three-axis stabilization in the Konig frame is analyzed. By the use of the Lyapunov direct method, conditions under which electrodynamic control solves the problem for a dynamically symmetric satellite are obtained. The procedure for the successive constructing of Lyapunov functions is suggested. On the basis of the analysis of nonlinear differential equations system, the domain of the control parameter values is found for which one can guarantee the asymptotic stability of the programmed satellite motion. The results of a numerical simulation are presented to demonstrate the effectiveness of the proposed approach.
ISSN:0924-090X
1573-269X
DOI:10.1007/s11071-015-2256-1