Farhad Fani Saberi; Mansor Kabganian; Alireza Fazlyab; Abbas Ajorkar
Volume 9, Issue 1 , May 2016, , Pages 25-35
Abstract
In this paper, a robust attitude control algorithm is developed based on backstepping-sliding mode control for a satellite using four reaction wheels in a tetrahedron configuration. In this method, asymptotic stability of the proposed algorithm has been proven in the presence of reaction wheels dynamic ...
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In this paper, a robust attitude control algorithm is developed based on backstepping-sliding mode control for a satellite using four reaction wheels in a tetrahedron configuration. In this method, asymptotic stability of the proposed algorithm has been proven in the presence of reaction wheels dynamic model based on Lyapunov theory. Then, in order to evaluate the performance of the proposed algorithm, a low-cost real-time prossecor in the loop test bed is provided. The presented test bed is capable of real-time assessing the attitude backstepping-sliding mode control algorithm. In this test bed, real-time modeling of satellite dynamic, environmental disturbances and reaction wheels are achieved in a simulator computer and the proposed control algorithm performance is investigated by implementing it in an electronic control board of the prossecor in the loop test bed.
A. Imani; M. Bahrami
Volume 7, Issue 1 , April 2014, , Pages 49-56
Abstract
The problem of relative motion control for spacecraft formation flying in eccentric orbits is considered in this paper. Due to the presence of nonlinear dynamics and external disturbances, a robust fuzzy sliding mode controller is developed. The slopes of sliding surfaces of the conventional sliding ...
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The problem of relative motion control for spacecraft formation flying in eccentric orbits is considered in this paper. Due to the presence of nonlinear dynamics and external disturbances, a robust fuzzy sliding mode controller is developed. The slopes of sliding surfaces of the conventional sliding mode controller are tuned according to error states using a fuzzy logic and reach the pre-defined slopes. The controller is designed based on the nonlinear model of relative motion and perturbation and atmospheric drag are considered as external disturbances. Using the Lyapunov second method, the stability of the closed-loop system is guaranteed. The performance of the presented controller in tracking the desired reference trajectory is compared to a sliding mode controller in which simulation results confirm the superior performance of the proposed controller.
M. Sayanjali; J. Roshanian; A. Ghafari
Volume 1, Issue 2 , December 2008, , Pages 51-56
Abstract
In this paper, based on the Lagrange method, attitude motion equations for a flexible spacecraft have been derived. Flexible appendages are modeled by Euler-Bernoulli beam. Hybrid control scheme ofand sliding mode are used for attitude regulation. Switching between these to algorithm is determined using ...
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In this paper, based on the Lagrange method, attitude motion equations for a flexible spacecraft have been derived. Flexible appendages are modeled by Euler-Bernoulli beam. Hybrid control scheme ofand sliding mode are used for attitude regulation. Switching between these to algorithm is determined using absolute error parameter, so that when this parameter is large (i.e. the attitude is far from its desired conditions) the sliding mode control is used. in contrast, when the spacecraft is close to the desired attitude, the control is based onmethod. This hybrid scheme leads to a fast response and also robustness against uncertainty. Switching surface has been designed so that a certain cost function is minimized. Incontroller design, the first three vibration modes of the flexible spacecraft are considered as well as the Euler angles and their rates.
