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This article has been retracted as it is essentially identical in content with a previously published paper “Luiz C. G. de Souza, Victor M. R. Arena, Design of Non Linear Controller for a Satellite Attitude Control Simulator, In Frontiers in Aerospace Engineering (FAE), 2012, Vol. 1, issue 1”.

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  1. L. C. G. de Souza and V. M. R. Arena, “Design of satellite attitude control algorithm based on the SDRE method using gas jets and reaction wheels,” Journal of Engineering, vol. 2013, Article ID 318072, 8 pages, 2013.
Journal of Engineering
Volume 2013, Article ID 318072, 8 pages
Research Article

Design of Satellite Attitude Control Algorithm Based on the SDRE Method Using Gas Jets and Reaction Wheels

National Institute for Space Research (INPE), Avnida dos Astronautas, 1758 S J Campos, SP, Brazil

Received 16 August 2012; Revised 19 October 2012; Accepted 3 November 2012

Academic Editor: Luis Carlos Rabelo

Copyright © 2013 Luiz C. G. de Souza and Victor M. R. Arena. This is an open access article distributed under the Creative Commons Attribution License, which permits unrestricted use, distribution, and reproduction in any medium, provided the original work is properly cited.


An experimental attitude control algorithm design using prototypes can minimize space mission costs by reducing the number of errors transmitted to the next phase of the project. The Space Mechanics and Control Division (DMC) of INPE is constructing a 3D simulator to supply the conditions for implementing and testing satellite control hardware and software. Satellite large angle maneuver makes the plant highly nonlinear and if the parameters of the system are not well determined, the plant can also present some level of uncertainty. As a result, controller designed by a linear control technique can have its performance and robustness degraded. In this paper the standard LQR linear controller and the SDRE controller associated with an SDRE filter are applied to design a controller for a nonlinear plant. The plant is similar to the DMC 3D satellite simulator where the unstructured uncertainties of the system are represented by process and measurements noise. In the sequel the State-Dependent Riccati Equation (SDRE) method is used to design and test an attitude control algorithm based on gas jets and reaction wheel torques to perform large angle maneuver in three axes. The SDRE controller design takes into account the effects of the plant nonlinearities and system noise which represents uncertainty. The SDRE controller performance and robustness are tested during the transition phase from angular velocity reductions to normal mode of operation with stringent pointing accuracy using a switching control algorithm based on minimum system energy. This work serves to validate the numerical simulator model and to verify the functionality of the control algorithm designed by the SDRE method.