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Unformatted text preview: TEMA Tend. Mat. Apl. Comput., 9 , No. 2 (2008), 321-330. c circlecopyrt Uma Publica¸c˜ao da Sociedade Brasileira de Matem´atica Aplicada e Computacional. Attitude Stabilization of the PMM Satellite Using a LQG-Based Control Strategy A.C. SANTANA 1 , Programa de P´ os-Gradua¸ c˜ ao em Engenharia da Informa¸ c˜ ao, Universidade Federal do ABC, Rua Catequese, 242, Bairro Jardim, 09090-400 Santo Andr´ e, SP, Brasil. L.S. MARTINS-FILHO 2 , Centro de Engenharia, Modelagem e Ciˆ encias Soci- ais Aplicadas, Universidade Federal do ABC, Rua Catequese, 242, Bairro Jardim, 09090-400 Santo Andr´ e, SP, Brasil. G. ARANTES JR. 3 , Zentrum f¨ur angewandte Raumfahrttechnologie und Mikro- gravitation, Universit¨at Bremen, Am Fallturm, D-28359 Bremen, Germany. Abstract . This paper deals with the problem of 3-axis attitude stabilization of a satellite subjected to dynamics perturbations. The controller is based on the Linear Quadratic Gaussian control theory (LQG). The main purpose of the work is to synthesize a control law characterized by simplicity on implementation. The study considers the specific case of the Brazilian satellite PMM. The article presents the system modelling, the proposed control, and analysis of simulation results. Keywords . Satellite attitude control, Three-axis attitude stabilization, Thruster actuators, LQG control theory. 1. Introduction An important problem of the artificial satellites technology is the precise control of the spacecraft orientation in a known reference frame. In fact, the success of differ- ent missions depends of the precision on the spacecraft attitude, ensuring the ade- quate performance of the payload equipments and instruments in terms of pointing precision. That is the case of applications in remote sensing, meteorology, commu- nication, and astrophysics as well. Though diverse solutions for this classic problem has been proposed since the beginning of the space engineering, this functional aspect of satellites stays as an interesting subject of studies. The main motivation is the search of a well adapted solution for each specific satellite, considering the peculiar features, and combining efficiency and robustness with implementation simplicity. In our precedent work, 1 [email protected] 2 [email protected] 3 [email protected] 322 Santana, Martins-Filho and Arantes Jr. we have proposed a linear control based on LQR theory . In other examples of studies, we find variations of the PID controller, e.g. in Show et al. . Application of nonlinear control techniques for a critical case, when a pair of attitude actuators fails, is proposed by Tsiotras et al. . Yang and Kung  propose a control approach using a nonlinear H ∞ controller; while in Wu and Chen  a mixed H 2 / H ∞ approach is investigated....
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This note was uploaded on 02/04/2012 for the course ECE 222 taught by Professor Goengi during the Spring '11 term at Maryland.
- Spring '11