Comparison of the Satellite Attitude Control System Design Using the Hoo Method and Hoo/LMI with Pole Allocation Considering the Parametric Uncertainty
Alain Giacoine de Souza1; Luiz Carlos Gadelha de Souza2
1 National Institute for Space Research - INPE; 2 University of Brasília - UnB
doi:10.20906/CPS/CILAMCE2017-0096
Resumo
This paper presents the comparison of the Attitude Control System (ACS) design for a rigid-flexible satellite with two vibrations mode, using the traditional H-infinity method and the H-infinity/LMI with pole allocation considering the parametric uncertainty. In the ACS design is important take into account the influence of the structure's flexibility, since they can interact with the satellite rigid motion, mainly, during translational and/or rotational maneuver, damaging the ACS. Usually the mathematic model obtained from the linearization and/or reduction of the rigid flexible model loses information about the flexible dynamical behavior and introduces some uncertainty. The satellite model is represented by a flexible beam connected to a central rigid hub considering a set of parametric uncertainties. Simulations results have shown that the control law designed by the Hoo/LMI method has better performance and it is more robust than Hoo method since the first was able to support the action of uncertainty and to control the rigid flexible satellite attitude and suppressing vibrations.
Palavras-chave: Satellite control; Robust control; H infinity method