%0 Journal Article
%4 sid.inpe.br/mtc-m21b/2014/11.18.23.57.49
%2 sid.inpe.br/mtc-m21b/2014/11.18.23.57.50
%@doi 10.1155/2014/260206
%@issn 1070-9622
%F scopus 2014-11 SouzaSouz:2014:SaAtCo
%T Satellite attitude control system design considering the fuel slosh dynamics
%D 2014
%A Souza, Luiz Carlos Gadelha de,
%A Souza, Alain Giacobini De,
%@affiliation Instituto Nacional de Pesquisas Espaciais (INPE)
%@affiliation Instituto Nacional de Pesquisas Espaciais (INPE)
%B Shock and Vibration
%V 2014
%K Communication satellites, Controllers, Design, Dynamics, Fuel tanks, Navigation, Controller performance, Flexible solar panels, Kalman filter technique, Linear quadratic Gaussian, Linear quadratic regulator, Mechanical manipulators, Satellite attitude control systems, Satellite structure, Satellite antennas.
%X The design of the satellite attitude control system (ACS) becomes more complex when the satellite structure has different type of components like, flexible solar panels, antennas, mechanical manipulators, and tanks with fuel. A crucial interaction can occur between the fuel slosh motion and the satellite rigid motion during translational and/or rotational manoeuvre since these interactions can change the satellite centre of mass position damaging the ACS pointing accuracy. Although, a well-designed controller can suppress such disturbances quickly, the controller error pointing may be limited by the minimum time necessary to suppress such disturbances thus affecting the satellite attitude acquisition. As a result, the design of the satellite controller needs to explore the limits between the conflicting requirements of performance and robustness. This paper investigates the effects of the interaction between the liquid motion (slosh) and the satellite dynamics in order to predict what the damage to the controller performance and robustness is. The fuel slosh dynamics is modelled by a pendulum which parameters are identified using the Kalman filter technique. This information is used to design the satellite controller by the linear quadratic regulator (LQR) and linear quadratic Gaussian (LQG) methods to perform a planar manoeuvre assuming thrusters are actuators. © 2014 Luiz Carlos Gadelha de Souza and Alain G. de Souza.
%@language en