@Article{FonsecaRadeGoesSale:2017:AtViCo,
               author = "Fonseca, Ijar Milagre da and Rade, Domingos A. and Goes, Luiz C. 
                         S. and Sales, Thiago de Paula",
          affiliation = "{Instituto Nacional de Pesquisas Espaciais (INPE)} and {Instituto 
                         Tecnol{\'o}gico de Aeron{\'a}utica (ITA)} and {Instituto 
                         Tecnol{\'o}gico de Aeron{\'a}utica (ITA)} and {Universidade 
                         Federal de Uberl{\^a}ndia (UFU)}",
                title = "Attitude and vibration control of a satellite containing flexible 
                         solar arrays by using reaction wheels, and piezoelectric 
                         transducers as sensors and actuators",
              journal = "Acta Astronautica",
                 year = "2017",
               volume = "139",
                pages = "357--366",
                month = "Oct.",
             abstract = "The primary purpose of this paper is to provide insight into 
                         control-structure interaction for satellites comprising flexible 
                         appendages and internal moving components. The physical model 
                         considered herein aiming to attend such purpose is a 
                         rigid-flexible satellite consisting of a rigid platform containing 
                         two rotating flexible solar panels. The solar panels rotation is 
                         assumed to be in a sun-synchronous configuration mode. The panels 
                         contain surface-bonded piezoelectric patches that can be used 
                         either as sensors for the elastic displacements or as actuators to 
                         counteract the vibration motion. It is assumed that in the normal 
                         mode operation the satellite platform points towards the Earth 
                         while the solar arrays rotate so as to follow the Sun. The vehicle 
                         moves in a low Earth polar orbit. The technique used to obtain the 
                         mathematical model combines the Lagrangian formulation with the 
                         Finite Elements Method used to describe the dynamics of the solar 
                         panel. The gravity-gradient torque as well as the torque due to 
                         the interaction of the Earth magnetic field and the satellite 
                         internal residual magnetic moment is included as environmental 
                         perturbations. The actuators are three reaction wheels for 
                         attitude control and piezoelectric actuators to control the 
                         flexible motion of the solar arrays. Computer simulations are 
                         performed using the MATLABŪ software package. The following 
                         on-orbit satellite operating configurations are object of 
                         analysis: i) Satellite pointing towards the Earth (Earth 
                         acquisition maneuver) by considering the initial conditions in the 
                         elastic displacement equal to zero, aiming the assessment of the 
                         flexible modes excitation by the referred maneuver; ii) the 
                         satellite pointing towards the Earth with the assumption of an 
                         initial condition different from zero for the flexible motion such 
                         that the attitude alterations are checked against the elastic 
                         motion disturbance; and iii) attitude acquisition accomplished by 
                         taking into account initial conditions different from zero for 
                         both attitude and elastic vibrations. Additionally, the control 
                         efforts for the three cases are compared. Results indicate that 
                         the attitude control is able to excite the solar panels' vibration 
                         modes and vice-versa. The piezoelectric vibration control shows 
                         significant performance improvement when compared to contributions 
                         of the attitude control to the vibration damping.",
                  doi = "10.1016/j.actaastro.2017.07.018",
                  url = "http://dx.doi.org/10.1016/j.actaastro.2017.07.018",
                 issn = "0094-5765",
             language = "en",
           targetfile = "fonseca_attitude.pdf",
        urlaccessdate = "27 abr. 2024"
}