@Article{SouzaAren:2012:DeSaCo,
               author = "Souza, Luiz Carlos Gadelha de and Arena, Victor M. R.",
          affiliation = "{Instituto Nacional de Pesquisas Espaciais (INPE)} and Federal 
                         University of ABC, Santo Andr{\'e}, S{\~a}o Paulo, Brazil",
                title = "Design of Satellite Control Algorihtm Using the State Dependent 
                         Ricatti Equation and Kalman Filter",
              journal = "Advances in the Astronautical Sciences",
                 year = "2012",
               volume = "I",
               number = "2",
                pages = "235--243",
                 note = "Setores de Atividade: Atividades profissionais, 
                         cient{\'{\i}}ficas e t{\'e}cnicas.",
             keywords = "Robust Control System, State Dependent Ricatti Equation.",
             abstract = "A properly attitude control algorithm design and test procedure 
                         can dramatically minimize space mission costs by reducing the 
                         number of errors that can be transmitted to the next phase of the 
                         project. Besides, when attitude control algorithm problems are 
                         discovered on-orbit the mission or at least part of it can be 
                         lost. One way to increase confidence in the control algorithm is 
                         its experimental validation through prototypes. The Space 
                         Mechanics and Control Division (DMC) of INPE is constructing a 3D 
                         simulator to supply the conditions for implementing and testing 
                         satellite hardware and software. The 3D simulator can accommodate 
                         various satellites components; like sensors, actuators, computers 
                         and its respective interface and electronic. Depending on the 
                         manoeuvre the 3D simulator plant can be highly non-linear and if 
                         its inertia parameters are not well determined the plant can also 
                         present some kind of uncertainty. As a result, controller designed 
                         by linear control technique can have its performance and 
                         robustness degraded. This paper presents the application of the 
                         State-Dependent Riccati Equation (SDRE) method in conjunction with 
                         Kalman filter to design and test a attitude control algorithm for 
                         a 3D satellite simulator. The control strategy is based on gas 
                         jets and reaction wheel torques to perform large angle manoeuvre 
                         in three axes. The simulator model allows investigating the 
                         dynamics and the control system taking into account effects of the 
                         plant non-linearities and system noise. Initially, a simple 
                         comparison between the LQR and SDRE controller is performed. 
                         Practical applications are presented to address problems like 
                         presence of noise in process and measurements and incomplete state 
                         information using Kalman filter technique. Simulation has shown 
                         the performance and robustness of the SDRE controller applied for 
                         angular velocity reduction associated with stringent pointing 
                         requirement.",
                 issn = "0065-3438",
                label = "lattes: 5801699053436537 1 SouzaAren:2012:DeSaCo",
             language = "en",
                  url = "http://www.space-flight.org/docs/2012_winter/2012_winter.html",
        urlaccessdate = "19 abr. 2024"
}