@Article{SouzaAren:2013:DeSaAt,
               author = "Souza, Luiz Carlos Gadelha de and Arena, Victor Massad Ruiz",
          affiliation = "{Instituto Nacional de Pesquisas Espaciais (INPE)} and {Instituto 
                         Nacional de Pesquisas Espaciais (INPE)}",
                title = "Design of satellite attitude control algorithm based on the SDRE 
                         method using gas jets and reaction wheels",
              journal = "Journal of Engineering",
                 year = "2013",
               volume = "2013",
                pages = "318072",
             keywords = "satellite attitude control algorithm, SDRE method, gas jets, 
                         reaction wheel torque, space mission cost, angle maneuver, LQR 
                         linear controller, SDRE filter, DMC 3D satellite simulator, 
                         state-dependent Riccati equation, plant nonlinearities, system 
                         noise, angular velocity reduction, switching control algorithm, 
                         minimum system energy.",
             abstract = "An experimental attitude control algorithm design using prototypes 
                         can minimize space mission costs by reducing the number of errors 
                         transmitted to the next phase of the project. The Space Mechanics 
                         and Control Division (DMC) of INPE is constructing a 3D simulator 
                         to supply the conditions for implementing and testing satellite 
                         control hardware and software. Satellite large angle maneuver 
                         makes the plant highly nonlinear and if the parameters of the 
                         system are not well determined, the plant can also present some 
                         level of uncertainty. As a result, controller designed by a linear 
                         control technique can have its performance and robustness 
                         degraded. In this paper the standard LQR linear controller and the 
                         SDRE controller associated with an SDRE filter are applied to 
                         design a controller for a nonlinear plant. The plant is similar to 
                         the DMC 3D satellite simulator where the unstructured 
                         uncertainties of the system are represented by process and 
                         measurements noise. In the sequel the State-Dependent Riccati 
                         Equation (SDRE) method is used to design and test an attitude 
                         control algorithm based on gas jets and reaction wheel torques to 
                         perform large angle maneuver in three axes. The SDRE controller 
                         design takes into account the effects of the plant nonlinearities 
                         and system noise which represents uncertainty. The SDRE controller 
                         performance and robustness are tested during the transition phase 
                         from angular velocity reductions to normal mode of operation with 
                         stringent pointing accuracy using a switching control algorithm 
                         based on minimum system energy. This work serves to validate the 
                         numerical simulator model and to verify the functionality of the 
                         control algorithm designed by the SDRE method.",
                  doi = "10.1155/2013/318072",
                  url = "http://dx.doi.org/10.1155/2013/318072",
                 issn = "2314-4904 and 2314-4912",
             language = "en",
           targetfile = "318072.pdf",
                  url = "http://dx.doi.org/10.1155/2013/318072",
        urlaccessdate = "24 abr. 2024"
}