@Article{RomeroSouz:2022:ApEvRe,
               author = "Romero, Alessandro Gerlinger and Souza, Luis Carlos Gadelha de",
          affiliation = "{Instituto Nacional de Pesquisas Espaciais (INPE)} and 
                         {Universidade Federal do ABC (UFABC)}",
                title = "An Approach to Evaluate the Region of Attraction of Satellites 
                         controlled by SDRE",
              journal = "WSEAS Transactions on Systems",
                 year = "2022",
               volume = "21",
                pages = "75--85",
             keywords = "control, LQR, Nonlinear, Region of Attraction, SDRE.",
             abstract = "The control of a satellite can be designed with success by linear 
                         control theory if the satellite has slow angular motions. However, 
                         for fast maneuvers, the linearized models are not able to 
                         represent the effects of the nonlinear terms. One candidate 
                         technique for the design of the satellite's control under fast 
                         maneuvers is the State-Dependent Riccati Equation (SDRE). SDRE 
                         provides an effective algorithm for synthesizing nonlinear 
                         feedback control by allowing nonlinearities. Nonetheless, much 
                         criticism has been leveled against the SDRE because it does not 
                         provide assurance of global asymptotic stability. Additionally, 
                         there are situations in which global asymptotic stability cannot 
                         be achieved (e.g., systems with multiple equilibrium points). 
                         Therefore, especially in aerospace, estimating the region of 
                         attraction (ROA) is fundamental. The Brazilian National Institute 
                         for Space Research (INPE, in Portuguese) was demanded by the 
                         Brazilian government to build remote-sensing satellites, such as 
                         the Amazonia-1 mission. In such missions, the satellite must be 
                         stabilized in three axes so that the optical payload can point to 
                         the desired target. In this paper, we share an approach to 
                         evaluate the ROAs of Amazonia-1 controlled by LQR (the linear 
                         counterpart of SDRE) and SDRE. The initial results showed SDRE has 
                         a larger ROA than LQR.",
                  doi = "10.37394/23202.2022.21.9",
                  url = "http://dx.doi.org/10.37394/23202.2022.21.9",
                 issn = "1109-2777",
             language = "en",
           targetfile = "a185102-006(2022).pdf",
        urlaccessdate = "05 jun. 2024"
}