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@Article{SantosRocBogBenRem:2015:MuOpAp,
               author = "Santos, Willer Gomes dos and Rocco, Evandro Marconi and Boge, 
                         Toralf and Benninghoff, Heike and Rems, Florian",
          affiliation = "{Instituto Nacional de Pesquisas Espaciais (INPE)} and {Instituto 
                         Nacional de Pesquisas Espaciais (INPE)} and {German Aerospace 
                         Center (DLR)} and {German Aerospace Center (DLR)} and {German 
                         Aerospace Center (DLR)}",
                title = "Multi-objective optimization applied to real-time command problem 
                         of spacecraft thrusters",
              journal = "Journal of Spacecraft and Rockets",
                 year = "2015",
               volume = "52",
               number = "5",
                pages = "1407--1416",
             keywords = "Coupling problem, Force and torques, Guidance , navigation , and 
                         controls, Management functions, Reaction control system, 
                         Simulation framework, Single objective optimization, Spacecraft 
                         thrusters.",
             abstract = "A novel approach to solve the real-time command problem of 
                         spacecraft thrusters, called the thruster multiobjectivecommand 
                         method, is proposed in this paper. The reaction control system 
                         technology uses a set of thrusters in a special setup to 
                         simultaneously provide force and torque to the spacecraft. The 
                         thruster management function calculates all the candidate 
                         solutions that solve the thruster coupling problem. Then, a 
                         discrete multi-objective optimization method selects at every 
                         control cycle the best combination of thrusters and their firing 
                         time duration, which simultaneously optimizes a group of four 
                         objectives: the force error, the torque error, the propellant mass 
                         consumption, and the total number of pulses. The proposed method 
                         is included in a coupled translational and attitude control system 
                         applied to the final approach rendezvous scenario. Furthermore, 
                         all elements of the guidance, navigation, and control loop are 
                         accurately designed and implemented in a simulation framework. 
                         Results indicate effectiveness, robustness, and a better 
                         performance when compared to the usual single-objective 
                         optimization case.",
                  doi = "10.2514/1.A33178",
                  url = "http://dx.doi.org/10.2514/1.A33178",
                 issn = "0022-4650",
             language = "en",
        urlaccessdate = "25 nov. 2020"
}


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