@Article{SantosRocBogBenRem:2016:HaReTe,
               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} and {German Aerospace Center} and {German Aerospace 
                         Center}",
                title = "Hardware-in-the-loop rendezvous tests of a novel actuators command 
                         concept",
              journal = "Journal of the Astronautical Sciences",
                 year = "2016",
               volume = "63",
               number = "4",
                pages = "287--307",
                month = "Dec.",
             keywords = "Hardware-in-the-loop simulation, Spacecraft control system, 
                         Multiobjective optimization, On-orbit servicing mission.",
             abstract = "Integration, test and validation results, in a real-time 
                         environment, of a novel concept for spacecraft control are 
                         presented in this paper. The proposed method commands 
                         simultaneously a group of actuators optimizing a given set of 
                         objective functions based on a multiobjective optimization 
                         technique. Since close proximity maneuvers play an important role 
                         in orbital servicing missions, the entire GNC system has been 
                         integrated and tested at a hardware-in-the-loop (HIL) rendezvous 
                         and docking simulator known as European Proximity Operations 
                         Simulator (EPOS). During the test campaign at EPOS facility, a 
                         visual camera has been used to provide the necessary measurements 
                         for calculating the relative position with respect to the target 
                         satellite during closed-loop simulations. In addition, two 
                         different configurations of spacecraft control have been 
                         considered in this paper: a thruster reaction control system and a 
                         mixed actuators mode which includes thrusters, reaction wheels, 
                         and magnetic torqrods. At EPOS, results of HIL closed-loop tests 
                         have demonstrated that a safe and stable rendezvous approach can 
                         be achieved with the proposed GNC loop.",
                  doi = "10.1007/s40295-016-0094-0",
                  url = "http://dx.doi.org/10.1007/s40295-016-0094-0",
                 issn = "0021-9142",
             language = "en",
           targetfile = "Santos_hardware.pdf",
        urlaccessdate = "27 abr. 2024"
}