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@Article{DeiennoMergPradSmir:2016:SaDeVi,
               author = "Deienno, Rog{\'e}rio and Merguizo Sanchez, Diogo and Prado, 
                         Antonio Fernando Bertachini de Almeida and Smirnov, Georgi",
          affiliation = "{Instituto Nacional de Pesquisas Espaciais (INPE)} and {Instituto 
                         Nacional de Pesquisas Espaciais (INPE)} and {Instituto Nacional de 
                         Pesquisas Espaciais (INPE)} and {University of Minho}",
                title = "Satellite de-orbiting via controlled solar radiation pressure",
              journal = "Celestial Mechanics and Dynamical Astronomy",
                 year = "2016",
               volume = "126",
               number = "4",
                pages = "433--459",
                month = "Nov.",
             keywords = "Astrodynamics, Orbital maneuvers, Satellite de-orbiting, Solar 
                         radiation pressure.",
             abstract = "The goal of the present research was to study the use of solar 
                         radiation pressure to place a satellite in an orbit that makes it 
                         to re-enter the atmosphere of the Earth. This phase of the mission 
                         is usual, since the orbital space around the Earth is crowded and 
                         all satellites have to be discarded after the end of their 
                         lifetimes. The technique proposed here is based on a device that 
                         can increase and decrease the area-to-mass ratio of the satellite 
                         when it is intended to reduce its altitude until a re-entry point 
                         is reached. Equations that predict the evolution of the 
                         eccentricity and semi-major axis of the orbit of the satellite are 
                         derived and can be used to allow the evaluation of the time 
                         required for the decay of the satellite. Numerical simulations are 
                         made, and they show the time required for the decay as a function 
                         of the area-to-mass ratio and the evolution of the most important 
                         orbital elements. The results show maps that indicate regions of 
                         fast decays as a function of the area-to-mass ratio and the 
                         initial inclination of the orbit of the satellite. They also 
                         confirmed the applicability of the equations derived here. The 
                         numerical results showed the role played by the evection and the 
                         Sun-synchronous resonances in the de-orbiting time.",
                  doi = "10.1007/s10569-016-9699-7",
                  url = "http://dx.doi.org/10.1007/s10569-016-9699-7",
                 issn = "0923-2958",
             language = "en",
           targetfile = "Deienno_satellite.pdf",
        urlaccessdate = "25 nov. 2020"
}


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