@Article{CarvalhoSanLimBrePra:2023:SiMoSo,
               author = "Carvalho, Jean P. S. and Santos, Josu{\'e} Cardoso dos and Lima, 
                         Jackson S. and Brej{\~a}o, Leandro Forne and Prado, Antonio 
                         Fernando Bertachini de Almeida",
          affiliation = "{Universidade Federal do Rec{\^o}ncavo da Bahia (UFRB)} and 
                         {Japan Aerospace Exploration Agency (JAXA)} and {Universidade 
                         Federal do Rec{\^o}ncavo da Bahia (UFRB)} and {Instituto Nacional 
                         de Pesquisas Espaciais (INPE)} and {Instituto Nacional de 
                         Pesquisas Espaciais (INPE)}",
                title = "A Single-Averaged Model for the Solar Radiation Pressure Applied 
                         to Space Debris Mitigation Using a Solar Sail",
              journal = "Symmetry",
                 year = "2023",
               volume = "15",
               number = "5",
                pages = "e1107",
                month = "May",
             keywords = "astrodynamics, averaged model, debris removal, GEO region, 
                         mitigation risk, orbital perturbations, solar radiation pressure, 
                         space debris.",
             abstract = "Several non-functional objects are orbiting around the Earth and 
                         they are called space debris. In this work, we investigate the 
                         process of space debris mitigation from the GEO region using a 
                         solar sail. The acceleration induced by the solar radiation 
                         pressure (SRP) is the most relevant perturbation for objects in 
                         orbit around the Earth with a high area-to-mass ratio ((Formula 
                         presented.)). We consider the single-averaged SRP model with the 
                         Sun in an elliptical and inclined orbit. In addition to the SRP 
                         effect, the orbital evolution of space debris is analyzed 
                         considering the perturbations due to the Earths flattening and 
                         third-body perturbations in the dynamical system. The idea is to 
                         use the solar sail as a propulsion system using the Sun itself as 
                         a clean and abundant energy source so that it can remove space 
                         debris from the geostationary orbit and also contribute to the 
                         sustainability of space exploration. Using averaged dynamical maps 
                         as a tool, the numerical simulations show that the solar sail 
                         contributes strongly to exciting the eccentricity of the space 
                         debris, causing its reentry into Earths atmosphere. To perform the 
                         numerical simulations, we consider data from real space debris. We 
                         also show that the solar sail can be used to remove space debris 
                         for a graveyard orbit. In this way, the solar sail can work as a 
                         clean and sustainable space-debris-removal mechanism. Finally, we 
                         show that the convenient choice of the argument of perigee and the 
                         longitude of the ascending node might contribute to amplify the 
                         growth of eccentricity. It is also shown that solar radiation 
                         pressure destroys the symmetry of the orbits that can be observed 
                         in keplerian orbits, so all the orbits will be asymmetric when 
                         considering the presence of this force.",
                  doi = "10.3390/sym15051107",
                  url = "http://dx.doi.org/10.3390/sym15051107",
                 issn = "2073-8994",
             language = "en",
           targetfile = "symmetry-15-01107.pdf",
        urlaccessdate = "03 maio 2024"
}