Fechar

@Article{CavalcaPradGomeMerg:2020:QuSaOr,
               author = "Cavalca, Marina Pires de Oliveira and Prado, Antonio Fernando 
                         Bertachini de Almeida and Gomes, Vivian M. and Merguizo Sanchez, 
                         Diogo",
          affiliation = "{Instituto Nacional de Pesquisas Espaciais (INPE)} and {Instituto 
                         Nacional de Pesquisas Espaciais (INPE)} and {Universidade Estadual 
                         Paulista (UNESP)} and {Instituto Nacional de Pesquisas Espaciais 
                         (INPE)}",
                title = "{"}Quasi satellite orbits{"} to observe a possible small moon of 
                         Pallas",
              journal = "New Astronomy",
                 year = "2020",
               volume = "75",
                pages = "UNSP 101317",
                month = "Feb.",
             keywords = "Astrodynamics, Restricted three-body problem, Quasi satellite 
                         orbits, Space trajectories.",
             abstract = "The purpose of this paper is to make a numerical search for 
                         natural orbits that can be used for a spacecraft to study a 
                         possible small moon of Pallas. There are many speculations about 
                         the existence of a small companion around this large asteroid, so 
                         finding and classifying orbits around this possible celestial body 
                         is an interesting problem in astrodynamics and that can be used 
                         for a spacecraft to observe this body. It is assumed that this 
                         moon has a radius that can vary from 0.125 to 1 km and that is 
                         located 750 or 500 km away from the center of Pallas. The idea is 
                         to show the effects of this parameter in the orbits around this 
                         moon. It means that the moon is much smaller than Pallas, so 
                         Keplerlan orbits are not possible around it. To solve this 
                         problem, it is possible to find some special orbits that are 
                         called {"}Quasi Satellite Orbits{"} (QSO). They are orbits 
                         dominated by the gravity of Pallas, but that use the smaller 
                         perturbation from the moon to keep the spacecraft close to it. The 
                         present work searches for orbits that make the spacecraft to 
                         remain at given limits in its distance from the moon, like in the 
                         range from 3 to 50 km, the values used as an example in the 
                         present paper. This value is used because it is a good range to 
                         observe the body without getting to close to it, so reducing the 
                         risks of collisions. Each trajectory can be identified by the 
                         initial conditions of the spacecraft with respect to the moon, 
                         which means its initial position and velocity. The dynamics 
                         considers the restricted three-body problem and the influence of 
                         the solar radiation pressure, because some spacecraft may have 
                         higher values for the area-to-mass ratio, which gives a 
                         non-negligible effect in the trajectory of the spacecraft.",
                  doi = "10.1016/j.newast.2019.101317",
                  url = "http://dx.doi.org/10.1016/j.newast.2019.101317",
                 issn = "1384-1076",
             language = "en",
           targetfile = "cavalca_quasi.pdf",
        urlaccessdate = "29 mar. 2024"
}


Fechar