@Article{MurciaPiñerosGomeDosSGole:2020:EfRoSp,
               author = "Murcia Piñeros, Jhonathan Orlando and Gomes, Vivian Martins and 
                         Dos Santos, Walter Abrah{\~a}o and Golebiewska, Justyna",
          affiliation = "{Instituto Nacional de Pesquisas Espaciais (INPE)} and 
                         {Universidade Estadual Paulista (UNESP)} and {Instituto Nacional 
                         de Pesquisas Espaciais (INPE)} and {Adam Mickiewicz University}",
                title = "Effects of the rotation of a spacecraft in an atmospheric close 
                         approach with the Earth",
              journal = "European Physical Journal Special Topics",
                 year = "2020",
               volume = "229",
               number = "8",
                pages = "1517--1526",
                month = "May",
             abstract = "A maneuver called {"}Aerogravity Assisted{"} is known in the 
                         literature to increase the energy gains given by a close approach 
                         between a spacecraft and a planet using the atmosphere of the 
                         planet. Several previous papers showed the importance of this 
                         topic in different aspects. The present paper has the goal of 
                         studying the effects of the spacecraft rotation in this maneuver. 
                         This rotation implies in a variable ballistic coefficient and this 
                         fact can change the results of the maneuver. Several masses, sizes 
                         and angular velocities will be tested and the effects of these 
                         parameters will be measured. The dynamical model considers the 
                         atmosphere of the Earth, in terms of drag, the gravitational 
                         fields of the Earth and the Sun, assumed to be points of mass, and 
                         the rotating spacecraft. The Earth and the Sun are assumed to be 
                         in circular coplanar orbits around their common center of mass. 
                         The equations of motion are the ones given by the circular planar 
                         restricted three-body problem with the addition of the forces 
                         generated by the atmospheric drag. The primary objective is to map 
                         the energy variations of the spacecraft orbits due to this close 
                         approach as a function of the spacecraft angular velocity. This 
                         rotation can be used as control of the maneuver to try to reach 
                         different goals.",
                  doi = "10.1140/epjst/e2020-900144-9",
                  url = "http://dx.doi.org/10.1140/epjst/e2020-900144-9",
                 issn = "1951-6355",
             language = "en",
           targetfile = "murica_effects.pdf",
        urlaccessdate = "27 abr. 2024"
}