Fechar

@Article{FerreiraPradWint:2018:PlPoSw,
               author = "Ferreira, Alessandra F. S. and Prado, Antonio Fernando Bertachini 
                         de Almeida and Winter, Othon C.",
          affiliation = "{Instituto Nacional de Pesquisas Espaciais (INPE)} and {Instituto 
                         Nacional de Pesquisas Espaciais (INPE)} and {Universidade Estadual 
                         Paulista (UNESP)}",
                title = "Planar powered Swing-By maneuvers to brake a spacecraft",
              journal = "Computational and Applied Mathematics",
                 year = "2018",
               volume = "37",
               number = "Suppl. 1",
                pages = "202--219",
                month = "Dec.",
             keywords = "Powered Swing-By, Close approach, Impulsive maneuvers, Spacecraft 
                         trajectory, Energy decrease.",
             abstract = "The Swing-By maneuver is a technique used in many space mission to 
                         modify the trajectory of a spacecraft. The most usual goal is to 
                         increase the energy of the spacecraft, but it is also possible to 
                         reduce this energy. An important application is to break a 
                         spacecraft coming to the Earth using a Swing-By with the moon, 
                         which is the example used in the present paper. Other 
                         possibilities also exist, such as reducing the velocity of a 
                         spacecraft going to the planets Mercury or Venus. The goal is to 
                         help a possible capture by the planet, or at least to provide a 
                         passage with smaller velocities to allow better observations 
                         during the passage. Therefore, the goal of the present paper is to 
                         study the energy loss that a spacecraft may have during a powered 
                         Swing-By maneuver, which is a maneuver that combines a close 
                         approach by a celestial body with the application of an impulsive 
                         maneuver. The behavior of the energy variation is analyzed as a 
                         function of the parameters related to the pure gravity maneuver: 
                         periapsis radius, angle of approach and approach velocity; and the 
                         parameters related to the impulsive maneuver: the location of 
                         application of the impulse and its direction and magnitude. The 
                         maneuver is performed in a system composed by two bodies, such as 
                         the Earth-moon system, around the secondary body, and the energy 
                         is measured with respect to the primary body of the system. This 
                         problem is solved by developing a mathematical algorithm that 
                         guides larger efforts in terms of computer simulations. The 
                         results show maps of conditions made from the numerical 
                         simulations for different points of application and direction of 
                         the impulse, where the maneuver is advantageous and how much more 
                         energy can be removed from the spacecraft.",
                  doi = "10.1007/s40314-017-0483-4",
                  url = "http://dx.doi.org/10.1007/s40314-017-0483-4",
                 issn = "2238-3603",
             language = "en",
           targetfile = "ferreira_planar.pdf",
        urlaccessdate = "28 mar. 2024"
}


Fechar