@InProceedings{FerreiraMoraPradWint:2019:ReEnSp,
               author = "Ferreira, Alessandra F. S. and Moraes, Rodolpho Vilhena and Prado, 
                         Antonio Fernando Bertachini de Almeida and Winter, Othon C.",
          affiliation = "{Universidade Estadual Paulista (UNESP)} and {Universidade 
                         Estadual Paulista (UNESP)} and {Instituto Nacional de Pesquisas 
                         Espaciais (INPE)} and {Universidade Estadual Paulista (UNESP)}",
                title = "Removing energy from a spacecraft using tethers",
            booktitle = "Proceedings...",
                 year = "2019",
         organization = "International Astronautical Congress (IAC), 70.",
             keywords = "Orbital maneuvers, removal of energy, spacecraft, tether, tethered 
                         slingshot maneuver.",
             abstract = "For a mission whose focus is the capture of the spacecraft by the 
                         main body or a close approach for observation, removing energy 
                         from a spacecraft can be an important maneuver. An option is the 
                         Tethered Slingshot Maneuver (TSSM) that consists of a cable 
                         anchored on the surface of a celestial body with the spacecraft 
                         attached to the other end. During the maneuver, the tether rotates 
                         by a given angle from the instant the spacecraft is connected to 
                         the cable. When detaching from the cable the spacecraft follows a 
                         new trajectory. The TSSM is recommended to be made in small 
                         bodies, because in this case the size of the tether does not need 
                         to be too large. This present paper shows an application of this 
                         type of maneuver for Jupiter-Themisto and Jupiter-Carpo systems. 
                         The study is numerical, based in the integration of the equations 
                         of motion of the spacecraft. Maps of solutions show the energy and 
                         inclination variation of the spacecraft relative to the main body 
                         for conditions where the spacecraft is decelerated, so reducing 
                         its energy. Captures also occur and they are analyzed in the 
                         present study. Copyright © 2019 by the International Astronautical 
                         Federation (IAF).",
  conference-location = "Washington, MD",
      conference-year = "21-25 Oct.",
             language = "en",
           targetfile = "ferreira_removing.pdf",
        urlaccessdate = "28 abr. 2024"
}