author = "Ferreira, Alessandra and Moraes, Rodolpho Vilhena de and Prado, 
                         Antonio Fernando Bertachini de Almeida and Winter, Othon",
          affiliation = "{Universidade Estadual Paulista (UNESP)} and {Universidade 
                         Estadual Paulista (UNESP)} and {Instituto Nacional de Pesquisas 
                         Espaciais (INPE)} and {Universidade Estadual Paulista (UNESP)}",
                title = "Tethered slingshot maneuver in the three-dimensional space",
                 year = "2018",
         organization = "International Astronautical Congress, 69.",
             abstract = "The Tethered Slingshot maneuver (TSM) [1] is an alternative 
                         technique to maneuver a spacecraft in space based in the use of 
                         space tethers. A space tether used for this type of application 
                         consists in a cable where one of the ends is fixed in a celestial 
                         body (a planet, moon or asteroid) while the other end is fixed in 
                         the spacecraft that will be maneuvered. The cable is considered 
                         thin, rigid, inextensible and with negligible mass. There are 
                         several options to make this maneuver. The tether can be taken 
                         on-board the spacecraft and then fixed to the celestial body by an 
                         harpoon mechanism during the passage, or it can installed in the 
                         celestial body previously [2]. The purpose of the maneuver is the 
                         variation of energy and/or inclination in the orbit of the 
                         spacecraft around the Sun. Both aspects obtained by Tethered 
                         Slingshot Maneuver will be analyzed. The maneuver works as 
                         follows: the spacecraft approaches the body, connects to the cable 
                         that makes up the tether, rotates around the body by a given angle 
                         and, in sequence, the spacecraft is released from the cable to 
                         follow its trajectory. The rotation made in the spacecraft makes 
                         significant modifications in the trajectory of the spacecraft. The 
                         rotation from the tether and the sequential trajectory of the 
                         spacecraft is modeled in three-dimensional space, using the 
                         restricted three-body problem for improved accuracy over the usual 
                         patched-conics approach. This tethered maneuver gives flexibility 
                         to the mission, making possible for the spacecraft to reach goals 
                         that would be too expensive, in terms of fuel consumption, for a 
                         standard maneuver based only in propulsion systems. Different 
                         geometries, sizes and locations of the tether will be considered 
                         to make general maps that can guide a mission designer to get the 
                         most gains possible for the desired mission. Several examples 
                         using moons and asteroids of the Solar System will be shown.",
  conference-location = "Bremen",
      conference-year = "01-05 oct.",
             language = "pt",
           targetfile = "IAC-ale.pdf",
        urlaccessdate = "28 nov. 2020"