@InProceedings{FerreiraMoraPradWint:2018:TeSlMa,
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 = "20 maio 2024"
}