@Article{NegriSukhPrad:2019:LuGrAs,
author = "Negri, Rodolfo Batista and Sukhanov, Alexander and Prado, Antonio
Fernando Bertachini de Almeida",
affiliation = "{Instituto Nacional de Pesquisas Espaciais (INPE)} and {Space
Research Institute of Russian Academy of Sciences} and {Instituto
Nacional de Pesquisas Espaciais (INPE)}",
title = "Lunar gravity assists using patched-conics approximation, three
and four body problems",
journal = "Advances in Space Research",
year = "2019",
volume = "64",
number = "1",
pages = "42--63",
keywords = "Flyby, Swing-by, Lunar gravity assist maneuver, Patched-conics,
Circular restricted three-body problem, Bi-circular restricted
four-bodyproblem.",
abstract = "The gravity assist is a maneuver greatly applied to space
missions, with the main goal of giving or removing energy of a
spacecraftthrough a passage near a celestial body. The
patched-conics approximation is the first approximation that is
usually considered in themission planning. It gives a good
accuracy in the majority of the situations. However, when using
the Moon for the close approach, theresults have a tendency to
diverge from a more complete three body dynamics. This is due to
the large mass of the Moon compared to theEarth. In that sense,
the goal of the present paper is to study the errors given by the
patched-conics approximation in a lunar gravityassist maneuver. To
find those errors we compare the results coming from this
approximation with the equivalent results obtained fromthe
circular restricted three body problem and the bi-circular
restricted four body problem for a same periselenium condition.
This com-parison is made in the orbital elements before the
maneuver and theC3of the spacecraft after the maneuver under the
three modelsconsidered. Different values for the initial
conditions of the spacecraft are used to obtain general
conclusions about the behavior ofthe errors involved. We conclude
that there is a tendency to a better agreement between the
patched-conics and the three body problemfor retrograde transfer
orbits. We also find that the effects of the Sun in the maneuver
needs to be included only in more accurate steps ofthe mission.",
doi = "10.1016/j.asr.2019.04.002",
url = "http://dx.doi.org/10.1016/j.asr.2019.04.002",
issn = "0273-1177 and 1879-1948",
label = "lattes: 0636218258038334 1 NegriSukhBert:2019:LuGrAs",
language = "en",
targetfile = "1-s2.0-S0273117719302455-main.pdf",
urlaccessdate = "27 abr. 2024"
}