@Article{TresacoCarPraEliMor:2018:AvMoSt,
author = "Tresaco, Eva and Carvalho, Jean Paulo S. and Prado, Antonio
Fernando Bertachini de Almeida and Elipe, Antonio and Moraes,
Rodolpho Vilhena de",
affiliation = "{Centro Universitario de la Defensa} and {Universidade Federal do
Rec{\^o}ncavo da Bahia} and {Instituto Nacional de Pesquisas
Espaciais (INPE)} and {Centro Universitario de la Defensa} and
{Universidade Federal de S{\~a}o Paulo (UNIFESP)}",
title = "Averaged model to study long-term dynamics of a probe about
Mercury",
journal = "Celestial Mechanics and Dynamical Astronomy",
year = "2018",
volume = "130",
number = "2",
pages = "e9",
month = "Feb.",
keywords = "Frozen orbits, Orbital dynamics, Averaged models.",
abstract = "This paper provides a method for finding initial conditions of
frozen orbits for a probe around Mercury. Frozen orbits are those
whose orbital elements remain constant on average. Thus, at the
same point in each orbit, the satellite always passes at the same
altitude. This is very interesting for scientific missions that
require close inspection of any celestial body. The orbital
dynamics of an artificial satellite about Mercury is governed by
the potential attraction of the main body. Besides the Keplerian
attraction, we consider the inhomogeneities of the potential of
the central body. We include secondary terms of Mercury gravity
field from J2 up to J6, and the tesseral harmonics C¯ 22 that is
of the same magnitude than zonal J2. In the case of science
missions about Mercury, it is also important to consider
third-body perturbation (Sun). Circular restricted three body
problem can not be applied to MercurySun system due to its
non-negligible orbital eccentricity. Besides the harmonics
coefficients of Mercurys gravitational potential, and the Sun
gravitational perturbation, our average model also includes Solar
acceleration pressure. This simplified model captures the majority
of the dynamics of low and high orbits about Mercury. In order to
capture the dominant characteristics of the dynamics, short-period
terms of the system are removed applying a double-averaging
technique. This algorithm is a two-fold process which firstly
averages over the period of the satellite, and secondly averages
with respect to the period of the third body. This simplified
Hamiltonian model is introduced in the Lagrange Planetary
equations. Thus, frozen orbits are characterized by a surface
depending on three variables: the orbital semimajor axis,
eccentricity and inclination. We find frozen orbits for an average
altitude of 400 and 1000 km, which are the predicted values for
the BepiColombo mission. Finally, the paper delves into the
orbital stability of frozen orbits and the temporal evolution of
the eccentricity of these orbits.",
doi = "10.1007/s10569-017-9801-9",
url = "http://dx.doi.org/10.1007/s10569-017-9801-9",
issn = "0923-2958",
language = "en",
urlaccessdate = "24 abr. 2024"
}