%0 Journal Article
%@nexthigherunit 8JMKD3MGPCW/446AF4B
%@resumeid
%@resumeid
%@resumeid 8JMKD3MGP5W/3C9JGJA
%X 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.
%8 Feb.
%N 2
%9 journal article
%T Averaged model to study long-term dynamics of a probe about Mercury
%@electronicmailaddress etresaco@unizar.es
%@electronicmailaddress
%@electronicmailaddress antonio.prado@inpe.br
%@secondarytype PRE PI
%K Frozen orbits, Orbital dynamics, Averaged models.
%@archivingpolicy denypublisher denyfinaldraft12
%@usergroup self-uploading-INPE-MCTI-GOV-BR
%@usergroup simone
%@group
%@group
%@group DIDMC-CGETE-INPE-MCTIC-GOV-BR
%@tertiarymark Trabalho não Vinculado à Tese/Dissertação
%@secondarymark A2_ENGENHARIAS_III B1_INTERDISCIPLINAR B1_ASTRONOMIA_/_FÍSICA B2_MATEMÁTICA_/_PROBABILIDADE_E_ESTATÍSTICA B3_ENSINO B3_CIÊNCIA_DA_COMPUTAÇÃO
%@issn 0923-2958
%2 sid.inpe.br/mtc-m21b/2018/02.06.13.00.57
%@affiliation Centro Universitario de la Defensa
%@affiliation Universidade Federal do Recôncavo da Bahia
%@affiliation Instituto Nacional de Pesquisas Espaciais (INPE)
%@affiliation Centro Universitario de la Defensa
%@affiliation Universidade Federal de São Paulo (UNIFESP)
%B Celestial Mechanics and Dynamical Astronomy
%@versiontype publisher
%P e9
%4 sid.inpe.br/mtc-m21b/2018/02.06.13.00
%@documentstage not transferred
%D 2018
%V 130
%@doi 10.1007/s10569-017-9801-9
%A Tresaco, Eva,
%A Carvalho, Jean Paulo S.,
%A Prado, Antonio Fernando Bertachini de Almeida,
%A Elipe, Antonio,
%A Moraes, Rodolpho Vilhena de,
%@dissemination WEBSCI; PORTALCAPES.
%@area ETES
%@holdercode {isadg {BR SPINPE} ibi 8JMKD3MGPCW/3DT298S}