%0 Journal Article
%@holdercode {isadg {BR SPINPE} ibi 8JMKD3MGPCW/3DT298S}
%@nexthigherunit 8JMKD3MGPCW/3F2UALS
%@nexthigherunit 8JMKD3MGPCW/446AF4B
%2 sid.inpe.br/mtc-m21b/2017/11.30.17.55.50
%4 sid.inpe.br/mtc-m21b/2017/11.30.17.55
%3 goncalves_orbital.pdf
%9 journal article
%@issn 1742-6588
%A Gonçalves, Liana Dias,
%A Rocco, Evandro Marconi,
%A Moraes, R. V. de,
%@secondarytype PRE PI
%B Journal of Physics: Conference Series
%D 2017
%@archivingpolicy denypublisher denyfinaldraft12
%P 012022
%@secondarymark B2_INTERDISCIPLINAR B2_ENGENHARIAS_III B3_MEDICINA_II B3_GEOCIÊNCIAS B4_MATERIAIS B4_ENGENHARIAS_II B4_BIOTECNOLOGIA C_QUÍMICA C_MATEMÁTICA_/_PROBABILIDADE_E_ESTATÍSTICA C_ENGENHARIAS_IV C_ECONOMIA C_ASTRONOMIA_/_FÍSICA
%T Orbital trajectories in deimos vicinity considering perturbations of gravitational origin
%V 911
%X The present work studies the possibility of maintaining an artificial satellite near to the Deimos surface, even when considering the intense Mars gravitational attraction. For this, a strategy is used in which the spacecraft orbits Mars, but with the same orbital period of Deimos and similar orbital elements. Using this strategy, the deviations in the keplerian elements that characterize the artificial satellite orbit, the magnitude of the main disturbing forces capable of altering the movement of the spacecraft and the variation of the distance between the spacecraft and Deimos are presented.
%@area ETES
%@electronicmailaddress lianadgon@gmail.com
%@electronicmailaddress evandro.rocco@inpe.br
%@documentstage not transferred
%@group CMC-ETES-SESPG-INPE-MCTIC-GOV-BR
%@group DIDMC-CGETE-INPE-MCTIC-GOV-BR
%@dissemination WEBSCI; PORTALCAPES; SCOPUS.
%@usergroup simone
%@resumeid
%@resumeid 8JMKD3MGP5W/3C9JH37
%@affiliation Instituto Nacional de Pesquisas Espaciais (INPE)
%@affiliation Instituto Nacional de Pesquisas Espaciais (INPE)
%@affiliation Universidade Federal de São Paulo (UNIFESP)
%@versiontype publisher
%@doi 10.1088/1742-6596/911/1/012022