%0 Journal Article
%4 dpi.inpe.br/plutao/2010/12.02.13.23.50
%2 dpi.inpe.br/plutao/2010/12.02.13.23.51
%@doi 10.1007/s10569-010-9310-6
%@issn 0923-2958
%F lattes: 7340081273816424 3 CarvalhoVilhPrad:2010:SoOrCh
%T Some orbital characteristics of lunar artificial satellites
%D 2010
%A Carvalho, Jean P S,
%A Vilhena de Moraes, R.,
%A Prado, Antonio Fernando Bertachini de Almeida,
%@affiliation Univ Estadual Paulista, BR-12516410 Guaratingueta, SP Brazil
%@affiliation Univ Estadual Paulista, BR-12516410 Guaratingueta, SP Brazil
%@affiliation Instituto Nacional de Pesquisas Espaciais (INPE)
%@electronicmailaddress
%@electronicmailaddress
%@electronicmailaddress abertachini@terra.com.br
%B Celestial Mechanics and Dynamical Astronomy
%V 108
%P 371-388
%K MAIN PROBLEM, 3RD-BODY PERTURBATION, CRITICAL INCLINATION, FROZEN ORBITS, POLAR, MODEL, BODY.
%X In this paper we present an analytical theory with numerical simulations to study the orbital motion of lunar artificial satellites. We consider the problem of an artificial satellite perturbed by the non-uniform distribution of mass of the Moon and by a third-body in elliptical orbit (Earth is considered). Legendre polynomials are expanded in powers of the eccentricity up to the degree four and are used for the disturbing potential due to the third-body. We show a new approximated equation to compute the critical semi-major axis for the orbit of the satellite. Lie-Hori perturbation method up to the second-order is applied to eliminate the terms of short-period of the disturbing potential. Coupling terms are analyzed. Emphasis is given to the case of frozen orbits and critical inclination. Numerical simulations for hypothetical lunar artificial satellites are performed, considering that the perturbations are acting together or one at a time.
%@language en
%3 prado.pdf