Some orbital characteristics of lunar artificial satellites

Author(s)

Carvalho, J. P. S. ^[1] ; Vilhena de Moraes, R. ^[1] ; Prado, A. F. B. A. ^[2]

Affiliation

^[1] Univ Estadual Paulista, BR-12516410 Guaratingueta, SP - Brazil

^[2] INPE, Div Space Mech & Control, BR-12227010 Sao Jose Dos Campos, SP - Brazil

• Document type: Journal article
• Source: CELESTIAL MECHANICS & DYNAMICAL ASTRONOMY; v. 108, n. 4, p. 371-388, DEC 2010.
• Web of Science Citations: 29

Abstract

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. (AU)

• FAPESP's process: 06/04997-6 - Close approach problems in orbital dynamics
• Grantee: Rodolpho Vilhena de Moraes
• Support Opportunities: Research Projects - Thematic Grants