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- Title
Long-term perturbations due to a disturbing body in elliptic inclined orbit.
- Authors
Liu, Xiaodong; Baoyin, Hexi; Ma, Xingrui
- Abstract
In the current study, a double-averaged analytical model including the action of the perturbing body's inclination is developed to study third-body perturbations. The disturbing function is expanded in the form of Legendre polynomials truncated up to the second-order term, and then is averaged over the periods of the spacecraft and the perturbing body. The efficiency of the double-averaged algorithm is verified with the full elliptic restricted three-body model. Comparisons with the previous study for a lunar satellite perturbed by Earth are presented to measure the effect of the perturbing body's inclination, and illustrate that the lunar obliquity with the value 6.68 is important for the mean motion of a lunar satellite. The application to the Mars-Sun system is shown to prove the validity of the double-averaged model. It can be seen that the algorithm is effective to predict the long-term behavior of a high-altitude Martian spacecraft perturbed by Sun. The double-averaged model presented in this paper is also applicable to other celestial systems.
- Subjects
LUNAR satellite orbits; LUNAR artificial satellites; LEGENDRE'S polynomials; ELLIPTICAL orbits; SPACE vehicles; MATHEMATICAL physics
- Publication
Astrophysics & Space Science, 2012, Vol 339, Issue 2, p295
- ISSN
0004-640X
- Publication type
Article
- DOI
10.1007/s10509-012-1015-8