Lunar Perturbations on Artificial Satellites of the Earth
SMITHSONIAN ASTROPHYSICAL OBSERVATORY CAMBRIDGE MA
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Lunisolar perturbations for general terms of the disturbing function were derived by Kaula 1962. However, his formulas use equatorial elements for the Moon and do not give a definite algorithm for computational procedures. As Kozai 1966 suggested, both inclination and node of the Moons orbit with respect to the equator of the Earth are not simple functions of time, while the same elements with respect to the ecliptic are well approximated by a constant and a linear function of time, respectively. In the present work, the author obtains the disturbing function for the Moons perturbations using ecliptic elements for the Moon and equatorial elements for the satellite. Secular, long- period, and short-period perturbations are then computed, with the expressions kept in closed form in both inclination and eccentricity of the satellite.
- Spacecraft Trajectories and Reentry