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- W2044152872 abstract "The motion of a satellite artificial or natural) around the earth, the moon or a major planet can often be treated as a restricted three-body problem with the oblateness of the primary body included. For a high altitude satellite, orbiting around the primary, the perturbation comes from the oblateness of the primary (th J2 term) and the attraction of the third body. The orbital lifetime of such a satellite depends on the oblateness of the primary, its altitude and the inclination of its orbit to the equator of the primary. For a high-altitude satellite, its lifetime cannot be very long if its inclination is large: the gravitational perturbation by the third body means that its orbital eccentricity will so increase that it will eventually fall into the primary." @default.
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- W2044152872 date "2000-07-01" @default.
- W2044152872 modified "2023-09-23" @default.
- W2044152872 title "On the orbital lifetime of high-altitude satellites" @default.
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- W2044152872 doi "https://doi.org/10.1016/s0275-1062(00)00055-2" @default.
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