We have emphasized the relative two-body solution to the trajectory problem. But forces other than the central body’s gravitational force act on a spacecraft, perturbing it away from the Keplerian orbit. In this chapter, we identify types of perturbations, using perturbation techniques, and draw from the astrodynamics techniques described in Chap. 4. We culminate our study of non-Keplerian motion by considering the satellite orbit paradox and its applications to atmospheric drag, libration of 24-hr, nearly circular equatorial satellites, and the fact that the Moon is slowly moving away from the Earth.


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