Abstract
The transformation of classical orbit element perturbations to perturbations in position and velocity in the radial, transverse and normal directions of the orbital frame is developed. The formulation is given for the case of mean anomaly perturbations as well as for eccentric and true anomaly perturbations. Approximate formulas are also developed for the case of nearly circular orbits and compared with those found in the literature.
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Casotto, S. Position and velocity perturbations in the orbital frame in terms of classical element perturbations. Celestial Mech Dyn Astr 55, 209–221 (1993). https://doi.org/10.1007/BF00692510
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DOI: https://doi.org/10.1007/BF00692510