NASA NTRS · 19830067546
An analytic solution for the J2 perturbed equatorial orbit
Abstract
An analytic solution for the J2 perturbed equatorial orbit is obtained in terms of elliptic functions and integrals. The necessary equations for computing the position and elocity vectors, and the time are given in terms of known functions. The perturbed periapsis and apoapsis distances are determined from the roots of a characteristic cubic.
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Jezewski, D. J.. 1983-08-01. An analytic solution for the J2 perturbed equatorial orbit. https://ntrs.nasa.gov/citations/19830067546
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