NASA NTRS · 19760014147
Pines method for circular and elliptical orbits
Abstract
The Pines method for trajectory integration is derived from the equations of two-body motion. The concept of the perturbation derivative is explained and a formal definition is presented. An algorithm for applying the Pines method to numerical integration of trajectories is included.
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Semar, C.. 1976-02-01. Pines method for circular and elliptical orbits. https://ntrs.nasa.gov/citations/19760014147
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