Abstract
A new symplectic algorithm is developed for cometary orbit integrations. The integrator can handle both high-eccentricity orbits and close encounters with planets. The method is based on time transformations for Hamiltonians separated into Keplerian and perturbation parts. The adaptive time-step of this algorithm depends on the distance from a centre and the magnitude of perturbations. The explicit leapfrog technique is simple and efficient.
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Emel'yanenko, V. An Explicit Symplectic Integrator for Cometary Orbits. Celestial Mechanics and Dynamical Astronomy 84, 331–341 (2002). https://doi.org/10.1023/A:1021125829276
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DOI: https://doi.org/10.1023/A:1021125829276