On numerical integration of the equations of motion of artificial earth satellites for orbits with large eccentricities.
Abstract
A numerical experiment on integration of the equations of satellite motion in the case of highly eccentric orbits is performed by applying KustaanheimoStifel (KS) regularization. The integration errors are estimated by comparing the initial and final values in forwardand backwarddifference integration; run times are also estimated for different choices of the index n in the formula ds = r to the n dt, which determines the independent variable s. It is shown that the best results are obtained for n = 1.
 Publication:

Byulleten' Instituta Teoreticheskoj Astronomii (Leningrad)
 Pub Date:
 1979
 Bibcode:
 1979BITA...14..486M
 Keywords:

 Eccentric Orbits;
 Numerical Integration;
 Orbital Mechanics;
 Satellite Orbits;
 Equations Of Motion;
 Error Analysis;
 Orbit Perturbation;
 Astrodynamics;
 Artificial Satellites:Motions