Fast computation of high eccentricity orbits by the stroboscopic method

Details Fast computation of high eccentricity orbits by the stroboscopic method Fast computation of high eccentricity orbits by the stroboscopic method

Sep 1973

adsabs.harvard.edu/cgi-bin/nph-data_query?bibcode=1973cemec...8..245r&link_type=abstract

Celestial Mechanics, Volume 8, Issue 2, pp.245-249

Computer Science

4

Scientific paper

In order to compute with a reasonable accuracy satellite orbits subjected to perturbations byJ 2, the Sun, the Moon and airdrag, a first order expansion is used. The Lagrange equations are solved semi-analytically by the stroboscopic method. The intermediate-, long-periodic and secular terms are obtained, but if desired the same formulism also produces the short-periodic terms. The method is well suited for use on a computer and requires only about 1% of the computing time needed for numerical integration.

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