The critical inclination problem with small eccentricity. II Application to earth satellites

Details The critical inclination problem with small eccentricity. II Application to earth satellites The critical inclination problem with small eccentricity. II Application to earth satellites

Jul 1983

adsabs.harvard.edu/cgi-bin/nph-data_query?bibcode=1983cemec..30..297j&link_type=abstract

Celestial Mechanics (ISSN 0008-8714), vol. 30, July 1983, p. 297-308.

Computer Science

2

Artificial Satellites, Eccentric Orbits, Orbital Mechanics, Satellite Orbits, Hamiltonian Functions, Long Term Effects

Scientific paper

The general theory described in an earlier paper is used to investigate the long-term behaviour of the eccentricity and argument of the perigee for Earth satellites which have nearly circular orbits and orbital inclinations in the neighbourhood of the critical value 63°.4. Taking into account the effect of all the zonal harmonics, it is shown that there are just two types of behaviour possible, compared with the six described in the earlier general theory and the four found by Aoki (1963).

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