A practical intermediate orbit for artificial satellites

Details A practical intermediate orbit for artificial satellites A practical intermediate orbit for artificial satellites

Jun 1988

adsabs.harvard.edu/cgi-bin/nph-data_query?bibcode=1988cha%26a..12..114c&link_type=abstract

Chinese Astronomy and Astrophysics, Volume 12, Issue 2, p. 114-118.

Astronomy and Astrophysics

Astrophysics

Scientific paper

Using an intermediate potential V0=-1/r -C1/r -2/2r2, where C1=-3J2/4a02(1-e0>2)3/2(5-6sin2i0C2=-3J2/a0(1-e02)(2-5/2sin2i0), the first order secular perturbations in the argument of pericenter and mean anomaly are included in the intermediate potential. The solution of the intermediate orbit is as simple as the solution of the two-body problem.

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