A practical intermediate orbit for artificial satellites

Astronomy and Astrophysics – Astrophysics

Scientific paper

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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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