A practical intermediate orbit for artificial satellites

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

Jun 1987

adsabs.harvard.edu/cgi-bin/nph-data_query?bibcode=1987acasn..28..380c&link_type=abstract

(Acta Astronomica Sinica, vol. 28, 1987, p. 380-389) Chinese Astronomy and Astrophysics (ISSN 0275-1062), vol. 12, June 1988, p.

Astronomy and Astrophysics

Astrophysics

1

Astrodynamics, Orbit Perturbation, Satellite Orbits, Two Body Problem, Differential Equations, Equations Of Motion, Hamilton-Jacobi Equation, Perturbation Theory

Scientific paper

A practical intermediate orbit solution for artificial satellites which includes first-order secular perturbations in the argument of pericenter and mean anomaly is presented. The equation of intermediate motion is solved by the Hamilton-Jacobi method to find the relation between the intermediate elements and the Jacobi elements. Equations of perturbed motion which use intermediate elements as variables are given. It is suggested that this intermediate orbit solution is as simple as the solution of the two-body problem.

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