Generalized solutions for relative spacecraft orbits under arbitrary perturbations

Details Generalized solutions for relative spacecraft orbits under arbitrary perturbations Generalized solutions for relative spacecraft orbits under arbitrary perturbations

Jan 2007

adsabs.harvard.edu/cgi-bin/nph-data_query?bibcode=2007acaau..60...61g&link_type=abstract

Acta Astronautica, v. 60, iss. 2, p. 61-78.

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Methodology

1

Orbital Elements, Orbit Evolution, Spacecraft

Scientific paper

This paper develops generalized analytic solutions of relative spacecraft dynamics in the presence of arbitrary perturbations and presents new perturbation-invariant relative orbits. The extension of existing results is achieved by using non-osculating orbital elements, i.e. removing the constraint that the instantaneous velocity vector be tangential to an instantaneous Keplerian ellipse. Generalized planetary equations are developed and averaged to yield a non-osculating description of the long-term effects of first-order small perturbations. The generalized planetary equations are linearized, and expressions for the relative dynamics are presented in terms of non-osculating classical orbital element differences. The developed methodology is utilized to find previously undetected J_2-invariant relative orbits.

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