Perturbations of a Spacecraft Orbit During an Hyperbolic Flyby

Details Perturbations of a Spacecraft Orbit During an Hyperbolic Flyby Perturbations of a Spacecraft Orbit During an Hyperbolic Flyby

May 2000

adsabs.harvard.edu/cgi-bin/nph-data_query?bibcode=2000dda....31.1302r&link_type=abstract

American Astronomical Society, DDA Meeting #31, #13.02; Bulletin of the American Astronomical Society, Vol. 32, p.869

Astronomy and Astrophysics

Astronomy

Scientific paper

An analytical theory of the motion of a spacecraft during an hyperbolic flyby will be presented. The perturbations considered are those due to the harmonic coefficients C20 and C22 of the body's gravity field. These harmonic coefficients are the only coefficients of degree two that need to be considered in the case where the gravity harmonic coefficients are refered to the principal axis system of the body. The new theory is a first order perturbation theory with respect to C20 and C22. The perturbations of the hyperbolic elements are expressed in function of the unperturbed values of the elements. There are no further approximation with respect to the eccentricity or inclination, i.e., the equations for the variations of the elements do not involve any infinite series. The results of the new theory will be compared with results of numerical integrations and with results predicted by the Anderson and Giampieri theory (1999).

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