Determination of an intermediate perturbed orbit from three position vectors

Details Determination of an intermediate perturbed orbit from three position vectors Determination of an intermediate perturbed orbit from three position vectors

Apr 2007

adsabs.harvard.edu/cgi-bin/nph-data_query?bibcode=2007astl...33..270s&link_type=abstract

Astronomy Letters, Volume 33, Issue 4, pp.270-282

Astronomy and Astrophysics

Astronomy

1

Scientific paper

We suggest a new approach to solving the problem of finding the orbit of a celestial body from its three spatial position vectors and the corresponding times. It allows most of the perturbations in the motion of a celestial body to be taken into account. The approach is based on the theory of intermediate orbits that we developed previously. We construct the orbit the motion along which is a combination of two motions: the motion of a fictitious attracting center whose mass varies according to Mestschersky’s first law and the motion relative to the fictitious center. The first motion is generally parabolic, while the second motion is described by the equations of the Gylden-Mestschersky problem. The constructed orbit has such parameters that their limiting values at any reference epoch define a superosculating intermediate orbit with a fourth-order tangency. We have performed a numerical analysis to estimate the accuracy of approximating the perturbed motion of two minor planets, 145 Adeona and 4179 Toutatis, by the orbits computed using two-position procedures (the classical Gauss method and the method that we suggested previously), a three-position procedure based on the Herrick-Gibbs equation, and the new method. Comparison of the results obtained suggests that the latter method has an advantage.

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