On the accuracy of approximation of a small celestial body motion using intermediate perturbed orbits calculated from two position vectors and three observations

Эндаумент фонд ТГУ!
Впиши своё имя в историю университета
- Сделать пожертвование -

Add to "Quick Collection"

Description	Size	Format
On the accuracy of approximation of a small celestial body motion using intermediate perturbed orbits calculated from two position vectors and three observations	593 KB	Adobe Acrobat PDF	Read	Download
DOI Доступ к ресурсу на сайте издателя			10.1134/S0038094615010074

Title: On the accuracy of approximation of a small celestial body motion using intermediate perturbed orbits calculated from two position vectors and three observations
Creator: Shefer, Vladimir A.
|
Shefer, Olga V.
Date: 2015
DOI: 10.1134/S0038094615010074
Description: We examine intermediate perturbed orbits proposed by the first author previously, defined from the two position vectors and three angular coordinates of a small celestial body. It is shown theoretically, that at a small reference time interval covering the measurements the approximation accuracy of real movements by these orbits corresponds approximately to the third order of osculation. The smaller reference interval of time, the better this correspondence. Laws of variation of the methodical errors in constructing intermediate orbits subject to the length of reference time interval are deduced. According to these laws, the convergence rate of the methods to the exact solution (upon reducing the reference interval of time) is higher by two orders of magnitude than in the case of conventional methods using the Keplerian unperturbed orbit. The considered orbits are among the most accurate in set of orbits of their class determined by the order of osculation. The theoretical results are validated by numerical examples.

Created: 28-11-2016

975 Visitors

783 Hits

200 Downloads

НИИ прикладной математики и механики On the accuracy of approximation of a small celestial body motion using intermediate perturbed orbits calculated from two position vectors and three observations