Orbit prediction using vector techniques

Details Orbit prediction using vector techniques Orbit prediction using vector techniques

Aug 1984

adsabs.harvard.edu/cgi-bin/nph-data_query?bibcode=1984adans..54.1049h&link_type=abstract

IN: Astrodynamics 1983; Proceedings of the Conference, Lake Placid, NY, August 22-25, 1983. Part 2 (A84-30526 13-13). San Diego,

Astronomy and Astrophysics

Astronomy

Artificial Satellites, Computer Programs, Error Analysis, Infrared Astronomy Satellite, Orbit Perturbation, Orbital Elements, Runge-Kutta Method, Algorithms, Differential Equations, Equations Of Motion, Numerical Integration, Vector Analysis

Scientific paper

Certain problems can arise in connection with the use of standard astronomical orbital elements in the integration of the Lagrange planetary equations. One of these problems is related to singularities occurring for near-circular or near-equatorial orbits. A suggestion by Newton (1961) was implemented by Sarnecki (1968) who considered the use of the angular momentum vector and eccentricity vector for developing the equations of motion. The present investigation is concerned with an extension of this approach utilizing a fourth order Runge-Kutta integration in order to develop accurately and compactly the orbital elements and events for predictions many month beyond the epoch. The developed methods are used by the program SPIRAL to provide extremely high accuracy element and event predictions for satellites.

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