Orbit prediction for IRAS using vector and analytic techniques
Abstract
This paper describes the techniques of a vector approach to the solution of the differential equations of motion of a nearearth satellite. The method provides a good stable foundation for developing the orbital elements, thus allowing an analytic approach to be used in subsidiary algorithms. The mathematical concepts used in these algorithms are explained, and equations are developed for calculating earth and moon eclipses, radiation zone crossings, atmospheric density effects, solar cell decay, look angles and a geographical ephemeris. Results are presented for the IRAS satellite, and show that prediction errors of less than 1 1/2 seconds over one week or errors of less than 15 seconds over 3 1/2 months are possible.
 Publication:

Budapest International Astronautical Federation Congress
 Pub Date:
 October 1983
 Bibcode:
 1983buda.iafcS....H
 Keywords:

 Infrared Astronomy Satellite;
 Orbit Calculation;
 Orbital Mechanics;
 Satellite Orbits;
 Vector Analysis;
 Aerodynamic Drag;
 Atmospheric Density;
 Equations Of Motion;
 Orbital Elements;
 Radiation;
 Astrodynamics