Method for numerical integration of differential equations of satellite motion
Abstract
The paper examines a numerical integration algorithm based on Encke's method for computing perturbations in coordinates and components of the velocity vector, with an intermediate orbit governed by the theory of two fixed centers. As a limiting case the study uses Adams' extrapolationinterpolation formulas with an iteration procedure at the start of integration. The integration is carried out in an inertial rectangular coordinate system; perturbing function coordinates are also computed in an inertial system.
 Publication:

Geodeziia i Aerofotos
 Pub Date:
 1979
 Bibcode:
 1979GeAer....Q..48C
 Keywords:

 Differential Equations;
 Encke Method;
 Equations Of Motion;
 Numerical Integration;
 Orbit Calculation;
 Satellite Orbits;
 Algorithms;
 Inertial Coordinates;
 Integral Equations;
 Perturbation Theory;
 RungeKutta Method