A semianalytical, artificial satellite orbit propagation procedure based on optimal parameter estimation
Abstract
A procedure to propagate the orbit of terrestrial artificial satellite using parameterized mathematical expression is presented. With numerically simulated observation data along one period and the help of linear systems estimation theory, particulary the Kalman filter technique, the parameters of the mathematical expressions are estimated. This allows approximate time variation equations for the orbital elements. Orbit propagation is then accomplished with considerable saving in computational efforts.
 Publication:

NASA STI/Recon Technical Report N
 Pub Date:
 October 1984
 Bibcode:
 1984STIN...8518997D
 Keywords:

 Artificial Satellites;
 Kalman Filters;
 Orbit Perturbation;
 Orbital Position Estimation;
 Parameter Identification;
 Computerized Simulation;
 Equations Of Motion;
 Interpolation;
 Linear Systems;
 Mathematical Models;
 Space Simulators;
 Vectors (Mathematics);
 Astrodynamics