Sequential orbit determination with autocorrelated gravity modeling errors
Abstract
A sequential orbit determination algorithm is given which models autocorrelated gravity errors for near circular orbits. Using results from geodesy theory (Kaula, 1959; Heiskanen, 1967), it is demonstrated that gravity modeling error autocorrelation cannot be approximated with the Kalman white process noise model. The resulting autocorrelated orbit error process is transformed from the status of nonMarkov to Markov at the expense of an assumption which imposes symmetries on certain covariance functions. It is emphasized that the character of the trajectory estimation problem is significantly changed by recognizing and using the autocorrelation property associated with gravity modeling errors.
 Publication:

AIAA, Aerospace Sciences Meeting
 Pub Date:
 January 1980
 Bibcode:
 1980aiaa.meetR....W
 Keywords:

 Error Analysis;
 Gravitational Effects;
 Orbit Calculation;
 Orbit Perturbation;
 Sequential Analysis;
 Algorithms;
 Approximation;
 Autocorrelation;
 Circular Orbits;
 Eccentric Orbits;
 Kalman Filters;
 Markov Processes;
 Mathematical Models;
 Astrodynamics