Accession Number : AD0766314

Title :   Analytical Approach to Orbit Determination in the Presence of Model Errors,

Corporate Author : TEXAS UNIV AUSTIN DEPT OF AEROSPACE ENGINEERING AND ENGINEERING MECHANICS

Personal Author(s) : Schutz,B. E.

Report Date : JAN 1973

Pagination or Media Count : 11

Abstract : The results of a study are presented in which a spacecraft's acceleration is separated into two components so that one component is tractable to analytical solution and the remaining component is treated as an unmodeled acceleration. By this procedure, an analytical solution to the dynamical equations used in the extended Kalman filter can be obtained. Two cases are considered: the modeled portion is taken to be the problem of two bodies with the perturbations treated as a model error, and the modeled portion is taken to be a straight line with all accelerations treated as a model error. The model error is approximated by a first-order Gauss-Markov process. The approach is evaluated using computer simulations of a lunar orbiter. (Author)

Descriptors :   (*ORBITS, MATHEMATICAL PREDICTION), PERTURBATION THEORY, ANOMALIES, MATRICES(MATHEMATICS), ACCELERATION, THRUST, LUNAR TRAJECTORIES, MATHEMATICAL MODELS

Subject Categories : Spacecraft Trajectories and Reentry

Distribution Statement : APPROVED FOR PUBLIC RELEASE