LinCov Analysis of an Automated Celestial InertialNavigation Approach for GEO Satellites

摘要

This paper describes a preliminary error analysis of an automated celestial based inertial navigation scheme for a spacecraft located at GEO. The navigation scheme employs line-of-sight measurements to the moon and sun for onboard inertial orbit determination. A linear covariance analysis is used to determine the expected navigation error envelope and to determine the navigation system's sensitivity to potential error sources.