Rapid Estimates of Covariance Matrices for Maneuvering Space Vehicle

摘要

A technique is developed for the trajectory parameter tracking of a thrust-maneuvering orbital vehicle when neither the time of the thrusting maneuver nor the magnitude or direction of the thrust vector are known by the tracking observer. The reduced problem of tracking an orbital vehicle constrained to planar movement is examined in order to develop a method of approach applicable to the general tracking problem. A new measurable covariance matrix is introduced to augment the standard sequential parameter estimation scheme and provide a rapid-estimate of both the state and its error covariance immediately following a thrusting maneuver. (Author)