Patent ID: 7860617
Filing Date: 2010-12-28
Classification: B64G

Abstract:
1. A spacecraft system comprising: a measurement device configured to measure information associated with position of a spacecraft; a filter configured to process the measured information and to provide estimated pre-maneuver information associated with position of the spacecraft and estimated post-maneuver information associated with position of the spacecraft; a propagator configured to predict post-maneuver information associated with position of the spacecraft based upon the estimated pre-maneuver information associated with position of the spacecraft and a model of a maneuver of the spacecraft; an error calculator configured to calculate an acceleration error using a state transition matrix, the acceleration error based upon the estimated post-maneuver information associated with position of the spacecraft and the predicted post-maneuver information associated with position of the spacecraft; and a maneuver archive configured to store the acceleration error for updating the model of the maneuver, wherein the state transition matrix is identified by Φ(t  where