Patent ID: 7860617

Claim:
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 s ,t m ) and satisfies the following relationship: [ δ ⁢ ⁢ r s δ ⁢ ⁢ v s ] = Φ ⁡ ( t s , t m ) ⁡ [ δ ⁢ ⁢ r m δ ⁢ ⁢ v m ] , where t m is the time of the maneuver of the spacecraft, t s is a time after the maneuver of the spacecraft, δr s is a difference between observed and predicted positions of the spacecraft at t s , δv s is a difference between observed and predicted velocities of the spacecraft at t s , δr m is a difference between observed and predicted positions of the spacecraft at t m , and δv m is a difference between observed and predicted velocities of the spacecraft at t m .