Patent ID: 6708116
Filing Date: 2004-03-16
Classification: B64G

Abstract:
A method of estimating in real-time an orbit of a satellite using a recursive filter and wherein the recursive filter first receives an a priori state estimate and an a priori state error covariance matrix for the satellite, and wherein the method comprises:inputting tracking measurements for the satellite received in real-time from tracking stations to the recursive filter at filter time update â€œTâ€ ; inputting filter tracking station platform data to the recursive at filter time update â€œTâ€ ; computing recursively the current state estimate, the current error covariance and the current filter measurement update of the satellite at filter time update â€œTâ€ ; moving the state estimate and error covariance from filter time update â€œTâ€  to filter time update â€œT+1â€ ; incorporating into the filter measurement update the information provided by the tracking data measurement at filter time update T; and determining a current estimate of the orbit of the satellite.