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Created Aug 11, 2021 by Bryan Cazabonne@bryanMaintainer

Wrong implementation of Kalman estimation using DSST propagator

Current implementation of orbit determination using both DSST propagator and Extended Kalman Filter (EKF) is not correct. Orbit determination based on semi-analytical satellite theory and recursive filter must be done using a specific algorithm: the Extended Semi-analytical Kalman Filter (ESKF). The EKF algorithm needs to re-initialize the orbital state at each observation epoch. However, the time difference between two observations is usually much smaller than the DSST step size (e.g., half a day). ESKF reconciles the conflicting goal of both theories.

Current implementation (DSSTKalmanModel) must be removed and replace by a new implementation.

For more details about the equations and the theory [1] [2] [3]

[1]: Taylor S. P., Semi-analytical Satellite Theory and Sequential Estimation, Master of Science Thesis, Department of Mechanical Engineering, MIT, September, 1981

[2]: Wagner E. A., Application of the Extended Semianalytical Kalman Filter to Synchronous Orbits, Master of Science Thesis, Department of Aeronautics and Astronautics, MIT, June, 1983

[3]: Folcik Z., Orbit Determination Using Modern Filters/Smoothers and Continuous Thrust Modeling, Master of Sci- ence Thesis, Department of Aeronautics and Astronautics, MIT, June, 2008

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