Near Earth spacecraft autonomous navigation using magnetometer measurements is presented. An orbit state vector comprised of six Keplerian elements, enables the estimation of the instantaneous orbital elements and the spacecraft position within a few km by a relatively simple formulation of an extended Kalman filter algorithm. Two kinds of measurements are examined: the magnitude of the magnetic field vector which can be used when there is no accurate knowledge of the spacecraft attitude and the magnetic field vector components which reduce the level of estimation errors and convergence time. The estimation algorithm presented was successfully applied to real satellite data obtained from the mgnetometer readings of the Earth Radiation Budget Satellite (ERBS).
Near Earth Orbit Determination Using Magnetometers
1991
6 pages
Report
No indication
English
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