Simultaneous spacecraft orbit estimation and control based on GPS measurements via extended Kalman filter

The primary aim of this work is to provide simultaneous spacecraft orbit estimation and control based on the global positioning system (GPS) measurements suitable for application to the next coming Egyptian remote sensing satellites. Disturbance resulting from earth’s oblateness till the fourth order (i.e., J4) is considered. In addition, aerodynamic drag and random disturbance effects are taken into consideration.