Abstract
This paper describes the experimental method for determining and controlling satellite attitude using a simulator. The simulator utilizes a satellite model supported by an air-bearing. A mini-computer is used in an on-line mode for processing data from the sun sensor and the earth sensor and for calculating the timing of gas jet firing.
The software system for the attitude determination and control of a spinning satellite in a geostationary orbit was tested by the above mentioned apparatus and its performance was confirmed.
The attitude determination program adopts the Kalman filter technique. The effect of attitude drift due to the earth rotation and gravity is taken away from the raw data. The attitude control program adopts the Rhumb line method and the great circle method.
