Abstract
This study examines the concepts of autonomous spacecraft navigation, attitude determination and control. Navigation in orbit requires a minimum of two independent horizon to celestial body measurements that are correlated with time to establish a position in orbit over the earth. Sensor systems applicable for navigation are combinations of one sun sensor, star sensor, horizon sensor and clock, or star sensor, horizon sensor and clock. The clock is necessary to correlate inertial position with the earth's rotation. Star sensor measurements have distinct advantages over use of a sun sensor. A star sensor provides a higher rate of usable data than a sun sensor because there are more celestial objects for it to detect. Star and horizon sensor data combinations allow independent and concurrent navigation and attitude determination.
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