FalconSAT-3 is a cadet-built and -operated satellite that was launched in 2007. In late 2014, cadets successfully stabilized the satellite for the first time through an operational test campaign using a B-dot controller. This paper describes the many challenges in attitude stabilization and determination, and the solutions provided to achieve partial mission capability of two payloads with a magnetometer as the only sensor. Due to problems with onboard sun sensors, engineers have used solar panel currents to create a sun vector to perform a full three-axis attitude determination. This paper compares two different methods for determining the sun vector from solar panel currents and uses the triad method to perform a three-axis attitude determination. A discussion of the key lessons learned from the cadet-run satellite operations is also included.
Stabilization and Attitude Determination Methods for FalconSAT-3
2016
Aufsatz (Zeitschrift)
Englisch
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