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.


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    Title :

    Stabilization and Attitude Determination Methods for FalconSAT-3


    Contributors:

    Published in:

    Publication date :

    2016-05-01




    Type of media :

    Article (Journal)


    Type of material :

    Electronic Resource


    Language :

    English




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