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 -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
Journal of Spacecraft and Rockets ; 53 , 3 ; 507-519
2016-05-01
Article (Journal)
Electronic Resource
English
Stabilization and Attitude Determination Methods for FalconSAT-3
Online Contents | 2016
|THE FALCONSAT-2 RESEARCH PROGRAM
British Library Conference Proceedings | 2006
|FalconSAT-3 and the Space Environment
AIAA | 2010
|Hybrid Diagnostics for the FalconSAT-5 Sciencecraft
AIAA | 2011
|FalconSAT-7: A Photon Sieve Solar Telescope
British Library Conference Proceedings | 2011
|