We present method for in-flight signal processing and calibration of a strap-down inertial navigation system (SINS) for the information mini-satellites at low Earth orbit. We have applied the SINS correction based on the signals of a sun-magnetic system and consider the problem at a long-term forecasting of the mini-satellite's orbital motion.
Low cost attitude determination system for a LEO information mini-satellite
01.06.2015
1349166 byte
Aufsatz (Konferenz)
Elektronische Ressource
Englisch
Mitigating Measurement Errors in a Low Cost Satellite Attitude Determination System
British Library Conference Proceedings | 1995
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