Abstract
In practical, there exist several occasions that satellitesmay temporarily lose their control over body rate: The high tip-off rate after the separation from launch vehicle, the tumbling caused by avionic reset during daily operation and accidental attitude loss during orbit correction. Unfortunately, uncontrolled body rate and attitude usually prevent on-board optical attitude sensors from locking targets, such as Sun, Earth or stars. This report provides a comprehensive analysis of such a process from initial rate reduction to terminal orientation from the perspective of Lyapunov stability.In addition, with proper coordinate transformation, the B-dot control efficiency is found to be orbit inclination angle dependent. Numerical analysis is performed where the conclusion suggests that the average B-dot control efficiency improves as the inclination angle increases.
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