The problem of maneuvering a satellite relative to a desired noninertial reference is examined by using linearizing transformations and the concept of relative quaternion. The rigid body attitude equations are transformed into an equivalent linear form which considers the fact that the control purpose is to align the satellite with a moving reference frame (e.g., and Earth resource satellite). The equations so obtained are used to design control strategies for stabilizing the satellite attitude by linear techniques. This approach is more useful for algorithm design for on-board processors than the technique using inertial quaternion since the laws obtained are a function of the noninertial sensor outputs (sun sensors, earth sensors, etc.) and of the inertial sensor (gyroscopes) outputs.
Satellite Attitude Control Analysis and Design Using Linearizing Transformations
1988
7 pages
Report
No indication
English
Dynamic Feedback Linearizing Attitude Control of Spacecraft with Uncertain Dynamics
British Library Conference Proceedings | 1998
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