Abstract
This paper presents an approach to steering control moment gyroscopes. A technique based on feedback linearization theory is used to transform the original nonlinear problem to an equivalent linear form without approximating assumptions. Under this transformation, the spacecraft dynamics appear linearly, and are decoupled from redundancy in the system of gyroscopes. A general approach to distributing control effort among the available actuators is described that includes provisions for redistribution of rotors, explicit bounds on gimbal rates, and guaranteed operation at and near singular configurations. A particular algorithm is developed for systems of double-gimballed devices, and demonstrated in two examples for which many existing approaches fail to give adequate performance.
Original language | English |
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Pages (from-to) | 96-106 |
Number of pages | 11 |
Journal | Journal of Guidance, Control, and Dynamics |
Volume | 14 |
Issue number | 1 |
DOIs | |
State | Published - Jan 1991 |
ASJC Scopus subject areas
- Aerospace Engineering
- Applied Mathematics
- Electrical and Electronic Engineering
- Control and Systems Engineering
- Space and Planetary Science