The problem of designing attitude control laws for a Low Earth Orbit (LEO) satellite on the basis of static feedback from a triaxial magnetometer and a set of high precision gyros is considered and an approach based on optimal static output feedback for linear time-periodic system is presented. Simulation results are used to demonstrate the feasibility of the proposed strategy and to evaluate its performance in a realistic setting.
Spacecraft Attitude Control based on Magnetometers and Gyros
LOVERA, MARCO
2013-01-01
Abstract
The problem of designing attitude control laws for a Low Earth Orbit (LEO) satellite on the basis of static feedback from a triaxial magnetometer and a set of high precision gyros is considered and an approach based on optimal static output feedback for linear time-periodic system is presented. Simulation results are used to demonstrate the feasibility of the proposed strategy and to evaluate its performance in a realistic setting.File in questo prodotto:
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