Spacecraft Attitude Control Based on Magnetometers and Gyros

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.