We apply the forward-integration Riccati-based feedback controller developed in prior work to a magnetically actuated spacecraft for the cases of both inertial and nadir pointing. The spacecraft is assumed to be in low-Earth orbit and actuated by only three orthogonal electromagnetic actuators. We assume no advance knowledge of the magnetic field, and thus make no periodicity assumptions, instead relying only on measurements that are available at the current time. We simulate the spacecraft attitude with actuator saturation, noisy magnetic measurements, and without rate feedback. The simulations are based on the International Geomagnetic Reference Field model of the magnetic field.
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