Abstract
The dynamics of flexible spacecraft structures with embedded magnetic actuators are studied. Discretized equations of motion for a constrained plate model and an unconstrained two-plate/rigid bus model are derived for actuators that create in-plane forces via current-carrying coils. Taking inputs to be the magnetic forces generated between pairs of coils, the goal of vibration suppression is shown to result in a bilinear control problem. The selection of a generalized rate output variable is used to obtain a passive map from coil-pair force inputs, yielding $$\mathscr {L}_2$$ stability for strictly passive feedback laws. The implementation of one such feedback corresponds to using collocated sensing at the actuator locations, and given mild assumptions about the actuator location, is a robust stabilizer with respect to unstructured uncertainties. Simulations of the closed-loop system are completed to support findings throughout.
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