Abstract
Spacecraft formations typically have to rely upon active control methods to maintain stable configurations. This requirement imposes an associated cost on the satellite through fuel expenditure, actuator mass, and computation time for the controller. This paper proposes using the flux-pinning interaction between a high-temperature superconductor and amagnetic field as ameans to reduce these costs by passively stabilizing the dynamics governing the relative motion between spacecraft. A simplified model of a flux-pinned spacecraft formation is developed to provide the framework for future analysis. Linearization of this model about an equilibrium state allows for the development of a state-feedback control law. This framework is then applied to a simplified two-spacecraft formation in a nominally circular orbit about a central body and controlled to two distinct equilibrium separations.
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