Time optimal magnetic attitude maneuvers
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abstract
Time-optimal magnetic attitude maneuvers for near-earth, spin-stabilized spacecraft are treated using Pontryagin's Principle. A nonlinear bang-bang switching function is derived for the electromagnets' polarity. The approach is quite general, allowing user prescribed orbit dynamics models and geomagnetic field models. For the case of a single electromagnet aligned with the nominal spin axis of a symmetric satellite, and retaining general orbit and geomagnetic models, the determination of time optimal magnetic maneuvers reduces to a bounded one-dimensional search of an initial costate variable. The formulation is used to construct extremal field maps of typical optimal maneuvers.
