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A novel method is presented to carry out near-minimum-time maneuvers of a spacecraft of unknown inertia. The formulation assumes the presence of three orthogonal reaction wheels located near the system mass center and oriented arbitrarily with respect to the spacecraft principal axes. Modie ed Rodrigues parameters along with their shadow set are used as the primary attitude coordinates. Open-loop maneuver laws are designed while solving the equations of motion by inversedynamics approach. This approach permits theapproximateimposition of the maximum saturation torque constraint. The torque proe les are near-bang-bang, with the instantaneous switches replaced by cubicsplinesof specie edduration.An adaptivetrackingcontrollawisdeveloped to determine perturbations to the nominal open-loop torque commands that will ensure the actual motion to follow the nominal motion in the presence of uncertainty in the inertia matrix and errors in the initial attitude. Global stability of the overall closed-loop controller is proved analytically and demonstrated by numerical simulations.
Junkins et al. (Sat,) studied this question.