Abstract
A near-minimum-t ime (near-maximum-acceleration/deceleration) control technique is presented to rotate a spacecraft around its eigenaxis (shortest angular path). Practical control constraints such as wheel torque and wheel speed are also taken into account. In this paper a nominally nadir pointing satellite in a circular low Earth orbit under passive gravity gradient stabilization and active reaction wheel control will be used as an example. A standard linear feedback quaternion regulator will be used to three-axis stabilize the spacecraft before and after each large angular rotation. Robustness against inertia modeling errors is ensured by tracking the reference maneuver. The algorithm presented can easily be adapted to be used on inertially stabilized spacecraft.
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