Model independent near eigenaxis rotation for spacecraft maneuver under slew rate and control constraints

The problem of reorientating a rigid spacecraft from arbitrary initial conditions to prescribed final conditions with zero angular velocity as fast as possible within the physical limits of actuators and sensors is investigated. With the Cascade-Saturation control logic, a nonlinear model independent feedback control law that accommodates the actuator and sensors saturation limits is introduced. Finally, the simulation of near-eigenaxis rotation control algorithm is provided, the result of which proves that this algorithm is of with effectiveness and reliability.