Feedback control logic for spacecraft eigenaxis rotations under slew rate and control constraints

The problem of reorienting a rigid spacecraft as fast as possible within the physical limits of actuators and sensors is investigated. In particular, a nonlinear feedback control logic which accommodates the actuator and sensor saturation limits is introduced. The nearminimum-time eigenaxis reorientation problem of the Xray Timing Explorer spacecraft under slew rate and control torque constraints is used as an example to demonstrate the effectiveness and simplicity of the proposed nonlinear feedback control logic.