Feedback Control Logic for Spacecraft Eigenaxis Rotations Under Slew Rate and Control Constraints

摘要

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 near-minimum-time eigenaxis reorientation problem of the X-ray 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.