Receding Horizon Control on Steering of Control Moment Gyro for Fast Attitude Maneuver

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  • TAKADA Kohei
    Department of Aerospace Engineering, Tokyo Metropolitan University
  • KOJIMA Hirohisa
    Department of Aerospace Engineering, Tokyo Metropolitan University

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  • Receding horizon control on steering of control moment gyro for fast attitude maneuvers

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Abstract

A Control Moment Gyro (CMG) is a momentum-exchange torque generator. Compared to other momentum-exchange torque generators, such as reaction wheels, this device has advantages of high output torques and rapid responses. Despite these advantages, singularities and the nonlinear nature of the steering logic of this device have hampered its application in small spacecraft control. Although there have been many studies of singularity avoidance, in practice, attitude settling times of maneuvers using CMG have been slow when trajectories produced by this control method pass through or near the singularities. In this works, we applied Receding Horizon (RH) control to CMG steering to overcome such problems described and obtain fast attitude maneuver times. This is achieved by choosing the difference between the current attitude and the target attitude as a performance index with which to determine controller gains for this control method. The results of numerical simulations show that our method achieves superior attitude maneuvering times to singularity avoidance steering laws when singularities are encountered.

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