Integrated Power and Attitude Control (IPAC) of a satellite via magnetic bearing supported, flexible shaft flywheels
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This paper provides simulation based demonstrations of IPAC effectiveness while removing the prior assumptions of rigid bearing - rigid shaft flywheels. Spacecraft benefits from IPAC utilization are also provided for lower earth orbit applications. Thus the paper further advances the concept of replacing control moment gyros and electrochemical batteries with an array of high speed, high energy density flywheels. Each flywheel is represented by a series of rigid disks connected by flexible beam elements for an accurate representation of its vibration response. These disks are capable of general 3D translational and rotational motions as is the rigid-modeled satellite. IPAC control is implemented via control of the speeds of the flywheels in the array. A globally asymptotically stable, nonlinear state feedback control law is developed based on Lyapunov stability theory. Excellent power tracking is demonstrated for both charging and delivery, simultaneous with attitude control. Case studies are also provided to demonstrate stability, tracking and disturbance rejection in the presence of initial condition error.
