Integrated Control and Magnetic Suspension for Fast Attitude Maneuvering and Stabilization

This paper presents a method for spacecraft to achieve the task of fast maneuvering and fast stabilization. To realize this task, a new type of vibration isolation platform whose actuators are based on magnetic suspension techniques and an attitude controller to suit the spacecraft with this new vibration isolation platform are presented. High-frequency vibrations would reduce the stability of the attitude control, and low-frequency vibrations would reduce the maneuvering time of the attitude control. The vibration isolation platform presented in this paper is assembled between the spacecraft bus and the attitude control actuators and acts to reduce the high-frequency vibrations. The vibration isolation platform, which consists of the vibration isolation strut with magnetic suspension, has better performance in the region of high frequency according to the frequency-domain analysis. An appropriate controller for the vibration isolation strut is designed based on the frequency-domain analysis. Then, the attitude controller of the spacecraft bus is designed using the finite-time control theory to reduce the low-frequency vibrations, thus reducing the maneuvering time. Finally, the numerical simulations show that the vibration isolation platform and the attitude controller do work and cooperate well.