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首页> 外文期刊>IEEE Transactions on Aerospace and Electronic Systems >Integrated Control and Magnetic Suspension for Fast Attitude Maneuvering and Stabilization
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Integrated Control and Magnetic Suspension for Fast Attitude Maneuvering and Stabilization

机译：用于快速姿态操纵和稳定的集成控制和磁悬浮

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摘要

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.
机译：本文提出了一种宇宙飞船的方法，实现快速机动和快速稳定的任务。为了实现这项任务，介绍了一种新型的振动隔离平台，其致动器基于磁悬浮技术和姿态控制器，以适应宇宙飞船与这种新的隔振平台。高频振动会降低姿态控制的稳定性，低频振动会降低姿态控制的机动时间。本文提出的振动隔​​离平台在航天器总线和姿态控制执行器之间组装并采用以降低高频振动。根据频域分析，振动隔离平台由具有磁悬浮带有磁悬浮的振动隔离支柱，在高频区域具有更好的性能。基于频域分析设计了用于振动隔离支柱的适当控制器。然后，使用有限时间控制理论设计航天器总线的姿态控制器以降低低频振动，从而减少机动时间。最后，数值模拟表明，隔振平台和姿态控制器确实工作并合作。

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