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A Spherical Magnetic Dipole Actuator for Spacecraft Attitude Control.

机译：用于航天器姿态控制的球形磁偶极执行器。

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摘要

Spacecraft generally require multiple attitude control devices to achieve full attitude actuation because of the limited control authority a single, traditional device can provide. This work presents a new momentum-exchange device that has the potential to replace traditional attitude control systems with a single actuator, in turn providing mass, volume, and power savings. The proposed actuator consists of a spherical dipole magnet enclosed in an array of coils that are fixed to the spacecraft body. Excitation of the coils as prescribed by the control law accelerates the dipole magnet in such a manner as to produce a desired reaction torque for orienting the spacecraft. The coils also control the magnet's position inside the spacecraft body via a separate control law, which is necessary because of the non-contact nature of the device. Analytical force and torque models are developed and are used in an attitude regulation maneuver. Simulations conducted so far indicate that full attitude control is possible from a single device despite the axisymmetric field of the magnetic dipole rotor, which was anticipated to cause control issues. Finally, the single actuator system is compared to a cluster of three reaction wheels, illustrating how this device can provide mass, volume, and power savings.
机译：由于单个传统设备可提供的控制权限有限，航天器通常需要多个姿态控制设备才能实现完全姿态致动。这项工作提出了一种新的动量交换装置，该装置有可能用单个执行器代替传统的姿态控制系统，进而节省质量，体积和功率。提出的致动器由球形偶极磁体组成，球形偶极磁体封装在固定于航天器主体的一系列线圈中。控制法规定的线圈的励磁以产生用于使航天器定向的期望反作用转矩的方式使偶极磁体加速。线圈还通过单独的控制律控制航天器内部磁体的位置，这是必需的，因为该装置具有非接触性。开发了分析力和扭矩模型，并将其用于姿态调节操作中。到目前为止进行的模拟表明，尽管磁偶极子转子的轴对称磁场可能会导致控制问题，但单个设备仍可以进行全姿态控制。最后，将单个执行器系统与三个反作用轮的集群进行了比较，说明了该设备如何提供质量，体积和功率节省。

著录项

  • 作者

    Chabot, J. A.;

  • 作者单位

    University of Colorado at Boulder.;

  • 授予单位 University of Colorado at Boulder.;
  • 学科 Aerospace engineering.;Mechanical engineering.
  • 学位 M.S.
  • 年度 2015
  • 页码 56 p.
  • 总页数 56
  • 原文格式 PDF
  • 正文语种 eng
  • 中图分类
  • 关键词

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