The invention discloses a permanent magnet momentum sphere for attitude adjustment of a small spacecraft, which comprises a stator, a rotor and a support structure, and is characterized in that the stator is provided with a spherical cavity, and coils are mounted at six vertex positions of the spherical cavity by using pole yokes to form a spherical inner cavity for accommodating the rotor; the rotor is arranged in the spherical inner cavity and is provided with a pair of disc-shaped magnetic conductive bridges, a pair of permanent magnets with opposite polarities are symmetrically arranged on the outer ring surface of each magnetic conductive bridge in the radial direction, and the permanent magnets are magnetized in the radial direction of the spherical inner cavity; the supporting structure is a T-shaped rod, and the upper end of a vertical rod in the T-shaped rod is supported on a beam component of the stator in a single-end rotating mode through a bearing, so that spinning motion of the rotor is achieved. The pair of magnetic bridges are rotationally arranged at the two ends of the cross rod through bearings respectively, so that the rotor can turn over; the spinning and overturning motion of the permanent magnet momentum sphere is realized by changing the coil current, so that momentum exchange is realized, and the attitude of a spacecraft is adjusted. The motor is high in power density, large in output torque, high and adjustable in rotating speed and stable in structure.

    本发明公开了一种小型航天器调姿用永磁动量球,包括定子、转子和支撑结构,定子具有球形空腔,在球形空腔的六个顶点位置处利用极轭安装线圈,形成用于容置转子的球形内腔;转子设置在球形内腔中,具有一对呈盘状的导磁桥,各导磁桥外环面上呈径向对称设置一对极性相反的永磁体,永磁体沿球形内腔的径向为充磁方向;支撑结构为“T”形杆,“T”形杆中竖杆的上端利用轴承单端转动支撑在定子的梁构件上,实现转子的自旋运动;一对导磁桥分别通过轴承转动设置在横杆的两端,实现转子的翻转运动;通过改变线圈电流实现永磁动量球的自旋与翻转运动进而实现动量交换,调整航天器姿态。本发明功率密度高、输出转矩大、转速高且可调且结构稳定。


    Zugriff

    Download


    Exportieren, teilen und zitieren



    Titel :

    Permanent magnet momentum ball for attitude adjustment of small spacecraft


    Weitere Titelangaben:

    一种小型航天器调姿用永磁动量球


    Beteiligte:
    GUO XIWEN (Autor:in) / FANG ZHAOWEI (Autor:in) / ZHOU RUI (Autor:in) / WANG QUNJING (Autor:in) / LI GUOLI (Autor:in) / ZHANG RONGLIN (Autor:in)

    Erscheinungsdatum :

    2024-03-01


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Chinesisch


    Klassifikation :

    IPC:    B64G Raumfahrt , COSMONAUTICS



    Three Axis Authority Momentum Spacecraft Attitude Control

    Barker, L. / Price, X. / Rodden, J. | AIAA | 2002



    Momentum Bias for Spacecraft Attitude (AAS 02-003)

    Rodden, J. / McGovern, L. / Higham, J. et al. | British Library Conference Proceedings | 2002


    Attitude and Momentum Management of Inertial Oriented Spacecraft

    Zhu, Mengping / Chen, Xinlong / Li, Zhi | ASCE | 2014