The invention discloses an asymmetric configuration satellite angular momentum unloading method and device, and the method comprises the steps: obtaining a sun vector under a satellite body system through a sun sensor, and converting the sun vector into a sun vector under an orbit system; calculating an included angle beta between the sun vector and the orbital plane under the orbital system, and setting a rotation angle of a solar wing rotation shaft and a preset offset angle of an offset shaft according to the included angle beta between the sun vector and the orbital plane under the orbital system; calculating the angular momentum of the flywheel system and converting the angular momentum into the angular momentum under the satellite system; and comparing the module value of the to-be-unloaded angular momentum of the satellite with a preset unloading threshold value, judging whether the magnetic torquer needs to be started for unloading or not according to a comparison result, and outputting a control instruction of the magnetic torquer according to the comparison result. According to the invention, angular momentum accumulation and space moment accumulation are effectively reduced; the method has the advantages of fuel saving, low power consumption requirement, high attitude stability and the like, and a theoretical basis is provided for angular momentum unloading of the low-intensity magnetic field planetary detector.
本发明公开一种非对称构型卫星角动量的卸载方法和装置,该方法包括:通过太阳敏感器获取卫星本体系下的太阳矢量,并将太阳矢量转换为轨道系下的太阳矢量;计算所述轨道系下的太阳矢量与轨道面的夹角β,并根据所述轨道系下的太阳矢量与轨道面的夹角β设置太阳翼转动轴的转动角度和偏置轴的偏置预设角度;计算飞轮系统的角动量并将其转换为卫星本体系下的角动量;根据卫星待卸载角动量的模值与预设卸载阈值进行比较,根据比较结果判断是否需要开启磁力矩器卸载,并根据比较结果输出磁力矩器的控制指令。本发明有效减少了角动量累积及空间力矩累积;具有节省燃料、功耗要求低和姿态稳定度高等优点,为弱磁场行星探测器的角动量卸载提供了理论依据。
Unloading method and device for asymmetric configuration satellite angular momentum
一种非对称构型卫星角动量的卸载方法和装置
2023-11-17
Patent
Electronic Resource
Chinese
IPC: | B64G Raumfahrt , COSMONAUTICS |
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