One embodiment of the invention discloses a satellite attitude control method, and the method comprises the following steps: S101, when a sunlight orbital plane included angle is sensed to be + 90 degrees or -90 degrees, a satellite flies along a satellite in-orbit flight direction as a first flight direction, so a first cabin plate of the satellite is a light receiving surface; S102, in the process that the sunlight orbital plane included angle is turned from + 90 degrees to -90 degrees or from -90 degrees to + 90 degrees, the attitude of the satellite is adjusted, the satellite rotates by 180 degrees around the gravity direction of the satellite, and the satellite flies in the satellite in-orbit flight direction as the second flight direction; S103, when it is sensed that the sunlight orbital plane included angle is changed from + 90 degrees to-90 degrees or from -90 degrees to + 90 degrees, the satellite still flies in the satellite in the in-orbit flight direction as the second flight direction, and it is guaranteed that the first deck of the satellite is still a light receiving face at the moment, wherein the sunlight orbital plane included angle is the minimum included angle between the sun vector and the orbital plane, and the change range of the sunlight orbital plane included angle is -90 degrees to + 90 degrees.
本发明的一个实施例公开了一种卫星姿态控制方法,该方法包括:S101:当感测到阳光轨道面夹角为+90°或‑90°时,卫星第一飞行方向沿卫星在轨飞行方向飞行,使得卫星的第一舱板为受光面;S102:在阳光轨道面夹角由+90°转向‑90°或由‑90°转向+90°的过程中,所述卫星进行姿态调整,所述卫星绕其重力方向旋转180°,使得卫星第二飞行方向沿卫星在轨飞行方向飞行;S103:当感测到阳光轨道面夹角由+90°变为‑90°后或由‑90°变为+90°后,所述卫星依旧保持其第二飞行方向沿卫星在轨飞行方向飞行,保证这时卫星的第一舱板仍为受光面;其中,阳光轨道面夹角为太阳矢量与轨道平面的最小夹角,它的变化范围为‑90°到+90°。
Satellite attitude control method
一种卫星姿态控制方法
2021-06-04
Patent
Electronic Resource
Chinese
IPC: | B64G Raumfahrt , COSMONAUTICS |
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