| 摘要 |
<p>The invention relates to a method for controlling the attitude of a satellite (1,2) in orbit around a celestial body, said satellite comprising an observation instrument (10,20), a solar panel (11,21a), a radiator (12,22), and a stellar sensor (13,23) which are arranged on the satellite (1,2) such that, in a reference point associated with said satellite and predetermined by three orthogonal axes X, Y, and Z therebetween, the observation instrument (10,20) is arranged such that the observation axis thereof is parallel to the Z axis of the satellite, the solar panel (11, 21a) is parallel to the Y axis, the radiator (12,22) is arranged on one of the surfaces -X, +Y, or -Y of the satellite, and the stellar sensor (13,23) is guided from the negative X side. According to the method, the attitude of the satellite (1,2) is controlled during a rolling and pitching activity period (J) to guide the observation instrument (10,20) towards two areas to be observed on the celestial body, and the twisting attitude of the satellite (1,2) is controlled to keep the sun on the positive X side and ensure that a minimum solar radiation stress C1 on the solar panel (11,21a) is confirmed during observation phases of said activity period.</p> |
