The present invention concerns a method (50) for attitude control of a satellite (10) in low inclined orbit in survival mode, the satellite (10) comprising at least one solar generator (12), at least one solar sensor (17a, 17b), magneto-couplers (15) designed to form internal magnetic moments in a satellite reference frame having three orthogonal axes X, Y and Z, and inertial actuators (16) designed to form internal kinetic moments in the satellite reference frame. The at least one solar sensor has a field of view at least 180° wide in the XZ plane around the Z axis, the method comprising: - a step (51) of attitude control using a first control law, - a step (52) of searching for the sun by means of the at least one solar sensor (17a, 17b), - when a first phase of visibility of the sun is detected: a step (53) of attitude control using a second control law.
展开▼
