Method for controlling the attitude of a satellite in survival mode without a priori knowledge of the local time of the orbit of the satellite

摘要

The present invention relates to a method (50) for controlling the attitude of a satellite (10) in an inclined low orbit in survival mode, the satellite (10) comprising at least one solar generator (12), at least one solar sensor ( 17a, 17b), magneto-couplers (15) adapted to form internal magnetic moments in a satellite frame comprising three orthogonal axes X, Y and Z, and inertial actuators (16) adapted to form internal angular moments in the frame satellite. The at least one solar sensor has a field of view with a width of at least 180 ° in the XZ plane around the Z axis, the method comprises: 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 law of control. Figure for the abstract: Fig. 3