Abstract

A method to control the attitude in roll (X) and in yaw (Z) of a satellite including two solar generator panels adapted to be oriented independently of each other about a pitch axis. In a preliminary stage: two geometrical axes x and z are selected in the plane of the roll and yaw axes, there being associated with the z axis a tolerable command torque error much lower than for the x axis, and a correlation law is established between satellite panel depointing angles γN and γS and possible command torques due to solar radiation pressure. Then cyclically while the satellite performs its orbit: a theoretical attitude correction torque in the plane of the roll and yaw axes is calculated, a possible torque is identified having on the z axis, a component substantially identical to that of the theoretical torque, and on the x axis, a component as close as possible to the theoretical torque component, and there are applied to the panels the depointing angles associated with the possible torque in accordance with the correlation law.