Patent ID: 8505853
Filing Date: 2013-08-13
Classification: B64G

Abstract:
1. Method for controlling the attitude of a satellite ( 1 , 2 ) in orbit around a celestial object, said satellite comprising at least: an observation instrument ( a solar panel ( a radiator ( a star sensor ( arranged on the satellite ( 1 , 2 ) such that, in a reference frame associated with said satellite and defined by three orthogonal axes X, Y, Z: the observation axis of the observation instrument ( the solar panel ( the radiator ( the star sensor ( in which said method, the attitude of the satellite ( 1 , 2 ) is controlled during an activity period (J) around the X-axis for roll control and around the Y-axis for pitch control to point one direction {right arrow over (z)}(t) of the axis of observation of the observation instrument ( 10 , 20 ) towards areas to be observed of the celestial object, said process being characterized in that the yaw attitude around the Z-axis of the satellite ( 1 , 2 ) is controlled to keep the Sun on the side of the half-space corresponding to positive X values and to ensure that a minimum insolation of the solar panel ( 11 , 21 a ) constraint C 1 is satisfied during observation phases of the activity period (J).