| 摘要 |
The present invention relates to a method (50) of supervising attitude of a satellite (10) in survival mode in inclined low orbit, the satellite (10) comprising a solar generator (12), a magneto-coupler (15) and an inertial flywheel (16). Said method (50) comprises: - a step (51), prior to the survival mode, of storing a non-zero internal magnetic moment setting which is constant in a satellite frame tied to the satellite (10), termed the "survival magnetic moment", and a non-zero internal kinetic moment setting which is constant in said satellite frame, termed the "survival kinetic moment", - a step (52) of controlling the magneto-coupler (15) and the inertial flywheel (16) in such a way as to simultaneously form the survival magnetic moment and the survival kinetic moment during part at least of the survival mode. |
