Method of controlling the attitude and stabilization of a...

B - Operations – Transporting – 64 – G

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B64G 1/32 (2006.01) B64G 1/36 (2006.01) G05D 1/08 (2006.01) B64G 1/28 (2006.01)

Patent

CA 2383255

For controlling the attitude of a satellite placed on a low earth orbit, components of a vector Bm of the earth's magnetic field along three measurement axes of a frame of reference bound with the satellite (typically by means of a three-axis magnetometer)are measured. The orientation of the earth's magnetic field in the frame of reference is computed and a derivative Bm of the vector is also computed. Magneto-couplers carried by the satellite are energized to create a torque for spinning the satellite at an angular frequency .omega.c about a determined spin axis of the satellite, where .omega.c is greater than an orbital angular frequency 2.omega.0 of the satellite.

Pour contrôler l'attitude d'un satellite en orbite à basse altitude autour de la terre, l'on mesure les composants d'un vecteur repère du champ magnétique planétaire le long des trois axes de mesure d'un système de coordonnées lié au satellite (généralement au moyen d'un magnétomètre triaxial). La direction du champ magnétique de la terre au sein du système de coordonnées est calculée, de même qu'un dérivé du vecteur repère. Des coupleurs magnétiques embarqués sont alimentés pour créer un couple qui fait tourner le satellite à une fréquence angulaire .omega.c autour d'un axe de rotation, où .omega.c est supérieur à une fréquence angulaire orbitale 2.omega.0 du satellite.

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