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A low earth orbiting satellite control arrangement according to the invention has an earth sensor for measuring roll and pitch of the satellite relative to an earth oriented moving reference system, a spin wheel mounted along an axis perpendicular to the orbital plane of the satellite for measuring

A low earth orbiting satellite control arrangement according to the invention has an earth sensor for measuring roll and pitch of the satellite relative to an earth oriented moving reference system, a spin wheel mounted along an axis perpendicular to the orbital plane of the satellite for measuring spin of the satellite, and two magnet coils for generating control. A first of the two magnet coils is aligned substantially in parallel to a roll axis of the satellite, and the second is aligned substantially parallel to the yaw axis. Alternative control algorithms are disclosed for controlling attitude, nutation and spin of the satellite based on information from the earth sensor, spin wheel and an observer which is also mounted on the satellite.

대표청구항 ▼

[ We claim:] [1.] Process for controlling attitude, nutation and momentum of a satellite orbiting in a low earth orbit, with a medium inclination in an earth oriented alignment, said satellite being of the type having an earth sensor for measuring in two axes; a spin wheel having an axis of rotation

[ We claim:] [1.] Process for controlling attitude, nutation and momentum of a satellite orbiting in a low earth orbit, with a medium inclination in an earth oriented alignment, said satellite being of the type having an earth sensor for measuring in two axes; a spin wheel having an axis of rotation oriented in parallel to a pitch axis of the satellite and two magnet coils for generating control moments, a first one of the two magnet coils being aligned substantially in parallel to a roll axis of the satellite and a second one of the two magnet coils being aligned substantially in parallel to a yaw axis of the satellite, said process comprising at least one of the steps of:controlling attitude and nutation of said satellite by activating said magnet coils based on a linear control algorithm which in the case of attitude control is a function of a roll angle measured by the earth sensor and of a yaw angle estimated by means of an observer or measured by an additional sensor on said satellite and, in the case of nutation control, a function of a roll angle chance determined by earth sensor measurements and a yaw angle chance estimated by the observer or measured by an additional sensor; andcontrolling wheel spin by activation of at least said first magnet coil, as a function of a deviation from a desired value for spin, and of a yaw component of th earth's magnetic field based on PI feedback control;wherein said linear control algorithm for attitude control is given by ]EQU31 ] m.sub.x.sup.(h), m.sup.(h) being the magnetic moments to be generated by the roll and yaw axis magnet coils; h.sub.0x, h.sub.0z being the roll and yaw components of the satellite spin vector, respectively, related to the yaw and roll angles, .phi. and .PHI. respectively, by the equations h.sub.0x =.phi.h.sub.w and h.sub.0z =-.phi.h.sub.w, h.sub.w being the magnitude of the wheel spin vector; and K.sub.ij.sup.(h) being amplification parameters.