Patent ID: 8149176

Claim:
A device for controlling a satellite tracking antenna comprising an azimuth drive configured to impart an azimuthal rotational motion to the antenna about an azimuth axis, an elevation axis drive configured to impart a rotational motion to the antenna about an elevation axis orthogonal to the azimuth axis, a tilt axis drive configured to impart a rotational motion to the antenna about a tilt axis, a polarization axis drive configured to impart a rotational motion to a transceiver head of the antenna about a polarization axis orthogonal to the tilt axis, wherein the polarisation axis is connected to the tilt axis, and wherein said tilt axis is connected to the elevation axis in such a way that a rotational freedom of motion of the antenna about the tilt axis is dependent on the elevation angle, such that: at an elevation angle of 0° the rotational freedom of motion of the antenna about the tilt axis corresponds to the azimuthal rotational motion; at an increasing elevation angle the rotational freedom of motion about the antenna successively transcends into a roll rotation; and at an elevation angle of 90° the rotational freedom of motion of the antenna about the tilt axis corresponds to a roll rotation about a roll axis orthogonal to said azimuth axis and to said elevation axis, a control configured to control operation of the azimuth axis drive, the elevation axis drive, the polarisation axis drive, and the tilt axis drive, said control comprising a true north seeking gyro, configured to track position, orientation, direction and speed of movement of the device, wherein said control further comprises absolute angular sensors arranged to sense the angle rotation of the azimuth axis, elevation axis, tilt axis and polarization axis, respectively, wherein said control further comprises an additional gyro comprising an elevation gyro axis arranged to sense the elevation movement and a tilt gyro axis arranged to sense the tilt movement, a compensator configured to compensate for drift of the additional gyro by calculating a pointing error of the antenna pointing vector based upon data of the desired antenna pointing vector, bearing, pitch and roll of the navigation system and the angle of rotation of the azimuth axis, elevation axis, tilt axis and polarisation axis, wherein said pointing error of the respective axis is arranged to be fed in an outer loop of a position controller, wherein said additional gyro further is arranged to feed information about movement of the axis to the velocity controller, in an inner loop so as to control the velocity of said drive of the respective axis, where the additional gyro is further arranged to control the high frequency disturbances by means of feed back of angular velocity data of the additional gyro to the drive, so as to minimize the angular velocity of the antenna pointing vector.