Patent ID: 8038101
Filing Date: 2011-10-18
Classification: B64G

Abstract:
1. An attitude change control method for controlling the attitude change of a space craft including a plurality of CMGs (control moment gyros) as actuators for controlling attitude of the space craft comprising: generating a weighted input output gain by providing different weighting to an input output gain in a torque main direction and in a torque non-main direction; applying the weighted input output gain by providing to a gradient method (GM), and generating target profiles of the angle and angular velocity for each gimbal of the CMGs by changing torque components in the for the torque main direction and in the torque non-main direction so that the torque component in the torque main direction is larger than the torque component in the torque non-main direction, wherein the torque main direction requires a larger torque to change the attitude of the space craft than the torque non-main direction does, and wherein the torque main direction is perpendicular to the torque non-main direction.