| 摘要 |
<P>PROBLEM TO BE SOLVED: To solve such a problem in a posture control apparatus for an artificial satellite using a conventional single gimbal CMG (control moment gyro) that when a singular state in which an inverse matrix of Jacobian matrix can not be obtained occurs in calculation of gimbal angular velocity of the CMG from a posture control torque, there is unreliability in a posture control system that for example, an excessive target value is set to the gimbal angle or the gimbal angular velocity of the CMG, or the CMG stays at the singular state regardless of the modification in the calculation of the inverse matrix of the Jacobian matrix to solve the problem. <P>SOLUTION: When the CMG stays at the singular state, a fine gimbal angular change of the CMG is obtained based on the nonlinear relationship between a fine angular momentum change of the artificial satellite and the fine gimbal angular change of the CMG. <P>COPYRIGHT: (C)2013,JPO&INPIT |
