| 摘要 |
PROBLEM TO BE SOLVED: To provide an attitude control device for an artificial satellite solving a problem that a control system becomes too specific when the artificial satellite is in an optional initial state. SOLUTION: This attitude control device comprises an attitude error computing unit 1 adapted to output triaxial attitude angle errors of the artificial satellite and time differentials of the errors computed on the basis of detected values of attitude angles and attitude angular velocities for outputting attitude angular velocities of a first axis and a second axis of the artificial satellite in a satellite body coordinate system, a spin controller 4 adapted to operate a thrust on the basis of the attitude angle errors of the first and second axes and the first and second attitude angular velocities for shifting the artificial satellite from the initial state to a spin state, a setting controller 5 adapted to operate the thrust on the basis of the triaxial attitude angle errors and the time differentials of the errors for setting the spin state, and state determining unit 2 adapted to switch from the spin controller to the setting controller when the attitude errors of the first and second axes decrease. The device allows controlling the attitude of the artificial satellite body in three axes only by the thrust generating torques around two axes without making the setting determining unit in a specific state.
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