To reduce an attitude determining filter, to simplify a control logic, and reduce a mounted memory.

When control axis maneuver instruction information is inputted at a normal operation, the yaw axis corresponding to the control axis maneuver instruction information within the control axis attitude information of three axes of a spacecraft 10 is rotated by nearly 90°. Roll axis attitude angle information and pitch axis attitude angel information are mutually exchanged, and the orbit rate is likewise changed. The attitude controlled variables of three axes are determined by first and second attitude determining filter parts 16, 17 like during the normal operation based on the changed roll axis attitude angle information, pitch axis attitude angel information, roll axis orbit rate, pitch axis orbit rate, and yaw axis orbit rate information. An attitude actuator 8 is driven based on the attitude controlled variables to control the attitude around three axes of spacecraft dynamics 13.