| 摘要 |
PROBLEM TO BE SOLVED: To provide a means capable of theoretically performing an attitude change in a triaxial satellite in the shortest time. SOLUTION: A target angular velocity profiler 38 inputs an attitude (an initial attitude) qi just before starting to the attitude change in an artificial satellite calculated by a quaternion caculating part 32 via a switch 37 and a target attitude qt commanded from a ground station to determine the Euler's axis, and next, determines a change in satellite angular velocity around the Euler's axis capable of physically realizing the attitude changed in the shortest time in a capacity range of an attitude control driving device mounted on the satellite by a calculation, and minutely generates the satellite angular velocity according to a change in this calculated satellite angular velocity in attitudinal change control of the satellite to impart the satellite angular velocity to a D control loop 34 as a target valueωt of control. When the satellite rotates as this target, the attitude change control can be realized in the shortest time.
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