| 摘要 |
PURPOSE: To quickly perform attitude control with a simple structure by measuring the direction of the sun with respect to only one measuring direction and improving a control means when the direction of the sun does not coincide with the reference direction fixed to a space vehicle. CONSTITUTION: In a method and a device for aligning a space vehicle, particularly, a geostationary satellite in the reference direction, the space vehicle is aligned by aid of a control functional unit so that the direction of the sun as a reference object may coincide with the reference direction fixed to the space vehicle. In this case, a sun sensor 11 is provided, and output signals are input into multipliers 15 and 17 through a limiter 13. In respective multipliers 15 and 17, control vectors a2 , a3 are obtained by multiplying a limit value L obtained from the limiter 13 by the rotational directions found by respective multipliers 14, 17. An added signal added by respective vectors a2 and a3 , a rotational speed vector a1 obtained by a multiplier 20, and a vectorωare respectively multiplied by a control parameter Kp, and the multiplied value is added 23 to obtain a control vector u.
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