| 摘要 |
PURPOSE: To effectively attenuate the disturbance torque, especially the torque caused by the solar radiation pressure by providing a closed loop consisting of a superconductor, a second loop parallel thereto, and an attitude control system comprising a resistive circuit, etc., on a deployable solar generator which is provided on a satellite. CONSTITUTION: A satellite is equipped with a deployable solar generator 2 from a mode stored in a satellite body 1 to an operational mode of being connected to the body 1, and an attitude control system 4 is supported by the solar generator 2. The attitude control system 4 comprises a support panel, a superconducting closed loop 7, a support frame 8, an auxiliary loop 9, a resistive circuit 10, and a control circuit 11, and in the support panel 6, its side to be exposed to the radioactive ray of the sun is covered with a highly reflecting material 12. The closed loop 7 is formed of a superconductor of YBa2 Cu3 O7 , and functions as a main current loop of a correction device. The auxiliary loop 9 is formed of a conducting material, and initially sets the current in the main loop 7.
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