| 摘要 |
<p>The satellite carries a solar generator (2) which can be deployed and oriented with respect to the satellite body (1) and which is intended to be maintained permanently facing the sun, and a device (4) for stabilizing the attitude, characterized in that this attitude- stabilizing device consists of at least:
&cirf& a closed loop (7) of superconducting material carried by a support (6) connected to the solar generator and placed on a face of this support which is oriented approximately in a direction opposite to that of the sun;
&cirf& a secondary loop (9) parallel to the closed loop, of approximately the same shape and size as the closed loop and carried by the support near the closed loop;
&cirf& a resistive circuit (10) carried by this support near at least a part of the closed loop;
&cirf& a selective electrical supply circuit (11) connected electrically to the secondary loop and to the resistive circuit.</p> |
