A plurality of panels are coupled rotatably by a hinge mechanism. The panels are folded when a rocket loaded with the panels is launched and unfolded in space after the artificial satellite is released. Each of the panels is loaded with at least functional elements such as a solar panel, a battery, an attitude control device and a communication device separately or together. The devices loaded on the panels are electrically connected to each other.

 
Web www.patentalert.com

> Conducting-fiber deicing systems and methods

~ 00313