PURPOSE: To prevent the formation of a number of new debris even if a satelite collides with debris and a honeycomb core member is disassembled to a number of metal places, by installing each fibrous mesh interposed between the honeycomb core member and an obverse surface skin member and between the honeycomb core member and a back surface skin member.

CONSTITUTION: A honeycomb panel for satelite is formed by interposing each fibrous mesh 2 between a surface skin member 1 and a honeycomb core member 3 and between the honeycomb core member 3 and a back surface skin member 4, and these members are adhesion-treated by each adhesive. As the honeycomb core member, are used aluminium, etc., and as the skin members 1 and 4, are used aluminium, CFRP, etc. Since the fibrous mesh 2 is interposed between the honeycomb core member 3 and the skin members 1 and 4, and adhesion is caused between these members, the disassembly to a number of metal pieces of the honeycomb core member after the satelite collides with debris can be prevented through the connection by the fibrous mesh 2.