| 摘要 |
<p>PROBLEM TO BE SOLVED: To provide a hybrid lamination and an outside plate panel of a hybrid lamination structure suitable for supersonic civil aeroplane. SOLUTION: This hybrid lamination is orientated optimally so as to negate forces encountering during use and, at the same time, contain titanium alloy foils 10, each of which is joined together in such a center core structure as a titanium alloy honeycomb, and the lay-up of layers of composite material plies 12. The reinforcing fibers of the composite material ply 12 are selected from between carbon and boron and are continuous and orientated parallel to one another in respective plies. However, some plies can be orientated to be oblique to other plies. Nevertheless, in the preferred working examples, substantially large number of or all the fibers of the hybrid lamination are orientated to a common direction. The outside surface of the lamination contains titanium foil layer so as to protect the structure including the inner composite material from being attacked by environment and a solvent.</p> |
