| 摘要 |
<p><P>PROBLEM TO BE SOLVED: To provide a hybrid laminate and skin panels of hybrid laminate structure that are suitable for a supersonic civilian aircraft. <P>SOLUTION: The hybrid laminates include layups of layers of titanium alloy foil (10) and composite plies (12) that are optimally oriented to counteract forces encountered in use, that are bonded to a central core structure, such as titanium alloy honeycomb. The reinforcing fibers of the composite plies (12) are selected from carbon and boron, and the fibers are continuous and parallel oriented within each ply. However, some plies may be oriented at angles to other plies. Nevertheless, in a preferred embodiment of the invention, a substantial majority of, or all of, the fibers of the hybrid laminates are oriented in a common direction. The outer surfaces of the laminates include a layer of titanium foil to protect the underlying composite-containing structure from the environment, and attack by solvents, and the like. <P>COPYRIGHT: (C)2007,JPO&INPIT</p> |
