초록 ▼

The invention provides a hybrid laminate and skin panels of hybrid laminate structure that are suitable for a supersonic civilian aircraft. The hybrid laminates include layups of layers of titanium alloy foil and composite plies, that are optimally oriented to counteract forces encountered in use, t

The invention provides a hybrid laminate and skin panels of hybrid laminate structure that are suitable for a supersonic civilian aircraft. The hybrid laminates include layups of layers of titanium alloy foil and composite plies, 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 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.

대표청구항 ▼

[ We claim:] [1.] A composite aircraft fuselage section comprising a symmetrical hybrid laminate layup, the layup comprising laminated together:(a) a first layer of metal foil comprising an outer surface of the fuselage section;(b) a second layer of metal foil comprising another layer of the laminat

[ We claim:] [1.] A composite aircraft fuselage section comprising a symmetrical hybrid laminate layup, the layup comprising laminated together:(a) a first layer of metal foil comprising an outer surface of the fuselage section;(b) a second layer of metal foil comprising another layer of the laminate layup; and(c) at least one hoop ply interposed between the first and second layers, and bonded to at least one of the first and second layers, the at least one hoop ply comprising commonly aligned fibers embedded in a polymeric matrix, wherein the at least one hoop ply has fibers extending helically around the circumference of the aircraft fuselage section.