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A method for fabricating a laminated composite body including a metal foil and a plurality of fiber plies. The method includes perforating a sheet of metal foil, stacking the perforated metal foil sheet and the plurality of fiber plies in face to face relation in a predetermined order and orientatio

A method for fabricating a laminated composite body including a metal foil and a plurality of fiber plies. The method includes perforating a sheet of metal foil, stacking the perforated metal foil sheet and the plurality of fiber plies in face to face relation in a predetermined order and orientation, and infusing resin into the stacked sheet and plies so that resin flows through the perforations in the metal foil sheet and intersperses between the plurality of fiber plies to form the laminated composite body.

대표청구항 ▼

1. A method of fabricating an aircraft part, the method comprising: laying up a plurality of fiber plies and flat metal foils, the fiber plies having reinforcing fibers oriented in a single direction, wherein said laying up includes positioning a plurality of said fiber plies between at least one of

1. A method of fabricating an aircraft part, the method comprising: laying up a plurality of fiber plies and flat metal foils, the fiber plies having reinforcing fibers oriented in a single direction, wherein said laying up includes positioning a plurality of said fiber plies between at least one of said foils in the form of a perforated metal sheet and at least one of said foils in the form of a non-perforated metal sheet;infusing resin into the resulting layup to flow past each perforated metal sheet and intersperse between the plurality of fiber plies and between the fibers of each ply; andcuring the resin-infused layup to form the aircraft part as a fiber-metal laminate including both the fiber plies and the metal foils,wherein the fibers provide strength to the resulting part in the single direction, andwherein the foils provide bearing strength to the resulting part. 2. The method of claim 1, wherein perforations in each perforated metal sheet are formed with a pulsed laser. 3. The method of claim 1, wherein a resin transfer molding process is used to infuse the resin. 4. The method of claim 1, wherein a vacuum assisted resin transfer molding process is used to infuse the resin. 5. The method of claim 1, wherein the metal foils have a thickness between 10.005 inches to 0.015 inches. 6. The method of claim 1, wherein each perforated metal sheet has perforations having sizes between about 0.01 inches and about 0.04 inches. 7. The method of claim 6, wherein the perforations are spaced apart between about 0.25 inches and 2.0 inches.