HYBRID COMPOSITE STRUCTURES

Abstract: A composite structure (1) utilizing graphite (20) which structure has a fastener area (18) for connecting it to other structures. In order to prevent corrosion between the graphite (20) and metal fasteners, the fastener area (18) does not contain graphite. Instead, the graphite (20) is replaced by Kevlar (24) reinforced laminates which about the graphite (20). The fastener area (18) is further reinforced with exterior Kevlar (28) laminates overlapping the graphite (20) partially.

Description: HYBRID COMPOSITE STRUCTURES BACKGROUND OF THE INVENTION Graphite reinforced laminated structures are wel known and they provide a high strength-to-weight ratio t the structure. These fibers are being used more and more 5 as structures for aircraft due to this high strength-to-weight ratio. However, graphite fibers present a problem in aircraft use as graphite, when physically contacted by or electrically coupled to aluminum, causes corrosion. -- •0 Aluminum fasteners are extensively used in aircraft, and all types of metal fasteners provide an electrical circuit that could electrically couple graphite containing laminates to aluminum aircraft structure. SUMMARY OF THE INVENTION 5 A composite structure has graphite as the primary reinforcing material. In the composite, the graphite laminate terminates adjacent to, and before entering into, the fastening area of the composite. Laminates of Kevlar are used to cover the fastener area and to overlap the 0 graphite laminate. It is an object of this invention to provide a graphite reinforced composite that does not have any graphite in an area of the structure that utilizes fasteners for joining to other structures. 5 DESCRIPTION OF THE DRAWINGS FIG. 1 shows a cabinet view of the invention. FIG. 2 shows a cabinet view of a different embodiment of the invention. DETAILED DESCRIPTION The composite structure 10 has a honeycomb core 12 which is tapered down at 14 near edge 16. The core may be any of the many known materials used to make honeycomb with nylon honeycomb core preferred. Adjacent the edge of the core the composite has a fastener or joining area 18. A graphite reinforced laminate 20a covers one side of the core but terminates at a point 22a that is adjacent to, but short of, the fastener area. The graphite laminate may be made up with any of the known resins with an epoxy preferred. A second graphite reinforced laminate 20b covers the opposite side of the core and also terminates at 22b at a point adjacent to, but not in, the fastener area. Abutting the graphite laminate at 22a and 22b, respectively, are Kevlar reinforced laminates 24a and 24b. These laminates extend outward into, and become part of, the fastener or join area. These layers of reinforcing Kevlar may be joined together or may, as is shown here, contact a separate Kevlar laminate 26. A pair- of Kevlar reinforced laminates 28a and 28b are located to cover the abutting Kevlar layers in the fastener area and to extend inward to overlap the graphite laminates. Holes 30 for accepting fasteners are located in the join or fastener area to permit joining the composite to other structures. FIG. 2 shows a different embodiment of a graphite reinforced composite structure with a honeycomb core 12a which is tapered down at 14a near edge 16a. The core is covered on each side with a Kevlar reinforced laminate. The Kevlar is preimpregnated with a resin, preferably epoxy, and a layer 32a is placed on the top side of the core and layer 32b is placed on the bottom side of the core. Each of these layers cover the core and extend to the side to form part of a joining or fastening area 18a. A graphite reinforced laminate 20c covers most of the Kevlar laminate in the core area but terminates at 22 adjacent to the join area, and another graphite reinforce laminate 20d covers most of the Kevlar laminate on th bottom side of the core area, but terminates at 22 adjacent to the join area. A pair of Kevlar reinforce laminates 24c and 24d abut laminates 20c and 20d, respectively, and extend over the join area. Kevlar reinforced laminates 28c and 28d are located to cover th abutting Kevlar laminates in the fastener area and to extend inward to overlap the graphite laminates.

Claims: I claim : 1. A joint for a graphite reinforced composite structure comprising: a graphite reinforced composite having the graphite terminate adjacent an area to be joined with a fastener, a Kevlar reinforced composite abutting the graphite to extend across the join area, and a Kevlar reinforced composite to overlap the graphite and extend across the join area and form a unified composite structure. 2. A lightweight composite structure having a honeycomb core and means for joining to other structures comprising: a honeycomb core, a layer of graphite and resin on each side of the core with the layer terminating adjacent an area to be joined with a fastener, a layer of Kevlar and resin abutting the graphite resin layer on each side and to extend over the join area, and a layer of Kevlar and resin to cover the join area and to overlap the graphite resin layer to form a composite structure. 3. A lightweight aircraft composite structure for joining to other structures comprising: a honeycomb core, a graphite reinforced laminate covering each side of the core, the graphite reinforced laminates each terminating adjacent an area on the structure for fastening to other structures, a Kevlar laminate abutting each graphite laminate and extending to form part of the fastening area, a covering Kevlar laminate overlapping each graphite laminate and covering the first Kevlar laminates, and holes through the fastening area for accepting fasteners to join the composite to other structures. 4. A lightweight aircraft composite structure as in claim 3 further comprising: an additional layer of Kevlar laminate between the core and the graphite laminate and to extend into the fastening area. 5. A lightweight aircraft composite structur for joining to other structures comprising: a honeycom core, a Kevlar laminate covering each side of the core an extending to form part of a fastening area, a coverin graphite laminate that terminates short of the fastenin area, a Kevlar laminate abutting the graphite laminate an to extend over the fastening area, and a Kevlar laminat covering the fastening area and overlapping the graphit laminate to form an integrated composite structure free o graphite in the fastening area. 6. A method of forming an aircraft composite structure for securing the composite to other structures with fasteners, with steps comprising: placing a layer of resin impregnated graphite over a honeycomb core with the graphite layers terminating adjacent a side of the core, extending the covering layer with a layer of resin impregnated Kevlar that extends sidewise past the core and forming a fastening area, covering the fastening area with a Kevlar reinforced resin layer that partially overlaps the graphite layers, and curing the layers and forming a composite structure for securing to other structures with fasteners. 7. A method of forming an aircraft composite structure for securing the composite to other structures with fasteners, with steps comprising: placing a layer of resin impregnated Kevlar over each side of a honeycomb core and extending the layers past the core forming part of a fastening area, placing a layer of graphite and resin over each Kevlar layer and terminating the graphite layer adjacent the fastening area, covering the fastening area with a Kevlar reinforced resin layer that partially overlaps each graphite layer, and curing the formed layers creating a composite structure for securing to other structures with fasteners. OMPI

Inventors: HAMMER R
Applicants: BOEING CO
Application year: 1981
Main classification: B32B3
IPC codes: B29C70, B29D24, B32B3, B32B19, B64C27