Hybrid composite structures
AssigneeThe Boeing Company
InventorRobert H. Hammer
Life of this patent
Estimating the term…
Abstract
A graphite containing composite structure having a fastener area for joining the composite to other structures terminates the graphite reinforced laminate adjacent to the fastener area. Kevlar reinforced laminates abut the graphite laminate and extend over the fastener area and are further reinforced with Kevlar laminates that overlap the graphite then extend over the fastener area.
Claims6
A lightweight composite structure having a honeycomb core and means for joining to other structures comprising:
- a honeycomb core, a layer of graphite reinforced on each side of the core with the layer terminating adjacent an area to be joined with a fastener, a layer of aramid reinforced resin abutting the graphite reinforced resin layer on each side of the honeycomb and extending over the join area, a layer of aramid reinforced resin to cover the join area and to overlap the graphite resin layer to form a composite structure, and holes through the fastening area for accepting fasteners to join the composite to other structures.
A lightweight aircraft composite structure for joining to other structures comprising:
- a honeycomb core, a graphite reinforced plastic covering each side of the core, the graphite reinforced layers each terminating adjacent an area on the structure for fastening to other structures, an aramid reinforced plastic abutting each graphite reinforced layer and extending to form part of the fastening area, a covering aramid reinforced plastic overlapping each graphite layer and covering the first aramid reinforced layers, and holes through the fastening area for accepting fasteners to join the composite to other structures.
A lightweight aircraft composite structure for joining to other structures comprising:
- a honeycomb core, a layer of aramid reinforced plastic covering each side of the core and extending to form part of a fastening area, a covering layer of graphite reinforced plastic that terminates short of the fastening area, a layer of aramid reinforced plastic abutting the graphite reinforced layer and extending over the fastening area, and a layer of aramid reinforced plastic covering the fastening area and overlapping the graphite reinforced layer to form an integrated composite structure free of graphite in the fastening area, and holes through the fastening area for accepting fasteners to join the composite structure to other structures.
A method of forming an aircraft composite structure for securing the composite to other structures with fasteners, with steps comprising:
- placing a covering layer of resin impregnated graphite over a honeycomb core with the graphite layers terminating adjacent a side of the core, abutting the covering layer with a layer of resin impregnated aramid that extends sidewise past the core and forming a fastening area, covering the fastening area with another aramid reinforced resin layer that partially overlaps the graphite layers, curing the layers forming a composite structure, and placing holes in the fastening area for securing to other structures with fasteners.
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 aramid 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 aramid layer and terminating the graphite layer adjacent the fastening area, covering the fastening area with another aramid reinforced resin layer that partially overlaps each graphite layer, curing the formed layers creating a composite structure, and placing holes in the fastening area for securing to other structures with fasteners.
Dependencies are inferred from the claim text.