Multi-layer metallic structure and composite-to-metal joint methods

Patent metadata

Field	Value
Publication number	US-8993084-B2
Application number	US-201213443687-A
Country	US
Kind code	B2
Filing date	Apr 10, 2012
Priority date	Aug 17, 2010
Publication date	Mar 31, 2015
Grant date	Mar 31, 2015

Abstract

A composite structure comprises stacked sets of laminated fiber reinforced resin plies and metal sheets. Edges of the resin plies and metal sheets are interleaved to form a composite-to-metal joint connecting the resin plies with the metal sheets.

First claim

What is claimed is:

1. An integrated attachment fitting for a structure, comprising:
a composite resin portion comprising layers of composite laminate;
a metal portion comprising a stack of metal plies, each metal ply in the stack of metal plies being substantially chemically non-reactive with any abutting composite resin, and connected to an adjoining metal ply via an adhesive layer such that: the stack of metal plies comprises performance properties superior to those of any monolithic metal comprising a thickness equal to a thickness of the stack of metal plies, and a reduction in a load carrying capability of any one ply in the stack of metal plies results in a transfer of the load across all other plies in the stack of plies, an end of each metal ply being vertically aligned with an end of a non-adjacent metal ply; and
a composite-to-metal joint between the composite resin portion and the metal portion such that each composite laminate comprises a thickness that is less than a thickness of any metal ply whose end abuts a termination of the each composite laminate, such that terminations of some composite laminates in the composite resin portion are recessed from a vertical alignment of terminations of composite laminates in the composite resin portion that are not recessed, and the termination of each of the some composite laminates is vertically aligned with a termination of each other of the some composite laminates and the termination of each of the some composite laminates abuts the end of an individual metal ply in the stack of metal plies to form a vertical lap finger joint, and each metal ply abuts multiple layers of composite laminate.

2. The integrated attachment fitting of claim 1 , wherein:
the composite resin portion includes a plurality of fiber reinforced resin plies, and each metal ply abuts at least three fiber reinforced plies.

3. The integrated attachment fitting of claim 2 , wherein the composite-to-metal joint comprises overlapping steps between the fiber reinforced resin plies and the stack of metal plies, a length of an overlap of the overlapping steps determined by a load requirement of the integrated attachment fitting.

4. The integrated attachment fitting of claim 3 , wherein the composite-to-metal joint is a finger joint and a first metal ply in the stack of metal plies comprises a different metal from a second metal ply in the stack of metal plies.

5. The integrated attachment fitting of claim 1 , wherein the structure is an aircraft wing and the metal portion is a metal laminate having a plurality of through holes therein adapted to receive fasteners for attaching the wing to a center wing box on an aircraft fuselage.

6. The integrated attachment fitting of claim 1 , wherein the structure is an aircraft wing and the metal portion is a metal laminate having a plurality of through holes therein adapted to receive fasteners, and further comprising a second composite portion such that forms a second composite-to-metal joint with the metal portion.

7. A fastener reinforcement for reinforcing an area of a multi-ply composite structure, comprising:
a metal laminate including a plurality of metal sheets bonded together, the metal laminate having a through hole therein adapted to receive a fastener therein, each metal sheet within the metal sheets bonded together comprising a shape being substantially circular and each metal sheet within the metal sheets bonded together comprising a radius that differs from a radius of an adjacent metal sheet within the metal sheets bonded together; and
a composite-to-metal joint between the metal laminate and the composite structure, the composite-to-metal joint comprising a variation in the radius relative to the radius of the adjacent metal sheet in the metal sheets bonded together being determined by a specified thermal expansion interface coefficient, such that multiple layers of composite laminate circumferentially abut a perimeter edge of each metal sheet respectively.

8. The fastener reinforcement of claim 7 , wherein the metal sheets comprise edges that are interleafed with edges of the plies of the composite structure, and further comprising the variation in the radius of one metal sheet relative to the radius of adjacent metal sheets in the metal sheets bonded together determined by a load requirement for the fastener.

9. An apparatus that increases a capacity of a joint, between a first composite structure and a second composite structure, to carry a load, over the capacity of the joint to carry the load without the apparatus, the apparatus comprising:
a first metal laminate comprising first metal sheets bonded to each other by an adhesive layer between each metal sheet that adjoins another metal sheet, each metal sheet in the first metal sheets comprising:
a first edge that aligns vertically with a first edge of each other metal sheet in the first metal sheets, such that the first metal laminate comprises performance properties superior to a monolithic metal structure of a width equal to a width of the first metal laminate, such that a load on a particular sheet in the first metal laminate redistributes to remaining metal sheets in the first metal laminate when a load carrying capacity of the particular sheet in the first metal laminate reduces; and
a second edge that abuts and bonds to multiple layers of fiber reinforced composite resin within the first composite structure, such that the second edge of each sheet aligns with the second edge of other first metal sheets in the first metal laminate in a vertical lap finger joint with the first composite structure, an overlap length in the vertical lap finger joint with the first composite structure being determined by a specified thermal expansion interface coefficient, and the second edge of each metal sheet in the first metal sheets being substantially non-reactive with the fiber reinforced composite resin that abuts each metal sheet respectively;

a second metal laminate comprising second metal sheets, each sheet in the second metal sheets comprising:
a first edge that aligns vertically with a first edge of each other sheet in the second metal sheets, such that the second metal laminate comprises performance properties superior to a monolithic metal structure of a width equal to a width of the second metal laminate, such that a load on a particular sheet in the second metal laminate redistributes to remaining metal sheets in the second metal laminate when a load carrying capacity of the particular sheet in the second metal laminate reduces; and
a second edge that abuts and bonds to multiple layers of fiber reinforced composite resin within the second composite structure, such that the second edge of each sheet aligns with the second edge of other second metal sheets in the second metal laminate in a lap finger joint with the second composite structure, overlap lengths in the lap finger joint with the second composite structure being determined by a specified thermal expansion interface coefficient, and the second edge of each metal sheet in the second metal sheets being substantially non-reactive with the fiber reinforced composite resin that abuts each metal sheet respectively; and

a joint that bonds the first metal laminate to the second metal laminate, the joint comprising:
an overlap of the first metal laminate and the second metal laminate, a length of the overlap comprising an adhesive layer that bonds a metal sheet of the first metal laminate to a metal sheet of the second metal laminate; and
a through hole in the first metal laminate aligned with a through hole in the second metal laminate, each through hole filled by a single fastener, the joint comprising characteristics of: a strength, a resistance to disbonds

Assignees

• Griess Kenneth Harlan
• Georgeson Gary E
• Boeing Co

Inventors

• Griess Kenneth Harlan
• Georgeson Gary E

Classifications

• B32B3/14

  characterised by a face layer formed of separate pieces of material {which are juxtaposed side-by-side (B32B5/02 takes precedence)} · CPC title

• B32B7/12

  using interposed adhesives or interposed materials with bonding properties · CPC title

• B32B2307/714

  Inert, i.e. inert to chemical degradation, corrosion · CPC title

• B29L2031/3088

  Helicopters · CPC title

• B32B3/18

  characterised by an internal layer formed of separate pieces of material {which are juxtaposed side-by-side (B32B5/02 takes precedence)} · CPC title