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US 2010/0276065 A1Published application
Bonded Patches With Bond Line Control
AssigneeThe Boeing Company
InventorsSteve Blanchard, Aydin Akdeniz, John Spalding, David M. Anderson, Michael W. Evens
Life of this patent
Estimating the term…
Abstract
A patch is used to rework an area of a structure. The patch is bonded to the structure by a layer of adhesive. A spacer placed between the patch and the structure is used to control the thickness of the adhesive and/or a bondline.
Claims25
A method of reworking an area of a structure, comprising:
- preparing a patch;
- placing a layer of viscous bonding adhesive between the structure and the patch;
- using a spacer to control the thickness of the adhesive layer;
- and
- compacting the patch against structure.
2 more elements
A method of bonding a patch on structure, comprising:
- placing a spacer on one of the patch and the structure;
- applying a layer of viscous bonding adhesive to one of the patch and the structure, including using the spacer to control the thickness of the adhesive layer as the adhesive is being applied;
- placing the patch on the structure with the adhesive layer therebetween;
- compacting the patch against the structure;
- and
- curing the adhesive.
3 more elements
A kit for reworking an area of a structure, comprising:
- a patch adapted to overlie the rework area and be compacted against the structure;
- a viscous adhesive for bonding the patch member to the structure;
- and
- a spacer for controlling the thickness of a layer of the adhesive used to bond the patch to the structure.
1 more element
For use in reworking a structure:
- a composite patch having a face adapted to be bonded to the structure by a layer of adhesive placed between the face and the structure,
- the patch including a plurality of spacer elements distributed across the face and formed integral with the patch for controlling the thickness of the adhesive layer.
A method of reworking a composite aircraft structure in the field, comprising:
- preparing an area of the structure to be reworked;
- forming a patch including forming perforations in the patch;
- placing a spacer on one of the patch and the structure;
- applying a layer of adhesive to one of the patch and the structure, including controlling the thickness of the adhesive layer by applying the adhesive through the spacer;
- removing the spacer after the adhesive layer has been applied;
- applying the patch to the structure;
- placing a caul plate over the patch;
- placing an anti-caul plate between the caul plate and the structure;
- installing a pressure applicator over the combination of the patch, the caul plate and the anti-caul plate;
- using the pressure applicator to apply pressure to the patch through the caul plate;
- using the anti-caul plate to limit the pressure applied by the caul plate to the periphery of the patch;
- installing a heat pack over the patch;
- and
- using the heat pack to cure the adhesive.
11 more elements
A kit for reworking a composite aircraft structure, comprising:
- a generally planar patch adapted to be compacted against the structure and bonded thereto, the patch including a plurality of perforations therein allowing air between the patch and the structure to escape through the patch as the patch is compacted against the structure;
- a pre-measured quantity of bonding adhesive;
- a mask adapted to be placed on the structure for defining the area on the structure to be reworked;
- a heat pack for curing the adhesive;
- a compaction device for compacting the patch against the structure;
- and
- a substantially non-compressible spacer adapted to be placed between the planar member and the structure for controlling the thickness of a bond line between the patch and the structure, the spacer including at least one of—
- a pre-measured quantity of beads adapted to be mixed with the adhesive,
- a spacer ring,
- a length of a filament adapted to be cut into individual lengths and placed on the structure overlying an area on the structure to be reworked,
- a plurality of spacer pins, and
- a screen.
9 more elements
Dependencies are inferred from the claim text.