Trapezoidal rework patch

Patent metadata

Field	Value
Publication number	US-9314979-B1
Application number	US-201313943124-A
Country	US
Kind code	B1
Filing date	Jul 16, 2013
Priority date	Jul 16, 2013
Publication date	Apr 19, 2016
Grant date	Apr 19, 2016

Abstract

A composite rework patch and method. The composite rework patch comprises a trapezoidal shape, a first region, and a second region. The trapezoidal has a first base and a second base, the first base parallel to the second base. The first region comprises a first composite material portion and a first adhesive portion. The second region comprises a second composite material portion and a second adhesive portion.

First claim

What is claimed is:

1. A composite rework patch comprising:
a trapezoidal planform shape comprising a first base and a second base, the first base parallel to the second base;
a first region comprising a first composite material portion and a first adhesive portion, such that the first region comprises an innermost region of a plurality of regions; and
a second region comprising a second composite material portion and a second adhesive portion, such that the second region concentrically surrounds the first region and comprises a strain elongation value lower than a strain elongation value of the first region.

2. The composite rework patch of claim 1 , wherein the first region is placed in a location over an inconsistency in a structure.

3. The composite rework patch of claim 2 , wherein increasing a ratio of the second base to the first base decreases at least one of a stress intensity or a strain energy release rate at the inconsistency.

4. The composite rework patch of claim 2 , further comprising properties of the trapezoidal shape, properties of the first region, and properties of the second region being each tailored to integrally arrest growth of the inconsistency.

5. The composite rework patch of claim 2 , wherein the trapezoidal shape is placed in an orientation relative to the structure such that a selected load path is perpendicular to the first base.

6. The composite rework patch of claim 5 , wherein the selected load path is a hoop load path of a body of an aircraft.

7. The composite rework patch of claim 5 , wherein the selected load path is an inboard outboard load path of a wing of an aircraft.

8. The composite rework patch of claim 5 , wherein the selected load path is a chordwise load path of a wing of an aircraft.

9. The composite rework patch of claim 1 , wherein a sum of interlaminar tensions of the plurality of regions is substantially zero.

10. The composite rework patch of claim 1 , wherein interlaminar shear of the first region is substantially zero.

11. The composite rework patch of claim 1 , wherein the first composite material portion of the first region comprises a taper.

12. The composite rework patch of claim 1 , further comprising properties of the trapezoidal shape, properties of the first region, and properties of the second region being each tailored to integrally prevent disbonding of the composite rework patch.

13. The composite rework patch of claim 1 , further comprising a value for a tensile modulus for the second region comprises a lower value than a tensile modulus for the first region.

14. The composite rework patch of claim 1 , further configured to arrest an extension of an inconsistency via a configuration tailored to: minimize effects of a sigma stress, a tau XZ stress, a tau YZ stress and a diagonal Qxy in-plane interfacial stress, such that the configuration comprises a value, that reduces progressively for each region located radially further from a center of the first region of the composite rework patch, of the plurality of regions, for a tensile modulus for each region.

15. A system that comprises:
a structure; and
a composite rework patch placed over a portion of the structure, in which the composite rework patch comprises a trapezoidal planform shape having a first base and a second base, the first base parallel to the second base; a first region that comprises a first composite material portion and a first adhesive portion such that the first region comprises an inner most region of a plurality of regions; and a second region comprising a second composite material portion and a second adhesive portion, such that the second region concentrically surrounds the first region and comprises a strain elongation value lower than a strain elongation value of the first region.

16. The system of claim 15 , wherein the structure is an aircraft.

17. A rework patch configured to arrest an extension of an inconsistency via a configuration tailored to: minimize effects of a sigma stress, a tau XZ stress, a tau YZ stress and a diagonal Qxy in-plane interfacial stress, such that the configuration comprises:
a trapezoidal planform shape; and
a plurality of concentric regions, such that a value for a tensile modulus for each region in the plurality of regions reduces progressively for each region located radially further from a center of an innermost region of the plurality of regions.

18. The rework patch of claim 17 , further comprising the tensile modulus for the innermost region comprising a value in a range from 35-38 million pounds per square inch.

19. The rework patch of claim 17 , further configured comprising a ratio of a shorter base to a longer base, of the trapezoidal planform shape, such that as the ratio of the shorter base to the longer base increases, a stress intensity at an edge of the inconsistency, covered by the rework patch, decreases.

20. The rework patch of claim 17 , further configured comprising a ratio of a shorter base to a longer base, of the trapezoidal planform shape, such that as the ratio of the shorter base to the longer base increases, a strain energy release rate at the inconsistency, covered by the rework patch, decreases.

21. The rework patch of claim 17 , further configured such that a value for a strain elongation for each region reduces progressively for each region located radially further from the center of the innermost region of the rework patch.

Assignees

• Boeing Co

Inventors

• Dan-Jumbo Eugene A
• Keller Russell Lee

Classifications

• B32B2250/44

  Number of layers variable across the laminate · CPC title

• B32B43/00

  Operations specially adapted for layered products and not otherwise provided for, e.g. repairing; Apparatus therefor · CPC title

• Y10T428/20

  Patched hole or depression · CPC title

• B32B7/14

  applied in spaced arrangements, e.g. in stripes · CPC title

• B29C73/10 Primary

  using patches sealing on the surface of the article (B29C73/14 takes precedence) · CPC title