Composite structure and method for barely visible impact damage detection

Patent metadata

Field	Value
Publication number	US-2019061310-A1
Application number	US-201816176562-A
Country	US
Kind code	A1
Filing date	Oct 31, 2018
Priority date	Oct 13, 2015
Publication date	Feb 28, 2019
Grant date	—

Abstract

A composite structure including a composite body having an outer surface and including a web portion having a proximal portion and a distal portion, and a base portion connected to the proximal portion of the web portion, wherein the composite body is elongated along a span axis, and a detection layer connected to the outer surface of the composite body at the distal portion of the web portion of the composite body, the detection layer including a plurality of glass fibers embedded in a first matrix material, wherein the composite body includes a plurality of carbon fibers embedded in a second matrix material, and wherein the outer surface of the composite body subjacent the detection layer is substantially free of exposed carbon fibers of the plurality of carbon fibers.

First claim

What is claimed is:

1 . A composite structure comprising:
a composite body having an outer surface and comprising a web portion having a proximal portion and a distal portion, and a base portion connected to the proximal portion of the web portion, wherein the composite body is elongated along a span axis; and a detection layer connected to the outer surface of the composite body at the distal portion of the web portion of the composite body, the detection layer comprising a plurality of glass fibers embedded in a first matrix material, wherein the composite body comprises a plurality of carbon fibers embedded in a second matrix material, and wherein the outer surface of the composite body subjacent the detection layer is substantially free of exposed carbon fibers of the plurality of carbon fibers.

2 . The composite structure of claim 1 wherein the detection layer continuously extends along the span axis.

3 . The composite structure of claim 2 wherein the detection layer continuously extends in a direction transverse to the span axis.

4 . The composite structure of claim 1 wherein the detection layer comprises a first edge and a second edge laterally opposed from the first edge, and wherein the detection layer continuously extends from the first edge to the second edge.

5 . The composite structure of claim 1 wherein the outer surface of the composite body subjacent the detection layer has a substantially continuous curvature.

6 . The composite structure of claim 1 wherein the outer surface of the composite body subjacent the detection layer is substantially flat.

7 . The composite structure of claim 1 wherein the first matrix material and the second matrix material have substantially the same composition.

8 . The composite structure of claim 1 wherein the composite body comprises a laminate structure comprising a plurality of composite plies.

9 . The composite structure of claim 1 wherein the detection layer has a total cross-sectional thickness ranging from about 0.003 inch to about 0.050 inch.

10 . The composite structure of claim 1 wherein the detection layer comprises a stacked structure comprising at least two plies.

11 . The composite structure of claim 10 wherein at least one ply of the stacked structure comprises a cross-sectional thickness ranging from about 0.003 inch to about 0.015 inch.

12 . The composite structure of claim 1 wherein the composite body is configured as a hat stringer.

13 . The composite structure of claim 1 wherein the composite body is configured as a J-type stringer.

14 . The composite structure of claim 1 wherein the composite body is configured as an I-type stringer.

15 . The composite structure of claim 1 wherein the composite body is configured as a blade stringer.

16 . The composite structure of claim 1 further comprising an aircraft skin, wherein the composite body is connected to the aircraft skin.

17 . An aircraft comprising the composite structure of claim 1 .

18 . A method for detecting barely visible impact damage on a composite body comprising a plurality of carbon fibers embedded in a matrix material, wherein the composite body comprises a web portion having a proximal portion and a distal portion, and a base portion connected to the proximal portion of the web portion, and wherein the distal portion of the web portion of the composite body has an outer surface that is substantially free of exposed carbon fibers of the plurality of carbon fibers, the method comprising:
connecting to the outer surface of the distal portion of the web portion of the composite body a detection layer comprising a plurality of glass fibers embedded in a matrix material.

19 . The method of claim 18 wherein the connecting comprises co-curing the detection layer with the composite body.

20 . The method of claim 18 wherein the connecting comprises bonding the detection layer to the composite body with an adhesive.

Assignees

• Boeing Co

Inventors

• Kwon Hyukbong
• Pham Khanh Mai
• Carlson Lisa C
• Hanson Garrett C

Classifications

• B64C1/12 Primary

  Construction or attachment of skin panels · CPC title

• B32B2605/18

  Aircraft · CPC title

• B32B2307/732

  Dimensional properties · CPC title

• B32B2307/718

  Weight, e.g. weight per square meter · CPC title

• B32B2305/72

  Cured, e.g. vulcanised, cross-linked · CPC title