Test system and method for creating controlled and repeatable out-of-plane fiber distortion in composite laminates

Patent metadata

Field	Value
Publication number	US-11090882-B2
Application number	US-201816142093-A
Country	US
Kind code	B2
Filing date	Sep 26, 2018
Priority date	Sep 26, 2018
Publication date	Aug 17, 2021
Grant date	Aug 17, 2021

Abstract

In one version there is provided a test system including a layup tool having a layup surface, and two fairing bars attached to the layup surface. The test system includes the composite laminate having a plurality of stacked plies, and positioned between the two fairing bars. The test system includes fiber distortion initiator(s) positioned at one or more locations under, and adjacent to, one or more plies of the plurality of stacked plies. The test system includes two caul plates with a gap in between, and positioned over the composite laminate. When the test system undergoes a pressurized cure process with a vacuum compaction, a restricted outward expansion of the plurality of stacked plies by the fairing bars, and a pressure differential region formed by the one or more fiber distortion initiators at the one or more locations, create the controlled and repeatable out-of-plane fiber distortion in the composite laminate.

First claim

What is claimed is:

1. A test system for creating controlled and repeatable out-of-plane fiber distortion in a composite laminate, the test system comprising:
a curved layup tool comprising a layup portion having a layup surface with a curved configuration and a convex profile, the layup portion coupled to a base structure portion, and the curved layup tool being in a stationary position;
two fairing bars attached to the layup surface and spaced opposite to one another;
the composite laminate comprising a plurality of stacked plies, the composite laminate manually laid up on the layup surface of the curved layup tool and positioned between the two fairing bars;
one or more fiber distortion initiators positioned at one or more locations under, and adjacent to, one or more plies of the plurality of stacked plies, each of the one or more fiber distortion initiators comprising a structure having a volume that increases a height of a portion of the one or more plies of the plurality of stacked plies stacked over each of the one or more fiber distortion initiators; and
two caul plates positioned over the composite laminate and positioned between the two fairing bars, the two caul plates having a gap in between the two caul plates,
wherein when the test system undergoes a pressurized cure process with a vacuum compaction, a restricted outward expansion of the plurality of stacked plies by the two fairing bars, and a pressure differential region formed by the one or more fiber distortion initiators at the one or more locations, create the controlled and repeatable out-of-plane fiber distortion of the one or more plies of the plurality of stacked plies in the composite laminate, at one or more controlled locations in the composite laminate, and
further wherein the pressure differential region includes a low pressure area next to a high pressure area, the low pressure area and the high pressure area located above the one or more locations of the one or more fiber distortion initiators.

2. The test system of claim 1 , further comprising a film layer positioned between the composite laminate and the two caul plates, wherein the film layer has a bottom side adjacent the composite laminate and a top side adjacent the two caul plates.

3. The test system of claim 1 , wherein the two fairing bars comprise a first fairing bar and a second fairing bar, and the composite laminate has a first peripheral end abutting the first fairing bar and has a second peripheral end abutting the second fairing bar.

4. The test system of claim 1 , wherein at least one of the one or more fiber distortion initiators is positioned adjacent to, and between, the layup surface of the curved layup tool and a first ply laid over the layup surface and the at least one fiber distortion initiator.

5. The test system of claim 1 , wherein at least one of the one or more fiber distortion initiators is positioned adjacent to, and between, two plies of the plurality of stacked plies.

6. The test system of claim 1 , wherein the one or more fiber distortion initiators comprises one of, a composite material overfill element, an outer mold line (OML) strip, an inner mold line (IML) strip, and a film layer.

7. The test system of claim 1 , wherein each of the one or more fiber distortion initiators has a length that is substantially equal to a length of the composite laminate.

8. The test system of claim 1 , wherein the two caul plates comprise a first caul plate positioned next to a second caul plate, with the gap in between the first caul plate and the second caul plate, prior to the test system undergoing the pressurized cure process.

9. The test system of claim 1 , wherein the test system is a sub-scale test system for creating the controlled and repeatable out-of-plane fiber distortion at a sub-scale level that is representative of out-of-plane fiber distortion of a full-scale size part.

10. The test system of claim 9 , wherein the curved layup tool of the sub-scale test system has a radius of curvature that is substantially equal to a part radius of curvature of the full-scale size part.

11. A test system for creating controlled and repeatable out-of-plane fiber distortion in a composite laminate, used for testing purposes and process improvement, the test system comprising:
a curved layup tool comprising a layup portion having a layup surface with a curved configuration and a convex profile, the layup portion coupled to a base structure portion, and the curved layup tool being in a stationary position;
a first fairing bar and a second fairing bar, both attached to the layup surface, the first fairing bar spaced opposite the second fairing bar in a parallel alignment;
the composite laminate comprising a plurality of stacked carbon fiber plies, the composite laminate manually laid up on the layup surface of the curved layup tool, and the composite laminate having a first peripheral end abutting the first fairing bar and having a second peripheral end abutting the second fairing bar;
one or more fiber distortion initiators positioned at one or more locations under, and adjacent to, one or more carbon fiber plies of the plurality of stacked carbon fiber plies, each of the one or more fiber distortion initiators comprising a structure having a volume that increases a height of a portion of the one or more carbon fiber plies of the plurality of stacked carbon fiber plies stacked over each of the one or more fiber distortion initiators;
a first caul plate positioned next to a second caul plate with a gap in between the first caul plate and the second caul plate, the first caul plate and the second caul plate positioned over the composite laminate and positioned between the first fairing bar and the second fairing bar, the first caul plate and the second caul plate each having an outer side end abutting the first fairing bar and the second fairing bar, respectively; and
a film layer positioned between the composite laminate and the first caul plate and the second caul plate, wherein the film layer has a bottom side adjacent the composite laminate and a top side adjacent the first caul plate and the second caul plate,
wherein when the test system undergoes a pressurized cure process with a vacuum compaction, the first fairing bar and the second fairing bar restrict the plurality of stacked carbon fiber plies from expanding outwardly, and the one or more fiber distortion initiators create a pressure differential region at the one or more locations, to form distorted out-of-plane fibers at one or more controlled locations in the one or more carbon fiber plies of the plurality of stacked carbon fiber plies stacked over the one or more fiber distortion initiators, and, in turn, creating the controlled and repeatable out-of-plane fiber distortion in the composite laminate, used for testing purposes and process improvement, and
further wherein the pressure differential region includes a low pressure area next to a high pressure area, the low pressure area and the high pressure area located above the one or more locations of the one or more fiber distortion initiators, and
further wherein the test system is a sub-scale test system for creating the controlled and repeatable out-of-plane fiber distortion at a sub-scale level that is representative of out-of-plane fiber distortion of a full-scale size part comprising a fuselage barrel section of a fuselage of an aircraft.

12. The test system of claim 11 , further comprising a third fairing bar and a fourth fairing bar, the composite laminate having a third peripheral end abutting the third fairing bar and having a fourth peripheral end abutting the fourth fairing bar.

13. Th

Assignees

• Boeing Co

Inventors

• Saini Gagandeep
• Nelson Karl M
• Ingram William H

Classifications

• B29C70/549

  Details of caul plates, e.g. materials or shape · CPC title

• B29C33/307 Primary

  Mould plates mounted on frames; Mounting the mould plates; Frame constructions therefor (shaping plates for making moulds B29C33/3842; thin walled moulds B29C33/0011) · CPC title

• G01N3/28

  Investigating ductility, e.g. suitability of sheet metal for deep-drawing or spinning · CPC title

• G01N2203/0298

  Manufacturing or preparing specimens · CPC title

• G01B21/32 Primary

  for measuring the deformation in a solid · CPC title