Composite test specimen

Patent metadata

Field	Value
Publication number	US-9464975-B2
Application number	US-201414458961-A
Country	US
Kind code	B2
Filing date	Aug 13, 2014
Priority date	Aug 13, 2014
Publication date	Oct 11, 2016
Grant date	Oct 11, 2016

Abstract

A particular composite test specimen includes a first tab, a second tab, and a gage section between the first tab and the second tab. The first tab, the second tab, and the gage section are machined from a composite test blank. The composite test blank includes a plurality of plies arranged with first ply layers having fibers oriented in a first direction and second ply layers having fibers oriented in a second direction, where the first direction is different than the second direction.

First claim

What is claimed is:

1. A composite test specimen comprising:
a first tab including a plurality of plies arranged with first ply layers having first fibers oriented in a first direction and second ply layers having second fibers oriented in a second direction, the first direction different from the second direction;
a second tab including the first ply layers and the second ply layers; and
a gage section positioned between the first tab and the second tab, the gage section including the first ply layers and the second ply layers, wherein a number of plies in the gage section is less than a number of plies of the first tab and a number of plies of the second tab.

2. The composite test specimen of claim 1 , wherein the first tab, the second tab, and the gage section are machined from a composite test blank, the composite test blank includes at least two stacks of plies formed from a single composite layup, the at least two stacks of plies including:
a first stack of plies from a first section of the single composite layup; and
a second stack of plies from a second section of the single composite layup.

3. The composite test specimen of claim 2 , wherein the first stack of plies is coupled to the second stack of plies before the single composite layup was cured, and wherein the second section is adjacent the first section in the single composite layup.

4. The composite test specimen of claim 2 , wherein the single composite layup has a first face and a second face opposite the first face, wherein the first stack of plies has a third face corresponding to the first face of the single composite layup and a fourth face corresponding to the second face of the single composite layup, wherein the second stack of plies has a fifth face corresponding to the first face of the single composite layup and a sixth face corresponding to the second face of the single composite layup, and wherein the third face of the first stack of plies is coupled to the fifth face of the second stack of plies to form the composite test blank.

5. The composite test specimen of claim 2 , wherein the first direction is rotated approximately 90 degrees relative to the second direction, and wherein the first ply layers include a fewer number of layers than the second ply layers.

6. The composite test specimen of claim 5 , wherein the first direction is along a length of the composite test blank, the length corresponding to a direction from the first tab toward the second tab, and wherein the second direction is across a width of the composite test blank.

7. The composite test specimen of claim 5 , wherein sides of the first tab and the second tab are substantially parallel to the first direction, and wherein the gage section is formed by removal of material from both faces of the composite test blank to reduce a thickness of the composite test blank, and wherein a portion of the gage section proximate a center of the thickness of the composite test blank is curved.

8. The composite test specimen of claim 1 , further comprising a strain gage coupled to the gage section.

9. The composite test specimen of claim 1 , further comprising:
a first cap plate coupled to an end of the first tab, the first cap plate covering the end of the first tab and covering at least a portion of one or more sides, at least a portion of one or more faces of the first tab, or a combination thereof; and
a second cap plate coupled to an end of the second tab, the second cap plate covering the end of the second tab and covering at least a portion of one or more sides, at least a portion of one or more faces of the second tab, or a combination thereof,
wherein the first cap plate and the second cap plate are configured to inhibit brooming of ends of respective tabs when the ends are subject to end-loaded compression testing.

10. A method comprising:
forming a composite layup by arranging first ply layers to have first fibers oriented in a first direction and arranging second ply layers to have second fibers oriented in a second direction, the first direction different from the second direction, wherein the composite layup has a first face and a second face opposite the first face;
cutting the composite layup to form a first section and a second section, the first section having a third face corresponding to the first face of the composite layup and a fourth face corresponding to the second face of the composite layup, and the second section having a fifth face corresponding to the first face of the composite layup and a sixth face corresponding to the second face of the composite layup;
coupling the third face of the first section to the fifth face of the second section to form a composite panel; and
forming one or more composite test blanks from the composite panel.

11. The method of claim 10 , further comprising machining a particular composite test blank of the one or more composite test blanks to form a composite test specimen, the composite test specimen having a first tab, a second tab, and a gage section positioned between the first tab and the second tab, the gage section including the first ply layers and the second ply layers, wherein a number of plies in the gage section is less than a number of plies of the first tab and a number of plies of the second tab.

12. The method of claim 11 , wherein machining the particular composite test blank to form the composite test specimen includes machining the gage section perpendicular to the first direction and perpendicular to the second direction, and wherein a number of plies in the gage section is less than a number of plies of the particular composite test blank.

13. The method of claim 11 , further comprising:
coupling a first cap plate to an end of the first tab, the first cap plate covering the end of the first tab and covering at least a portion of one or more sides, at least a portion of one or more faces of the first tab, or a combination thereof; and
coupling a second cap plate to an end of the second tab, the second cap plate covering the end of the second tab and covering at least a portion of one or more sides, at least a portion of one or more faces of the second tab, or a combination thereof,
wherein the first cap plate and the second cap plate inhibit brooming of ends of respective tabs when the composite test specimen is subject to end-loaded during compression testing.

14. The method of claim 11 , wherein machining the particular composite test blank to form the composite test specimen includes:
milling sides of the particular composite test blank to be substantially parallel to the first direction; and
forming the gage section by removing material from both faces of the particular composite test blank to reduce a thickness of the particular composite test blank, wherein a portion of the gage section proximate a center of the thickness of the particular composite test blank is curved.

15. The method of claim 10 , wherein the plurality of plies used to fonn the composite layup include pre-impregnated (pre-preg) plies, and further comprising curing the pre-preg plies while a first face of the composite layup contacts a substantially smooth surface and while a second face of the composite layup contacts a substantially smooth caul plate.

16. The method of claim 10 , wherein the first section and the second section are adjacent to one another in the composite layup.

17. The method of claim 10 , wherein the first direction is rotated approximately 90 degrees relative to the second direction and wherein the first ply layers include fewer layers than the second ply layers

Assignees

• Boeing Co

Inventors

• Esposito Jack J
• Dustin Joshua S

Classifications

• G01N2203/0298

  Manufacturing or preparing specimens · CPC title

• G01N2203/0096

  Fibre-matrix interaction in composites · CPC title

• G01N2203/0019

  Compressive · CPC title

• G01N3/08 Primary

  by applying steady tensile or compressive forces (G01N3/28 takes precedence) · CPC title

• G01N2033/0003

  Physics · mapped topic