Fracture mechanics based method for composite damage tolerance criteria

Patent metadata

Field	Value
Publication number	US-10330563-B2
Application number	US-201415128316-A
Country	US
Kind code	B2
Filing date	Mar 26, 2014
Priority date	Mar 26, 2014
Publication date	Jun 25, 2019
Grant date	Jun 25, 2019

Abstract

A system and method to substantiate safe-life criteria of a structure with an anomaly includes a flaw in a critical loaded region of a test structure; a processor; and memory having instructions stored thereon that, when executed by the processor, cause the system to receive first signals indicative of strain energy release rates (SERR) for the flaw at the critical loaded region of a test structure; fit the first signals for the flaw SERR to a Benzeggah-Kenane (B-K) mixed mode curve shape; determine values indicative of B-K criteria of the test structure in response to the fitting of the first signals; receive second signals indicative of SERR for the production structure; and compare the second signals with the B-K criteria of the test structure to substantiate the safe-life criteria.

First claim

The invention claimed is:

1. A method to substantiate safe-life criteria of a nonconforming composite structure, comprising:
receiving, with a processor, first signals indicative of strain energy release rates (SERR) for an artificial flaw at a critical loaded region of a test composite structure, in response to the artificial flaw being embedded at the critical loaded region of the test composite structure;
fitting, with the processor, the first signals for the artificial flaw SERR to a Benzeggah-Kenane (B-K) mixed mode curve shape;
determining, with the processor, values indicative of B-K criteria of the test composite structure in response to the fitting of the first signals;
receiving, with the processor, second signals indicative of SERR for a production composite structure;
comparing, with the processor, the second signals with the B-K criteria of the test composite structure to substantiate the safe-life criteria;
wherein the production composite structure is used on an aircraft in response to the comparison substantiating that the production composite structure meets the safe-life criteria.

2. The method of claim 1 , wherein the artificial flaw is artificially created in the test composite structure; and
wherein the first signals used to determine the B-K criteria are for the artificial flaw SERR.

3. The method of claim 2 , further comprising subjecting the critical loaded region to qualification test load conditions in response to the embedding of the artificial flaw.

4. The method of claim 1 , wherein the B-K criteria is indicative of allowable threshold values for a composite structure.

5. The method of claim 1 , wherein the comparing of the second signals further comprises determining whether the second signals are within limits of the B-K criteria of the test composite structure.

6. The method of claim 1 , wherein the fitting of the first signals to the B-K curve shape further comprises receiving third signals indicative of SERR values of a predetermined material substantially similar to a material of the test composite structure.

7. The method of claim 1 , wherein the receiving of the production composite structure SERR further comprises determining the production composite structure SERR from finite element analysis with virtual closure crack techniques.

8. The method of claim 1 , wherein the receiving of the test composite structure SERR further comprises determining the test composite structure SERR from finite element analysis with virtual closure crack techniques.

9. The method of claim 1 , further comprising receiving the production composite structure SERR for a critical loaded region with an anomaly.

10. The method of claim 1 , wherein the composite structure is a blade.

11. The method of claim 1 , wherein the artificial flaw comprises Teflon films, Teflon rods, or planar voids.

12. A system to substantiate safe-life criteria in a composite structure, comprising:
a processor; and
memory having instructions stored thereon that, when executed by the processor, cause the system to:
receive first signals indicative of strain energy release rates (SERR) for an artificial flaw at a critical loaded region of a test composite structure, in response to the artificial flaw being embedded at the critical loaded region of the test composite structure;
fit the first signals for the flaw SERR to a Benzeggah-Kenane (B-K) mixed mode curve shape;
determine values indicative of B-K criteria of the test structure in response to the fitting of the first signals;
receive second signals indicative of SERR for a production composite structure with an anomaly;
compare the second signals with the B-K criteria of the test composite structure to substantiate the safe-life criteria;
wherein the production composite structure is used on an aircraft in response to the comparison substantiating that the production composite structure meets the safe-life criteria.

13. The system of claim 12 , wherein the artificial flaw comprises embedded Teflon as the embedded test specimen at the critical loaded region.

14. The system of claim 13 , wherein the critical loaded region is configured to be subjected to qualification test load conditions.

15. The system of claim 12 , wherein the B-K criteria is indicative of allowable threshold values for a test composite structure.

16. The system of claim 12 , wherein the processor is configured to determine whether the second signals are within limits of the B-K criteria of the test composite structure.

17. The system of claim 12 , wherein the processor is configured to receive third signals indicative of SERR values of a predetermined material substantially similar to a material of the test composite structure.

18. The system of claim 12 , wherein the processor is configured to determine the production composite structure SERR from finite element analysis with virtual closure crack techniques.

19. The system of claim 12 , wherein the processor is configured to determine the test composite structure SERR from finite element analysis with virtual closure crack techniques.

20. The system of claim 12 , wherein the artificial flaw comprises Teflon films, Teflon rods, or planar voids.

Assignees

• Sikorsky Aircraft Corp

Inventors

• Chen Yih-Farn
• Meyer Leon M
• Byrnes Fran

Classifications

• G06F2113/26

  Composites · CPC title

• G01M5/0016

  of aircraft wings or blades · CPC title

• G06F30/23

  using finite element methods [FEM] or finite difference methods [FDM] · CPC title

• G01M5/0033 Primary

  by determining damage, crack or wear · CPC title

• G06F17/5018

  Physics · mapped topic