Optical fiber communications with composite structural monitoring for determining damaged structure based on the analysis of optical signal

Patent metadata

Field	Value
Publication number	US-10018569-B2
Application number	US-201615153565-A
Country	US
Kind code	B2
Filing date	May 12, 2016
Priority date	May 12, 2016
Publication date	Jul 10, 2018
Grant date	Jul 10, 2018

Abstract

A method for detecting defects in a composite structure, such as in an aircraft structure, that includes sending an optical signal down an optical fiber embedded in the composite structure and analyzing the optical signal at a detector. If it is determined that the optical signal is turning on and off or an increase in the bit error rate is occurring at the detector, the composite structure may be delaminating or the composite structure may be somehow damaged. If it is determined that the composite structure is damaged, the optical signal can be sent down a different optical fiber that may not be at a location where the composite structure is damaged, and a continuous beam of light can be sent down the optical fiber that is at the damaged part of the composite structure to determine whether the damage is increasing.

First claim

What is claimed is:

1. A method for detecting defects in a composite structure, said method comprising:
providing at least one optical fiber in the composite structure;
sending an optical signal down the at least one optical fiber;
detecting the optical signal propagating down the fiber at a detector;
determining that the optical signal is turning on and off at the detector;
determining that the composite structure is damaged because of the turning on and off of the signal; and
determining whether the damage to the composite structure is increasing by analyzing changes in spectral content of how often the detected optical signal turns on and off.

2. The method according to claim 1 further comprising determining that a bit error rate (BER) of the optical signal has significantly increased at the detector, wherein determining that the composite structure is damaged includes determining that the composite structure is damaged if the increased BER is detected.

3. The method according to claim 2 wherein providing at least one optical fiber includes providing a plurality of optical fibers, and wherein if it is determined that the composite structure is damaged, sending the optical signal down an undamaged optical fiber to the detector.

4. The method according to claim 1 further comprising providing a continuous unmodulated light beam on the at least one optical fiber if it is determined that the composite structure is damaged so as to observe the spectral content of the detected optical signal caused by the damage.

5. The method according to claim 1 further comprising predicting when the composite structure will fail based on changes in the spectral content of the detected optical signal.

6. The method according to claim 1 wherein determining that the composite structure is damaged includes determining that the composite structure is delaminating.

7. The method according to claim 1 wherein providing at least one optical fiber includes providing at least one optical fiber configured in a serpentine manner.

8. The method according to claim 1 wherein the composite structure is a carbon fiber composite structure.

9. The method according to claim 1 wherein the composite structure is on an aircraft.

10. A method for detecting defects in a composite structure, said method comprising:
providing at least one optical fiber in the composite structure;
sending an optical signal down the at least one optical fiber;
detecting the optical signal propagating down the fiber at a detector;
identifying a bit error rate (BER) of the optical signal at the detector;
determining whether the BER has significantly increased; and
determining that the composite structure is damaged as a result of the increase in the BER.

11. The method according to claim 10 wherein providing at least one optical fiber includes providing a plurality of optical fibers, and wherein if it is determined that the composite structure is damaged, sending the optical signal down a different optical fiber to the detector.

12. The method according to claim 10 further comprising providing a continuous unmodulated light beam down the at least one optical fiber if it is determined that the composite structure is damaged so as to observe the spectral content of the detected optical signal.

13. The method according to claim 12 further comprising predicting when the composite structure will fail based on changes in the spectral content of the detected optical signal.

14. The method according to claim 10 wherein determining that the composite structure is damaged includes determining that the composite structure is delaminating.

15. The method according to claim 10 wherein providing at least one optical fiber includes providing at least one optical fiber configured in a serpentine manner.

16. The method according to claim 10 wherein the composite structure is a carbon fiber composite structure.

17. The method according to claim 10 wherein the composite structure is on an aircraft.

18. A method for detecting defects in a composite structure, said method comprising:
providing a plurality of optical fibers in the composite structure;
sending an optical signal down one of the optical fibers;
detecting the optical signal propagating down the one optical fiber at a detector;
analyzing the optical signal at the detector;
determining that the composite structure is damaged based on the analysis of the optical signal; and
sending the optical signal down another one of the optical fibers if it is determined that the one optical fiber is damaged.

19. The method according to claim 18 wherein analyzing the optical signal includes determining that the optical signal is turning on and off and determining whether the damage to the composite structure is increasing by analyzing changes in a spectral frequency of how often the detected optical signal turns on and off.

20. The method according to claim 18 wherein analyzing the optical signal includes determining that a bit error rate (BER) of the optical signal has significantly increased.

Assignees

• Northrop Grumman Systems Corp

Inventors

• Evans David W

Classifications

• H04B10/07953

  Monitoring or measuring OSNR, BER or Q · CPC title

• B64D45/00

  Aircraft indicators or protectors not otherwise provided for · CPC title

• G01N2021/8472

  Investigation of composite materials · CPC title

• B64D2045/0085

  Devices for aircraft health monitoring, e.g. monitoring flutter or vibration · CPC title

• G01N2201/088

  Using a sensor fibre · CPC title