[12] Patent
[11] Patent No.:GC0009381  
[45] Date of Publishing the Grant of the Patent: 31/Dec /2018                56/2018  
Number of the Decision to Grant the Patent:2018/141741
Date of the Decision to Grant the Patent:17/Dec/2018

[21] Application No.:GC 2014-28634

[22] Filing Date:22/12/2014

[30] Priority:

[33] State [32] Priority date [31] Priority No.

[72] Inventors:1- Li Chun Chang،2- James M. Fortier،3- Ronald J. Steckman،4- Richard M. Coleman

[73] Owner: The Boeing Company, 100 North Riverside Plaza, Chicago 60606-2016, Illinois , USA

[74] Agent: Saud M. A. Shawwaf Law Office




Int. Cl.: G01N 3/02 (2006.01)

[56] Cited Documents:

-US 2013/192381 A1 (BECKER THOMAS [DE] ET AL) 01 August 2013
-US 2009/259411 A1 (LOOMIS KEVIN S [US] ET AL) 15 October 2009
-US 2011/316712 A1 (MCIVER KEITH L [US] ET AL) 29 December 2011
-US 2009/033323 A1 (GEORGESON GARY E [US] ET AL) 05 February 2009
Examiner: Eng. Fahad M. AlBaker

[57] Abstract: A methodfor monitoring structural integrity of a repaired aircraft (202) component made of composite material. The method (100) comprises: (a) placing a multiplicity of plies (36a-36c) of repair composite material over a repair site (32) on the component with a sensor (10) disposed between two plies (36a-36c); (b) curing the plies (36a-36c) of repair composite material so that the repair composite material, with the sensor (10) embedded therein, is bonded to the repair site (32); (c) acquiring first sensor data from the sensor (10) before a flight of the aircraft (202); (d) acquiring second sensor data from the sensor (10) during or after the flight; (e) comparing the first sensor data to the second sensor data; (f) identifying differences between the first and second sensor data indicative of structural change; and (g) determining whether the identified differences indicate structural change in excess of a specified threshold. Steps (c) through (g) are performed by a computer system.
No. of claims: 7     No. of figures: 13


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