发明名称 |
Detection And Assessment Of Damage To Composite Structure |
摘要 |
A method for 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. |
申请公布号 |
SG10201408647W(A) |
申请公布日期 |
2015.07.30 |
申请号 |
SG10201408647W |
申请日期 |
2014.12.23 |
申请人 |
THE BOEING COMPANY |
发明人 |
CHANG, LI CHUN;FORTIER, JAMES M.;STECKMAN, RONALD J.;COLEMAN, RICHARD M. |
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