Adhesively bonded repair patches are used to extend the useful life of aircraft. Any damage to the repair patch, like the adhesive and cohesive weaknesses similar to that found in adhesively bonded joints, can reduce the expected life of the aircraft. A conventional inspection approach using normal or oblique incidence of ultrasonic waves has only limited capability in detecting adhesive and cohesive weaknesses. A systematic approach to guided wave mode selection for the inspection of adhesive and cohesive weaknesses in an adhesively bonded repair patch comprising of aluminum and titanium is presented in this paper. A guided wave mode with large in-plane displacement at the aluminum-epoxy interface in a titanium-epoxy-aluminum bonded joint was selected for the inspection. Epoxy bonded aluminum-titanium repair patch samples were fabricated in the lab with simulated interfacial weaknesses. Using an acrylic angle beam wedge based approach for guided wave mode generation, the suitability of the 10 deg wedge angle and 2.5 MHz excitation source was proved by sweeping the frequencies in the range 1 MHz to 3 MHz. A fixed angle beam wedge pair with 10 deg incidence angle and 2.5 MHz excitation frequency, kept in a pitchcatch mode, was shown to be successful in discriminating between the adhesive and cohesive weaknesses and a good joint.
Aircraft bond repair patch inspection using ultrasonic guided waves
Untersuchung von Flugzeug Reparatur-Klebeflicken mittels geführter Schallwellen
2009
6 Seiten, 4 Bilder, 6 Quellen
Aufsatz (Konferenz)
Datenträger
Englisch
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