A prototype acoustic system for detecting unstable crack growth in structure has been developed and flight tested on an aircraft. The system is known as the Flight Structural Monitoring System (FSMS). The system consists of transducers for monitoring 24 locations on the wing structure, a Signal Processing and Display Unit (SPADU) located on the flight deck, and a warning light on the pilot's annunciator panel. Design criteria were established by conducting fracture test on large-scale structural components. Signals generated by various crack extensions were measured to determine the detectability limits and singnal attenuation in aircraft structure. Structure-borne noise measurements were made during flight to establish signal-to-noise criteria.
Acoustic emission for in-flight monitoring on aircraft structures
Akustische Emission fuer die Ueberwachung von Flugzeugbauteilen waehrend des Fluges
Materials Evaluation ; 34 , 8 ; 165-171
1976
7 Seiten, 11 Bilder, 3 Tabellen, 10 Quellen
Article (Journal)
English
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