This paper reviews procedures for distinguishing between acoustic emission (AE) from fatigue crack propagation and from spurious sources in aircraft applications. Particular emphasis is placed on the development at the ARL of procedures applicable during AE monitoring of complex-shaped components. First procedures to eliminate extraneous sources are evaluated, including the use of guard sensors and source location systems. The capabilities of additional signal-processing (which in principle can range from adaptive to non-adaptive) for identifying and locating AE from fatigue crack propagation are then evaluated. The problems in applying adaptive processing are illustrated by AE results from a Macchi aircraft in-flight and Mirage aircraft during full-scale fatigue testing. The ARL development of semi-adaptive processing based on background research on AE sources, sensors, calibration and other techniques is described. Successful application of this processing to the Mirage test above is then detailed, and the value of using reduced adaptation in processing is demonstrated. Keywords: Fatigue crack growth, Nondestructive testing; Signal processing; Australia. (edc)
Development of Acoustic Emission for Structural Integrity Monitoring of Aircraft
1988
35 pages
Report
No indication
English
Aircraft , Nondestructive Testing , Acoustic emissions , Nondestructive testing , Adaptation , Adaptive systems , Calibration , Crack propagation , Detectors , Fatigue tests(Mechanics) , Fatigue(Mechanics) , Inflight , Monitoring , Processing , Reduction , Reliability , Signal processing , Sources , Spurious effects , Structural properties , Foreign technology
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