Preliminary testing of a complete landing gear under fatigue test has demonstrated the applicability of the test using Acoustic Emission (AE) resonant sensors attached to the outer surface of the landing gear assembly. Attenuation trials were conducted which confirmed that attenuation through the main casing is low and provided data for optimisation of sensor positioning. Background noise levels were found to be well below the normal threshold used for detection of fatigue cracking. Fatigue crack monitoring of compact test specimens has confirmed that AE can detect the initial stages of crack growth in typical landing gear materials. This study examines AE from fatigue cracks in compact tension (CT) specimens. 8 CT specimens were fatigue tested to failure and AE recorded throughout the test. The research has shown that detection of fatigue crack growth in CT specimens using appropriate AE techniques is possible. Two types of AE sensor were investigated and both confirmed to be appropriate for the detection of fatigue crack growth in the aerospace grade material. It would be preferable to use the higher resonant frequency sensor allowing more lower frequency emissions, relating to unwanted events, to be filtered out, however due to the smaller size of the miniature sensor and restrictions of access on the landing gear, both sensors will prove useful in the future of this project. Orientation of the sensors proved important, sensors orientated parallel to the crack growth recorded a significantly higher amplitude event than one perpendicular with the crack growth. It has proven possible to distinguish between emissions from a hydraulic actuator and fatigue crack growth in the laboratory.
Detection of fatigue crack growth in aircraft landing gear
Nachweis des Ermüdungsrisswachstums in Flugzeug-Fahrgestellen
2004
8 Seiten, 13 Bilder, 4 Quellen
Conference paper
Storage medium
English
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