Initial Fatigue Quality Assessment for Aircraft Wing Panel Fastener Hole
نویسندگان
چکیده
منابع مشابه
Experimental verification of a Kalman filter approach for estimating the size of fastener hole fatigue cracks
Ultrasonic methods have been implemented for in situ sizing of fatigue cracks near fastener holes. These techniques, however, only provide an estimate at the time of the measurement and cannot predict the remaining life of the structure. In contrast, statistical crack propagation approaches model the expected fatigue life based on worst-case fatigue process assumptions. The authors have recentl...
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The ®nite element alternating method is extended further for analyzing multiple arbitrarily curved cracks in an isotropic plate under plane stress loading. The required analytical solution for an arbitrarily curved crack in an in®nite isotropic plate is obtained by solving the integral equations formulated by Cheung and Chen (1987a, b). With the proposed method several example problems are solv...
متن کاملDiscrimination between Fatigue Cracking and Mechanical Damage in Aircraft Fastener Holes by Eddy-Current Phase Rotation
Fatigue cracking in metallic aircraft structure often originates at fastener holes and can be detected using the nondestructive inspection technique of bolt-hole eddy-current (BHEC) testing. BHEC testing is based on detection of a disturbance in the induced current or magnetic field caused by a surface-breaking crack in the bore of the hole. However, if the surface of the hole contains benign m...
متن کاملAn integrated approach to local ultrasonic monitoring of fastener hole fatigue cracks
a crack depth in mm, same as x â measurement system response, 1 – R– A(x) system model for evolving crack depth x A(n) linearised system model at measurement set n B(x) measurement model giving normalised energy ratio R– as a function of crack depth x B(n) linearised measurement model at measurement set n B(R) inverse measurement model giving crack depth x as a function of normalised energy rat...
متن کاملSimultaneous Ultrasonic Monitoring of Crack Growth and Dynamic Loads during a Full Scale Fatigue Test of an Aircraft Wing
An in situ ultrasonic angle beam method has been developed to detect and size fatigue cracks emanating from fastener holes. The method employs transducers mounted in a pitch-catch configuration on each side of the hole, and the modulation of received signals with load is used to detect and size small fatigue cracks. The focus of this paper is the monitoring of a series of critical fastener hole...
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ژورنال
عنوان ژورنال: Xibei Gongye Daxue Xuebao/Journal of Northwestern Polytechnical University
سال: 2018
ISSN: 1000-2758
DOI: 10.1051/jnwpu/20183610091