Bolting Elements of Helicopter Fuselage and Tail Boom Joints Using Acoustic Emission Amplitude and Absolute Energy Criterion
Publication: Journal of Aerospace Engineering
Volume 32, Issue 3
Abstract
This research was devoted to the development of a structural health monitoring (SHM) system for helicopter structures using the acoustic emission (AE) method. Experiments were carried out on a test bench to test helicopter fuselage and tail boom joints under dynamic loads. During the experiments, several bolted joints fractured. The process of crack development in the bolt material was controlled by the AE method. The results presented in the paper link AE parameters to the process of crack development. Fractographic analysis was used to validate the experimental results. The dependence of fatigue crack growth in a bolt material taking into account bolt retightening in the joint between the tail boom and fuselage was revealed.
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Published In
Journal of Aerospace Engineering
Volume 32 • Issue 3 • May 2019
Copyright
©2019 American Society of Civil Engineers.
History
Received: Jul 17, 2017
Accepted: Jul 3, 2018
Published online: Jan 23, 2019
Published in print: May 1, 2019
Discussion open until: Jun 23, 2019
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