Acoustic Emission Characteristics of Fatigue Crack Development in a Pitch Control Arm of Helicopter Lifting Propeller Blades
Transport Means 2010: Proceedings of the 14th International Conference 2010
Aleksejs Nasibullins, Jevgēņijs Garbuzs, Sergejs Doroško

It is observed change of acoustic emission (AE) parameters during stand fatigue tests of pitch control arm of helicopter lifting propeller. The total AE and AE intensity in a loading cycle were analyzed during these researches. It was confirmed the stepped change of the total AE which is typical for strong structures of aircraft and reflects irregular development of fatigue crack. It is shown that micro-cracks formation is securely fixed by AE method long before visible crack appearance. It is recognized that AE signal emergence in a loading cycle and crack development are as during load growth as during load decreasing in the loading cycle.


Atslēgas vārdi
acoustic emission, fatigue crack, helicopter

Nasibullins, A., Harbuz, Y., Doroško, S. Acoustic Emission Characteristics of Fatigue Crack Development in a Pitch Control Arm of Helicopter Lifting Propeller Blades. No: Transport Means 2010: Proceedings of the 14th International Conference, Lietuva, Kaunas, 21.-21. oktobris, 2010. Kaunas: Technologija, 2010, 49.-52.lpp. ISSN 1822-296X.

Publikācijas valoda
English (en)
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