10.14489/td.2018.05.pp.014-019

2018, 05 May

DOI: 10.14489/td.2018.05.pp.014-019

Stepanova L. N., Kojemjakin V. L., Ramazanov I. S., Chernova V. V.
METHOD OF SUPERVISION OF COMPOSITE AIRPLANE CONSTRUCTION INTEGRITY DURING STATIC LOADING TEST WITH ACOUSTIC EMISSION AND STRAIN MEASUREMENT APPLICATION
(pp. 14-19)

Abstract. The results of the integrity supervision of the TVS-2DTS composite aircraft construction during the static strength test are given. The acoustic emission (AE) monitoring of defects and the strain measurements of the aircraft structure during the static loading is performed. By AE method the coordinates of increased activity of the detected signals zones were determined. By SCAD-16.10 diagnostic system sources of AE signals were localized along the left and right side of the fuselage, in the wing attachment to the center wing section zone, and also in the area of the chassis beam to the bulkhead attachment. The main informative parameters of AE signals were analyzed. The most active source of emission were mapped to AE signals with an amplitude 200...260 mV and dominant frequencies 150...200 kHz. Strain gauging were conducted using microprocessor multichannel tensometric systems MMTS-64.01 of accuracy class 0.2, and deformations of several zones of the aircraft structure were determined in real time mode. According to the results of tensometry, zones of tension and compression of the structure with minimum and maximum values of the relative strain were located.

Keywords: Keywords: airplane, carbon plastic, acoustic emission, strain gauge, strength tests.

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L. N. Stepanova, V. L. Kojemjakin, I. S. Ramazanov (FSUE “Siberian Aeronautical Research Institute named after S. A. Chaplygin”, Novosibirsk, Russia) E-mail: Данный адрес e-mail защищен от спам-ботов, Вам необходимо включить Javascript для его просмотра.
V. V. Chernova (Siberian Transport University (STU), Novosibirsk, Russia) E-mail: Данный адрес e-mail защищен от спам-ботов, Вам необходимо включить Javascript для его просмотра.

+ - References Click to collapse

1. Barsuk V. E., Stepanova L. N., Chernova V. V. et al. (2017). Location of the ruptured zone during the strength test of carbon fiber reinforced plastic fuselage. Polyot, (2), pp. 21-26. [in Russian language]
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5. Kablov E. N., Startsev O. V., Krotov A. S. et al. (2010). Climate ageing of composite materials for aircraft purpose. Deformatsiya i Razrushenie Materialov, (11), pp. 19-27. [in Russian language]

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DOI: 10.14489/td.2018.05.pp.014-019

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