Fatigue test of an integrally stiffened panel: Prediction and crack growth monitoring using acoustic emission

Kód výsledku v IS VaVaI

<a href="https://www.isvavai.cz/riv?ss=detail&h=RIV%2F00010669%3A_____%2F16%3AN0000042" target="_blank" >RIV/00010669:_____/16:N0000042 - isvavai.cz</a>

Výsledek na webu

<a href="http://www.sciencedirect.com/science/article/pii/S2452321616303997" target="_blank" >http://www.sciencedirect.com/science/article/pii/S2452321616303997</a>

DOI - Digital Object Identifier

<a href="http://dx.doi.org/10.1016/j.prostr.2016.06.381" target="_blank" >10.1016/j.prostr.2016.06.381</a>

Jazyk výsledku

angličtina

Název v původním jazyce

Fatigue test of an integrally stiffened panel: Prediction and crack growth monitoring using acoustic emission

Popis výsledku v původním jazyce

Airworthiness regulations require operating advanced aircraft structures in compliance with a damage tolerance philosophy. Therefore, flight safety and structure reliability in service must be ensured using many types of additional activities, such as damage detection, crack growth prediction and critical size of cracks determination. As a result, the structural health monitoring of aircrafts using various detection principles is needed. The paper documents the use of an acoustic emission method for the health monitoring of a typical airframe structure. It is represented by an integrally stiffened metallic panel demonstrating a bottom wing panel of a commuter aircraft. A fatigue test of the panel under a flight-by-flight loading sequence was performed. The crack growth was monitored by a visual method (VT) and an acoustic emission (AE) method. Several AE sensors placed in different configurations were used. AE reached very good agreement with the crack growth data, although the presented test was partially conducted in a noisy environment. The de-noised AE parameters were evaluated according to the actual position of the sensors and the crack tip. The influence of stringers on the measured signal changes was studied as well.

Název v anglickém jazyce

Fatigue test of an integrally stiffened panel: Prediction and crack growth monitoring using acoustic emission

Popis výsledku anglicky

Airworthiness regulations require operating advanced aircraft structures in compliance with a damage tolerance philosophy. Therefore, flight safety and structure reliability in service must be ensured using many types of additional activities, such as damage detection, crack growth prediction and critical size of cracks determination. As a result, the structural health monitoring of aircrafts using various detection principles is needed. The paper documents the use of an acoustic emission method for the health monitoring of a typical airframe structure. It is represented by an integrally stiffened metallic panel demonstrating a bottom wing panel of a commuter aircraft. A fatigue test of the panel under a flight-by-flight loading sequence was performed. The crack growth was monitored by a visual method (VT) and an acoustic emission (AE) method. Several AE sensors placed in different configurations were used. AE reached very good agreement with the crack growth data, although the presented test was partially conducted in a noisy environment. The de-noised AE parameters were evaluated according to the actual position of the sensors and the crack tip. The influence of stringers on the measured signal changes was studied as well.

Druh

D - Stať ve sborníku

CEP obor

JL - Únava materiálu a lomová mechanika

OECD FORD obor

—

Projekt

—

Návaznosti

I - Institucionalni podpora na dlouhodoby koncepcni rozvoj vyzkumne organizace

Rok uplatnění

2016

Kód důvěrnosti údajů

S - Úplné a pravdivé údaje o projektu nepodléhají ochraně podle zvláštních právních předpisů

Název statě ve sborníku

Procedia Structural Integrity

ISBN

—

ISSN

2452-3216

e-ISSN

—

Počet stran výsledku

8

Strana od-do

3049–3056

Název nakladatele

Elsevier Science B.V.

Místo vydání

Neuveden

Místo konání akce

Catania, Italy

Datum konání akce

20. 6. 2016

Typ akce podle státní příslušnosti

WRD - Celosvětová akce

Kód UT WoS článku

000387976803016