Influence of Operational and Environmental Conditions on Lamb Wave Signals

Kód výsledku v IS VaVaI

<a href="https://www.isvavai.cz/riv?ss=detail&h=RIV%2F00010669%3A_____%2F22%3AN0000051" target="_blank" >RIV/00010669:_____/22:N0000051 - isvavai.cz</a>

Výsledek na webu

<a href="https://link.springer.com/chapter/10.1007/978-3-031-07322-9_4" target="_blank" >https://link.springer.com/chapter/10.1007/978-3-031-07322-9_4</a>

DOI - Digital Object Identifier

<a href="http://dx.doi.org/10.1007/978-3-031-07322-9_4" target="_blank" >10.1007/978-3-031-07322-9_4</a>

Jazyk výsledku

angličtina

Název v původním jazyce

Influence of Operational and Environmental Conditions on Lamb Wave Signals

Popis výsledku v původním jazyce

The paper is focused on the investigation of Lamb wave signals measured in different operational and environmental conditions of an ultralight aircraft. Transducers were mounted on the right side of the fuselage skin behind the pilot seat and the circular cover located on the bottom of the fuselage. The fatigue crack of about 1 mm in length was cycled into the drilled hole in the center of the cover part in the laboratory before the test. The side fuselage skin remained intact. Five test flights were conducted within four months. The temperature effect on Lamb wave signals was realized through measurements in different flight altitudes ranging between 2,000 and 7,000 ft. Both A0 and S0 mode were analyzed within the frequency range of 50 to 500 kHz. Based on the...

Název v anglickém jazyce

Influence of Operational and Environmental Conditions on Lamb Wave Signals

Popis výsledku anglicky

The paper is focused on the investigation of Lamb wave signals measured in different operational and environmental conditions of an ultralight aircraft. Transducers were mounted on the right side of the fuselage skin behind the pilot seat and the circular cover located on the bottom of the fuselage. The fatigue crack of about 1 mm in length was cycled into the drilled hole in the center of the cover part in the laboratory before the test. The side fuselage skin remained intact. Five test flights were conducted within four months. The temperature effect on Lamb wave signals was realized through measurements in different flight altitudes ranging between 2,000 and 7,000 ft. Both A0 and S0 mode were analyzed within the frequency range of 50 to 500 kHz. Based on the...

Druh

D - Stať ve sborníku

CEP obor

—

OECD FORD obor

20302 - Applied mechanics

Projekt

—

Návaznosti

I - Institucionalni podpora na dlouhodoby koncepcni rozvoj vyzkumne organizace

Rok uplatnění

2022

Kód důvěrnosti údajů

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

Název statě ve sborníku

European Workshop on Structural Health Monitoring

ISBN

978-3-031-07254-3

ISSN

2366-2557

e-ISSN

2366-2565

Počet stran výsledku

10

Strana od-do

34-43

Název nakladatele

Springer Cham

Místo vydání

Švýcarsko

Místo konání akce

Palermo

Datum konání akce

4. 7. 2022

Typ akce podle státní příslušnosti

WRD - Celosvětová akce

Kód UT WoS článku

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