Compression after impact and fatigue behaviour of CFRP stiffened panels
Identifikátory výsledku
Kód výsledku v IS VaVaI
<a href="https://www.isvavai.cz/riv?ss=detail&h=RIV%2F00010669%3A_____%2F15%3A%230001898" target="_blank" >RIV/00010669:_____/15:#0001898 - isvavai.cz</a>
Výsledek na webu
<a href="http://www.emeraldinsight.com/doi/full/10.1108/IJSI-06-2014-0030" target="_blank" >http://www.emeraldinsight.com/doi/full/10.1108/IJSI-06-2014-0030</a>
DOI - Digital Object Identifier
<a href="http://dx.doi.org/10.1108/IJSI-06-2014-0030" target="_blank" >10.1108/IJSI-06-2014-0030</a>
Alternativní jazyky
Jazyk výsledku
angličtina
Název v původním jazyce
Compression after impact and fatigue behaviour of CFRP stiffened panels
Popis výsledku v původním jazyce
Impact and fatigue are critical loading conditions for composite aerostructures. Compression behavior after impact and fatigue is a weak point for composite fuselage panels. The purpose of this paper is to characterize experimentally the compression behavior of carbon fiber reinforced plastic (CFRP) stiffened fuselage panels after impact and fatigue. The panels were tested using ultrasound inspection just after manufacturing to check material quality and between different tests to detect impact and fatigue damage accumulation. During tests the mechanical behavior of the panel was monitored using an optical displacement measurement system. Experimental results show that the presence of impact damage significantly degrades the compression behavior of thepanels. Moreover, the combined effect of BVID and fatigue was proven more severe than VID. The paper gives information about the compression after impact and fatigue behavior of CFRP fuselage stiffened panels, which represent the most re
Název v anglickém jazyce
Compression after impact and fatigue behaviour of CFRP stiffened panels
Popis výsledku anglicky
Impact and fatigue are critical loading conditions for composite aerostructures. Compression behavior after impact and fatigue is a weak point for composite fuselage panels. The purpose of this paper is to characterize experimentally the compression behavior of carbon fiber reinforced plastic (CFRP) stiffened fuselage panels after impact and fatigue. The panels were tested using ultrasound inspection just after manufacturing to check material quality and between different tests to detect impact and fatigue damage accumulation. During tests the mechanical behavior of the panel was monitored using an optical displacement measurement system. Experimental results show that the presence of impact damage significantly degrades the compression behavior of thepanels. Moreover, the combined effect of BVID and fatigue was proven more severe than VID. The paper gives information about the compression after impact and fatigue behavior of CFRP fuselage stiffened panels, which represent the most re
Klasifikace
Druh
J<sub>imp</sub> - Článek v periodiku v databázi Web of Science
CEP obor
—
OECD FORD obor
20304 - Aerospace engineering
Návaznosti výsledku
Projekt
—
Návaznosti
I - Institucionalni podpora na dlouhodoby koncepcni rozvoj vyzkumne organizace
Ostatní
Rok uplatnění
2015
Kód důvěrnosti údajů
S - Úplné a pravdivé údaje o projektu nepodléhají ochraně podle zvláštních právních předpisů
Údaje specifické pro druh výsledku
Název periodika
International Journal of Structural Integrity
ISSN
1757-9864
e-ISSN
1757-9872
Svazek periodika
6
Číslo periodika v rámci svazku
2
Stát vydavatele periodika
GB - Spojené království Velké Británie a Severního Irska
Počet stran výsledku
18
Strana od-do
176-193
Kód UT WoS článku
000214188800003
EID výsledku v databázi Scopus
2-s2.0-84928480400