Fatigue behavior and damage tolerant design of bonded joints for aerospace application on Fiber Metal Laminates and composites
Identifikátory výsledku
Kód výsledku v IS VaVaI
<a href="https://www.isvavai.cz/riv?ss=detail&h=RIV%2F00010669%3A_____%2F17%3AN0000122" target="_blank" >RIV/00010669:_____/17:N0000122 - isvavai.cz</a>
Výsledek na webu
<a href="http://calvinrans.com/wp-content/uploads/2017/06/ICAF2017-paper1.pdf" target="_blank" >http://calvinrans.com/wp-content/uploads/2017/06/ICAF2017-paper1.pdf</a>
DOI - Digital Object Identifier
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Alternativní jazyky
Jazyk výsledku
angličtina
Název v původním jazyce
Fatigue behavior and damage tolerant design of bonded joints for aerospace application on Fiber Metal Laminates and composites
Popis výsledku v původním jazyce
Today, the application of adhesive bonding technology for primary aerospace structures is limited due to the certification regulations. State of the art is the widely used “chicken rivet” as crack arrestor which is limiting the benefits of bonding technology, particularly in composite bonded joints. In this paper results from fatigue testing of novel design approaches for damage tolerant high load transfer (HLT) joints as e.g. Panel Joints or large bonded repairs will be discussed for CFRP and for Fiber Metal Laminates´(FML) dherents. Results from fatigue testing with Wide Single Lapshear (WSLS) specimen will be presented for different configurations to proof the crack stopping behavior of sate of the art fasteners as reference crack arrestor concept.
Název v anglickém jazyce
Fatigue behavior and damage tolerant design of bonded joints for aerospace application on Fiber Metal Laminates and composites
Popis výsledku anglicky
Today, the application of adhesive bonding technology for primary aerospace structures is limited due to the certification regulations. State of the art is the widely used “chicken rivet” as crack arrestor which is limiting the benefits of bonding technology, particularly in composite bonded joints. In this paper results from fatigue testing of novel design approaches for damage tolerant high load transfer (HLT) joints as e.g. Panel Joints or large bonded repairs will be discussed for CFRP and for Fiber Metal Laminates´(FML) dherents. Results from fatigue testing with Wide Single Lapshear (WSLS) specimen will be presented for different configurations to proof the crack stopping behavior of sate of the art fasteners as reference crack arrestor concept.
Klasifikace
Druh
O - Ostatní výsledky
CEP obor
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OECD FORD obor
20501 - Materials engineering
Návaznosti výsledku
Projekt
<a href="/cs/project/7E13058" target="_blank" >7E13058: Boltless assembling Of Primary Aerospace Composite Structures</a><br>
Návaznosti
P - Projekt vyzkumu a vyvoje financovany z verejnych zdroju (s odkazem do CEP)
Ostatní
Rok uplatnění
2017
Kód důvěrnosti údajů
S - Úplné a pravdivé údaje o projektu nepodléhají ochraně podle zvláštních právních předpisů