Fatigue Life Enhancement of a D16at Aluminum Alloy for Aircraft Components with Fastener Holes

Kód výsledku v IS VaVaI

<a href="https://www.isvavai.cz/riv?ss=detail&h=RIV%2F68407700%3A21340%2F20%3A00345005" target="_blank" >RIV/68407700:21340/20:00345005 - isvavai.cz</a>

Výsledek na webu

<a href="https://doi.org/10.1007/s11223-020-00144-3" target="_blank" >https://doi.org/10.1007/s11223-020-00144-3</a>

DOI - Digital Object Identifier

<a href="http://dx.doi.org/10.1007/s11223-020-00144-3" target="_blank" >10.1007/s11223-020-00144-3</a>

Jazyk výsledku

angličtina

Název v původním jazyce

Fatigue Life Enhancement of a D16at Aluminum Alloy for Aircraft Components with Fastener Holes

Popis výsledku v původním jazyce

D16AT aircraft Al-alloy was evaluated. The friction stir hole expansion (FSHE), solid mandrel cold working and symmetric cold expansion (SCE) methods were compared. The results are summarized on the basis of fatigue tests, S–N curves, X-ray diffraction, and microstructural analysis. Under the high-cycle fatigue, SCE provides more than 66 times longer fatigue life as compared to the solid mandrel method and more than 82 times greater fatigue life in comparison with the FSHE method. Through X-ray diffraction analysis it was found that the higher efficiency of the SCE method was due to symmetric distribution (with respect to the plate middle plane) of residual hoop stresses around the hole. On the other hand, the solid mandrel cold working method causes a significant gradient of the residual stress distribution through the plate thickness, which is a precondition for nucleation and propagation of corner fatigue cracks. The FSHE method efficiency was established to be primarily dependent on generated heat and equivalent plastic strains. The combination of these factors determines the beneficial microeffect of the microstructure modifying in the vicinity of the hole and a useful macroeffect due to residual compressive stresses. It was concluded that SCE method should be used for prestressing of fastener holes in the most loaded components in D16AT aircraft structures – wings and fuselage, while the FSHE one can be applied to processing of fastener holes in less loaded aircraft components.

Název v anglickém jazyce

Fatigue Life Enhancement of a D16at Aluminum Alloy for Aircraft Components with Fastener Holes

Popis výsledku anglicky

D16AT aircraft Al-alloy was evaluated. The friction stir hole expansion (FSHE), solid mandrel cold working and symmetric cold expansion (SCE) methods were compared. The results are summarized on the basis of fatigue tests, S–N curves, X-ray diffraction, and microstructural analysis. Under the high-cycle fatigue, SCE provides more than 66 times longer fatigue life as compared to the solid mandrel method and more than 82 times greater fatigue life in comparison with the FSHE method. Through X-ray diffraction analysis it was found that the higher efficiency of the SCE method was due to symmetric distribution (with respect to the plate middle plane) of residual hoop stresses around the hole. On the other hand, the solid mandrel cold working method causes a significant gradient of the residual stress distribution through the plate thickness, which is a precondition for nucleation and propagation of corner fatigue cracks. The FSHE method efficiency was established to be primarily dependent on generated heat and equivalent plastic strains. The combination of these factors determines the beneficial microeffect of the microstructure modifying in the vicinity of the hole and a useful macroeffect due to residual compressive stresses. It was concluded that SCE method should be used for prestressing of fastener holes in the most loaded components in D16AT aircraft structures – wings and fuselage, while the FSHE one can be applied to processing of fastener holes in less loaded aircraft components.

Druh

J_imp - Článek v periodiku v databázi Web of Science

CEP obor

—

OECD FORD obor

20501 - Materials engineering

Projekt

—

Návaznosti

I - Institucionalni podpora na dlouhodoby koncepcni rozvoj vyzkumne organizace

Rok uplatnění

2020

Kód důvěrnosti údajů

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

Název periodika

Strength of Materials

ISSN

0039-2316

e-ISSN

1573-9325

Svazek periodika

52

Číslo periodika v rámci svazku

1

Stát vydavatele periodika

US - Spojené státy americké

Počet stran výsledku

15

Strana od-do

1-15

Kód UT WoS článku

000528074600001

EID výsledku v databázi Scopus

2-s2.0-85084061699