Structural Overloading Evaluation Based on the Identification of Subcritical Crack Increments

Kód výsledku v IS VaVaI

<a href="https://www.isvavai.cz/riv?ss=detail&h=RIV%2F68407700%3A21340%2F15%3A00239170" target="_blank" >RIV/68407700:21340/15:00239170 - isvavai.cz</a>

Nalezeny alternativní kódy

RIV/00010669:_____/15:#0001911

Výsledek na webu

<a href="http://dx.doi.org/10.1016/j.engfailanal.2015.01.016" target="_blank" >http://dx.doi.org/10.1016/j.engfailanal.2015.01.016</a>

DOI - Digital Object Identifier

<a href="http://dx.doi.org/10.1016/j.engfailanal.2015.01.016" target="_blank" >10.1016/j.engfailanal.2015.01.016</a>

Jazyk výsledku

angličtina

Název v původním jazyce

Structural Overloading Evaluation Based on the Identification of Subcritical Crack Increments

Popis výsledku v původním jazyce

A complex approach using fractographic and FE analysis was used to assess the load level of a lower root spar assembly under conditions, which were close to the critical load of the structure.A Damage Tolerance scheme of determining the conditions for subcritical crack increments was used. The stress state for the measured subcritical increments in an airplane structure was determined using a proposed iterative solution to match the material R curve to the J-integral solution. A structural stress analysis of the root of the wing structure assigned a load level to the crack state identified above. The numerical FE solutions of the J-integral along the identified crack fronts were generated using ABAQUS SW at the Strength of Structures Dpt., Aerospace Research and Test Establishment.The analysis provides information regarding the near-critical loading condition of the wing structure.

Název v anglickém jazyce

Structural Overloading Evaluation Based on the Identification of Subcritical Crack Increments

Popis výsledku anglicky

A complex approach using fractographic and FE analysis was used to assess the load level of a lower root spar assembly under conditions, which were close to the critical load of the structure.A Damage Tolerance scheme of determining the conditions for subcritical crack increments was used. The stress state for the measured subcritical increments in an airplane structure was determined using a proposed iterative solution to match the material R curve to the J-integral solution. A structural stress analysis of the root of the wing structure assigned a load level to the crack state identified above. The numerical FE solutions of the J-integral along the identified crack fronts were generated using ABAQUS SW at the Strength of Structures Dpt., Aerospace Research and Test Establishment.The analysis provides information regarding the near-critical loading condition of the wing structure.

Druh

J_x - Nezařazeno - Článek v odborném periodiku (Jimp, Jsc a Jost)

CEP obor

JL - Únava materiálu a lomová mechanika

OECD FORD obor

—

Projekt

—

Návaznosti

I - Institucionalni podpora na dlouhodoby koncepcni rozvoj vyzkumne organizace

Rok uplatnění

2015

Kód důvěrnosti údajů

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

Název periodika

Engineering Failure Analysis

ISSN

1350-6307

e-ISSN

—

Svazek periodika

56

Číslo periodika v rámci svazku

—

Stát vydavatele periodika

NL - Nizozemsko

Počet stran výsledku

10

Strana od-do

265-274

Kód UT WoS článku

000361832300027

EID výsledku v databázi Scopus

2-s2.0-84941995383