Probabilistic Method to predict Remaining Usage Life of Aircraft Structures

Kód výsledku v IS VaVaI

<a href="https://www.isvavai.cz/riv?ss=detail&h=RIV%2F27617793%3A_____%2F16%3AN0000004" target="_blank" >RIV/27617793:_____/16:N0000004 - isvavai.cz</a>

Výsledek na webu

<a href="https://www.phmsociety.org/sites/phmsociety.org/files/phm_submission/2016/phmec_16_044.pdf" target="_blank" >https://www.phmsociety.org/sites/phmsociety.org/files/phm_submission/2016/phmec_16_044.pdf</a>

DOI - Digital Object Identifier

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Jazyk výsledku

angličtina

Název v původním jazyce

Probabilistic Method to predict Remaining Usage Life of Aircraft Structures

Popis výsledku v původním jazyce

The 3rd European Conference of the Prognostics and Health Management Society 2016, Bilbao, Spain, July, 2016. This paper presents a probabilistic method for RUL prediction. A hybrid approach is used, comprising of two different algorithms. The first algorithm adopts fracture mechanics based fatigue crack growth model. This approach uses physics of failure to predict the crack growth curve and underlying degradation process. It calculates the accurate value of Stress Intensity Factor (SIF) to calculate the crack growth curve. The second algorithm is a mathematical model which quantify various sources of uncertainty such as future loading, crack length, model parameters etc. The process described in this paper results in enhanced remaining usage life estimation by compensating for the aforementioned modeling uncertainties. The model results were verified and validated on a typical aero structure with experimental, FEA simulation and fractography data.

Název v anglickém jazyce

Probabilistic Method to predict Remaining Usage Life of Aircraft Structures

Popis výsledku anglicky

The 3rd European Conference of the Prognostics and Health Management Society 2016, Bilbao, Spain, July, 2016. This paper presents a probabilistic method for RUL prediction. A hybrid approach is used, comprising of two different algorithms. The first algorithm adopts fracture mechanics based fatigue crack growth model. This approach uses physics of failure to predict the crack growth curve and underlying degradation process. It calculates the accurate value of Stress Intensity Factor (SIF) to calculate the crack growth curve. The second algorithm is a mathematical model which quantify various sources of uncertainty such as future loading, crack length, model parameters etc. The process described in this paper results in enhanced remaining usage life estimation by compensating for the aforementioned modeling uncertainties. The model results were verified and validated on a typical aero structure with experimental, FEA simulation and fractography data.

Druh

O - Ostatní výsledky

CEP obor

JU - Aeronautika, aerodynamika, letadla

OECD FORD obor

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Projekt

<a href="/cs/project/TA03010140" target="_blank" >TA03010140: Integrace SHM do systému zajištění pokračující letové způsobilosti malého dopravního letounu</a><br>

Návaznosti

P - Projekt vyzkumu a vyvoje financovany z verejnych zdroju (s odkazem do CEP)

Rok uplatnění

2016

Kód důvěrnosti údajů

C - Předmět řešení projektu podléhá obchodnímu tajemství (§ 504 Občanského zákoníku), ale název projektu, cíle projektu a u ukončeného nebo zastaveného projektu zhodnocení výsledku řešení projektu (údaje P03, P04, P15, P19, P29, PN8) dodané do CEP, jsou upraveny tak, aby byly zveřejnitelné.