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Advanced damage tolerance and risk analysis methodologies and tools for aircraft structures containing multiple-site and multiple-element fatigue damages

Par Conseil national de recherches du Canada

DOITrouver le DOI : https://doi.org/10.1177/0954410011423466
AuteurRechercher : 1; Rechercher : 1; Rechercher : 1; Rechercher : 1
Affiliation
  1. Conseil national de recherches du Canada. Institut de recherche aérospatiale du CNRC
FormatTexte, Article
SujetAircraft structure; Canadian forces; Closed form solutions; Crack growth analysis; Crack size distribution; Critical location; Damage tolerance analysis; DTA methods; FE model; Finite elements; Flight hour; Inspection intervals; Life-cycle management; Load redistribution; Monte Carlo Simulation; Monte carlo simulation technique; Multiple crack; multiple-element damage; National Research Council; Probabilistic damage tolerance analysis; Probability of failure; Residual strength; Structural configurations; Wing structures; Aircraft manufacture; Airframes; Cracks; Fatigue damage; Finite element method; Fits and tolerances; Monte Carlo methods; Risk analysis; Damage tolerance
Résumé
This article presents the results obtained from the development of advanced damage tolerance analysis (DTA) and risk analysis methodologies and tools for aircraft structures, including build-up structures containing multiple-site fatigue damage (MSD) and multiple-element damage, to support the Canadian Forces aircraft structural life cycle management. The DTA methods developed include new closed-form solutions and generic finite element (FE) based tools to calculate the stress intensity factors and the β-solutions for build-up structural configurations. To facilitate the risk assessment, an in-house crack growth analysis program, CanGROW, was developed to simultaneously grow multiple cracks. Guidelines were established to calculate the residual strength of structures with MSD and multiple-element damage using global and/or local FE models, considering load redistribution among adjacent components. For the MSD risk analysis, an efficient Monte Carlo simulation technique was developed to determine the crack size distributions at different inspection intervals, which were then used in National Research Council Canada's risk analysis code probabilistic damage tolerance analysis to calculate the single flight hour probability of failure. Case studies on critical locations of the CC-130 centre wing structure are presented to demonstrate the capability of the developed methods and tools.
Date de publication
Dans
  • Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering 226, nº 11 (1 novembre 2011) : 1412–1423.
Langueanglais
Publications évaluées par des pairsOui
Numéro NPARC21269388
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Identificateur de l’enregistrement868ea515-528c-4b22-b0b7-13cda7fe5613
Enregistrement créé2013-12-12
Enregistrement modifié2020-04-21
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