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

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DOIResolve DOI: http://doi.org/10.1177/0954410011423466
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TypeArticle
Journal titleProceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering
ISSN0954-4100
Volume226
Issue11
Pages14121423; # of pages: 12
SubjectAircraft 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
AbstractThis 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.
Publication date
LanguageEnglish
AffiliationNRC Institute for Aerospace Research; National Research Council Canada
Peer reviewedYes
NPARC number21269388
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Record identifier868ea515-528c-4b22-b0b7-13cda7fe5613
Record created2013-12-12
Record modified2016-05-09
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