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" Fatigue crack growth failure and Lifing analyses for metallic aircraft structures and components / "
Russell Wanhill, Simon Barter, Loris Molent.
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BL
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| Record Number
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888214
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| Main Entry
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Wanhill, R. J. H.
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| Title & Author
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Fatigue crack growth failure and Lifing analyses for metallic aircraft structures and components /\ Russell Wanhill, Simon Barter, Loris Molent.
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| Publication Statement
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Dordrecht, Netherlands :: Springer,, 2019.
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| Series Statement
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SpringerBriefs in applied sciences and technology,
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| Page. NO
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1 online resource (xi, 99 pages) :: illustrations (some color)
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| ISBN
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9402416757
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: 9789402416756
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9789402416732
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Includes bibliographical references.
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| Contents
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Intro; Preface; Contents; Abstract; 1 Historical Review; 1.1 FCG Parameters, Concepts and Testing; 1.2 FCG 'Laws' and Models; 1.2.1 Long Crack Growth 'Laws'; 1.2.2 Long Crack Growth Models: LEFM Analyses; 1.2.3 Characteristic K Approaches; 1.2.4 The Effective Block Approach (EBA) Framework; 1.2.5 Exponential FCG Behaviour; 1.3 Summary; 2 Basic Information for Aircraft FCG Failure and Lifing Analyses; 2.1 Importance of Fatigue for Aircraft Structural Failures; 2.2 Fatigue Crack Nucleation, Discontinuities, Early FCG and Damage Tolerance
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2.2.1 Fatigue-Nucleating Discontinuities in Aircraft Structures2.2.2 Early FCG and Damage Tolerance; 2.3 Summary of FCG Lifing Methods; 3 Quantitative Fractography (QF) for FCG Analyses; 3.1 Introduction; 3.2 Fatigue Striation FCG Analyses; 3.3 Progression Marking FCG Analyses; 3.4 Fatigue-Nucleating Discontinuities and Equivalent Pre-crack Sizes (EPS); 3.4.1 Defining the Initial Crack Sizes for FCG Analyses; 3.5 QF Techniques for Fatigue Fracture Surfaces; 3.5.1 Optical Fractography; 3.5.2 Electron Fractography and Optical Fractography; 3.6 A Cautionary Note
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4 Aermacchi MB-326H Wing Spar (1990): Exponential FCG Analysis4.1 Introduction; 4.2 FCG Analysis for the Failed Spar; 4.3 Further Examination of Wing Spars; 4.3.1 Safe Life Reassessment; 4.3.2 Fleet Recovery Programme; 4.4 Lessons Learned; 5 P & W 125B Engine Bearing (1994): 2-Stage Exponential FCG Analysis; 5.1 Introduction; 5.2 The Failed No. 3 Bearing: Macroscopic and Metallographic Examination; 5.3 Cage Failure and FCG Analysis; 5.3.1 Progression Marking QF Analysis; 5.4 Interpretation of the Results and Remedial Action
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6 EBA Example Lifing Assessment (2004): F/A-18 Horizontal Stabilator Spindles6.1 Introduction; 6.2 EBA Validation for the F/A-18 Horizontal Stabilator Spindles; 6.3 EBA and Total Life Assessment for the F/A-18 Horizontal Stabilator Spindles; 7 LCFLF Example Lifing Assessment (2004): F/A-18 Vertical Tail Attachment Stubs; 7.1 Introduction; 7.2 The FT46 Stub Flange Crack; 7.3 Fractography of the FT46 Stub Flange Crack; 7.4 LCFLF Life Assessment for the FT46 Stub Flange Crack; 8 Cubic Rule Life Prediction Examples; 8.1 Introduction; 8.2 McDonnell Douglas F4E Spectrum Coupon Test Data
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8.3 Lockheed Martin P3C Spectrum Coupon Test Data8.4 Summary; 9 Fokker 100 Fuselage Test: Lap Joints Exponential FCG Analysis; 9.1 Introduction; 9.2 FCG Analysis of the Cracked Lap Splice [71, 72, 95]; 10 Sikorsky S-61N Rotor Blade (1974): Exponential FCGR Analysis; 10.1 Introduction; 10.2 FCG Analysis for the Crashed Helicopter; 10.2.1 Prediction of Detectable FCG Lives; 10.3 Results and Remedial Actions (Lessons Learned); 11 Westland Lynx Rotor Hub (1998): Progression Marking LEFM Analysis; 11.1 Introduction; 11.2 Fractography of Early Fatigue Cracking in the M326 'Yellow' Arm
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| Abstract
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This book provides a concise discussion of fatigue crack growth (FCG) failure and lifing analysis methods for metallic aircraft structures and components. After a reasonably concise historical review, surveys are made of (i) the importance of fatigue for aircraft structural failures and the sources of fatigue nucleation and cracking, (ii) contemporary FCG lifing methods, and (iii) the Quantitative Fractography (QF) required for determining the actual FCG behaviour. These surveys are followed by the main part of the book, which is a discussion, using case histories, of the applicabilities of Linear Elastic Fracture Mechanics (LEFM) and non-LEFM methods for analysing service fatigue failures and full- and sub-scale test results. This discussion is derived primarily from the experiences of the Defence Science and Technology Group in Melbourne, Australia, and the Netherlands Aerospace Centre, Marknesse, the Netherlands.
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| Subject
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Fracture mechanics.
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Materials-- Fatigue.
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Fracture mechanics.
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Materials-- Fatigue.
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| Dewey Classification
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620.1/126
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| LC Classification
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TA418.38
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| Added Entry
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Barter, Simon
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Molent, Loris
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