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Fatigue Crack Growth Failure and Lifing Analyses for Metallic Aircraft Structures and Components (Record no. 75931)

000 -LEADER
fixed length control field 05884nam a22006015i 4500
001 - CONTROL NUMBER
control field 978-94-024-1675-6
005 - DATE AND TIME OF LATEST TRANSACTION
control field 20220801214057.0
008 - FIXED-LENGTH DATA ELEMENTS--GENERAL INFORMATION
fixed length control field 190219s2019 ne | s |||| 0|eng d
020 ## - INTERNATIONAL STANDARD BOOK NUMBER
ISBN 9789402416756
-- 978-94-024-1675-6
082 04 - CLASSIFICATION NUMBER
Call Number 629.1
100 1# - AUTHOR NAME
Author Wanhill, Russell.
245 10 - TITLE STATEMENT
Title Fatigue Crack Growth Failure and Lifing Analyses for Metallic Aircraft Structures and Components
250 ## - EDITION STATEMENT
Edition statement 1st ed. 2019.
300 ## - PHYSICAL DESCRIPTION
Number of Pages XI, 99 p. 50 illus., 47 illus. in color.
490 1# - SERIES STATEMENT
Series statement SpringerBriefs in Applied Sciences and Technology,
505 0# - FORMATTED CONTENTS NOTE
Remark 2 1 Historical Review -- 1.1 FCG Parameters, Concepts and Testing -- 1.2 FCG ‘Laws’ and Models -- 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 -- 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) -- 3.5 QF Techniques for Fatigue Fracture Surfaces -- 3.6 A Cautionary Note -- 4 Aermacchi MB-326H Wing Spar (1990): Exponential FCG Analysis -- 4.1 Introduction -- 4.2 FCG Analysis for the Failed Spar -- 4.3 Further Examination of Wing Spars -- 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 -- 5.4 Interpretation of the Results, Conclusions, and Remedial Action -- 6. EBA Example Lifing Assessment (2004): F/A-18 Horizontal StabilatorSpindles -- 6.1 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 -- 8.3 Lockheed Martin P3C Spectrum Coupon Test Data -- 8.4 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 -- 10.3 Prediction of Detectable FCG Lives -- 10.4 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 -- 11.3 Fractography of Early Fatigue Cracking in the M6 Arm and M326Specimens -- 11.4 FRTB + LEFM Estimations of Damaging Service Fatigue Stress Levels -- 11.5 Measurements of Service Loads and Fatigue Analysis by GKNW -- 11.6 Causes of Failure and Remedial Action -- 12. Closing Remarks -- References.
520 ## - SUMMARY, ETC.
Summary, etc 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.
700 1# - AUTHOR 2
Author 2 Barter, Simon.
700 1# - AUTHOR 2
Author 2 Molent, Loris.
856 40 - ELECTRONIC LOCATION AND ACCESS
Uniform Resource Identifier https://doi.org/10.1007/978-94-024-1675-6
942 ## - ADDED ENTRY ELEMENTS (KOHA)
Koha item type eBooks
264 #1 -
-- Dordrecht :
-- Springer Netherlands :
-- Imprint: Springer,
-- 2019.
336 ## -
-- text
-- txt
-- rdacontent
337 ## -
-- computer
-- c
-- rdamedia
338 ## -
-- online resource
-- cr
-- rdacarrier
347 ## -
-- text file
-- PDF
-- rda
650 #0 - SUBJECT ADDED ENTRY--SUBJECT 1
-- Aerospace engineering.
650 #0 - SUBJECT ADDED ENTRY--SUBJECT 1
-- Astronautics.
650 #0 - SUBJECT ADDED ENTRY--SUBJECT 1
-- Mechanics, Applied.
650 #0 - SUBJECT ADDED ENTRY--SUBJECT 1
-- Solids.
650 #0 - SUBJECT ADDED ENTRY--SUBJECT 1
-- Building materials.
650 14 - SUBJECT ADDED ENTRY--SUBJECT 1
-- Aerospace Technology and Astronautics.
650 24 - SUBJECT ADDED ENTRY--SUBJECT 1
-- Solid Mechanics.
650 24 - SUBJECT ADDED ENTRY--SUBJECT 1
-- Structural Materials.
830 #0 - SERIES ADDED ENTRY--UNIFORM TITLE
-- 2191-5318
912 ## -
-- ZDB-2-ENG
912 ## -
-- ZDB-2-SXE

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