000 05884nam a22006015i 4500
001 978-94-024-1675-6
003 DE-He213
005 20220801214057.0
007 cr nn 008mamaa
008 190219s2019 ne | s |||| 0|eng d
020 _a9789402416756
_9978-94-024-1675-6
024 7 _a10.1007/978-94-024-1675-6
_2doi
050 4 _aTL1-4050
072 7 _aTRP
_2bicssc
072 7 _aTTDS
_2bicssc
072 7 _aTEC002000
_2bisacsh
072 7 _aTRP
_2thema
072 7 _aTTDS
_2thema
082 0 4 _a629.1
_223
100 1 _aWanhill, Russell.
_eauthor.
_4aut
_4http://id.loc.gov/vocabulary/relators/aut
_936151
245 1 0 _aFatigue Crack Growth Failure and Lifing Analyses for Metallic Aircraft Structures and Components
_h[electronic resource] /
_cby Russell Wanhill, Simon Barter, Loris Molent.
250 _a1st ed. 2019.
264 1 _aDordrecht :
_bSpringer Netherlands :
_bImprint: Springer,
_c2019.
300 _aXI, 99 p. 50 illus., 47 illus. in color.
_bonline resource.
336 _atext
_btxt
_2rdacontent
337 _acomputer
_bc
_2rdamedia
338 _aonline resource
_bcr
_2rdacarrier
347 _atext file
_bPDF
_2rda
490 1 _aSpringerBriefs in Applied Sciences and Technology,
_x2191-5318
505 0 _a1 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 _aThis 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.
650 0 _aAerospace engineering.
_96033
650 0 _aAstronautics.
_936152
650 0 _aMechanics, Applied.
_93253
650 0 _aSolids.
_93750
650 0 _aBuilding materials.
_931878
650 1 4 _aAerospace Technology and Astronautics.
_936153
650 2 4 _aSolid Mechanics.
_931612
650 2 4 _aStructural Materials.
_931883
700 1 _aBarter, Simon.
_eauthor.
_4aut
_4http://id.loc.gov/vocabulary/relators/aut
_936154
700 1 _aMolent, Loris.
_eauthor.
_4aut
_4http://id.loc.gov/vocabulary/relators/aut
_936155
710 2 _aSpringerLink (Online service)
_936156
773 0 _tSpringer Nature eBook
776 0 8 _iPrinted edition:
_z9789402416732
776 0 8 _iPrinted edition:
_z9789402416749
830 0 _aSpringerBriefs in Applied Sciences and Technology,
_x2191-5318
_936157
856 4 0 _uhttps://doi.org/10.1007/978-94-024-1675-6
912 _aZDB-2-ENG
912 _aZDB-2-SXE
942 _cEBK
999 _c75931
_d75931