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020			_a9789402416756
024	7		_a10.1007/978-94-024-1675-6 _2doi
040			_bspa _dES-MaUEC _cES-MaUEC
050		4	_aTA418.38 _b2019 EB
100	1		_aWanhill, R. J. H. _eautor _9670801
245	1	0	_aFatigue Crack Growth Failure and Lifing Analyses for Metallic Aircraft Structures and Components _cby Russell Wanhill, Simon Barter, Loris Molent
264		1	_aDordrecht _bSpringer _c2019
300			_a1 recurso en línea (XI, 99 páginas) _b50 ilustraciones, 47 ilustraciones a color
336			_2rdacontent _aTexto _btxt
337			_2rdamedia _aelectrónico _bc
338			_2rdacarrier _arecurso electrónico _bcr
347			_atext file _bPDF
490	0		_aEngineering (Springer-11647)
490	0		_aSpringerBriefs in Applied Sciences and Technology _x2191-530X
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	3		_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		7	_2embne _aMecánica de fractura _9144222
650		7	_2embne _9169426 _aMateriales _xFatiga
653		7	_aAstronautics.
653		7	_aMechanics, Applied.
653		7	_aMechanics.
700	1		_aBarter, Simon _eautor _9670802
700	1		_aMolent, Loris _eautor _9670803
776	0	8	_iPrinted edition: _z9789402416732
776	0	8	_iPrinted edition: _z9789402416749
856	4	0	_uhttps://go.openathens.net/redirector/universidadeuropea.es?url=https://doi.org/10.1007/978-94-024-1675-6 _zAcceso a este recurso digital (usuarios Universidad Europea de Madrid)
942			_2lcc _cLE
988			_aPrimersemestre_2019_Engineering
998			_aSI _cm _dz _feng _ggw _h0 _b09/2019 _eu _zSI