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fatigue spectrum

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Published: 30 August 2021
Fig. 14 Plan view image of a pin fracture surface that failed by uniaxial bending fatigue. Spectrum loading led to episodic fatigue and overload fracture prior to ultimate separation. Subcritical overload fracture regions among the beach marks are indicated by arrows. More
Series: ASM Handbook Archive
Volume: 11
Publisher: ASM International
Published: 01 January 2002
DOI: 10.31399/asm.hb.v11.a0003516
EISBN: 978-1-62708-180-1
..., which employs the stress-life method of fatigue life assessment. The article examines the behavior of three different metallic materials used in the design and manufacture of structural components: steel, aluminum, and titanium. It also reviews the effects of retardation and spectrum load on component...
Series: ASM Handbook
Volume: 19
Publisher: ASM International
Published: 01 January 1996
DOI: 10.31399/asm.hb.v19.a0002396
EISBN: 978-1-62708-193-1
... and interpreting the influence of various microstructural features on material fatigue resistance. This article will first review general trends in cyclic response for representative commercial alloys to establish the spectrum of cyclic properties attainable through microstructural alteration. Individual alloy...
Series: ASM Handbook
Volume: 21
Publisher: ASM International
Published: 01 January 2001
DOI: 10.31399/asm.hb.v21.a0003445
EISBN: 978-1-62708-195-5
... not experience repeated loads that approach their ultimate loads, composite structures are not fatigue critical. Even if they were to experience loads near this threshold, or slightly above, there are so few of these high cycles in the spectrum life of the vehicle that no significant fatigue damage would occur...
Image
Published: 01 January 2001
Fig. 7 Typical load cycle response for constant amplitude versus spectrum-loading fatigue testing. R = 10.0 (compression-compression). More
Image
Published: 01 January 1996
Fig. 23 Schematic effect of yield strength (peak and overaged tempers) on fatigue crack growth rate under spectrum loading. Source: Ref 60 More
Image
Published: 01 January 1996
Fig. 17 Fatigue crack growth rates of alloys 7050-T76, A201-T7, and A357-T6 under spectrum loading conditions. From Ref 35 More
Series: ASM Handbook
Volume: 19
Publisher: ASM International
Published: 01 January 1996
DOI: 10.31399/asm.hb.v19.a0002356
EISBN: 978-1-62708-193-1
... with a discussion on the conditions associated with engineering applications of VA loading. crack growth crack initiation fatigue metallic material variable-amplitude load FATIGUE is a practical problem for all kinds of structures subjected to a spectrum of many load cycles under normal service...
Series: ASM Handbook
Volume: 21
Publisher: ASM International
Published: 01 January 2001
DOI: 10.31399/asm.hb.v21.a0003382
EISBN: 978-1-62708-195-5
... on unidirectional static and fatigue properties. MRLife allows selection of failure criteria, strength degradation functions, and stiffness degradation functions. The strength-based residual strength model has shown good predictive capability for spectrum fatigue loading ( Ref 18 ). It is considered as a good...
Series: ASM Handbook
Volume: 22A
Publisher: ASM International
Published: 01 December 2009
DOI: 10.31399/asm.hb.v22a.a0005419
EISBN: 978-1-62708-196-2
...(60)90013-2 21. Newman J.C. Jr. , Prediction of Fatigue Crack Growth under Amplitude and Spectrum Loading Using a Closure Model , Design of Fatigue and Fracture Resistant Structures , ASTM STP 761, American Society for Testing and Materials , Philadelphia, PA , 1982 , p 255 – 277...
Series: ASM Handbook
Volume: 19
Publisher: ASM International
Published: 01 January 1996
DOI: 10.31399/asm.hb.v19.a0002393
EISBN: 978-1-62708-193-1
... ksi (14 MPa) than at 4.0 ksi (28 MPa). The economic issue is most important when developing spectra to be used for full-scale fatigue testing. The highest loads in the spectrum should be those that occur once in one-tenth the projected life of the aircraft. Including higher loads can increase...
Series: ASM Handbook
Volume: 8
Publisher: ASM International
Published: 01 January 2000
DOI: 10.31399/asm.hb.v08.a0009217
EISBN: 978-1-62708-176-4
.... , A Crack Closure Model for Predicting Fatigue Crack Growth under Aircraft Spectrum Loading , in Methods and Models for Predicting Fatigue Crack Growth Under Random Loading , STP 748, ASTM , Philadelphia , 1981 36. Johnson W.S. , Multiparameter Yield Zone Model for Predicting Spectrum Crack...
Series: ASM Handbook
Volume: 21
Publisher: ASM International
Published: 01 January 2001
DOI: 10.31399/asm.hb.v21.a0003386
EISBN: 978-1-62708-195-5
... tolerance single circular delamination: 50 mm (2 in.) in diameter. This tolerance limit is also applicable to all fracture critical structures. Residual strength requirement: The structure must carry maximum spectrum load after two lifetimes of fatigue loading under the critical environmental...
Series: ASM Handbook
Volume: 2B
Publisher: ASM International
Published: 15 June 2019
DOI: 10.31399/asm.hb.v02b.a0006617
EISBN: 978-1-62708-210-5
...) T-L 40 (36) … (a) K app from 400 mm (16-in.) wide panel Fig. 1 Plane stress R -curves of 2624 compared with 2024-T351 and 2324-T39 Fig. 2 Fatigue crack growth resistance of 2624 compared with 2024-T351 and 2324-T39 Fig. 3 Spectrum fatigue crack growth...
Series: ASM Handbook
Volume: 2B
Publisher: ASM International
Published: 15 June 2019
DOI: 10.31399/asm.hb.v02b.a0006612
EISBN: 978-1-62708-210-5
.... In addition, alloy 2297-T87 exhibited significant improvements in standard fatigue and fatigue crack growth tests. The spectrum fatigue performance was especially improved compared with 2124-T851 ( Fig. 1 ). Alloy 2397, introduced in 2003, is identical in the main alloying elements in alloy 2297, except...
Series: ASM Handbook
Volume: 19
Publisher: ASM International
Published: 01 January 1996
DOI: 10.31399/asm.hb.v19.a0002394
EISBN: 978-1-62708-193-1
... in the airframe of the C-5A aircraft, which was designed using stress analysis and fatigue as the primary design tools. Fracture mechanics was used as a tool to determine the extent of these problems and to define “a fix” for them. During the 1970s and 1980s, the U.S. Air Force established and evaluated a set...
Series: ASM Handbook
Volume: 19
Publisher: ASM International
Published: 01 January 1996
DOI: 10.31399/asm.hb.v19.a0002407
EISBN: 978-1-62708-193-1
... et al. ( Ref 6 ) performed weld repair on a precracked open-hole fatigue specimen to observe crack growth behavior in the weld. Prior to welding, the specimen was subjected to two lifetimes of a modified F-18 lower wing root spectrum. The resulting 0.09 in. crack was welded, the hole was reamed...
Series: ASM Handbook
Volume: 13A
Publisher: ASM International
Published: 01 January 2003
DOI: 10.31399/asm.hb.v13a.a0003706
EISBN: 978-1-62708-182-5
... to a design usage spectrum. This usage spectrum is often based on a critical usage point, resulting in a lower bound limit on fatigue life for analysis and testing. Typically, the structure is considered to have consumed its service life and is replaced when this fatigue life limit is reached...
Series: ASM Handbook
Volume: 19
Publisher: ASM International
Published: 01 January 1996
DOI: 10.31399/asm.hb.v19.9781627081931
EISBN: 978-1-62708-193-1
Series: ASM Handbook
Volume: 13A
Publisher: ASM International
Published: 01 January 2003
DOI: 10.31399/asm.hb.v13a.a0003714
EISBN: 978-1-62708-182-5
... activities and are classified here as “broad spectrum.” Included in their activities are standards that address corrosion and related topics. The second are more focused organizations that address a particular constituency or interest group—such as TAPPI, which is concerned with the pulp and paper industry...