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Effects of proof loads and combined mode loadings on fracture and flaw growth characteristics of aerospace alloysThis experimental program was undertaken to determine the effects of (1) combined tensile and bending loadings, (2) combined tensile and shear loadings, and (3) proof overloads on fracture and flaw growth characteristics of aerospace alloys. Tests were performed on four alloys: 2219-T87 aluminum, 5Al-2.5Sn (ELl) titanium, 6Al-4V beta STA titanium and high strength 4340 steel. Tests were conducted in room air, gaseous nitrogen at -200F (144K), liquid nitrogen and liquid hydrogen. Flat center cracked and surface flawed specimens, cracked tube specimens, circumferentially notched round bar and surface flawed cylindrical specimens were tested. The three-dimensional photoelastic technique of stress freezing and slicing was used to determine stress intensity factors for surface flawed cylindrical specimens subjected to tension or torsion. Results showed that proof load/temperature histories used in the tests have a small beneficial effect or no effect on subsequent fracture strength and flaw growth rates.
Document ID
19740024241
Acquisition Source
Legacy CDMS
Document Type
Contractor Report (CR)
Authors
Shah, R. C. (Boeing Aerospace Co. Seattle, WA, United States)
Date Acquired
September 3, 2013
Publication Date
March 1, 1974
Subject Category
Structural Mechanics
Report/Patent Number
NASA-CR-134611
D180-17997-1
Accession Number
74N32354
Funding Number(s)
CONTRACT_GRANT: NAS3-14346
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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