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Title
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Exploratory Investigation of Rapid Crack Propagation and Crack Arrest
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Date
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1973
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Index Abstract
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Not Available
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Photo Quality
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Complete
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Report Number
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AFFDL TR 73-95
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Corporate Author
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Boeing Aersopace Company
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Laboratory
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Air Force Flight Dynamics Laboratory
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Extent
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102
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Identifier
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AD0778822
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Access Rights
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Approved for public release; distribution unlimited
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Distribution Classification
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1
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Contract
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F33615-72-C-1063
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DoD Project
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None Given
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DoD Task
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None Given
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DTIC Record Exists
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No
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Distribution Change Authority Correspondence
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None
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Distribution Conflict
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No
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Abstract
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This experimental program was undertaken to study and investigate the effects of crack velocity and maetrial parameters on the crack characteristics of aircraft structural alloys. Materials tested included 2219-T851 and 7075-T6 Aluminum, 6Al-4V beta-annealed Titanium, 9Ni-4Co-0.2C and 4340 steel alloys. Tests were conducted with radially flared and uniform height DCB (Double Cantiler Beam) specimens containing either sharp cracks or notches with finite root radii. The specimens were instrumented to measure crack velocity, crack length, crack opening displacement, instantaneous load, strain and crack lengths and the stress intensity factors at the initiation and the arrest of the crack propagation. An instrumentation system for the measurement of crack velocities from zero to several thousands of feet per second is presented. Experimental results are presented and are evaluated with fracture mechanics parameters. The test results indicate that a cracked DCB specimen of any configuration under static loading is not suitable for investigating the dynamic behavior of rapidly running cracks or crack arrest conditions. Recommendations for suitable test specimens are provided.
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Report Availability
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Full text available
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Date Issued
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1973-08
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Provenance
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Bombardier/Aero
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Type
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report
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Format
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1 online resource
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Creator
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Shah, R. C.
AFFDLTR73-095.pdf