Computer-Controlled Decreasing Stress Intensity Technique for Low Rate Fatigue Crack Growth Testing

DOI PDF 被引用文献1件
  • A Saxena
    Westinghouse Research Laboratories 1 Senior engineers , , 1310 Beulah Rd., Pittsburgh, Pa.15235 . Members of ASTM .
  • SJ Hudak
    Westinghouse Research Laboratories 1 Senior engineers , , 1310 Beulah Rd., Pittsburgh, Pa.15235 . Members of ASTM .
  • JK Donald
    Del Research Division, PSC-Professional Services Group, Inc. 2 Vice-president and staff engineer , , 427 Main St., Hellertown, Pa.18055 . Mr. Donald is a member of ASTM .
  • DW Schmidt
    Del Research Division, PSC-Professional Services Group, Inc. 2 Vice-president and staff engineer , , 427 Main St., Hellertown, Pa.18055 . Mr. Donald is a member of ASTM .

書誌事項

公開日
1978-05-01
DOI
  • 10.1520/jte10938j
公開者
ASTM International

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説明

<jats:title>Abstract</jats:title> <jats:p>An automated test system utilizing computer control was developed to obtain crack growth rate data down to the fatigue crack growth threshold with a decreasing stress intensity technique and compact type specimens. The starting stress intensity range ΔK0 was chosen to yield crack growth rates in the range of 2.54 × 10−8 m/cycle (10−6 in./cycle) and subsequent values of ΔK are controlled to the equation ΔK = ΔK0 exp [C(a − a0)] (a0 and a are the initial and instantaneous crack lengths and C is a test variable). Crack length is continuously monitored by using the elastic compliance technique, thereby enabling ΔK to be decreased continuously. Comparison crack growth data were also obtained by the more conventional constant load amplitude or K-increasing method. Excellent agreement was observed between data obtained from the two procedures for a Society of Automotive Engineers 1045 steel at load ratios R of 0.1 and 0.5, an A356-T6 sand-cast aluminum alloy at load ratios of 0.1 and 0.8, and a 2219-T851 aluminum alloy at a load ratio of 0.1.</jats:p>

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