A large portion of the fatigue crack growth threshold data in this report is inappropriate due to the load reduction test procedure that was used to generate these data. The author, in collaboration with National Aeronautics and Space Administration (NASA) Langley Research Center (LaRC) personnel, is developing new test procedures to generate threshold data under steady-state constant-amplitude loading conditions without any load history effects. The new test method involves using compression precracking to generate a crack at a V-notch and then to test the specimen under constant-amplitude loading. A large test program on the development of these fatigue crack growth databases, for use in damage-tolerant analyses for aircraft propellers and rotorcraft components, was conducted at NASA LaRC under a Memorandum of Agreement with the Federal Aviation Administration (FAA). Some materials tested and analyzed herein were 7050-T7451 and 7075-T7351 aluminum alloys and D6AC and 4340 steels. Only the steels were tested as part of the FAA program. The 7075 alloy was tested at the NASA Johnson Space Center, and the 7050 and 7075 alloys were tested at NASA LaRC. This test program was conducted to generate more accurate representations of fatigue crack growth rate behavior in the near-threshold regime and approaching fracture under a wide range of constant stress ratio. The objective of the proposed research grant was to analyze the test data on selected propeller and rotorcraft materials to develop the effective stress-intensity factor range against crack growth rate relationship for use in damage tolerance analyses.
Analysis of Fatigue Crack Growth Databses for Use in a Damage Tolerance Approach for Aircraft Propellers and Rotorcraft
2007
93 pages
Report
Keine Angabe
Englisch
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