SEDL / STP / STP743-EB / STP28788S

Fatigue Crack Growth Behavior and Life Predictions for 2219-T851 Aluminum Subjected to Variable-Amplitude Loadings

Chang, JB
Program manager and technical staff, Rockwell International Corp., North American Aircraft Division, Los Angeles, Calif.

Engle, RM
Aerospace engineer, U.S. Air Force Flight Dynamics Laboratory, WPAFB, Ohio

Stolpestad, J
Program manager and technical staff, Rockwell International Corp., North American Aircraft Division, Los Angeles, Calif.

Pages: 25    Published: Jan 1981

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Abstract

Fatigue crack growth behavior of 2219-T851 aluminum is characterized for variable-amplitude loading conditions which include the single and periodic tensile or compressive overload, single tensile overload followed by a single compressive load, multiple tensile and compressive overloads, high-low or low-high block loading, and compression-compression loads followed by tension-tension loads. A load interaction model which accounts for the overload retardation and compressive load acceleration effects on fatigue crack growth lives is introduced. Fatigue crack growth analyses are performed on all test cases using a computer program which employs this load interaction model. Analytical predictions are correlated with the test data. Results show that this model adequately predicted fatigue crack growth behavior and fatigue crack lives for most of the test loading conditions to within ±30 percent.