Accession Number : ADA327868

Title :   Structural Integrity Analysis And Verification for Aircraft Structures: Volume 2: Effects Of Compressive Loading On The Fatigue Crack Growth Rates Of 7075-T651 And 2024-T3 Aluminum Alloys.

Descriptive Note : Final rept. 1 Jan-31 Dec 95,

Corporate Author : ANALYTICAL SERVICES AND MATERIALS INC HAMPTON VA

Personal Author(s) : Harter, J. A.

PDF Url : ADA327868

Report Date : AUG 1996

Pagination or Media Count : 47

Abstract : The purpose of this research was to determine the effects of constant amplitude high compressive stresses on the fatigue life of 7O75-T651 and 2024-T3 aluminum alloys. This project consisted of three components: finite element modeling/analysis, generation of fatigue crack growth data for AFGROW modifications, and verification testing. An elastic-plastic finite element analysis program (ZIP2D) was used to determine the stress field in the crack plane for the different testing conditions. Fatigue crack growth data from center-notched, through-cracked panels were collected for both alloys at several loads and stress ratios, and these data were used to modify tabular crack growth data for the AGROW program. Center-notched and surface-cracked specimens were then tested to verify AFGROW predictions (with updated tabular data) for crack shape and fatigue lifetimes.

Descriptors :   *FATIGUE LIFE, *ALUMINUM ALLOYS, *COMPRESSIVE PROPERTIES, TEST AND EVALUATION, MATHEMATICAL MODELS, RATIOS, AIRCRAFT, VERIFICATION, FINITE ELEMENT ANALYSIS, STRUCTURAL ANALYSIS, STRESS(PHYSIOLOGY), CRACKS, SHAPE, RATES, RELIABILITY, CRACK PROPAGATION, AIRFRAMES, TABLES(DATA), FATIGUE(MECHANICS).

Subject Categories : Metallurgy and Metallography
      Mechanics

Distribution Statement : APPROVED FOR PUBLIC RELEASE