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):
Report Date:
1996-08-01
Pagination or Media Count:
47.0
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 modelinganalysis, 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:
Subject Categories:
- Metallurgy and Metallography
- Mechanics