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.

Subject Categories:

  • Metallurgy and Metallography
  • Mechanics

Distribution Statement:

APPROVED FOR PUBLIC RELEASE