Accession Number:

ADA109054

Title:

Fracture and Fatigue Characterization of Aircraft Structural Materials under Biaxial Loading

Descriptive Note:

Final scientific rept. 1 Oct 76-30 May 80

Corporate Author:

GEORGE WASHINGTON UNIV WASHINGTON DC DEPT OF CIVIL MECHANICAL AND ENVIRONMENTAL ENGINEERING

Personal Author(s):

Report Date:

1981-12-01

Pagination or Media Count:

205.0

Abstract:

A general fracture mechanics analysis was performed to examine the influence of biaxial applied loads on the mechanical state of the body. The geometries examined were the single crack and two coplanar cracks with an arbitrary orientation and the cracked shear panel. It was found that the biaxial loads influenced all aspects of the mechanical state of the body, with the exception of the stress intensity factor for a crack oriented parallel to the biaxial load. The extent and nature of the biaxial effect on the crack-tip stress field, stress intensity factor, angle of initial crack extension, crack- tip displacements, elastic strain energy, fracture load and fatigue crack growth rates are all discussed. A biaxial test facility was developed and a considerable number of photoelastic, fracture toughness, and fatigue crack growth rate experiments were performed. Confirmation of the analytical predictions was obtained for the biaxial effects on the crack-tip stress field, the angle of initial crack extension, the fracture load, and the fatigue crack growth rates. The biaxial loads were seen to influence all of these parameters in varying degrees.

Subject Categories:

  • Aircraft
  • Numerical Mathematics
  • Mechanics

Distribution Statement:

APPROVED FOR PUBLIC RELEASE