Accession Number:

ADA326432

Title:

Experimental Stress Analysis of a Plate Containing an Elongated Hole to Determine Buckling Behaviour under Representative F-111 C Loading Conditions.

Descriptive Note:

Technical note,

Corporate Author:

DEFENCE SCIENCE AND TECHNOLOGY ORGANIZATION CANBERRA (AUSTRALIA)

Personal Author(s):

• Allan, Robert B.

Report Date:

1997-03-01

Pagination or Media Count:

28.0

Abstract:

This report presents an experimental investigation into the tension and compression behavior of a plate specimen with a angled elongated hole. This specimen type will be used for validation of three life management options on the F-111 wing pivot fitting DADTA, cold expansioninterference fit plug and stress bridge. Two different brands of strain gauges were used to determine their suitability for use in regions of high plastic strains. The buckling load capability of the plate specimen was determined and found to be suitable for further validation tests.

Descriptors:

• *RESIDUAL STRESS
• *BUCKLING
• *WINGS
• *COMPRESSIVE STRENGTH
• FATIGUE LIFE
• STRAIN(MECHANICS)
• PLATES
• HOLES(OPENINGS)
• TENSION
• STRAIN GAGES
• PLASTIC PROPERTIES
• AUSTRALIA

Subject Categories:

• Aircraft
• Mechanics

Distribution Statement:

APPROVED FOR PUBLIC RELEASE