Accession Number:

AD0773672

Title:

Fatigue Behaviour of Hat Section Stringer Stiffened Panels Compressed in the Post-Buckling Range.

Descriptive Note:

Final technical rept.,

Corporate Author:

PISA UNIV (ITALY) INST OF AERONAUTICS

Personal Author(s):

• Salvetti,A.
• Casarosa,C.

Report Date:

1973-07-01

Pagination or Media Count:

89.0

Abstract:

The report presents results of research on the fatigue behaviour of riveted hat section stringer stiffened panels which buckle under constant amplitude fatigue loading. Panels made with 2024-T3 as well as 7075-T6 Aluminum alloys were tested, and cracks were found to develop systematically in the stringer top plate along the rivet lines. It was demonstrated that the tensile bending stresses which take place in the stringer when the sheet cover buckles are responsible for crack initiation. The fatigue cracked panels were statically tested. Results are discussed.

Descriptors:

• *ALUMINUM ALLOYS
• *AIRCRAFT PANELS
• *FATIGUE(MECHANICS)
• LOADS(FORCES)
• CRACK PROPAGATION
• BUCKLING
• COMPRESSIVE PROPERTIES
• FAILURE(MECHANICS)
• STATISTICAL ANALYSIS
• DYNAMIC TESTS
• STATIC TESTS
• ITALY

Subject Categories:

• Aircraft
• Metallurgy and Metallography

Distribution Statement:

APPROVED FOR PUBLIC RELEASE