Accession Number:

AD0919145

Title:

Evaluation of Structural Reliability Analysis Procedures as Applied to a Fighter Aircraft

Descriptive Note:

Final rept. 1 May 1972-1 May 1973

Corporate Author:

MCDONNELL AIRCRAFT CO ST LOUIS MO

Personal Author(s):

• Impellizzeri, L. F.
• Siegel, A. E.
• McGinnis, R. A.

Report Date:

1973-09-01

Pagination or Media Count:

230.0

Abstract:

Structural reliability analysis procedures were evaluated for estimating the variability in fighter aircraft fatigue performance. The expected magnitude of this variability was determined based on an investigation of scatter in fatigue test results for aluminum structures. This study revealed that 1 the scatter for spectrum fatigue tests is considerably less than for constant amplitude fatigue tests 2 the Weibull probability distribution provides a better fit of the spectrum data than the log-normal and 3 the Weibull shape parameter alpha is 5.27.

Descriptors:

• *STRUCTURAL RESPONSE
• *JET FIGHTERS
• FLIGHT TESTING
• ALUMINUM ALLOYS
• STRUCTURAL PROPERTIES
• PROBABILITY
• ATTRITION
• FRACTURE(MECHANICS)
• RELIABILITY
• CRACK PROPAGATION
• FUSELAGES
• AIRFRAMES
• DYNAMIC LOADS
• FATIGUE(MECHANICS)
• STATISTICAL ANALYSIS
• FLIGHT MANEUVERS
• BULKHEADS
• FLIGHT LOADS
• SWEPTBACK WINGS
• HONEYCOMB STRUCTURES

Subject Categories:

• Attack and Fighter Aircraft
• Structural Engineering and Building Technology
• Mechanics

Distribution Statement:

APPROVED FOR PUBLIC RELEASE