Accession Number:

ADA090553

Title:

Sonic Fatigue Design Techniques for Advanced Composite Aircraft Structures

Descriptive Note:

Final technical rept. Aug 1977-Dec 1979

Corporate Author:

ROHR INDUSTRIES INC CHULA VISTA CA

Personal Author(s):

• Holehouse, Ian

Report Date:

1980-04-01

Pagination or Media Count:

357.0

Abstract:

A combined analytical and experimental program was conducted in order to develop a semi-empirical sonic fatigue design method for curved and flat graphite-epoxy skin-stringer panels. A range of multi-bay panels was subjected to high intensity noise environments in a progressive-wave tube. Shaker tests were also performed in order to provide additional random fatigue data. Finite- element analyses were carried out on the test panel designs, generating static strains and frequencies. Multiple stepwise regression analysis was used to develop the sonic fatigue design method. Design equations and a nomograph are presented. Comparisons of sonic fatigue resistance between graphite and aluminum panels were also carried out. The design method developed is presented as a self-contained section in this report and is suitable for practical design use.

Descriptors:

• *COMPOSITE MATERIALS
• *GRAPHITE
• *SONIC FATIGUE
• ALUMINUM ALLOYS
• FINITE ELEMENT ANALYSIS
• INTENSITY
• ALUMINUM
• EPOXY LAMINATES
• TABLES(DATA)
• AIRCRAFT PANELS
• NOISE(SOUND)
• HONEYCOMB STRUCTURES
• NOMOGRAPHS

Subject Categories:

• Aircraft
• Laminates and Composite Materials

Distribution Statement:

APPROVED FOR PUBLIC RELEASE