Accession Number:

AD0920282

Title:

Acoustic Fatigue of Aircraft Structures at Elevated Temperatures

Descriptive Note:

Final rept. Apr 1972-Dec 1973

Corporate Author:

LOCKHEED-GEORGIA CO MARIETTA

Personal Author(s):

• Schneider, Cecil W.

Report Date:

1974-03-01

Pagination or Media Count:

218.0

Abstract:

An analytical and experimental program was conducted to develop acoustic fatigue design criteria for aircraft structures subjected to intense noise in a high temperature environment. Equations for the dynamic response of a buckled panel were formulated for simply supported boundary conditions using large deflection plate theory. Random amplitude acoustic fatigue testing of representative aircraft structure was accomplished at temperatures up to 600 F to provide data for correlation with the analytical results. Empirical design criteria are presented in the form of design equations and nomographs for predicting the combined thermal and dynamic response of aircraft structures.

Descriptors:

• *AIRFRAMES
• *THERMAL FATIGUE
• *SONIC FATIGUE
• COMPUTER PROGRAMS
• MATHEMATICAL MODELS
• VIBRATION
• EXPERIMENTAL DATA
• LIFE EXPECTANCY(SERVICE LIFE)
• DEGRADATION
• ALUMINUM ALLOYS
• STRUCTURAL PROPERTIES
• HIGH TEMPERATURE
• DYNAMIC RESPONSE
• STIFFNESS
• NUMERICAL ANALYSIS
• STIFFENING
• TEST METHODS
• STRAIN(MECHANICS)
• CURVATURE
• MATHEMATICAL PREDICTION
• STRUCTURAL RESPONSE
• BUCKLING
• FLANGES
• CORRELATION TECHNIQUES
• SURFACE TEMPERATURE
• SKIN(STRUCTURAL)
• THERMAL STRESSES
• CONFIDENCE LEVEL
• FREQUENCY RESPONSE
• TITANIUM ALLOYS
• BAYS(STRUCTURAL UNITS)
• NOMOGRAPHS

Subject Categories:

• Aircraft
• Structural Engineering and Building Technology
• Mechanics

Distribution Statement:

APPROVED FOR PUBLIC RELEASE