Accession Number : AD0810558

Title :   SONIC FATIGUE TOLERANCE OF GLASS FILAMENT STRUCTURE: VOLUME II. EXPERIMENTAL RESULTS.

Descriptive Note : Final rept. 15 May 65-15 Jul 66,

Corporate Author : NORTH AMERICAN AVIATION INC COLUMBUS OH COLUMBUS DIV

Personal Author(s) : Hayes, John A.

Report Date : DEC 1966

Pagination or Media Count : 155

Abstract : Sonic fatigue experimental test results on a series of sixty flat rectangular glass fiber sandwich test panels are presented and discussed. The panels were of the fluted core (corrugated) type, had nominal overall dimensions of 24 in. x 30 in. x 0.45 in., and a nominal surface weight of one pound per square foot. The fluted core glass fabric (181 and 151S glass) was of the integrally woven variety. A vacuum process was employed to impregnate the glass cloth with resin. Twenty each of three types of panels were sonic fatigue tested using a discrete frequency siren, five identical panels at four different sound pressure levels, to provide three S-N (Sound Pressure Level Vs. Cycles to Failure) plots. Twenty aluminum skin-stringer panels of the same overall dimensions and surface weight were similarly tested for control. (Author)

Descriptors :   *FILAMENTS), *TOLERANCES(MECHANICS)), (*GLASS TEXTILES, (*SONIC FATIGUE, (*SANDWICH CONSTRUCTION, SONIC FATIGUE), PANELS, FAILURE(MECHANICS), ALUMINUM ALLOYS, COMPOSITE MATERIALS, HONEYCOMB CORES, REINFORCING MATERIALS, INSTRUMENTATION, DAMPING, SUPERSONIC AIRCRAFT.

Subject Categories : Plastics

Distribution Statement : APPROVED FOR PUBLIC RELEASE