Accession Number : AD0866206

Title :   A Method for Preventing Catastrophic Failure in Aluminum Stressed Skin Panels.

Descriptive Note : Technical note,

Corporate Author : ARMY AVIATION MATERIEL LABS FORT EUSTIS VA

Personal Author(s) : Roach, Charles D. ; Figge, I. E., Sr

Report Date : DEC 1969

Pagination or Media Count : 37

Abstract : Crack arrest and residual strength tests were conducted on 12-inch-wide bare and clad T6 aluminum alloy specimens to determine the effects of thin straps of fiberglass tape bonded to the specimens. The tests indicated that running cracks can be arrested by the fiberglass straps. Significant increases in the crack arrest behavior of up to 48 percent were obtained with two 0.75-inch by 0.010-inch straps spaces 2.75 inches apart on the front and back sides of the specimen. Residual static strength values for a specimen with a 2-4 inch-long crack) APPROACHING THE ULTIMATE TENSILE STRENGTH OF THE MATERIAL WERE ACHIEVED BY THIS METHOD. (Author, modified-PL)

Descriptors :   *GLASS TEXTILES), (*AIRPLANE PANELS, STRESSES), (*ALUMINUM ALLOYS, CRACKS), (*REINFORCING MATERIALS, SUBSTRATES, COMPOSITE MATERIALS, CRACK PROPAGATION, BONDING, TAPES, TOUGHNESS, LOADS(FORCES).

Subject Categories : Aircraft
      Coatings, Colorants and Finishes
      Mechanics

Distribution Statement : APPROVED FOR PUBLIC RELEASE