Accession Number : ADA301542

Title :   A Comparison of the Static and Fatigue Strengths of Formed and Drilled Holes in Composite Laminates.

Descriptive Note : Final rept.,

Corporate Author : NAVAL AIR DEVELOPMENT CENTER WARMINSTER PA

Personal Author(s) : Huang, S. L. ; Richey, R.

PDF Url : ADA301542

Report Date : 31 MAY 1977

Pagination or Media Count : 35

Abstract : Holes in structural members introduce areas of high stress concentration When "laying-up" a laminate composite, it is possible to form the holes before cure, instead of cutting the fibers by drilling the holes after cure. The diverted fibers maintain their continuity and provide added strength in the highly stressed region around the hole. Accordingly, it was hypothesized that a laminate with formed holes would be stronger than a similar laminate with drilled holes.

Descriptors :   *AIRCRAFT, *LAMINATES, *HOLES(OPENINGS), *FATIGUE(MECHANICS), *FASTENINGS, *GRAPHITE EPOXY COMPOSITES, LOAD DISTRIBUTION, TENSILE STRENGTH, COMPOSITE MATERIALS, STATIC LOADS, FIBER REINFORCED COMPOSITES, STRENGTH(MECHANICS), EPOXY LAMINATES, YIELD STRENGTH, CURING, PREPREGS, FAILURE(MECHANICS), COMPRESSIVE STRENGTH, STRUCTURAL COMPONENTS, DRILLING, MATERIAL FORMING, STRESS CONCENTRATION.

Subject Categories : Aircraft
      Laminates and Composite Materials
      Couplers, Fasteners, and Joints

Distribution Statement : APPROVED FOR PUBLIC RELEASE