Accession Number:

ADA164110

Title:

The Effects of through the Thickness Delaminations on Curved Composite Panels.

Descriptive Note:

Master's thesis,

Corporate Author:

AIR FORCE INST OF TECH WRIGHT-PATTERSON AFB OH SCHOOL OF ENGINEERING

Personal Author(s):

Report Date:

1985-12-01

Pagination or Media Count:

105.0

Abstract:

The buckling loads of 8-ply A543501-6 graphiteepoxy delaminated cylindrical panels were determined experimentally. The delaminations fabricated into the laminate, with mylar and teflon inserts, were indicative of low velocity projectile impact damage. The mylar and teflon inserts caused partial and total delaminations, respectively. Two types of delaminations were used namely, eccentric, off mid-surface, and mid-surface. The eccentric delaminations were placed progressively through the thickness of the laminate. STAGSC-1 finite element computer code results for undelaminated composite panels were compared to the experimental results to obtain a percent strength degradation. The experimental testing was accomplished by the Air Force Flight Dynamics Laboratory. The test device provided boundary conditions of clamped top and bottom edges and simply supported vertical sides. Two destructive techniques, stereo x-ray and deply, were used to determine the total delaminated areas and locations. Based in part on these results, one equivalent delamination was obtained corresponding to the total area of the multiple partial delaminations. The panels with multiple delaminations were found to be approximately 5 weaker than a single delaminated area of the same total size. Keywords Composites, Cylindrical panels, Though the thickness delaminations, Experimental shell analysis, Finite elements STAGSC-1.

Subject Categories:

  • Laminates and Composite Materials
  • Structural Engineering and Building Technology

Distribution Statement:

APPROVED FOR PUBLIC RELEASE