Accession Number : ADA300529
Title : Properties of Two Composite Materials Made of Toughened Epoxy Resin and High-Strain Graphite Fiber.
Descriptive Note : Technical paper,
Corporate Author : NATIONAL AERONAUTICS AND SPACE ADMINISTRATION HAMPTON VA LANGLEY RESEARCH CEN TER
Personal Author(s) : Dow, Marvin B. ; Smith, Donald L.
PDF Url : ADA300529
Report Date : JUL 1988
Pagination or Media Count : 44
Abstract : Brittle behavior of graphite-epoxy materials remains a major barrier to expanding their applications in aircraft structures. Holes, notches, or induced damage severely degrade the structural efficiency of these materials, particularly their compression properties. As a result, the design of composite structures must assume very conservative performance limits. A long-recognized need continues for composite materials that tolerate damage and resist delaminations. This paper presents results from an experimental evaluation of IM7/8551-7 and IM6/1808I. Data include ply level strengths and moduli, notched tension and compression strengths, and compression-after-impact assessments. The purpose was to (1) compile tension and compression properties useful in preliminary design and (2) make a limited comparison of these materials with other graphite-epoxy systems. Specimen fabrication and testing were performed at the NASA Langley Research Center. jg p.4
Descriptors : *FIBERS, *COMPOSITE MATERIALS, *STRAIN(MECHANICS), *GRAPHITED MATERIALS, *EPOXY RESINS, TEST AND EVALUATION, COMPRESSION, HIGH RATE, AIRCRAFT, DAMAGE, DEGRADATION, STRUCTURAL PROPERTIES, LAMINATES, COMPARISON, EFFICIENCY, COMPOSITE STRUCTURES, RESEARCH FACILITIES, STRENGTH(MECHANICS), STRAIN RATE, BRITTLENESS, HOLES(OPENINGS), AIRFRAMES, DELAMINATION, NOTCH TOUGHNESS.
Subject Categories : Laminates and Composite Materials
Distribution Statement : APPROVED FOR PUBLIC RELEASE