Properties of Two Composite Materials Made of Toughened Epoxy Resin and High-Strain Graphite Fiber.
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
Document Details
- Document Type
- Technical Report
- Publication Date
- Jul 01, 1988
- Accession Number
- ADA300529
Entities
People
- Donald L. Smith
- Marvin B. Dow
Organizations
- Langley Research Center