Hybridized Polymer Matrix Composites.
Abstract
This report describes the results of a program designed to determine the extent to which graphite fibers are released from resin matrix composites that are exposed to fire and impact conditions. The conditions evaluated were laboratory simulations of those that could exist in the event of an aircraft crash and burn situation. Another objective of the program was to evaluate the effectiveness of various hybridizing concepts in preventing this release of graphite fibers. The baseline (i.e., unhybridized) laminates evaluated were prepared from commercially available graphite/epoxy, graphite/polyimide, and graphite/phenolic materials. Hybridizing concepts investigated included resin fillers, laminate coatings, resin blending, and mechanical interlocking of the graphite reinforcement. The baseline and hybridized laminates' mechanical properties, before and after isothermal and humidity aging, also were compared. It was found that a small amount of graphite fiber was released from the graphite/epoxy laminates during the burn and impact conditions used in this program. However, the extent to which the fibers were released is not considered a severe enough problem to preclude the use of graphite-reinforced composites in civil aircraft structure. It also was found that several hybrid concepts eliminated this fiber release. Isothermal and humidity aging did not appear to alter the fiber release tendencies. Under the burn conditions used in the program, no fibers were released from the baseline graphite/phenolic laminates. Next in order of effectiveness in fiber retention was the polyimide resin, followed by the epoxy resin. (MM)
Document Details
- Document Type
- Technical Report
- Publication Date
- Oct 20, 1980
- Accession Number
- ADA301565
Entities
People
- E. E. House
- J. T. Hoggatt
- W. A. Symonds
Organizations
- Boeing