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high temperature resin matrix composites for aerospace structuresAccomplishments and the outlook for graphite-polyimide composite structures are briefly outlined. Laminates, skin-stiffened and honeycomb sandwich panels, chopped fiber moldings, and structural components were fabricated with Celion/LARC-160 and Celion/PMR-15 composite materials. Interlaminar shear and flexure strength data obtained on as-fabricated specimens and specimens that were exposed for 125 hours at 589 K indicate that epoxy sized and polyimide sized Celion graphite fibers exhibit essentially the same behavior in a PMR-15 matrix composite. Analyses and tests of graphite-polyimide compression and shear panels indicate that utilization in moderately loaded applications offers the potential for achieving a 30 to 50 percent reduction in structural mass compared to conventional aluminum panels. Data on effects of moisture, temperature, thermal cycling, and shuttle fluids on mechanical properties indicate that both LARC-160 and PMR-15 are suitable matrix materials for a graphite-polyimide aft body flap. No technical road blocks to building a graphite-polyimide composite aft body flap are identified.
Document ID
19800019940
Document Type
Conference Paper
Authors
Davis, J. G., Jr.
(NASA Langley Research Center Hampton, VA, United States)
Date Acquired
August 10, 2013
Publication Date
January 1, 1980
Publication Information
Publication: Selected NASA Research in Composite Materials and Structures
Subject Category
COMPOSITE MATERIALS
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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