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Development and demonstration of manufacturing processes for fabricating graphite/PMR-15 polyimide structural elementsThe processing requirements for graphite/PMR-15 polyimide composites developed to demonstrate the structural integrity of polyimide composite structural elements at temperatures up to 589K (600 F) are described. Major tasks included: quality assurance development; materials and process development; specification verification; flat panel fabrication; stiffened panel fabrication; honeycomb panel fabrication; chopped fiber moldings; and demonstration component fabrication. Materials, processing, and quality assurance documents were prepared from experimentally derived data. Structural elements consisting of flat panels, corrugated stiffeners, I-beams, hat stiffeners, honeycomb panels, and chopped fiber moldings were made and tested. Property data from 219K (-65 F) to 589K (600 F) were obtained. All elements were made in a production environment. The size of each element was sufficient to insure production capability and structural component applicability. Problems associated with adhesive bonding, laminate and structural element analysis, material variability, and test methods were addressed.
Document ID
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Sheppard, C. H.
(Boeing Aerospace Co. Seattle, WA, United States)
Hoggatt, J. T.
(Boeing Aerospace Co. Seattle, WA, United States)
Symonds, W. A.
(Boeing Aerospace Co. Seattle, WA, United States)
Date Acquired
August 9, 2013
Publication Date
August 1, 1979
Publication Information
Publication: NASA. Langley Res. Center Graphite(Polyimide Composites
Subject Category
Composite Materials
Accession Number
Funding Number(s)
Distribution Limits
Work of the US Gov. Public Use Permitted.

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