NASA Logo

NTRS

NTRS - NASA Technical Reports Server

Due to the lapse in federal government funding, NASA is not updating this website. We sincerely regret this inconvenience.

Back to Results
A model of the thermal-spike mechanism in graphite/epoxy laminatesThe influence of a thermal spike on a moisture-saturated graphite/epoxy composite was studied in detail. A single thermal spike from 25 C to 132 C was found to produce damage as evidenced by a significant increase in the level of moisture saturation in the composite. Approximately half of this increase remained after a vacuum anneal at 150 C for 7 days, suggesting the presence of an irreversible damage component. Subsequent thermal spikes created less and less additional moisture absorption, with the cumulative effect being a maximum or limiting moisture capacity of the composite. These observations are explained in terms of a model previously developed to explain the reverse thermal effect of moisture absorption in epoxy and epoxy matrix composites. This model, based on the inverse temperature dependence of free volume, contributes an improved understanding of thermal-spike effects in graphite/epoxy composites.
Document ID
19830003903
Acquisition Source
Legacy CDMS
Document Type
Technical Memorandum (TM)
Authors
Adamson, M. J.
(NASA Ames Research Center Moffett Field, CA, United States)
Date Acquired
September 4, 2013
Publication Date
October 1, 1982
Subject Category
Composite Materials
Report/Patent Number
A-8905
NAS 1.15:84299
NASA-TM-84299
Report Number: A-8905
Report Number: NAS 1.15:84299
Report Number: NASA-TM-84299
Accession Number
83N12173
Funding Number(s)
PROJECT: RTOP 505-33-21
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.
No Preview Available