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A cure-rate model for the Shuttle filament-wound caseAn epoxy and carbon fiber composite has been used to produce a light-weight rocket case for the Space Shuttle. A kinetic model is developed which can predict the extent of epoxy conversion during the winding and curing of the case. The model accounts for both chemical and physical kinetics. In the model, chemical kinetics occur exclusively up to the time the transition temperature equals the reaction temperature. At this point the resin begins to solidify and the rate of this process limits the rate of epoxy conversion. A comparison of predicted and actual epoxy conversion is presented for isothermal and temperature programmed cure schedules.
Document ID
19870059250
Acquisition Source
Legacy CDMS
Document Type
Reprint (Version printed in journal)
External Source(s)
Authors
Cagliostro, D. E.
(NASA Ames Research Center Moffett Field, CA, United States)
Islas, A.
(NASA Ames Research Center Moffett Field, CA, United States)
Hsu, Ming-Ta
(HC Chem. Corp. San Jose, CA, United States)
Date Acquired
August 13, 2013
Publication Date
June 1, 1987
Publication Information
Publication: Polymer Composites
Volume: 8
ISSN: 0272-8397
Subject Category
Composite Materials
Accession Number
87A46524
Distribution Limits
Public
Copyright
Other

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