Skip to content

Atomic oxygen degradation mechanisms of epoxy composites for space applications

Research output: Contribution to journalArticle

Original languageEnglish
Pages (from-to)108-120
Number of pages13
JournalPolymer Degradation and Stability
Volume166
Early online date23 May 2019
DOIs
DateAccepted/In press - 20 May 2019
DateE-pub ahead of print - 23 May 2019
DatePublished (current) - 1 Aug 2019

Abstract

The effects of atomic oxygen on three commercial composite materials, based on two space-qualified epoxy resins (tetraglycidyl-4,4′-diaminodiphenylmethane (TGDDM) cured with a blend of 4,4′-methylenebis(2,6-diethylaniline) and 4,4′-methylenebis(2-isopropyl-6-methylaniline); and a blend of TGDDM, bisphenol A diglycidyl ether (DGEBA), and epoxidised novolak resin initiated by N’-(3,4-dichlorophenyl)-N,N-dimethylurea) are studied. Samples were exposed to a total fluence of (3.82 × 1020atom/cm2), equating to a period of 43 days in low Earth orbit. The flexural rigidity and modulus of all laminates displayed a reduction of 5–10% after the first exposure (equivalent to 20 days in orbit). Fourier transform infrared (FTIR) spectra, obtained during prolonged exposure to atomic oxygen, were interpreted using multivariate analysis to explore the degradation mechanisms.

    Research areas

  • Atomic oxygen, Epoxy resins, Principal components analysis, Thermoset polymers, Ultra-thin space composites

    Structured keywords

  • Bristol Composites Institute ACCIS

Download statistics

No data available

Documents

Documents

  • Full-text PDF (final published version)

    Rights statement: This is the final published version of the article (version of record). It first appeared online via Elsevier at https://www.sciencedirect.com/science/article/pii/S0141391019301843. Please refer to any applicable terms of use of the publisher.

    Final published version, 2 MB, PDF document

    Licence: CC BY

DOI

View research connections

Related faculties, schools or groups