SYMPOSIA PAPER Published: 01 January 1976
STP27779S

Effects of Thermal Cycling Environment on Graphite/Epoxy Composites

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Graphite/epoxy (Gr/E) composites have attractive properties—low density, high stiffness, and a low coefficient of thermal expansion (CTE)—that make them prime candidates for many spacecraft applications. The effects of a thermal cycling environment on the dimensional stability and microstructural integrity of Gr/E composites were evaluated. Severe microcracking was found in several high-modulus fiber (HMS)-reinforced 350°F-cure epoxy resin systems after exposure to 25 thermal cycles between the temperature of liquid nitrogen (−320°F) and that of boiling water (+212°F). A hybrid system combining Thornel-300 (T-300) fabric and HMS tape exhibited fewer microcracks, with the fabric acting as a crack stopper. Of the material systems investigated, a 250°F-cure system, HMS/CE 339, was found to be the most resistant to microcracking. The effects of thermal cycling on the microyield strength (MYS) and CTE of several near-zero expansion Gr/E composites were also studied.

Author Information

Camahort, JL
Lockheed Missiles and Space Company, Incorporated, Sunnyvale, Calif.
Rennhack, EH
Lockheed Missiles and Space Company, Incorporated, Sunnyvale, Calif.
Coons, WC
Lockheed Palo Alto Research Laboratory, Palo Alto, Calif.
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Details
Developed by Committee: D30
Pages: 37–49
DOI: 10.1520/STP27779S
ISBN-EB: 978-0-8031-4677-8
ISBN-13: 978-0-8031-0333-7