NASA NTRS · 19820046563
High temperature composites for advanced missile and space transportation systems
Abstract
A study has been conducted to characterize a state-of-the-art graphite/polyimide composite system by determining mechanical and thermophysical properties of selected laminates over a temperature range of -250 F to 600 F. The material studied was Celion 3000/PMR-15. Material property data obtained from testing included tension, compression and shear strengths, and coefficient of thermal expansion. Environmental conditions examined were: as cured/post-cured, isothermal aged at 600 F, thermal cycled from -250 F to 600 F, and moisture conditioned. This study has provided an initial data base on a graphite/polyimide composite system capable of operating in 500/600 F applications.
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Mccleskey, S. F., Cushman, J. B., Skoumal, D. E.. 1982-01-01. High temperature composites for advanced missile and space transportation systems. https://ntrs.nasa.gov/citations/19820046563
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