| 摘要 |
1. A composition for lining the combustion chamber of a rocket motor employing a solid propellant comprised of an epoxy resin, a copolymer of butadiene and acrylic acid, a curing agent, and between about 2.5 and about 30 per cent by weight of an inert inorganic filler selected from the group consisting of carbon, ferric oxide, titanium dioxide and mixtures thereof.
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