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AssigneeCordant Technologies Inc.
InventorsKenneth P. Wilson, John K. Shigley, Allan P. Thompson
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A rocket motor assembly is insulated or thermally protected with a rocket motor ablative material formed from a prepreg. The prepreg contains at least an impregnating resin matrix and, as a precursor prior to carbonization, either carded and yarn-spun solvent-spun staple cellulosic fibers, solvent-spun cellulosic filaments, or a combination thereof. When patterned and carbonized, the rocket motor ablative material can be lined or otherwise placed into a rocket motor assembly, such as between the solid propellant and case, in the bulk area of the exit nozzle liner, or at susceptible portions of a re-entry vehicle, such as the nose cone.
A method for insulating or thermally protecting a rocket motor assembly comprising a rocket motor casing, a solid propellant, and a nozzle assembly, said process comprising (a) forming a rocket motor ablative material from a prepreg comprising at least one impregnating resin matrix and, as a precursor prior to carbonization, either carded and yarn spun solvent-spun staple cellulosic fibers, solvent-spun cellulosic filaments, or a combination thereof and (b) insulating or lining a portion of the rocket motor assembly with the rocket motor ablative material.
A rocket motor ablative material comprising a prepreg, said prepreg comprising at least one carbon-based reinforcement structure impregnated with at least one resin, said reinforcement structure being formed from, as a precursor prior to carbonization, either carded and yarn-spun solvent-spun staple cellulosic fibers, solvent-spun cellulosic filaments, or a combination thereof.
Dependencies are inferred from the claim text.