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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, carded and spun staple cellulosic fibers. When patterned and carbonized, the

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, carded and spun staple cellulosic fibers. 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.

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1. A method for insulating or thermally protecting a rocket motor assembly comprising a rocket motor casing containing a solid propellant, and a nozzle assembly coupled to the rocket motor casing, said process comprising (a) forming a rocket motor insulation from a prepreg comprising at least one re

1. A method for insulating or thermally protecting a rocket motor assembly comprising a rocket motor casing containing a solid propellant, and a nozzle assembly coupled to the rocket motor casing, said process comprising (a) forming a rocket motor insulation from a prepreg comprising at least one resin matrix impregnated into a carbonized reinforcement, the carbonized reinforcement being formed from, as a precursor prior to carbonization, carded and yarn-spun staple cellulosic fibers and (b) insulating a portion of the rocket motor assembly with the rocket motor ablative material. 2. The process of claim 1, wherein the staple cellulosic fibers comprise non-solvent-spun rayon fibers. 3. The process of claim 2, wherein the non-solvent-spun rayon fibers have an average length in a range of from 38 mm to 225 mm, and are spun into yarn having a denier per fiber in a range of from 1.5 dpf to 9.0 dpf. 4. The process of claim 1, wherein the staple cellulosic fibers are formed from a cellulose-derivative. 5. The process of claim 1, wherein the staple cellulosic fibers are untreated. 6. The process of claim 1, wherein said insulating comprises applying the rocket motor ablative material between the solid propellant and the casing surrounding the solid propellant. 7. The process of claim 1, wherein said insulating comprises applying the ablative material as a bulk ablative material of an exit nozzle liner. 8. The process of claim 1, wherein said insulating comprises applying the ablative material as a bulk ablative material of a reentry vehicle nose cone. 9. The process of claim 1, further comprising carbonizing the prepreg at at least 1350° C. 10. The process of claim 1, wherein the prepreg comprises 31.0-36.0 wt % phenolic resin, 13.0-17.5 wt % carbon black filler, and 46.5 to 56.0 wt % carbon fabric. 11. Rocket motor insulation comprising a prepreg, said prepreg comprising at least one carbonized reinforcement structure impregnated with at least one resin, said reinforcement structure being formed from, as a precursor prior to carbonization, carded and spun cellulosic fibers. 12. The rocket motor insulation of claim 11, wherein the staple cellulosic fibers comprise non-solvent-spun rayon fibers. 13. The rocket motor insulation of claim 12, wherein the non-solvent spin rayon fibers have an average length in a range of from 38 mm to 225 mm, and the yarn has a denier per fiber in a range of from 1.5 dpf to 9.0 dpf. 14. The rocket motor insulation of claim 11, wherein the staple cellulosic fibers are formed from a cellulosic derivative. 15. The rocket motor insulation of claim 11, wherein the staple cellulosic fibers are untreated. 16. A rocket motor assembly comprising the insulation of claim 11. 17. The rocket motor assembly of claim 16, wherein the insulation is constructed and arranged as a bulk insulation of an exit nozzle liner. 18. The rocket motor assembly of claim 16, wherein the insulation is constructed and arranged as a bulk insulation of a re-entry vehicle nose cone. 19. The rocket motor assembly of claim 16, wherein the insulation is interposed between a solid propellant and casing of the rocket motor assembly. 20. The process of claim 1, wherein said insulating comprises lining the portion of the rocket motor assembly. 21. A method of thermally protecting a vehicle, the method comprising; forming an ablative material comprising at least one resin matrix impregnated into a carbonized reinforcement including forming the at least one carbonized reinforcement from, as a precursor prior to carbonization, carded and yarn-spun staple cellulosic fibers; andinsulating at least a portion of the vehicle including applying the ablative material to the at least a portion of the vehicle. 22. A method of thermally protecting a surface exposed to combustion products, the method comprising: forming an ablative material comprising at least one resin matrix impregnated into a carbonized reinforcement including forming the at least one carbonized reinforcement from, as a precursor prior to carbonization, carded and yarn-spun staple cellulosic fibers; andinsulating at least a portion of a surface along an expected flow path of the combustion products, insulating the at least a portion of the surface including applying the ablative material to the at least a portion of the surface along the expected flow path.