Rocket assembly ablative materials formed from solvent-spun cellulosic precursors, and method of insulating or thermally protecting a rocket assembly with the same

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-s...

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Bibliographische Detailangaben
Hauptverfasser:	KENNETH P. WILSON, JOHN K. SHIGLEY, ALLAN P. THOMPSON
Format:	Patent
Sprache:	eng
Schlagworte:	AFTER-TREATMENT NOT COVERED BY SUBCLASSES C08B, C08C, C08F,C08G APPARATUS SPECIALLY ADAPTED FOR THE MANUFACTURE OF CARBONFILAMENTS BLASTING CHEMICAL FEATURES IN THE MANUFACTURE OF ARTIFICIAL FILAMENTS,THREADS, FIBRES, BRISTLES OR RIBBONS CHEMISTRY COMBUSTION ENGINES COMPOSITIONS BASED THEREON EXPLOSIVES EXPLOSIVES OR THERMIC COMPOSITIONS GENERAL PROCESSES OF COMPOUNDING HEATING HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS JET-PROPULSION PLANTS LIGHTING MANUFACTURE THEREOF MATCHES MECHANICAL ENGINEERING METALLURGY NATURAL OR ARTIFICIAL THREADS OR FIBRES ORGANIC MACROMOLECULAR COMPOUNDS SPINNING TEXTILES THEIR PREPARATION OR CHEMICAL WORKING-UP USE OF SINGLE SUBSTANCES AS EXPLOSIVES WEAPONS WORKING-UP
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Beschreibung
Zusammenfassung:	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.