Alliant Techsystems Inc.

Cordant Technologies Inc.

Northrop Grumman Innovation Systems, Inc.

Allan P Thompson

John K Shigley

Kenneth P Wilson

Duane J Garbe

Shelley Rawding, Legal Representative

Edward L Collins

A flexible bearing assembly includes at least one metal end ring, a flexible bearing core having a plurality of layers of a resilient material between layers of a reinforcement material, and a phenolic composite material between and bonded to each of the at least one metal end ring and the flexible bearing core. A rocket motor assembly includes a chamber configured to contain a propellant and a movable thrust nozzle coupled to the chamber. The movable thrust nozzle includes a phenolic composite material between and bonded to each of a metal end ring and a flexible bearing core. Methods of forming a flexible bearing assembly include bonding a phenolic composite material to at least one metal end ring and bonding a flexible bearing core to the phenolic composite material. The flexible bearing core includes a plurality of layers of a resilient material between layers of a reinforcement material.

Flexible bearing assemblies, rocket motors including such assemblies, and methods of forming flexible bearings

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.

Rocket assembly ablative materials formed from, as a precursor, staple cellulosic fibers, and method of insulating or thermally protecting a rocket assembly with the same

A process for producing low-density composite components as disclosed herein involves forming a compacted and curable pre-preg into a selected level of compaction whereby voids are capable of forming in the compacted cuable pre-preg. The compacted curable pre-preg is then cured at a pressure sufficiently low to permit evolving gases to form voids in the pre-preg as the pre-preg cures into the composite article. The pre-preg is only partially debulked in the process. Rocket nozzle components can be produced with reduced densities while still exhibiting satisfactory erosion and other characteristics desired for products subject to the harsh erosive environment of a rocket motor.

Low density composite rocket nozzle components and process for making the same from standard density phenolic matrix, fiber reinforced materials

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.

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

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Tremonton, UT, United States of America

Allan P Thompson