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US 6,324,833 B1Granted
Reinforced composite articles and method of making same
AssigneeCordant Technologies Inc.
InventorsVictor Singer, Frederick W. VanName, James A. Hartwell
Life of this patent
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AssigneeCordant Technologies Inc.
InventorsVictor Singer, Frederick W. VanName, James A. Hartwell
Estimating the term…
A composite tubular article such as a nozzle or a polar boss for a rocket motor wherein straight matrix impregnated yarn portions extend from one end portion to the other in a non-cylindrical ply to achieve increased strength while affording lighter weight. The matrix material may be at least partially curable by actinic radiation to anchor the yarn portions in position as they are applied on a mandrel so that radial rods or the like for anchoring the yarn may be eliminated. For high performance rocket motor nozzle components and the like, the yarn portions may be straight or non-straight and applied by braiding or the like, and the matrix material may be decomposed to a char adequate to anchor the yarn portions and subjected to one or more densification cycles whereby the matrix material may be carbonized.
A composite article comprising a tubular material having an axis, at least one ply of straight yarn portions of fibrous material, a matrix material impregnating said straight yarn portions, said at least one ply shaped to define a pair of circular end portions and an intermediate circular portion the diameter of which intermediate circular portion is less than the diameter of either of said circular end portions, and said straight yarn portions extending from one of said circular end portions to the other of said circular end portions.
A composite polar boss comprising a tubular material having an axis, at least one ply of straight yarn portions of fibrous material, a matrix material impregnating said straight yarn portions, said at least one ply shaped to define a pair of circular end portions and an intermediate circular portion the diameter of which intermediate circular portion is less than the diameter of either of said circular end portions, and said straight yarn portions extending from one of said circular end portions to the other of said circular end portions.
A composite rocket motor nozzle component comprising a tubular article having an axis, at least one ply of straight yarn portions of fibrous material, a matrix material impregnating said yarn portions, said at least one ply shaped to define a pair of circular end portions and an intermediate circular portion, the diameter of said intermediate circular portion being less than the diameter of either of said circular end portions, and said straight yarn portions extending from one of said circular end portions to the other of said circular end portions.
Dependencies are inferred from the claim text.