Integral Composite Bushing System and Method
AssigneeAurora Flight Sciences Corporation
InventorBrandon Pollett
Life of this patent
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Abstract
A composite bearing comprising a densified portion, wherein a hole location is positioned at the approximate center of said densified portion; and a plurality of filament tendrils, wherein the plurality of filament tendrils are configured to wrap around the hole location to create a “U” shape.
Claims20
A composite aircraft structure, said composite aircraft structure comprising:
- a body portion having a first density;
- a disk-shaped densified portion comprising ceramic, metal, high-strength plastic, or a combination thereof,
- wherein the disk-shaped densified portion is configured to receive a hole positioned at an approximate center of said disk-shaped densified portion,
- wherein, the densified portion has a density that is greater than said first density and is configured to resist a load imparted via said hole;
- and
- a plurality of filament tendrils,
- wherein, the plurality of filament tendrils are configured to wrap around at least a portion of said hole to form a form a “U” shape,
- wherein at least one of said plurality of filament tendrils comprises a carbon fiber material, a para-aramid synthetic fiber material, or a fiberglass material,
- wherein, said plurality of filament tendrils direct stress away from said hole and into the body portion.
The composite aircraft structure of claim 3, wherein said densified portion's diameter is approximately 1.5 to 3 times said hole's diameter.
A composite bearing for use in a composite structure, the composite bearing comprising:
- a densified portion, wherein the densified portion is configured to receive a hole positioned at an approximate center of said densified portion;
- and
- a plurality of filament tendrils, wherein the plurality of filament tendrils are configured to encircle at least a portion of said hole,
- wherein the densified portion is configured to resist a load imparted upon the composite bearing,
- wherein plurality of filament tendrils direct stress away from the composite bearing and into the composite structure.
A composite structure, said composite structure comprising:
- a body portion;
- a densified portion, wherein the densified portion is configured to receive a hole positioned at an approximate center of said densified portion;
- and
- a plurality of filament tendrils,
- wherein, the plurality of filament tendrils are configured to wrap around at least a portion of said hole,
- wherein, the densified portion is configured to resist a load imparted via said hole,
- wherein, said plurality of filament tendrils direct stress away from said hole and into the body portion.
Dependencies are inferred from the claim text.