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US 10,300,668 B2Granted
Composite structure and methods of assembling same
AssigneeThe Boeing Company
InventorThomas Karl Tsotsis
Life of this patent
Estimating the term…
Abstract
A composite structure and method of assembling a composite structure is provided. The composite structure includes a base member having an outer surface and an inner surface. The inner surface defines a channel therethrough. The composite structure further includes a support member coupled to the outer surface. A fabric overwrap is coupled to the support member.
Claims15
A method of forming a composite structure, said method comprising:
- extruding a base member having an outer surface and inner surface;
- coupling at least one of a plurality of pultruded rods and a plurality of unidirectional fiber tows to the outer surface;
- and
- coupling a fabric overwrap to at least one of the plurality of pultruded rods and the plurality of unidirectional fiber tows, wherein coupling the at least one of the plurality of pultruded rods and the plurality of unidirectional fiber tows comprises coupling the plurality of unidirectional fiber tows to the outer surface, wherein the plurality of unidirectional fiber tows comprise a majority of fibers oriented in a first direction and a minority of fibers oriented in a second direction, the minority of fibers configured to hold the majority of fibers together, wherein coupling the fabric overwrap comprises coupling the fabric overwrap comprising strands of structural fibers to the plurality of pultruded rods or the plurality of unidirectional fiber tows and to the outer surface of the base member, and wherein coupling the fabric overwrap further comprises interweaving the strands of structural fibers to and about the base member and the plurality of pultruded rods or the plurality of unidirectional fiber tows.
1 more element
A method of forming a fuselage section, said method comprising:
- extruding a base member having an outer surface and inner surface;
- coupling at least one of a plurality of pultruded rods and a plurality of unidirectional fiber tows to the outer surface;
- and
- coupling a fabric overwrap to the at least one of the plurality of pultruded rods and the plurality of unidirectional fiber tows to form a composite structure;
- and
- coupling the composite structure to a fuselage skin to form the fuselage section, wherein coupling the at least one of the plurality of pultruded rods and the plurality of unidirectional fiber tows comprises coupling the plurality of pultruded rods or the plurality of unidirectional fiber tows to the outer surface, wherein the plurality of unidirectional fiber tows comprise a majority of fibers oriented in a first direction and a minority of fibers oriented in a second direction, the minority of fibers configured to hold the majority of fibers together, and wherein coupling the fabric overwrap comprises coupling the fabric overwrap comprising strands of structural fibers to the plurality of pultruded rods or the plurality of unidirectional fiber tows and to the outer surface of the base member by interweaving the strands of structural fibers to and about the base member and the plurality of pultruded rods or the plurality of unidirectional fiber tows.
3 more elements
Dependencies are inferred from the claim text.