Multi-piece assembly for a tubular composite body

Patent metadata

Field	Value
Publication number	US-11565800-B2
Application number	US-201816048869-A
Country	US
Kind code	B2
Filing date	Jul 30, 2018
Priority date	Jul 30, 2018
Publication date	Jan 31, 2023
Grant date	Jan 31, 2023

Abstract

Embodiments are directed to systems and methods for two or more cured composite assemblies that are bonded together to form a tubular composite structure, wherein each of the cured composite assemblies do not have a tubular shape. The tubular composite structure may form a spar for an aerodynamic component, for example. The two or more cured composite assemblies may comprise carbon or fiberglass composite materials or a combination of materials. Each of the cured composite assemblies may further comprise axial edges that are configured to be bonded to another of the cured composite assemblies, wherein the axial edges have a sloped shape. An adhesive agent may be applied on the axial edges for bonding two cured composite assemblies. Alternatively, or additionally, one or more fasteners may be used to attach the axial edges of at least two cured composite assemblies.

First claim

What is claimed is:

1. A device, comprising:
two or more cured composite components each having a component outer surface, the composite component parts bonded together to form a composite structure in which the component outer surface of each component forms at least a portion of an overall outer surface of the composite structure, wherein each of the cured composite assemblies do not have a tubular shape;
one or more composite torque-wrap plies laid up inside the composite components; and
one or more composite plies wrapped around the two or more cured composite components, wherein the one or more composite plies and an assembly of the two or more cured composite components have been co-cured using an adhesive agent.

2. The device of claim 1 , wherein the composite structure forms a spar for an aerodynamic component.

3. The device of claim 1 , wherein the two or more cured composite components comprise at least one of carbon and fiberglass composite materials.

4. The device of claim 1 , wherein each of the cured composite components further comprise:
an aerodynamic component configured to be bonded to another of the cured composite components, and wherein at least one axial edge has a sloped shape.

5. The device of claim 4 , further comprising:
an adhesive agent on the at least one axial edge for bonding the two cured composite components.

6. The device of claim 1 , wherein each of the cured composite components further comprise:
at least one axial edge configured to be bonded to another of the cured composite components, and one or more fasteners attaching the axial edges of the at least two cured composite components.

7. The device of claim 1 , further comprising:
one or more composite plies wrapped around an assembled and bonded two or more cured composite components.

8. A rotor blade for an aircraft, the rotor blade comprising:
two or more cured composite components each having a component outer surface, the composite component parts bonded together to form a composite structure in which the component outer surface of each component forms at least a portion of an overall outer surface of the composite structure, wherein each of the cured composite assemblies do not have a tubular shape;
one or more composite torque-wrap plies laid up inside the composite components; and
one or more composite plies wrapped around the two or more cured composite components, wherein the one or more composite plies and an assembly of the two or more cured composite components have been co-cured using an adhesive agent.

9. The rotor blade of claim 8 , wherein the two or more cured composite components comprise at least one of carbon and fiberglass composite materials.

10. The rotor blade of claim 8 , wherein each of the cured composite components further comprise:
an aerodynamic component configured to be bonded to another of the cured composite components, and wherein at least one axial edge has a sloped shape.

11. The rotor blade of claim 10 , further comprising:
an adhesive agent on the at least one axial edge for bonding the two cured composite components.

12. The rotor blade of claim 8 , wherein each of the cured composite components further comprise:
at least one axial edge configured to be bonded to another of the cured composite components, and one or more fasteners attaching the axial edges of the at least two cured composite component.

13. The rotor blade of claim 8 , further comprising:
one or more composite plies wrapped around an assembled and bonded two or more cured composite components.

Assignees

• Bell Helicopter Textron Inc
• Textron Innovations Inc

Inventors

• Paulson Jared Mark
• Mays Mark
• Burnett Michael Christopher

Classifications

• B29L2031/082

  Blades, e.g. for helicopters · CPC title

• Y10T428/13

  Hollow or container type article [e.g., tube, vase, etc.] · CPC title

• B64C3/185

  Spars · CPC title

• B32B2603/00

  Vanes, blades, propellers, rotors with blades · CPC title

• B32B1/08

  Tubular products · CPC title