All-fabric spar for aerodynamic components

Patent metadata

Field	Value
Publication number	US-11440652-B2
Application number	US-201816056610-A
Country	US
Kind code	B2
Filing date	Aug 7, 2018
Priority date	Aug 7, 2018
Publication date	Sep 13, 2022
Grant date	Sep 13, 2022

Abstract

Embodiments are directed to systems and methods for creating a tubular composite structure. In one embodiment, a device comprises multiple layers of cured composite fabric bonded together to form a tubular composite structure, wherein alternating groups of the multiple layers comprise on-axis fabric and off-axis fabric. The tubular composite structure may form a spar for an aerodynamic component. The composite fabric may comprise one or more of carbon, fiberglass, or other composite materials, or a combination of materials. One or more stacks of the fabric wrap completely around the tubular composite structure, and other stacks of fabric may not wrap completely around the tubular composite structure.

First claim

What is claimed is:

1. A method for manufacturing a tubular composite structure, comprising:
circumferentially laying up a first stack of a plurality of composite fabric layers all the way around a mandrel, wherein the layers in the first stack comprise a woven fabric having a first axis of orientation;
laying up a second stack of composite fabric layers partially around the first stack after the first stack has been laid up around the mandrel, wherein the layers in the second stack comprise a woven fabric having a second axis of orientation, wherein the first axis of orientation is different than the second axis of orientation;
laying up additional stacks of composite fabric on top of the first and second stacks and around the mandrel, wherein the additional stacks comprise fabric having the first axis of orientation alternating with stacks having the second axis of orientation; and
curing the first, second, and additional stacks of composite fabric layers to form the tubular composite structure.

2. The method of claim 1 , further comprising:
laying up limited stacks of composite fabric interleaved with the additional stacks of composite fabric, wherein the limited stacks of composite fabric wrap partially around the mandrel.

3. The method of claim 1 , wherein the tubular composite structure forms a spar for an aerodynamic component.

4. The method of claim 1 , wherein the composite fabric comprises one or more of carbon and fiberglass composite materials.

5. The method of claim 1 , wherein the woven fabric having the first axis of orientation and the woven fabric having the second axis of orientation comprise the same composite material.

6. The method of claim 1 , wherein the woven fabric having the first axis of orientation comprises a first set of fibers oriented in a first direction, and a second set of fibers oriented generally orthogonal to the first direction.

7. The method of claim 6 , wherein the woven fabric having the second axis of orientation comprises a third set of fibers that are oriented at an angle relative to the first set of fibers in the woven fabric having the first axis of orientation, and the woven fabric having the second axis of orientation further comprises a fourth set of fibers oriented generally orthogonal to the third set of fibers.

8. The method of claim 7 , wherein the angle is selected from 15-degrees to 75 degrees.

9. The method of claim 1 , wherein the tubular composite structure has a spanwise axis, and wherein the woven fabric having the first axis of orientation comprises a first set of fibers oriented generally parallel to the spanwise axis, and a second set of fibers oriented generally orthogonal to the spanwise axis, and wherein the woven fabric having the second axis of orientation comprises a third set of fibers oriented at angle of 15-degrees to 75-degrees relative to the spanwise axis, and the woven fabric having the second axis of orientation comprises a fourth set of fibers oriented generally orthogonal to the third set of fibers.

10. A method for manufacturing a tubular composite structure, comprising:
circumferentially laying up a first stack of a plurality of composite fabric layers all the way around a mandrel, wherein the layers in the first stack comprise a woven fabric comprising a first axis of orientation including at least one of an on-axis orientation and an off-axis orientation;
laying up a second stack of composite fabric layers partially around the first stack after the first stack has been laid up around the mandrel, wherein the layers in the second stack comprise a woven fabric with a second axis of orientation including at least one of the on-axis orientation and the off-axis orientation, wherein the second axis of orientation of the second stack is different than the first axis of orientation;
laying up additional stacks of composite fabric on top of the first and second stacks and around the mandrel, wherein the additional stacks comprise fabric having the first axis of orientation alternating with stacks having the second axis of orientation; and
curing the first, second, and additional stacks of composite fabric layers to form the tubular composite structure.

11. The method of claim 10 , further comprising:
laying up limited stacks of composite fabric interleaved with the additional stacks of composite fabric, wherein the limited stacks of composite fabric wrap partially around the mandrel.

12. The method of claim 10 , wherein the tubular composite structure forms a spar for an aerodynamic component.

13. The method of claim 10 , wherein the composite fabric comprises one or more of carbon and fiberglass composite materials.

14. The method of claim 10 , wherein the woven fabric having the first axis of orientation and the woven fabric having the second axis of orientation comprise the same composite material.

15. The method of claim 10 , wherein the woven fabric having the first axis of orientation comprises a first set of fibers oriented in a first direction, and a second set of fibers oriented generally orthogonal to the first direction.

16. The method of claim 15 , wherein the woven fabric having the second axis of orientation comprises a third set of fibers that are oriented at an angle relative to the first set of fibers in the woven fabric having the first axis of orientation, and the woven fabric having the second axis of orientation further comprises a fourth set of fibers oriented generally orthogonal to the third set of fibers.

17. The method of claim 16 , wherein the angle is selected from 15-degrees to 75 degrees.

18. The method of claim 10 , wherein the tubular composite structure has a spanwise axis, and wherein the woven fabric having the first axis of orientation comprises a first set of fibers oriented generally parallel to the spanwise axis, and a second set of fibers oriented generally orthogonal to the spanwise axis, and wherein the woven fabric having the second axis of orientation comprises a third set of fibers oriented at angle of 15-degrees to 75-degrees relative to the spanwise axis, and the woven fabric having the second axis of orientation comprises a fourth set of fibers oriented generally orthogonal to the third set of fibers.

Assignees

• Bell Helicopter Textron Inc
• Textron Innovations Inc

Inventors

• Foskey Christopher Edward
• Paulson Jared Mark
• Burnett Michael Christopher
• Mays Mark

Classifications

• B32B5/12

  characterised by the relative arrangement of fibres or filaments of {different layers, e.g. the fibres or filaments being parallel or perpendicular to each other} · CPC title

• B32B2305/076

  Prepregs · CPC title

• B32B2305/188

  Woven fabrics · CPC title

• B29C70/54

  Component parts, details or accessories; Auxiliary operations {, e.g. feeding or storage of prepregs or SMC after impregnation or during ageing} · CPC title

• B32B2307/554

  Wear resistance · CPC title