Composite stringer and methods for forming a composite stringer

Patent metadata

Field	Value
Publication number	US-10857751-B2
Application number	US-201916408401-A
Country	US
Kind code	B2
Filing date	May 9, 2019
Priority date	May 9, 2019
Publication date	Dec 8, 2020
Grant date	Dec 8, 2020

Abstract

A composite stringer assembly includes a composite stringer and a radius filler. The composite stringer includes a skin flange, a web, a corner portion extending from the skin flange to the web, an inner surface, and an outer surface. At the corner portion, the outer surface is defined by a first radius of curvature, which is substantially constant between the skin flange and the web. The support structure includes at least one of a skin of a vehicle or a base charge. The radius filler includes a first surface coupled to the inner surface at the corner portion, a second surface configured to couple to the support structure, and a third surface extending between the first surface and the second surface. The first surface of the radius filler is defined by a second radius of curvature, which is substantially constant between the second surface and the third surface.

First claim

What is claimed is:

1. A composite stringer assembly, comprising:
a plurality of composite stringers axially aligned with each other along a longitudinal axis of the plurality of composite stringers, wherein each composite stringer comprises:
a skin flange configured to be coupled to a support structure, wherein the support structure comprises at least one of a skin of a vehicle or a base charge,
a web,
a top flange,
a lower corner portion extending from the skin flange to the web,
an upper corner portion extending from the web to the top flange,
an inner surface extending along the skin flange, the lower corner portion, the web, the upper corner portion, and the top flange, and
an outer surface extending along the skin flange, the lower corner portion, the web, the upper corner portion, and the top flange,
wherein, at the lower corner portion, the outer surface is defined by a first radius of curvature; and

a radius filler comprising:
a first surface coupled to the inner surface at the lower corner portion of each composite stringer,
a second surface configured to couple to the support structure, and
a third surface extending between the first surface and the second surface,
wherein the first surface of the radius filler is defined by a second radius of curvature,

wherein the top flange of a first composite stringer of the plurality of composite stringers has a gage that is different than a gage of the top flange of a second composite stringer of the plurality of composite stringers, and
wherein, along the longitudinal axis: (i) the composite stringer assembly has a total length that is equal to a sum of a respective length of each composite stringer, (ii) the first radius of curvature is substantially constant over the total length of the composite stringer assembly, and (iii) the second radius of curvature is substantially constant over the total length of the composite stringer assembly.

2. The composite stringer assembly of claim 1 , wherein, at the lower corner portion of each composite stringer, the inner surface is defined by the second radius of curvature.

3. The composite stringer assembly of claim 1 , wherein the third surface of the radius filler is defined by a third radius of curvature, which is approximately equal to the second radius of curvature.

4. The composite stringer assembly of claim 1 , wherein, for each composite stringer, the inner surface faces the support structure when the skin flange is coupled to the support structure, and
wherein, for each composite stringer, the outer surface faces away from the support structure when the skin flange is coupled to the support structure.

5. The composite stringer assembly of claim 1 , wherein, for each composite stringer:
the web is a planar portion of the composite stringer extending in a first plane, (ii) the skin flange is a planar portion of the composite stringer extending in a second plane, and
(iii) the first plane is transverse to the second plane.

6. The composite stringer assembly of claim 1 , further comprising an overwrap layer coupled to the third surface of the radius filler and the inner surface at the web of each composite stringer.

7. The composite stringer assembly of claim 1 , wherein the web and the skin flange of the first composite stringer have a gage that is approximately equal to a gage of the web and the skin flange of the second composite stringer.

8. The composite stringer assembly of claim 1 , wherein, for each composite stringer, the gage of the top flange is greater than a gage of the web and a gage of the skin flange.

9. The composite stringer assembly of claim 8 , wherein, for each composite stringer, the web of the composite stringer has a gage that is approximately equal to a gage of the skin flange of the composite stringer.

10. The composite stringer assembly of claim 1 , wherein, for each composite stringer, the first radius of curvature is substantially constant between the skin flange and the web.

11. The composite stringer assembly of claim 1 , wherein the second radius of curvature is approximately equal to a sum of the first radius of curvature and a gage of the skin flange.

12. The composite stringer assembly claim 1 , wherein the second radius of curvature of the first surface is substantially constant between the second surface of the radius filler and the third surface of the radius filler.

13. The composite stringer assembly of claim 1 , wherein the support structure comprises the base charge.

14. A method for forming a composite stringer assembly, comprising:
forming a plurality of composite stringers, wherein forming the plurality of composite stringers comprises for each composite stringer:
forming, from a plurality of plies of composite material: (i) a skin flange, (ii) a web, (iii) a top flange, (iii) a lower corner portion extending from the skin flange to the web, (iv) an upper corner portion extending from the web to the top flange, (v) an inner surface extending along the skin flange, the lower corner portion, the web, the upper corner portion, and the top flange, and (vi) an outer surface extending along the skin flange, the lower corner portion, the web, the upper corner portion, and the top flange, and
forming, at the lower corner portion, the outer surface with a first radius of curvature;

positioning, on a support structure, the plurality of composite stringers in axial alignment with each other along a longitudinal axis, wherein the support structure comprises at least one of a skin of a vehicle or a base charge; and
coupling, to the inner surface of each composite stringer, a radius filler at the lower corner portion of the composite stringer, wherein a first surface of the radius filler is defined by a second radius of curvature,
wherein forming the plurality of composite stringers comprises forming the top flange of a first composite stringer of the plurality of composite stringers with a gage that is different than a gage of the top flange of a second composite stringer of the plurality of composite stringers, and
wherein, along the longitudinal axis: (a) the composite stringer assembly has a total length that is equal to a sum of a respective length of each composite stringer, (b) the first radius of curvature is substantially constant over the total length of the composite stringer assembly, and (c) the second radius of curvature is substantially constant over the total length of the composite stringer assembly.

15. The method of claim 14 , wherein forming the plurality of composite stringers comprises, for each composite stringer, forming the web with a gage that is approximately equal to a gage of the skin flange.

16. The method of claim 14 , wherein forming the plurality of composite stringers comprises forming the first composite stringer and the second composite stringer such that the web and the skin flange of the first composite stringer have a gage that is approximately equal to a gage of the web and the skin flange of the second composite stringer.

17. The method of claim 14 , wherein forming the plurality of composite stringers comprises, for each composite stringer, forming the gage of the top flange to be greater than a gage of the web and a gage of the skin flange.

18. The method of claim 14 , wherein forming the plurality of composite stringers comprises, for each composite stringer, forming the web with a gage that is approximately equal to a gage of the skin flange of the composite stringer.

19. The method of claim 14 , wherein, for each composite stringer, t

Assignees

• Boeing Co

Inventors

• Cheng Jiangtian

Classifications

• B29D99/0014 Primary

  provided with ridges or ribs, e.g. joined ribs · CPC title

• B29D99/0005

  Producing noodles, i.e. composite gap fillers, characterised by their construction · CPC title

• B29C70/30

  Shaping by lay-up, i.e. applying fibres, tape or broadsheet on a mould, former or core; Shaping by spray-up, i.e. spraying of fibres on a mould, former or core · CPC title

• B64C1/064 Primary

  Stringers; Longerons · CPC title

• B64F5/10

  Manufacturing or assembling aircraft, e.g. jigs therefor · CPC title