Shaped composite stringers and methods of making

• US 8,377,247 B2
• Filed: 12/22/2010
• Issued: 02/19/2013
• Est. Priority Date: 05/24/2007
• Status: Active Grant

• Current Assignee: The Boeing Co.
• Original Assignee: The Boeing Co.
• Inventors: Guzman, Juan C., McCarville, Douglas A., Rotter, Daniel M., Robins, Brian G.
• Primary Examiner(s): SCHATZ, CHRISTOPHER T
• Application Number:
  US12/976,070
• Publication Number:
  US 20110088833A1
• Time in Patent Office: 790 Days
• Field of Search: 156/285, 156/286, 156/381, 156/382, 156/212, 156/213, 156/215, 264/510, 264/511, 244/119, 244/120, 244/123, 244/123.3
• US Class Current: 156/285
• CPC Class Codes: B29C 2043/3649 Inflatable bladders using gas or fluid and related details
• CPC Class Codes: B29C 43/10 Isostatic pressing, i.e. using non-rigid pressure-exerting members against rigid parts or dies
• CPC Class Codes: B29C 70/342 using isostatic pressure
• CPC Class Codes: B29D 99/0014 provided with ridges or ribs, e.g. joined ribs
• CPC Class Codes: B29L 2022/00 Hollow articles tubular articles B29L2023/00; pneumatic tyres B29L2030/00
• CPC Class Codes: B29L 2031/54 Balls
• CPC Class Codes: B64C 1/064 Stringers; Longerons
• CPC Class Codes: B64C 2001/0072 from composite materials
• CPC Class Codes: B64C 3/182 Stringers, longerons
• CPC Class Codes: Y02T 50/40 Weight reduction
• CPC Class Codes: Y10T 156/1028 by bending, drawing or stretch forming sheet to assume shape of configured lamina while in contact therewith
• CPC Class Codes: Y10T 428/31504 Composite [nonstructural laminate]

Abstract

A stiffened skin panel of an aircraft that includes an aircraft skin panel of composite material and a composite stringer consolidated with the aircraft skin panel. The stringer has a pair of stringer sides, each extending from a stringer top to a stringer leg. The stringer sides may each extend through a wide radius, smooth continuous curve to a stringer leg. The wide radius, smooth continuous curve may be proximate the base of the stringer side in a region where the stringer side transitions to the stringer leg.

Claims

1. A method for fabricating a composite stringer on a composite panel, the method comprising the steps of:

placing a form on a first surface of the composite panel;

draping a composite material over the form so as to form a lay up;

enclosing the composite panel and lay up-covered form with a vacuum bag; and

consolidating the lay up to the composite panel so as to form a stringer wherein the stringer is characterized by a profile having a first stringer side and a second stringer side, wherein the first stringer side extends from a stringer top to a first stringer leg and a second stringer side extends from the stringer top to a second stringer leg, the first stringer side and second stringer side each extending in a continuous curve from the stringer top to a respective stringer leg and wherein the curve of each stringer side is characterized by at least one inflection point such that the curve of each stringer side is characterized by at least a first convex section and at least a first concave section.

2. The method according to claim 1 further comprising the step of positioning a second surface of the composite panel on a mold tool.

3. The method according to claim 1, wherein the step of consolidating the lay up to the composite panel further comprises consolidating with heat and pressure.

4. The method according to claim 1, wherein the composite material comprises tape.

5. The method according to claim 1, wherein the composite material comprises woven fabric.

6. The method according to claim 1, wherein the form is one of a bladder or a mandrel.

7. The method according to claim 6 further comprising the step of inflating and deflating the bladder.

8. The method according to claim 1 further comprising the step of determining a location and spacing of stringers on the composite panel.

9. The method according to claim 1, wherein the step of consolidating further comprises consolidating a footing of the composite material with the composite panel.

10. The method according to claim 1 excluding a step of preforming the stringer.

11. A method for fabricating a composite stringer on a composite panel, the method comprising the steps of:

positioning a first surface of the composite panel on a mold tool;

placing a form on a second surface of the composite panel, wherein the form is one of a bladder or a mandrel;

draping a composite material over the form so as to form a lay up;

enclosing the composite panel and lay up-covered forms with a vacuum bag; and

consolidating the lay up to the composite panel with heat and pressure so as to form a stringer wherein the stringer is characterized by a profile having a first stringer side and a second stringer side, wherein the first stringer side extends from a stringer top to a first stringer leg and a second stringer side extends from the stringer top to a second stringer leg, the first stringer side and second stringer side each extending in a continuous curve from the stringer top to a respective stringer leg and wherein the curve of each stringer side is characterized by at least one inflection point such that the curve of each stringer side is characterized by at least a first convex section and at least a first concave section.

12. The method according to claim 11, wherein the stringer is characterized by an attachment zone comprising a portion of the stringer and a portion of the panel comprising a stringer point of attachment to the panel, the attachment zone also comprising cured resin.

13. The method according to claim 11, wherein the lay up comprises a plurality of tape plies, wherein each tape ply in the plurality of tape plies is characterized by an orientation, and wherein the plurality of tape plies comprise different orientations.

14. The method according to claim 11, wherein a stringer side is characterized by a substantially flat top and a curve that extends from the top to the panel with a tangent to the curve at the inflection point set at an angle of substantially 90 degrees to the panel.

15. The method according to claim 11, wherein the stringer side is characterized by a curve that extends downward to the panel with a tangent to the curve at the inflection point set at an angle to the panel wherein the angle is between about 35 to about 65 degrees.

16. A method of fabricating a composite panel with a composite stringer, the method comprising:

determining location and spacing of stringers on a composite panel;

positioning the composite panel on a mold tool;

laying down on the composite panel, at determined locations and spacing, forms conforming to a shape of the stringers to be formed;

preparing lay ups of composite material for forming into stringers;

laying a prepared lay up of composite material over each of the forms;

enclosing at least the composite panel and lay up-covered forms with a vacuum bag; and

consolidating the stringers to the composite panel under heat and pressure so as to produce a stiffened composite panel, wherein the stringer is characterized by a profile having a first stringer side and a second stringer side, wherein the first stringer side extends from a stringer top to a first stringer leg and a second stringer side extends from the stringer top to a second stringer leg, the first stringer side and second stringer side each extending in a continuous curve from the stringer top to a respective stringer leg and wherein the curve of each stringer side is characterized by at least one inflection point such that the curve of each stringer side is characterized by at least a first convex section and at least a first concave section.

17. The method of claim 16, wherein the step of positioning comprises positioning in an outside mold line tool.

18. The method of claim 16, wherein the step of consolidating comprises forming an attachment zone substantially free of composite fibers separated from and protruding from fibrous material of the stringer, and substantially free of excess resin.