Shaped composite stringers and methods of making

• US 7,861,969 B2
• Filed: 05/24/2007
• Issued: 01/04/2011
• Est. Priority Date: 05/24/2007
• Status: Active Grant

• Current Assignee: The Boeing Co.
• Original Assignee: The Boeing Co.
• Inventors: Rotter, Daniel M., Robins, Brian G., McCarville, Douglas A., Guzman, Juan C.
• Primary Examiner(s): Michener; Joshua J
• Application Number:
  US11/753,482
• Publication Number:
  US 20080290214A1
• Time in Patent Office: 1,321 Days
• Field of Search: 244/119, 244/120, 244/123.1, 244/123.3, 526/30
• US Class Current: 244/120
• 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 stiffened skin panel of an aircraft comprising:

a composite aircraft skin panel; and

a composite stringer consolidated with the aircraft skin panel, the stringer comprising a first stringer side and a second stringer side, wherein the first stringer side extends from a stringer top through a first stringer leg and a second stringer side extends from the stringer top through a second stringer leg, the first stringer side and second stringer side each extending in a continuous curve from the stringer top through 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 further characterized by at least a first convex section and at least a first concave section.

2. The stiffened skin panel of claim 1, wherein the composite stringer is substantially bell-shaped in cross section.

3. The stiffened skin panel of claim 1, wherein the stringer top comprises a substantially flat stringer top or a substantially curved shape.

4. The stiffened skin panel of claim 1, wherein the composite stringer comprises consolidated stacked tape plies, at least some of the stacked tape plies oriented in different directions.

5. The stiffened skin panel of claim 1 further comprising an attachment zone comprising a portion of the composite stringer leg and a portion of the composite aircraft skin panel proximate the composite stringer leg, the attachment zone comprising a point of attachment between the composite stringer and the composite aircraft skin panel, the attachment zone further comprising a cured resin and filler material common to the stringer leg and the panel.

6. The stiffened skin panel of claim 5, wherein the attachment zone is substantially free of excess resin.

7. The stiffened skin panel of claim 1 wherein the curve extending from the stringer top to the inflection point defines a first stringer section curve which is characterized by a first radius of curvature and wherein the curve extending from the inflection point to the stringer leg defines a second stringer section curve which is characterized by a second radius of curvature, and wherein the second radius of curvature is greater than the first radius of curvature.

8. The stiffened skin panel of claim 1 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.

9. The stiffened skin panel of claim 1 wherein a 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.

10. The stiffened skin panel of claim 1 wherein the curve is characterized by a first inflection point and a second inflection point on each stringer leg.

11. The stiffened skin panel of claim 10 wherein the first inflection point is proximate the top and the second inflection point is proximate the panel, and wherein a tangent line to the curve at the second inflection point is set an angle to the panel of between about 35 to about 65 degrees.

12. The stiffened skin panel of claim 1 wherein the composite stringer comprises composite material draped naturally to conform to the smooth continuous curve shape of each stringer side.

13. The stiffened skin panel of claim 1 further comprising a transition zone on each stringer side, the transition zone characterized by at least one characteristic selected from the group consisting of minimal excess resin accumulation, minimal fiber parting, minimal delamination, minimal fiber wrinkling, minimal in-plane waviness, minimal narcelling, and minimal porosity in the matrix resin.

14. A stiffened panel comprising:

a panel comprising composite material;

a stringer consolidated with the panel, the stringer comprising composite material, the stringer comprising a first stringer side and a second stringer side, wherein the first stringer side extends from a stringer top in a smooth continuous curve through a first stringer leg and the second stringer side extends from the stringer top in a smooth continuous curve through a second stringer leg;

wherein the curve of each stringer side is characterized by at least one inflection point such that the curve of each stringer side is further characterized by at least a first convex section and at least a first concave section; and

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.

15. The stiffened panel of claim 14, wherein the stringer comprisesconsolidated stacked tape plies, at least some of the stacked tape plies oriented in different directions.

16. The stiffened panel of claim 14, wherein the attachment zone is substantially free of excess resin.

17. The stiffened panel of claim 14, wherein the attachment zone is substantially free of composite fibers separated from and protruding from fibrous material of the stringer.