Composite skin and stringer structure and method for forming the same

• US 8,444,087 B2
• Filed: 04/28/2005
• Issued: 05/21/2013
• Est. Priority Date: 04/28/2005
• Status: Active Grant

• Current Assignee: The Boeing Co.
• Original Assignee: The Boeing Co.
• Inventors: Kismarton, Max U.
• Primary Examiner(s): Lee, Benjamin P
• Application Number:
  US11/118,594
• Publication Number:
  US 20060243860A1
• Time in Patent Office: 2,945 Days
• Field of Search: 244/119, 244/132, 244/133, 428/119, 428/292.1, 428/178, 428/113, 527/301, 527/211, 527/291
• US Class Current: 244/119
• CPC Class Codes: B29C 65/562 using extra joining elements, i.e. which are not integral with the parts to be joined using plastic snap elements B29C65/58; using plastic rivets B29C65/601
• CPC Class Codes: B29C 66/112 Single lapped joints
• CPC Class Codes: B29C 66/1122 Single lap to lap joints, i.e. overlap joints B29C66/45, B29C66/472, B29C66/52272 take precedence
• CPC Class Codes: B29C 66/131 Single flanged joints, i.e. one of the parts to be joined being rigid and flanged in the joint area
• CPC Class Codes: B29C 66/474 said single elements being substantially non-flat
• CPC Class Codes: B29C 66/524 Joining profiled elements
• CPC Class Codes: B29C 66/721 Fibre-reinforced materials B29C66/729 takes precedence
• CPC Class Codes: B29C 66/7212 characterised by the composition of the fibres
• CPC Class Codes: B29C 66/72141 Fibres of continuous length
• CPC Class Codes: B29C 70/228 the structure being stacked in parallel layers with fibres of adjacent layers crossing at substantial angles
• CPC Class Codes: B29C 70/30 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 Class Codes: B29K 2101/00 Use of unspecified macromolecular compounds as moulding material use of unspecified rubbers B29K2021/00
• CPC Class Codes: B29K 2307/00 Use of elements other than metals as reinforcement
• CPC Class Codes: B29K 2307/04 Carbon
• CPC Class Codes: B29L 2031/3076 Aircrafts blades, propellers B29L2031/08
• CPC Class Codes: B64C 1/064 Stringers; Longerons
• CPC Class Codes: B64C 1/12 Construction or attachment of skin panels
• CPC Class Codes: B64C 3/182 Stringers, longerons
• CPC Class Codes: B64C 3/26 Construction, shape, or attachment of separate skins, e.g. panels
• CPC Class Codes: Y02T 50/40 Weight reduction
• CPC Class Codes: Y10T 428/24124 : Fibers

Abstract

Composite stringer and skin structures and methods for forming the same are disclosed. In one embodiment, a composite stringer and skin structure includes a polymer-based elongated stringer portion having reinforcing fibers positioned in a plurality of adjacent plies, a first portion of the reinforcing fibers being oriented at a relatively shallow angle relative to a selected reference direction, and a second portion of the reinforcing fibers being oriented at a relatively broad angle relative to the selected reference direction. A polymer-based and fiber reinforced skin member adjoins the stringer portion, and an adhesive material is interposed between the stringer portion and the skin member.

Claims

1. An aerospace vehicle comprising:

a fiber-reinforced composite stringer having reinforcing fibers positioned in a plurality of adjacent plies, a first one of the plies having reinforcing fibers oriented at a first non-zero angle between approximately zero degrees to twenty degrees relative to a direction of loading, a second one of the plies having reinforcing fibers oriented at about +65 degrees relative to the loading direction, and a third one of the plies having reinforcing fibers oriented at about −

65 degrees relative to the loading direction; and

a skin member secured to a flange of the stringer.

2. The vehicle of claim 1, wherein the first angle is approximately five degrees.

3. The vehicle of claim 1, wherein the stringer and the skin member are comprised of reinforcement fibers having different moduli.

4. A method of fabricating the stringer and skin structure of claim 1, comprising:

forming the stringer by bonding first plies of reinforced fibers oriented at a first angle between approximately zero degrees to twenty degrees relative to a reference direction to second and third plies of reinforced fibers oriented at second and third angles of between approximately +65 degrees and −

65 degrees relative to the selected reference direction; and

adhesively joining the stringer to the skin member.

5. The method of claim 4, wherein forming a stringer member comprises bonding the first plies of the reinforcing fibers oriented at a first angle of approximately five degrees to the second plies of the reinforcing fibers oriented at a second angle of approximately sixty-five degrees.

6. The method of claim 4, wherein the first plies include a first layer oriented at a positive first angle, and a second layer oriented at a negative first angle, and wherein the second plies includes a third layer oriented at a positive second angle, and a fourth layer oriented at a negative second angle.

7. The method of claim 6, wherein forming a stringer member further comprises forming a first layer group, a second layer group, a third layer group and a fourth layer group, wherein forming each layer group includes bonding five layers selected from the first layer, the second layer, the third layer and the fourth layer.

8. The method of claim 7, wherein forming each of the first layer group and the fourth layer group include interposing a third layer between a selected pair of the first and second layers.

9. The method of claim 7, wherein forming each of the second layer group and the third layer group includes interposing the fourth layer between a selected pair of the first and second layers.

10. The method of claim 4, wherein adhesively joining the stringer member to the skin member further comprises curing at least one of the stringer portion and the skin member, interposing a film adhesive between the stringer portion and the skin member, and curing the film adhesive.

11. The method of claim 4, wherein adhesively joining the stringer member to the skin member comprises interposing a paste adhesive between the stringer portion and the skin member.

12. The method of claim 4, further comprising forming at least one aperture that projects through a selected portion of the stringer member and the skin member, inserting a fastener in the at least one aperture, and applying a predetermined torque to the fastener to generate a predetermined compressive force.

13. The vehicle of claim 1, wherein the fibers oriented at the first angle comprise approximately about eighty percent of the total number of fibers in the stringer.

14. A stringer for an aerospace vehicle, the stringer comprising first and second flanges and a web between the flanges, at least one of the flanges and web including first, second and third plies of reinforcing fibers, the fibers in the first ply oriented at a non-zero angle between 0 and 20 degrees with respect to an axis of loading, the fibers in the second and third plies oriented at an angle of about +65 degrees and −

65 degrees with respect to the axis.

15. The stringer of claim 14, wherein the fibers in the first ply are oriented at an angle of approximately five degrees.

16. The stringer of claim 14, wherein the fibers oriented at the angle between 0 and 20 degrees are oriented at about 5 degrees and comprise approximately about eighty percent of the total number of fibers in the flanges.