Aeropspace structure including composite beam chord clamped between reinforcement plates

• US 9,302,427 B2
• Filed: 08/30/2010
• Issued: 04/05/2016
• Est. Priority Date: 03/31/2005
• Status: Active Grant

• Current Assignee: The Boeing Co.
• Original Assignee: The Boeing Co.
• Inventors: Kismarton, Max U.
• Primary Examiner(s): WENDELL, MARK R
• Application Number:
  US12/871,262
• Publication Number:
  US 20100320320A1
• Time in Patent Office: 2,045 Days
• Field of Search: 521/261, 523/091.6, 525/78, 525/926, 528/31, 528/37, 528/41, 248/188.2, 428/298.1, 428/299.1, 428/299.4, 428/105, 428/107, 428/109, 428/113, 428/292.1, 428/293.1, 244/123, 244/119, 244/133, 442/218, 442/268, 442/269, 442/271, 442/277, 442/278
• US Class Current: 1/1
• CPC Class Codes: B29C 43/24 Calendering
• CPC Class Codes: B29C 65/08 using ultrasonic vibrations non-plastics element to plastics elements B29C65/645
• 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 65/564 hidden in the joint, e.g. dowels or Z-pins B29C65/603 takes precedence
• CPC Class Codes: B29C 65/72 by combined operations or combined techniques, e.g. welding and stitching
• 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 66/304 Joining through openings in an intermediate part of the article B29C66/3034 takes precedence
• CPC Class Codes: B29C 66/45 Joining of substantially the whole surface of the articles methods or apparatus for laminating B32B37/00
• 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 66/7392 characterised by the material of at least one of the parts being a thermoplastic
• CPC Class Codes: B29C 66/7394 characterised by the material of at least one of the parts being a thermoset
• CPC Class Codes: B29C 66/742 to metals or their alloys
• CPC Class Codes: B29C 70/24 oriented in at least three directions forming a three dimensional structure
• CPC Class Codes: B29C 70/545 Perforating, cutting or machining during or after moulding
• CPC Class Codes: B29K 2105/101 Oriented
• CPC Class Codes: B29K 2105/162 Nanoparticles
• CPC Class Codes: B29K 2277/10 Aromatic polyamides [Polyaramides] or derivatives thereof
• CPC Class Codes: B29K 2283/00 Use of polymers having silicon, with or without sulfur, nitrogen, oxygen or carbon only, in the main chain, as reinforcement
• CPC Class Codes: B29K 2307/00 : Use of elements other than metals as reinforcement
• CPC Class Codes: B29K 2307/02 : Boron
• CPC Class Codes: B29K 2307/04 : Carbon
• CPC Class Codes: B29K 2309/04 : Carbides; Nitrides
• CPC Class Codes: B29K 2309/08 : Glass
• CPC Class Codes: B29K 2705/00 : Use of metals, their alloys or their compounds, for preformed parts, e.g. for inserts
• CPC Class Codes: B29L 2031/3082 : Fuselages
• CPC Class Codes: B32B 15/14 : next to a fibrous or filamentary layer
• CPC Class Codes: B32B 15/20 : comprising aluminium or copper B32B15/016 and B32B15/017 take precedence
• CPC Class Codes: B32B 2260/021 : Fibrous or filamentary layer layers of natural mineral fibres or particles being impregnated in a plastic substance B32B19/02
• CPC Class Codes: B32B 2260/04 : Impregnation, embedding, or binder material
• CPC Class Codes: B32B 2260/046 : Synthetic resin
• CPC Class Codes: B32B 2262/0269 : Aromatic polyamide fibres
• CPC Class Codes: B32B 2262/10 : Inorganic fibres layered products comprising a layer of natural mineral fibres B32B19/00
• CPC Class Codes: B32B 2262/101 : Glass fibres
• CPC Class Codes: B32B 2262/103 : Metal fibres
• CPC Class Codes: B32B 2262/106 : Carbon fibres, e.g. graphite fibres
• CPC Class Codes: B32B 2307/50 : having particular mechanical properties
• CPC Class Codes: B32B 2307/546 : Flexural strength; Flexion stiffness
• CPC Class Codes: B32B 2307/718 : Weight, e.g. weight per square meter
• CPC Class Codes: B32B 2605/18 : Aircraft blades, propellers B32B2603/00
• CPC Class Codes: B32B 3/266 : characterised by an apertured layer, the apertures going through the whole thickness of the layer, e.g. expanded metal, perforated layer, slit layer regular cells B32B3/12
• CPC Class Codes: B32B 5/022 : Non-woven fabric
• CPC Class Codes: B32B 5/06 : characterised by a fibrous or filamentary layer mechanically connected, e.g. by needling to another layer, e.g. of fibres, of paper
• CPC Class Codes: B32B 5/12 : 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 Class Codes: B32B 5/22 : characterised by the presence of two or more layers which are next to each other and are fibrous, filamentary, formed of particles or foamed layer formed of natural mineral fibres or particles next to a foam layer B32B19/047, next to a layer made of particles B32B19/048, or next to a fibrous or filamentary layer B32B19/06; paper layer or cardboard layer next to a paper layer or cardboard layer B32B29/005, next to a foam layer B32B29/007, next to a fibrous or filamentary layer B32B29/02, or next to a particulate layer B32B29/04
• CPC Class Codes: B32B 5/26 : another layer next to it also being fibrous or filamentary relative arrangement of fibres or filaments of different layers B32B5/12
• CPC Class Codes: B64C 1/065 : Spars
• CPC Class Codes: E04C 3/29 : built-up from parts of different material, i.e. composite structures
• CPC Class Codes: Y02T 50/40 : Weight reduction

Abstract

A structure for an aerospace vehicle includes a composite beam chord clamped between first and second metal plates. The beam chord is clamped at a force that precludes or reduces beam chord delamination under axial loading during operation of the vehicle.

Claims

1. A structure for an aerospace vehicle, the structure comprising:

first and second metal plates; and

a beam chord permanently clamped between the first and second metal plates at a force that precludes or reduces delamination of the beam chord under axial loading during operation of the vehicle, the beam chord having a longitudinal axis and comprising a plurality of plies of reinforcing fibers extending in an x-y plane, wherein the reinforcing fibers of at least 60 percent of the plies of the plurality of plies are oriented at ±

α

degrees with respect to the longitudinal axis, where α

is from 2 to 12 degrees.

2. The structure of claim 1, wherein holes are drilled through the plurality of plies in a z-direction;

and wherein fasteners extend through the holes to clamp the plates to the beam chord.

3. The structure of claim 2, wherein the fasteners include pre-tensioned bolts.

4. The structure of claim 1, wherein the plurality of plies comprises plies having the reinforcing fibers oriented at ±

β

degrees with respect to the longitudinal axis, where β

is between 15 and 85 degrees.

5. The structure of claim 1, wherein the composite beam chord includes carbon fibers in a polymer matrix.

6. The structure of claim 1, wherein the plates are aluminum or titanium plates.

7. The structure of claim 1 further comprising at least one attachment plate positioned between the beam chord and at least one of the first and second reinforcement plates, the attachment plate including a plurality of apertures for attaching to external structures.

8. The structure of claim 1, further comprising:

a second beam chord clamped between third and fourth metal plates at a force that precludes or reduces delamination of the second beam chord under axial loading during operation of the vehicle; and

a splicing plate for splicing the first and second beam chords together; and

a plurality of fasteners extending through the splicing plate and the first and second beam chords.

9. The structure of claim 1, wherein the structure is an aircraft keel beam.

10. The structure of claim 1, wherein the beam chord is elongated along the longitudinal axis and has a first longitudinal length, wherein the first metal plate has a second longitudinal length, and wherein the first longitudinal length is substantially the same as the second longitudinal length.

11. An aerospace structure comprising a shear web and first and second end caps for the shear web, each end cap including the beam chord and plates of claim 1.

12. The aerospace structure of claim 11, wherein each beam chord includes stacks of composite plates on opposite sides of the shear web, wherein the plates are at opposite ends of the stacks, and wherein the shear web, stacks and plates are clamped together.

13. The structure of claim 11, wherein the structure is a wing stringer.

14. The structure of claim 11, wherein the structure is a landing gear beam.

15. The structure of claim 11, wherein the structure is a floor beam.

16. An aerospace vehicle comprising a fuselage, and wing assemblies coupled to the fuselage, at least one of the fuselage and the wing assemblies including a structure having first and second plates, a beam chord between the plates, and fasteners for clamping the beam chord between the plates at a force that precludes or reduces delamination of the beam chord under axial loading during operation of the vehicle, the beam chord having a longitudinal axis and comprising a plurality of plies of reinforcing fibers extending in an x-y plane, wherein the reinforcing fibers of at least 60 percent of the plies of the plurality of plies are oriented at ±

α

degrees with respect to the longitudinal axis, where α

is from 2 to 12 degrees.

17. The vehicle of claim 16, wherein the structure is a fuselage keel beam.

18. The vehicle of claim 16, wherein the structure is a fuselage floor beam.

19. The vehicle of claim 16, wherein the structure is a wing assembly stringer.

20. The vehicle of claim 16, wherein the structure is a landing gear beam.

21. A fuselage comprising a keel beam including first and second metal plates and a beam chord permanently clamped between the plates at a force that precludes or reduces delamination of the beam chord under service conditions, the beam chord having a longitudinal axis and comprising a plurality of plies of reinforcing fibers extending in an x-y plane, wherein the reinforcing fibers of at least 60 percent of the plies of the plurality of plies are oriented at ±

α

degrees with respect to the longitudinal axis, where α

is from 2 to 12 degrees.