COMPOSITE LAMINATED PLATE HAVING REDUCED CROSSPLY ANGLE

• US 20160009368A1
• Filed: 02/28/2013
• Published: 01/14/2016
• Est. Priority Date: 02/28/2013
• Status: Abandoned Application

• Current Assignee: The Boeing Co.
• Original Assignee: The Boeing Co.
• Inventors: Kismarton, Max U.
• Application Number:
  US13/780,382
• Publication Number:
  US 20160009368A1
• Time in Patent Office: Days
• US Class Current: 1/1
• CPC Class Codes: B29C 70/207 arranged in parallel planes of fibres crossing at substantial angles
• CPC Class Codes: B32B 2260/023 Two or more layers
• CPC Class Codes: B32B 2260/046 Synthetic resin
• 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 2307/542 Shear strength
• CPC Class Codes: B32B 2307/546 Flexural strength; Flexion stiffness
• CPC Class Codes: B32B 2307/558 Impact strength, toughness
• CPC Class Codes: B32B 2605/18 Aircraft blades, propellers B32B2603/00
• CPC Class Codes: B32B 37/12 characterised by using adhesives
• 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 5/26 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 3/26 Construction, shape, or attachment of separate skins, e.g. panels
• 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 composite laminated plate comprising a first plurality of plies of reinforcing fibers for lengthwise strength with respect to a dominant load direction, and a second plurality of reinforcing fibers oriented at angles ±β with respect to the dominant load direction, where β is between 15 and 35 degrees.

Claims

1. A composite laminated plate comprising a first plurality of plies of reinforcing fibers for lengthwise strength with respect to a dominant load direction, and a second plurality of reinforcing fibers oriented at angles ±

β

with respect to the dominant load direction, where β

is between 15 and 35 degrees.

2. The plate of claim 1, wherein β

is about 25 degrees.

3. The plate of claim 1, wherein the angles of the β

-fibers are blurred.

4. The plate of claim 1, wherein the first plurality of plies of reinforcing fibers are oriented at angles ±

α

with respect to the dominant load direction, where α

is between 2 and 12 degrees.

5. The plate of claim 4, wherein the angles of the α

-fibers are blurred.

6. The plate of claim 1, further comprising a third plurality of plies of reinforcing fibers oriented at an angle γ

with respect to the dominant load direction, where γ

is between 87 and 92 degrees.

7. The plate of claim 1, further comprising a matrix, wherein the fibers are embedded in the matrix.

8. The plate of claim 7, wherein the matrix is a plastic matrix, and wherein the fibers include carbon fibers embedded in the plastic matrix.

9. The plate of claim 1, wherein a greater percentage of fibers is used in the first plurality than the second plurality.

10. A structure having a dominant load direction, the structure comprising a laminated composite plate including a plurality of plies of α

-fibers oriented at angles +α and

−

α

with respect to an x-axis; and

a plurality of plies of β

-fibers oriented at angles +β and

−

β

with respect to the x-axis, where β

is between 15 and 35 degrees, and where α

is 0 degrees or between 2 and 12 degrees.

11. The structure of claim 10, further comprising a box beam stiffening substructure subject to bending that creates lengthwise forces along the x-axis;

wherein the plate is attached to the stiffening substructure.

12. The structure of claim 10, further comprising a beam including a web and flange;

wherein the plate is attached to the flange as a cap.

13. A box beam comprising a stiffening substructure;

a first laminated plate covering one side of the substructure; and

a second laminated plate covering an opposite side of the substructure, each plate including a first plurality of reinforcing fibers oriented at an angle between 15 and 35 degrees with respect to a longitudinal axis of the substructure.

14. The box beam of claim 13, wherein each plate further includes a second plurality of reinforcing fibers oriented at an angle between 2 and 12 degrees with respect to the longitudinal axis of the substructure.

15. The box beam of claim 14, wherein a greater percentage of fibers is used in the second plurality than the first plurality.

16. A method of forming a plate having an x-axis, the method comprising forming a ply stack including a first plurality of reinforcing fibers oriented at an angle ±

α

with respect to the x-axis, and a second plurality of reinforcing fibers oriented at an angle ±

β

with respect to the x-axis, where β

is between 15 and 35 degrees, and α

is 0 degrees or between 2 and 12 degrees.

17. The method of claim 16, further comprising laying up a third plurality of fibers at an angle of γ

with respect to the x-axis, where γ

is between 87 and 92 degrees.

18. The method of claim 16, further comprising laying up integral stiffeners on the ply stack.

19. The method of claim 16, further comprising embedding the fibers in a resin, and curing the ply stack.

20. The method of claim 19, further comprising cutting fibers in the cured ply stack.