Composite material structure, aircraft wing and aircraft fuselage provided with same, and method for manufacturing composite material structure

Patent metadata

Field	Value
Publication number	US-10137664-B2
Application number	US-201515117895-A
Country	US
Kind code	B2
Filing date	Mar 17, 2015
Priority date	Mar 28, 2014
Publication date	Nov 27, 2018
Grant date	Nov 27, 2018

Abstract

In a composite material structure, which is configured as a fiber-reinforced plastic composite material extending in one direction and having a plurality of holes defined at intervals in a row in the one direction and which is subjected to a tensile load and/or a compressive load in the one direction, a peripheral region around the holes comprises a first area obtained by bending composite material, which is reinforced using continuous fibers that have been made even in a longitudinal direction, so that a center line of a width of the composite material weaves between adjacent holes and zigzags in the one direction. A tensile rigidity and/or a compressive rigidity in the one direction of the peripheral region around the holes is lower than a tensile rigidity and/or a compressive rigidity in the one direction of other regions that surround the peripheral region.

First claim

The invention claimed is:

1. A composite material structure, comprising a fiber-reinforced plastic composite material extending in one direction, wherein the one direction is 0°, and having a plurality of holes defined at intervals in a row in the one direction, that is subjected to a tensile load or a compressive load in the one direction, wherein:
a peripheral region around the holes includes a first area obtained by bending a composite material reinforced using continuous fibers made even in a longitudinal direction so that a center line of a width of the composite material weaves between adjacent holes and zigzags in the one direction;
a tensile rigidity and/or compressive rigidity in the one direction of the peripheral region is lower than a tensile rigidity and/or compressive rigidity in the one direction of another region that surrounds the peripheral region;
the first area includes at least two parallel parts, wherein a first parallel part is positioned on a side and in contact with a hole of the plurality and is connected to a second parallel part on a side and in contact with an adjacent hole of the plurality by a slanted part disposed between the hole and the adjacent hole, such that first parallel part on the side of the hole and the second parallel part on the side of the adjacent hole are on opposite sides; and
wherein the parallel part comprises the continuous fibers oriented in a 0° direction, is parallel to a first diameter of its corresponding hole, and includes an extension line of a second diameter of its corresponding hole that is oriented in a ±90° direction, wherein a portion of the parallel part has a length equal to or greater than the first diameter of its corresponding hole.

2. The composite material structure according to claim 1 ,
wherein the slanted part comprises the continuous fibers oriented in a direction greater than or equal to ±30° and less than or equal to ±60°.

3. The composite material structure according to claim 2 ,
wherein the slanted part comprises the continuous fibers oriented in a direction of ±45°.

4. The composite material structure according to claim 1 , wherein the portion of the parallel part equal to or greater than the first diameter of its corresponding hole is at an outer edge of the peripheral region.

5. The composite material structure according to claim 1 , wherein the slanted part is a first slanted part, and in a case where an orientation of the continuous fibers in the first slanted part is orthogonal to an orientation of continuous fibers to an adjacent second slanted part, the width of the composite material is defined as less than or equal to 1/√2 a distance between centers of adjacent holes.

6. The composite material according to claim 1 , wherein the first diameter is a major axis and the second diameter is a minor axis, forming an elongated hole in the 0° direction.

7. The composite material structure according to claim 1 ,
wherein a first layer including a first area in which the composite material reinforced using continuous fibers made even in the longitudinal direction is repeatedly bent so as to define peak areas and valley areas in that order, and
a second layer including a first area in which the composite material reinforced using continuous fibers made even in the longitudinal direction is repeatedly bent so as to define valley areas and peak areas in that order,
are laminated together so that the peak areas in the first area of the first layer and the valley areas in the first area of the second layer define vertical pairs.

8. The composite material structure according to claim 1 , wherein the holes are access holes defined in a lower surface outer plate of an aircraft wing.

9. The composite material structure according to claim 1 , wherein the holes are window holes defined in an outer plate of an aircraft fuselage.

10. An aircraft wing comprising the composite material structure according to claim 8 .

11. An aircraft fuselage comprising the composite material structure according to claim 9 .

12. A method of manufacturing a composite material structure, the composite material structure comprising a fiber-reinforced plastic composite material extending in one direction, wherein the one direction is 0°, and having a plurality of holes defined at intervals in a row in the one direction, that is subjected to a tensile load or a compressive load in the one direction, the method comprising:
bending a composite material reinforced using continuous fibers made even in a longitudinal direction in a peripheral region around the holes so that a center line of a width of the composite material weaves between adjacent holes and zigzags in the one direction, thereby obtaining a first area,
wherein:
a tensile rigidity and/or compressive rigidity in the one direction of the peripheral region is lower than a tensile rigidity and/or compressive rigidity in the one direction of another region that surrounds the peripheral region;
the first area includes at least two parallel parts, wherein a first parallel part is positioned on a side and in contact with a hole of the plurality and is connected to a second parallel part on a side and in contact with an adjacent hole of the plurality by a slanted part disposed between the hole and adjacent hole, such that first parallel part on the side of the hole and the second parallel part on the side of the adjacent hole are on opposite sides; and
wherein the parallel part comprises the continuous fibers oriented in a 0° direction, is parallel to a first diameter of its corresponding hole, and includes an extension line of a second diameter of its corresponding hole oriented in a ±90° direction, wherein a portion of the parallel part has a length equal to or greater than the first diameter of its corresponding hole.

13. The method of manufacturing a composite material structure according to claim 12 , wherein the slanted part comprises the continuous fibers oriented in a direction greater than or equal to ±30° and less than or equal to ±60°.

14. The method of manufacturing a composite material structure according to claim 13 , wherein the slanted part comprises the continuous fibers oriented in a direction of ±45°.

15. The method of manufacturing a composite material structure according to claim 12 , wherein the portion of the parallel part equal to or greater than the first diameter of its corresponding hole is at an outer edge of the peripheral region.

16. The method of manufacturing a composite material structure according to claim 12 , wherein the first diameter is a major axis and the second diameter is a minor axis, forming an elongated hole in the 0° direction.

Assignees

• Mitsubishi Heavy Ind Ltd

Inventors

• Kashiwagi Masahiro
• Nonaka Yoshinori
• Abe Toshio

Classifications

• B32B5/142

  Variation across the area of the layer · CPC title

• Y10T428/24942

  including components having same physical characteristic in differing degree · CPC title

• B64C3/20

  Integral or sandwich constructions · CPC title

• B64C1/14

  Windows; Doors; Hatch covers or access panels; Surrounding frame structures; Canopies; Windscreens {accessories therefor, e.g. pressure sensors, water deflectors, hinges, seals, handles, latches, windscreen wipers}(fairings movable in conjunction with undercarriage elements B64C25/16; bomb doors B64D1/06) · CPC title

• B64C3/34

  Tanks constructed integrally with wings, e.g. for fuel or water · CPC title