Method of repairing composite material and composite material

Patent metadata

Field	Value
Publication number	US-9365282-B2
Application number	US-201314079952-A
Country	US
Kind code	B2
Filing date	Nov 14, 2013
Priority date	Nov 20, 2012
Publication date	Jun 14, 2016
Grant date	Jun 14, 2016

Abstract

A method of repairing a composite material is provided in which a frustum-shaped portion of a composite material is removed, and the composite material and a repair material are bonded with each other while evacuating. The repair method includes step S 2 of removing a damaged part 11 from the front side so as to pass through in the thickness direction while leaving a support wall protruding inward in the radial direction from the periphery of the top face of the frustum-shaped portion; step S 3 of sealing the back side by placing a sealing plate, which is inserted from the front side into a through hole formed by the removing step, on the support wall; step S 5 of placing the repair material through an adhesive on the composite material where the frustum-shaped portion has been removed; and step S 6 of evacuating in a state in which the front side is sealed.

First claim

What is claimed is:

1. A method of repairing a composite material that is formed of fibers and resin in a plate shape and has a to-be-removed frustum-shaped portion having a diameter enlarging from a back side toward a front side, the composite material being bonded with a repair material replacing the removed portion, comprising the steps of:
removing, from the front side, at least a first portion of a top face of the frustum-shaped portion so as to form a through hole that passes completely through the composite material in a thickness direction while leaving a support wall protruding inward in a radial direction from a periphery of the through hole, the first portion extending from the top face so as to include at least a projected area of the top face on a bottom of the frustum-shaped portion;
then sealing the back side by placing a sealing plate on the support wall to close the through hole while the back side is accessible from the front side via the through hole, the sealing plate being inserted from the front side into the through hole formed by the removing step;
then placing the repair material through an adhesive on the composite material where the frustum-shaped portion has been removed; and
then evacuating in a state in which the front side is sealed.

2. The method of repairing a composite material according to claim 1 , wherein
the first portion is removed at the step of removing; and
a remaining portion of the frustum-shaped portion is removed after the sealing plate has been placed on the support wall.

3. The method of repairing a composite material according to claim 1 , wherein the first portion is a cylindrical portion.

4. The method of repairing a composite material according to claim 1 , wherein the sealing plate has a sealing plate slope having a diameter enlarging from the back side toward the front side; and the support wall has a support wall slope facing to the sealing plate slope.

5. The method of repairing a composite material according to claim 4 , wherein as well as removal of a frustum-shaped portion of the composite material, the periphery of the frustum-shaped through hole formed by the removal on the back side is rendered to be the support wall.

6. The method of repairing a composite material according to claim 4 , wherein the sealing plate slope and a slope of the frustum-shaped portion continue at an identical inclination angle.

7. The method of repairing a composite material according to claim 1 , wherein the composite material constitutes a skin of an aircraft.

8. The method of repairing a composite material according to claim 1 , wherein an opening diameter of the through hole is equivalent to a diameter of the top face of the frustum-shaped portion, the frustum-shaped portion being formed by scarf machining.

9. The method of repairing a composite material according to claim 1 , wherein the support wall is formed integrally with the composite material.

10. The method of repairing a composite material according to claim 1 , wherein the support wall is formed over an entire circumference of the through hole.

11. The method of repairing a composite material according to claim 1 , wherein the support wall is formed so as to have an annular shape, the inside and outside of which each are a circle.

12. The method of repairing a composite material according to claim 1 , wherein the sealing plate is composed of at least one sheet of CFRP.

13. The method of repairing a composite material according to claim 1 , wherein the sealing plate is a perfect circle.

14. The method of repairing a composite material according to claim 1 , wherein the evacuating is conducted only from the front side.

15. The method of repairing a composite material according to claim 1 , wherein the sealing plate is placed on the support wall without previously installing a patch inserted through the through hole on the back side to close the through hole.

Assignees

• Mitsubishi Aircraft Corp

Inventors

• Shigetomi Toshikazu
• Suhara Masayoshi
• Ishida Morimasa
• Muto Shuhei

Classifications

• B29C73/06 Primary

  using plugs sealing in the hole · CPC title

• Y10T428/20

  Patched hole or depression · CPC title

• B29C73/26

  for mechanical pretreatment · CPC title

• B32B38/10

  Removing layers, or parts of layers, mechanically or chemically · CPC title

• B64F5/0081

  Operations & Transport · mapped topic