Systems and methods for on-aircraft composite repair using double vacuum debulking

Patent metadata

Field	Value
Publication number	US-10336019-B2
Application number	US-201514621634-A
Country	US
Kind code	B2
Filing date	Feb 13, 2015
Priority date	Sep 30, 2010
Publication date	Jul 2, 2019
Grant date	Jul 2, 2019

Abstract

An in-situ double vacuum debulk (DVD) composite repair system designed to produce partially or fully cured autoclave-quality hot-bond composite repairs on contoured structures. The system provides vacuum pressure for hot bond repairs to be performed on flat and contoured structures using one set-up capable of debulking (partially curing) and then fully curing composite repairs on composite and metallic aircraft structures. The use of in-situ DVD also eliminates handling of the patch/adhesive when transferring from an off-aircraft DVD chamber to the repair site on the aircraft. This can increase the probability of successful repairs because the possibility of contaminating and misaligning the adhesive and repair patch are eliminated.

First claim

The invention claimed is:

1. A system for repairing a site on a parent structure, comprising:
an outer bagging film sealed to the parent structure along a first perimeter that surrounds the site to form a chamber;
a strongback support tool that is disposed between said outer bagging film and the parent structure;
a solid standoff spacer that contacts said strongback support tool along a perimeter thereof and spaces said strongback support tool from the parent structure to form a portion of said chamber that is bounded by the strongback support tool, the spacer and the parent structure;
a first vacuum probe installed in an aperture in said outer bagging film for evacuating said chamber when said first vacuum probe is coupled to a vacuum source; and
a heat blanket overlying the site.

2. The system as recited in claim 1 , wherein said strongback support tool has a contour that matches a contour of a confronting portion of the parent structure.

3. The system as recited in claim 1 , further comprising:
an inner bagging film installed in said chamber and sealed to the parent structure along a second perimeter that surrounds the site and is surrounded by said first perimeter; and
a second vacuum probe installed in an aperture in said inner bagging film for evacuating a sealed space under said inner bagging film when said second vacuum probe is connected to a vacuum source.

4. The system as recited in claim 1 , further comprising an inflatable bladder attached to said strongback support tool, said inflatable bladder exerting pressure on said heat blanket when inflated.

5. The system as recited in claim 1 , further comprising compressible solid material disposed between said strongback support tool and said heat blanket.

6. The system as recited in claim 1 , wherein the parent structure is a component of an aircraft.

7. The system as recited in claim 1 , wherein the parent structure is made of composite material.

8. The system as recited in claim 1 , wherein the parent structure is made of metallic material.

9. The system as recited in claim 1 , further comprising a repair patch made of composite material adhered to the site.

10. A system for repairing a site on a parent structure, comprising:
a strongback support tool overlying the site;
a vacuum bag having a first portion sealed to the parent structure along a perimeter surrounding said strongback support tool and a second portion overlying said strongback support tool;
a vacuum probe installed in an aperture in said vacuum bag;
a stack of repair plies in a position overlying the site;
a heat blanket in a position above said stack of repair plies and below said strongback support tool;
a first inflatable bladder attached to said strongback support tool and disposed between said strongback support tool and said heat blanket; and
a second inflatable bladder attached to a perimetral portion of said strongback support tool, said second inflatable bladder being disposed between said strongback support tool and the parent structure,
wherein said first inflatable bladder is disposed in a space surrounded by said second inflatable bladder.

11. The system as recited in claim 10 , wherein said strongback support tool has a contour that matches a contour of a confronting portion of the parent structure.

12. The system as recited in claim 10 , wherein the parent structure is a component of an aircraft.

13. The system as recited in claim 10 , wherein the parent structure is made of composite material.

14. The system as recited in claim 10 , wherein the parent structure is made of metallic material.

15. The system as recited in claim 10 , wherein said repair plies are made of composite material.

16. A system for repairing a site on a parent structure, comprising:
a box having a perimetral portion that is supported by the parent structure, said box and the parent structure defining a portion of a chamber therebetween that overlies at least the site;
an outer bagging film having a first portion that covers the box and a second portion sealed to the parent structure along a first perimeter that surrounds the box and forms the chamber, said outer bagging film having an aperture;
a first vacuum probe installed in said aperture in said outer bagging film for evacuating said chamber when said first vacuum probe is coupled to a vacuum source;
a stack of repair plies in a position overlying the site;
a heat blanket overlying said stack of repair plies;
an inner bagging film installed in said chamber and sealed to the parent structure along a second perimeter that surrounds said heat blanket, said inner bagging film having an aperture; and
a second vacuum probe installed in said aperture in said inner bagging film for evacuating a sealed space under said inner bagging film when said second vacuum probe is connected to a vacuum source,
wherein said box comprises:
a strongback support tool that is disposed between said outer bagging film and the parent structure; and
a spacer that is attached to said strongback support tool along a perimeter thereof and spaces said strongback support tool from the parent structure to form said portion of said chamber.

17. The system as recited in claim 16 , wherein said spacer is made of silicone and said strongback support tool is made of honeycomb composite material.

18. The system as recited in claim 16 , wherein said box has an aperture, further comprising a hose that passes through said aperture in said box and is connected to said second vacuum probe.

19. A system for repairing a site on a parent structure, comprising:
an outer bagging film sealed to the parent structure along a first perimeter that surrounds the site to form a chamber;
a strongback support tool that is disposed between said outer bagging film and the parent structure;
a spacer that contacts said strongback support tool along a perimeter thereof and spaces said strongback support tool from the parent structure to form a portion of said chamber that is bounded by the strongback support tool, the spacer and the parent structure;
a first vacuum probe installed in an aperture in said outer bagging film for evacuating said chamber when said first vacuum probe is coupled to a vacuum source; and
a heat blanket overlying the site,
wherein the strongback support tool and the spacer are made of different materials.

20. The system as recited in claim 19 , wherein said spacer is made of silicone and said strongback support tool is made of honeycomb composite material.

21. A system for repairing a site on a parent structure, comprising:
an outer bagging film sealed to the parent structure along a first perimeter that surrounds the site to form a chamber;
a strongback support tool that is disposed between said outer bagging film and the parent structure;
a spacer that contacts said strongback support tool along a perimeter thereof and spaces said strongback support tool from the parent structure to form a portion of said chamber that is bounded by the strongback support tool, the spacer and the parent structure;
a first vacuum probe installed in an aperture in said outer bagging film for evacuating said chamber when said first vacuum probe is coupled to a vacuum source; and
a heat blanket overlying the site,
wherein said spacer is inflatable.

Assignees

• Boeing Co

Inventors

• Nelson Karl Edward
• Evens Michael W
• Spalding Jr John F
• Chanes James D
• Baldwin Joel P
• Rutherford Paul S

Classifications

• B29C73/12

  Apparatus therefor, e.g. for applying (B29C73/30 takes precedence) · CPC title

• B29C66/81455

  being a fluid inflatable bag or bladder, a diaphragm or a vacuum bag for applying isostatic pressure (inflatable element positioned between the joining tool and a backing-up part B29C66/82421) · CPC title

• B30B9/22

  using a flexible member, e.g. diaphragm, urged by fluid pressure · CPC title

• B32B37/1018

  using only vacuum · CPC title

• B29L2031/3076

  Aircrafts (blades, propellers B29L2031/08) · CPC title