Method to reduce residual stress in an integrally-stiffened co-bonded structure

Patent metadata

Field	Value
Publication number	US-2016346995-A1
Application number	US-201514723355-A
Country	US
Kind code	A1
Filing date	May 27, 2015
Priority date	May 27, 2015
Publication date	Dec 1, 2016
Grant date	—

Abstract

A method of reducing residual stress in a composite assembly may include assembling a first composite part to a second composite part to form a detail assembly. The first and second composite part may each have a flange and a web connected by a bend radius. The webs may be arranged back-to-back. The detail assembly may be cured on a compensated cure tool compensated for cure shrinkage spring-in predicted to occur in the first and second composite part. The method may include allowing the first and second composite part to spring in from cure shrinkage, and assembling the detail assembly to an uncured third composite. The method may also include co-bonding the detail assembly to the third composite part on an assembly cure tool to form a composite assembly having reduced cure shrinkage residual stress in the bend radii of the first and second composite part.

First claim

What is claimed is:

1 . A method of reducing residual stress in a composite assembly, comprising:
assembling a first composite part to a second composite part to form a detail assembly, the first and second composite part each having a flange and a web connected by a bend radius, the web of the first and second composite part being back-to-back; curing the detail assembly on a compensated cure tool compensated for cure shrinkage spring-in predicted to occur in the first and second composite part; allowing the first and second composite part to spring in from cure shrinkage; assembling the detail assembly to a third composite part that is uncured, the third composite interconnecting the flange of the first and second composite part; and co-bonding the detail assembly to the third composite part on an assembly cure tool to form a composite assembly having reduced cure shrinkage residual stress in the bend radii of the first and second composite part.

2 . The method of claim 1 , wherein:
the compensated cure tool is compensated for cure shrinkage spring-in by an amount such that the flange of the first and second composite part spring out and are flush with the third composite part during co-bonding.

3 . The method of claim 1 , wherein:
the uncured third composite part extends from the flange of the first to the flange of the second composite part.

4 . The method of claim 1 , wherein:
the uncured third composite part comprises two or more uncured composite parts.

5 . The method of claim 4 , wherein:
the uncured third composite part comprises an uncured base laminate stacked on top of an uncured skin panel.

6 . The method of claim 5 , wherein the step of assembling the cured detail assembly to the third composite part comprises:
laying up the third composite part on an assembly cure tool; and mating the detail assembly to the third composite part.

7 . The method of claim 5 , wherein the step of assembling the cured detail assembly to the third composite part comprises:
installing an adhesive layer between the third composite part and the detail assembly.

8 . The method of claim 1 , further including:
laying up at least one of the first and second composite parts on a compensated layup tool.

9 . The method of claim 1 , wherein the step of assembling the first and second composite part includes:
installing a radius filler within a notch between back-to-back bend radii of the first and second composite part.

10 . The method of claim 1 , further including:
providing at least one of the first and second composite part as a composite laminate formed of preimpregnated composite plies.

11 . The method of claim 1 , further including:
providing the first and second composite part in a configuration such that the detail assembly has one of a blade section, a C-section, an I-section, and a hat section.

12 . A method of reducing residual stress in a composite assembly, comprising:
assembling a first composite part to a second composite part to form an uncured detail assembly, the first and second composite part each having a flange and a web connected by a bend radius and being assembled such that the web of the first and second composite part are back-to-back; curing the detail assembly on a compensated cure tool with the flange of the first and second composite part supported on a tool surface compensated for cure shrinkage spring-in and thermally-induced spring-in predicted to occur in the first composite part and second composite part; allowing the flange of the first and second composite part to undergo cure shrinkage spring-in and thermally-induced spring-in; assembling the detail assembly to a third composite part that is uncured and which extends across and interconnects the flange of the first and second composite part, an adhesive layer installed between the detail assembly and the third composite part; and co-bonding the detail assembly to the third composite part on an assembly cure tool to form a composite assembly with reduced or non-existent cure shrinkage residual stress and thermally-induced residual stress in the bend radii of the first and second composite part.

13 . The method of claim 12 , wherein:
the compensated cure tool is compensated for cure shrinkage spring-in and thermally-induced spring-in by an amount such that when the detail assembly is at room temperature after cure, the flanges are flush with the third composite part.

14 . The method of claim 12 , wherein:
the uncured third composite part extends across and interconnects the flange of the first composite part and second composite part.

15 . The method of claim 12 , wherein the step of assembling the detail assembly to the third composite part comprises:
laying up an uncured skin panel and an uncured base laminate on an assembly cure tool prior to co-bonding the uncured detail assembly to the uncured skin panel and uncured base laminate.

16 . The method of claim 12 , further including:
laying up at least one of the first and second composite parts on a compensated layup tool.

17 . The method of claim 12 , wherein the step of assembling the first composite part and the second composite part includes:
installing a radius filler within a notch between back-to-back bend radii of the first composite part and second composite part when assembled.

18 . The method of claim 12 , further including:
providing the first composite part and the second composite part in a configuration such that the detail assembly has one of the following cross-sections: a blade section, a C-section, an I-section, a hat section.

19 . A method of forming an integrally-stiffened panel assembly, comprising:
assembling a first composite part, a second composite part, and a radius filler to form an uncured detail assembly, the first and second composite part each having a flange and a web connected by a bend radius, the web of the first and second composite part being in back-to-back contact with one another and forming a notch between the bend radii for receiving the radius filler; curing the detail assembly on a compensated cure tool with the radius filler and the flange of the first and second composite part supported on a tool surface compensated for cure shrinkage spring-in and thermally-induced spring-in; allowing cure shrinkage spring-in and thermally-induced spring-in to occur in the flange of the first and second composite part after curing of the detail assembly; assembling the detail assembly to an uncured base laminate and uncured skin panel located beneath the base laminate and supported on an assembly cure tool, an adhesive layer installed between the base laminate and the detail assembly, the base laminate extending across and interconnecting the flange of the first and second composite part; and co-bonding the detail assembly to the uncured base laminate and uncured skin panel on an assembly cure tool to form an integrally-stiffened panel assembly with reduced or non-existent cure shrinkage residual stress and thermally-induced residual stress in the radius filler and the bend radii of the first and second composite part.

20 . The method of claim 19 , wherein:
the detail assembly has one of a blade section, a C-section, an I-section, a J-section, and a hat section.

Assignees

• Boeing Co

Inventors

• Butler Geoffrey A
• Courdji Robert

Classifications

• B29C65/48

  using adhesives {, i.e. using supplementary joining material; solvent bonding} · CPC title

• B29K2063/00

  Use of {EP, i.e.} epoxy resins {or derivatives thereof}, as moulding material · CPC title

• B29C66/721

  Fibre-reinforced materials (B29C66/729 takes precedence) · CPC title

• B29C35/02

  Heating or curing, e.g. crosslinking or vulcanizing {during moulding, e.g. in a mould}(cold vulcanisation B29C35/18 {; vulcanising tyres, presses therefor B29D30/0601}) · CPC title

• B29C66/496

  using a support which remains in the joined object · CPC title