Staged cocuring of composite structures

Patent metadata

Field	Value
Publication number	US-9669587-B2
Application number	US-201414269157-A
Country	US
Kind code	B2
Filing date	May 4, 2014
Priority date	Nov 19, 2008
Publication date	Jun 6, 2017
Grant date	Jun 6, 2017

Abstract

A composite structure is fabricated by staging at least a portion of an uncured, first composite component. The first composite component is assembled with a second composite component, and the staged portion of the first composite component is cocured with the second composite component.

First claim

What is claimed is:

1. A method of fabricating a composite structure, comprising:
forming a first composite layup and a second composite layup;
staging at least a first portion of the first composite layup and a first portion of the second composite layup by partially curing each of the first portion of the first composite layup and the first portion of the second composite layup to a stage in which the first portion of the first composite layup and the first portion of the second composite layup are each substantially rigid but less than fully cured, with a second portion of the first composite layup and a second portion of the second composite layup each being fully cured;
subsequently, assembling the layups, including using fully cured second portions of the first composite layup and the second composite layup as reference surfaces to locate the first composite layup relative to the second composite layup, bringing the first portion of the first composite layup into contact with the second composite layup and bringing the first portion of the second composite layup into contact with the first composite layup; and
subsequently, cocuring the first portion of the first composite layup with the first portion of the second composite layup, including wherein other portions of the first composite layup other than the first portion located along a width of the first composite layup are brought to a full cure without cocuring the other portions to the second composite layup.

2. The method of claim 1 , wherein staging the first composite layup includes:
heating the first composite layup to a first temperature sufficient to cure the second portion of the first composite layup, and
limiting heating of the first portion to a second temperature below a temperature sufficient to result in a full cure of the first portion.

3. The method of claim 2 , wherein limiting heating of the first portion of the first composite layup comprises controlling an amount of staging of the first portion by placing at least one thermal control element in contact with the first portion.

4. A method of fabricating a composite structure, comprising:
staging a first portion of a first composite component, initially uncured, by curing the first portion to an intermediate cure state in which the first portion acts as a vitreous solid at substantially room temperature but is not fully cured, the first portion being less than a first entirety of the first composite component;
staging a second portion of a second composite component, initially uncured, by curing the second portion to the intermediate cure state in which the second portion acts as the vitreous solid at substantially room temperature but is not fully cured, the second portion being less than a second entirety of the second composite component;
assembling the first composite component with the second composite component using fully cured portions of the first composite component and the second composite component as reference surfaces to locate the first composite component relative to the second composite component; and,
cocuring the first portion of the first composite component and the second portion of the second composite component, including wherein other portions of the first composite component other than the first portion located along a width of the first composite component are brought to a full cure without cocuring the other portions to the second composite component.

5. The method of claim 4 , further comprising:
after assembling, heating the first portion until the first portion is substantially consolidated and plastically deforms to conform to the second composite component.

6. The method of claim 4 , wherein cocuring is performed by placing thermal control elements on the first portion and the second portion.

7. The method of claim 6 , wherein cocuring includes placing at least one thermal control element in contact with the first portion of the first composite component.

8. A method of reinforcing a skin comprising a composite, the method comprising:
curing the skin such that:
a first portion of the skin reaches a first state being fully cured; and
a second portion of the skin reaches a second state partially cured such that the second portion of the skin may be cocured;

curing a layup comprising a multi-ply composite such that:
a first portion of the layup reaches the first state; and
a second portion of the layup reaches the second state;

subsequently, aligning the second portion of the skin adjacent to the second portion of the layup using fully cured first portions of the skin and the layup as reference surfaces to locate the skin relative to the layup;
reinforcing the skin by forming a unified structure comprising the skin cocured to the layup by cocuring the second portion of the skin to the second portion of the layup, including wherein other portions of the layup other than the second portion located along a width of the layup are brought to a full cure without cocuring the other portions to the skin.

9. The method of claim 8 , wherein aligning comprises using a cocuring tool and compression mold.

10. The method of claim 8 , wherein the unified structure is fully cured.

11. The method of claim 8 , wherein curing the second portion of the skin comprises using a thermal control element.

12. The method of claim 8 , wherein curing the second portion of the layup comprises using a thermal control element.

13. The method of claim 8 , wherein the layup comprises a stringer.

14. The method of claim 8 , wherein the layup comprises a second skin.

15. The method of claim 8 , further comprising the skin being undulated.

Assignees

• Boeing Co

Inventors

• Nelson Karl M
• Hafenrichter Joseph L
• Willden Kurtis S

Classifications

• B29C66/232

  said joint lines being multiple and parallel, i.e. the joint being formed by several parallel joint lines · CPC title

• B29L2031/003

  having a profiled transverse cross-section · CPC title

• B29L2031/3082

  Fuselages · CPC title

• B29C65/785

  using magnetic forces to hold at least one of the parts to be joined (magnetic work holders in general B25B11/002) · CPC title

• B29C35/0288

  Controlling heating or curing of polymers during moulding, e.g. by measuring temperatures or properties of the polymer and regulating the process (controlling or regulating chemical, physical or physico- chemical processes in general B01J19/0006) · CPC title