Tool assembly for composite part fabrication

Patent metadata

Field	Value
Publication number	US-11529771-B2
Application number	US-202017134762-A
Country	US
Kind code	B2
Filing date	Dec 28, 2020
Priority date	Jun 14, 2018
Publication date	Dec 20, 2022
Grant date	Dec 20, 2022

Abstract

A method of heating a tool assembly includes the step of joining a first piece of the tool assembly with a second piece of the tool assembly via a first joint portion and a second joint portion. The method further includes the step of inserting a fastener through the first joint portion and the second joint portion of the tool assembly. The method further includes the step of applying heat to the tool assembly, wherein upon heating, interlock surfaces of the first joint portion and the second joint portion tighten against each other.

First claim

What is claimed is:

1. A method of heating a tool assembly, the method comprising steps of:
joining a first piece of the tool assembly with a second piece of the tool assembly via a first joint portion and a second joint portion, wherein the first joint portion comprises a top surface and at least a first interlock surface, the first interlock surface configured to interface with the second piece responsive to the first piece being joined to the second piece;
inserting a fastener through the first joint portion and the second joint portion of the tool assembly, wherein the fastener comprises a spring-loaded device, comprising a spring, wherein the spring is configured to compress along a first axis responsive to thermal expansion of the tool assembly, wherein the first axis is parallel to a first surface, defined by the top surface, wherein a second axis is perpendicular to the first axis, and wherein the second axis intersects the top surface, the first interlock surface, and the fastener;
applying composite material onto the top surface, the top surface configured to support formation of a composite part and having a shape that is complementary to a shape of the composite part; and
applying heat to the tool assembly and the composite material, wherein upon heating, interlock surfaces of the first joint portion and the second joint portion tighten against each other.

2. The method of claim 1 , further comprising inserting a second spring-loaded device, wherein a second spring of the second spring-loaded device is configured to compress along the second axis responsive to the thermal expansion of the tool assembly.

3. The method of claim 1 , wherein the step of inserting the fastener through the first joint portion and the second joint portion of the tool assembly comprises:
inserting the fastener through tangs of the first joint portion and the second joint portion; and
securing the fastener to the first joint portion and the second joint portion.

4. The method of claim 1 , further comprising generating vacuum pressure between the composite material and the top surface.

5. The method of claim 1 , further comprising trimming the composite material to generate the composite part.

6. The method of claim 1 , wherein:
the second joint portion is configured to interlock with the first joint portion, and
the second joint portion comprises a second top surface and at least a second interlock surface that is complementary to the first interlock surface.

7. The method of claim 6 , wherein:
the first interlock surface and the top surface form an obtuse-angle corner, and
the second interlock surface and the second top surface form an acute-angle corner.

8. The method of claim 6 , wherein the first interlock surface is configured to contact the second interlock surface to inhibit relative movement between the first piece and the second piece along a longitudinal axis of the tool assembly.

9. The method of claim 6 , wherein:
the first interlock surface has a first surface portion and a second surface portion,
the second interlock surface has a third surface portion and a fourth surface portion,
the first surface portion is configured to directly couple to the third surface portion while the first interlock surface contacts the second interlock surface, and
the second surface portion is configured to form a gap with the fourth surface portion while the first interlock surface contacts the second interlock surface.

10. The method of claim 1 , further comprising generating a vacuum seal between the first piece and the second piece via an annular ring seal.

11. The method of claim 1 , further comprising applying adhesive material to the first piece or the second piece.

12. The method of claim 11 , wherein the adhesive material comprises thermoset polyimides, benzoxazine resins, bis-maleimides, thermoset polyurethanes, phenolics, vinyl esters, or a combination thereof.

13. A method of applying composite material to a tool assembly, the method comprising:
joining a first piece of the tool assembly with a second piece of the tool assembly via a first joint portion and a second joint portion, wherein the tool assembly comprises a layup surface, wherein the first joint portion comprises at least a first interlock surface, the first interlock surface configured to interface with the second piece responsive to the first piece being joined to the second piece, wherein a fastener couples the first joint portion with the second joint portion, the fastener comprises a spring-loaded device, comprising a spring, wherein the spring is configured to compress along a first axis responsive to thermal expansion of the tool assembly, wherein the first axis is parallel to a first surface, defined by the layup surface, wherein a second axis is perpendicular to the first axis, and wherein the second axis intersects the layup surface, the first interlock surface, and the fastener; and
applying the composite material onto the layup surface, the layup surface configured to support formation of a composite part and having a shape that is complementary to a shape of the composite part, wherein the composite material, applied onto the layup surface, defines a working part.

14. The method of claim 13 , further comprising generating vacuum pressure between the composite material and the layup surface.

15. The method of claim 13 , further comprising applying heat or light to the composite material to cure the composite material.

16. The method of claim 13 , further comprising trimming the working part to generate the composite part.

17. A method of making a tool assembly, the method comprising steps of:
forming a first joint portion of a first piece of the tool assembly using an additive manufacturing process, the first joint portion comprising a top surface and at least a first interlock surface;
forming a second joint portion of a second piece of the tool assembly using the additive manufacturing process, the second joint portion comprising a second top surface and at least a second interlock surface that is complementary to the first interlock surface;
joining the first piece with the second piece;
inserting a fastener through the first joint portion and the second joint portion of the tool assembly, wherein the fastener comprises a spring-loaded device, comprising a spring, wherein the spring is configured to compress along a first axis responsive to thermal expansion of the tool assembly, wherein the first axis is parallel to a first surface, defined by the top surface, wherein a second axis is perpendicular to the first axis, and wherein the second axis intersects the top surface, the first interlock surface, and the fastener; and
applying composite material onto the top surface, the top surface configured to support formation of a composite part and having a shape that is complementary to a shape of the composite part.

18. The method of claim 17 , wherein:
the step of forming the first joint portion of the first piece of the tool assembly comprises forming an obtuse angle corner between the first interlock surface and the top surface of the first joint portion using the additive manufacturing process; and
the step of forming the second joint portion of the second piece of the tool assembly comprises forming an acute angle corner between the second interlock surface and the top surface of the second joint portion using the additive manufacturing process.

19. The method of claim 17 , further comprising forming tangs of the first joint portion and the seco

Assignees

• Boeing Co

Inventors

• Matlack Michael P
• Polus Dylan E

Classifications

• B29C70/443 Primary

  and impregnating by vacuum or injection · CPC title

• B33Y10/00

  Processes of additive manufacturing · CPC title

• B29C33/301

  Modular mould systems [MMS], i.e. moulds built up by stacking mould elements, e.g. plates, blocks, rods (B29C33/0088 takes precedence) · CPC title

• Y02T50/40

  Weight reduction · CPC title

• B29C64/10

  Processes of additive manufacturing · CPC title