Methods and apparatus for fabricating panels

Patent metadata

Field	Value
Publication number	US-11220064-B2
Application number	US-201816132311-A
Country	US
Kind code	B2
Filing date	Sep 14, 2018
Priority date	Sep 14, 2018
Publication date	Jan 11, 2022
Grant date	Jan 11, 2022

Abstract

A composite sandwich panel includes a first composite part and a second composite part. A plurality of stiffeners extend between the first and second composite parts. A fiberglass composite perimeter edge closeout is positioned along one or more edges of the first and second composite parts. The fiberglass composite perimeter edge closeout controls a magnetic flux to bond the first and second composite parts to the plurality of stiffeners.

First claim

What is claimed is:

1. A composite sandwich panel comprising:
a first composite part;
a second composite part;
a plurality of stiffeners extending between the first and second composite parts; and
a fiberglass composite perimeter edge closeout positioned along one or more edges of the first and second composite parts, the fiberglass composite perimeter edge closeout having an angled body extending between a pair of planar ends such that the angled body is sloped from one end of the pair of planar ends to another end of the pair of planar ends, the pair of planar ends extending along a surface of the first and second composite parts, the fiberglass composite perimeter edge closeout configured to control a directional magnetic flux to inductively bond the first and second composite parts to the plurality of stiffeners and close open ends of and form edges between the bonded first and second composite parts as the directional magnetic flux is being directionally controlled to re-direct the directional magnetic flux within the composite sandwich panel where an energy field acts on a plurality of susceptor resin assemblies placed at co-bonding interface flange faces to weld the fiberglass composite perimeter edge closeout, the plurality of stiffeners, the first composite part, and the second composite part into an assembled single part structure.

2. The composite sandwich panel of claim 1 , wherein one or more susceptor resin assemblies of the plurality of susceptor resin assemblies are positioned between one or more surfaces of (i) the first and second composite parts and (ii) the plurality of stiffeners.

3. The composite sandwich panel of claim 2 , wherein the fiberglass composite perimeter edge closeout is configured to direct the direction magnetic flux to the plurality of susceptor resin assemblies.

4. The composite sandwich panel of claim 1 , wherein the fiberglass composite perimeter edge closeout is formed from a material having dielectric material properties to control directional flux induced welding of the first and second composite parts to the plurality of stiffeners.

5. The composite sandwich panel of claim 1 , wherein the fiberglass composite perimeter edge closeout comprises a fiberglass reinforced thermoplastic and the first and second composite parts are inner and outer skins of an aircraft landing gear door.

6. The composite sandwich panel of claim 1 , wherein the fiberglass composite perimeter edge closeout comprises the angled body between the pair of planar ends, wherein the angled body extends in a single plane between the pair of planar ends and together form an “S” shaped profile.

7. A composite sandwich panel comprising:
a first composite part;
a second composite part;
a fiberglass composite perimeter edge closeout positioned along one or more edges of the first and second composite parts, the fiberglass composite perimeter edge closeout comprising:
a body formed from a material having dielectric properties to control a directional magnetic flux to inductively bond the first and second composite parts to the fiberglass composite perimeter edge closeout, the body being angled, and sized and shaped to form edges of the composite sandwich panel; and
a pair of planar ends extending from the body, the body being angled between the pair of planar ends such that the body is sloped from one end of the pair planar ends to another end of the pair of planar ends, the pair of planar ends configured to abut edges of and extend along a surface of the composite sandwich panel and inductively bond thereto to close open ends of and form the edges between the bonded first and second composite parts as the directional magnetic flux is being directionally controlled to re-direct the directional magnetic flux within the composite sandwich panel where an energy field acts on a plurality of susceptor resin assemblies placed at co-bonding interface flange faces to weld the fiberglass composite perimeter edge closeout and the first and second composite parts into an assembled single part structure.

8. The composite sandwich panel of claim 7 , wherein the plurality of susceptor resin assemblies is configured to be positioned between the pair of planar ends and one or more surfaces of the sandwich panel, and bond the pair of planar ends to the edges of the first and second composite parts as the directional magnetic flux flows into the first and second composite parts.

9. The composite sandwich panel of claim 7 , wherein the composite sandwich panel further comprises a plurality of stiffeners having one or more susceptor resin assemblies of the plurality of susceptor resin assemblies positioned between ends of the plurality of stiffeners and one or more surfaces of the first and second composite parts, and the body is configured to direct the directional magnetic flux to the plurality of susceptor resin assemblies.

10. The composite sandwich panel of claim 7 , wherein the pair of planar ends comprise parallel end portions configured to bond to abutting surfaces of the first and second composite parts.

11. The composite sandwich panel of claim 7 , wherein the body is formed from the material having dielectric properties to control directional flux induced welding of the pair of planar ends to the first and second composite parts in a single manufacturing step to inductively bond the body to the first and second composite parts to form the assembled single part structure and redirect the directional magnetic flux within the first and second composite parts, and having dielectric properties that block the directional magnetic flux from encountering the first and second composite parts at a substantially non-parallel angle.

12. The composite sandwich panel of claim 7 , wherein the fiberglass composite perimeter edge closeout is formed from fiberglass reinforced thermoplastic having properties selected based on at least one of a conductivity, a melting temperature, and a frequency relating to magnetic flux inductive welding.

13. The composite sandwich panel of claim 7 , wherein the body is angled between the pair of planar ends to have a constant slope, the pair of planar ends of the pair of planar ends being in different parallel planes, each planar end in the pair of planar ends having first and second surfaces, the first and second surface being opposing surfaces, the second surfaces of the pair of planar ends bonded with offset ends of the first and second composite parts, and the pair of planar ends extending from the body at an angle greater than ninety degrees.

14. The composite sandwich panel of claim 7 , wherein the body extends in a single plane between the pair of planar ends and together form an “S” shaped profile.

15. An aircraft landing gear door comprising the composite sandwich panel of claim 7 , wherein the first and second composite parts are configured as consolidated thermoplastic inner and outer skins of the aircraft landing gear door.

Assignees

• Boeing Co

Inventors

• Matsen Marc R
• Voss Bret Alan Mcginness
• Ku Vincent C
• Hottes Christopher J

Classifications

• B64C2001/0072

  from composite materials · CPC title

• B29C66/636

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

• B29C65/3676

  being metallic · CPC title

• B29C66/1122

  Single lap to lap joints, i.e. overlap joints (B29C66/45, B29C66/472, B29C66/52272 take precedence) · CPC title

• B29C66/543

  joining more than two hollow-preforms to form said hollow articles · CPC title