Panel-Insert Assembly and Method

Patent metadata

Field	Value
Publication number	US-2016368242-A1
Application number	US-201615251195-A
Country	US
Kind code	A1
Filing date	Aug 30, 2016
Priority date	Jul 29, 2014
Publication date	Dec 22, 2016
Grant date	—

Abstract

A panel-insert assembly including a panel having a core and a skin layer positioned over the core, wherein the skin layer defines an opening therein, and an insert positioned below the skin layer, wherein the insert is aligned with the opening.

First claim

What is claimed is:

1 . A method for connecting an insert to a panel, said panel comprising a core and a skin layer, said method comprising:
forming an opening in said skin layer; inserting said insert through said opening such that said insert is positioned below said skin layer; and rotating said threaded insert relative to said opening.

2 . The method of claim 1 further comprising aligning said insert with said opening.

3 . The method of claim 1 wherein said forming said opening comprises elongating said opening along an opening axis.

4 . The method of claim 3 wherein said rotating comprises rotating said insert until a major axis of said insert is substantially parallel with said opening axis, wherein said insert comprises a major dimension along said major axis and a minor dimension along a minor axis.

5 . The method of claim 4 wherein said minor axis is perpendicular to said major axis.

6 . The method of claim 4 wherein said inserting comprises aligning said minor dimension with said opening.

7 . The method of claim 1 wherein said panel is a sandwich panel.

8 . The method of claim 1 wherein said panel further comprises a second skin layer, wherein said core is positioned between said skin layer and said second skin layer.

9 . The method of claim 1 wherein said opening has a maximum length.

10 . The method of claim 9 wherein said insert has a major dimension and a minor dimension, said minor dimension being less than or equal to said maximum length.

11 . The method of claim 10 wherein said major dimension is greater than said maximum length.

12 . The method of claim 1 wherein said inserting comprises positioning said insert between said skin layer and said core.

13 . The method of claim 1 wherein said insert defines a bore.

14 . The method of claim 13 wherein said bore is threaded.

15 . The method of claim 1 wherein said insert comprises a combination of materials.

16 . A method for connecting a threaded insert to a panel, said panel comprising a core and a skin layer, said method comprising:
forming an opening in said skin layer; inserting said threaded insert through said opening such that said threaded insert is positioned below said skin layer; and rotating said threaded insert relative to said opening.

17 . The method of claim 16 further comprising aligning said threaded insert with said opening.

18 . The method of claim 16 wherein said forming said opening comprises elongating said opening along an opening axis.

19 . The method of claim 18 wherein said rotating comprises rotating said insert until a major axis of said insert is substantially parallel with said opening axis, wherein said insert comprises a major dimension along said major axis and a minor dimension along a minor axis.

20 . The method of claim 19 wherein said inserting comprises aligning said minor dimension with said opening.

Assignees

• Boeing Co

Inventors

• Lewis Michael S
• Sakurai Jessica
• Reeves Brad J

Classifications

• B32B3/266

  characterised by an apertured layer, the apertures going through the whole thickness of the layer, e.g. expanded metal, perforated layer, slit layer regular cells B32B3/12 · CPC title

• B32B2605/18

  Aircraft · CPC title

• B64F5/0009

  Operations & Transport · mapped topic

• F16B21/02

  Releasable fastening devices locking by rotation (with snap-action F16B21/06; studs or coupling pins with resilient protrusions F16B21/08) · CPC title

• B32B7/08 Primary

  by mechanical means · CPC title