Fixing element for components of an assembly

Patent metadata

Field	Value
Publication number	US-10072695-B2
Application number	US-201414547802-A
Country	US
Kind code	B2
Filing date	Nov 19, 2014
Priority date	Nov 25, 2013
Publication date	Sep 11, 2018
Grant date	Sep 11, 2018

Abstract

A fixing element for components of an assembly, comprising a rod which is formed by a cylindrical shaft and an end, the rod being a metal component which is at least partially surface-treated by means of anode oxidation and coated over at least a portion of the cylindrical shaft with a lubricating coating. Such a fixing element enables the electrical continuity to be ensured with the components during mounting with moderate interference in the assembly.

First claim

What is claimed is:

1. A fixing element for securing components of an assembly, the fixing element comprising:
a metal rod comprising a cylindrical shaft extending between a head and an end, and a frustoconical connection portion between the cylindrical shaft and the end, the metal rod comprising:
a first region that is surface-treated by means of anode oxidation, wherein the first region comprises a first annular ring about the cylindrical shaft and between the head and the frustoconical connection portion; and
a second region coated with a lubricating coating,
wherein the second region comprises a second annular ring about the cylindrical shaft and between the head and the frustoconical connection portion.

2. The fixing element of claim 1 , wherein the second region further comprises a third annular ring about the cylindrical shaft and between the head and the frustoconical connection portion.

3. The fixing element of claim 2 , wherein the first region further comprises a fourth annular ring about the cylindrical shaft and between the head and the frustoconical connection portion.

4. The fixing element of claim 2 , wherein the second region includes the frustoconical connection portion.

5. The fixing element of claim 1 , wherein the second annular ring of the second region is contiguous with the lubricating coating on the frustoconical connection portion.

6. The fixing element of claim 1 , wherein the rod is at least partially surface-treated by means of sulphuric anode oxidation.

7. The fixing element of claim 6 , wherein lubricating coating is a coating comprising phenolic resin.

8. The fixing element of claim 1 wherein the end of the metal rod is threaded and the end is surface-treated by means of anode oxidation.

9. The fixing element of claim 1 wherein the end is coated with the lubricating coating.

10. An aircraft assembly, comprising:
a first component;
a second component; and
a metal rod for securing the first and second components, the metal rod comprising:
a cylindrical shaft extending between a head and an end;
a frustoconical connection portion between the head and the end;
a first region that is surface-treated by means of anode oxidation; and
a second region coated with a lubricating coating,
wherein the first region comprises a first annular ring surface-treated by the anode oxidation, and
wherein the second region comprises a second annular ring about the cylindrical shaft and between the head and the frustoconical connection portion.

11. The aircraft assembly of claim 10 , wherein the cylindrical shaft comprises:
at least a first strip that extends in the length of the cylindrical shaft and which is surface-treated by means of anode oxidation; and
at least a second strip that extends in the length of the cylindrical shaft and which is coated with the lubricating coating.

12. The aircraft assembly of claim 11 wherein the cylindrical shaft comprises;
a plurality of first strips that are surface-treated by means of anode oxidation; and
a plurality of second strips that are coated with a lubricating coating, the first and second strips extending over angular sectors that are distributed around the periphery of the cylindrical shaft.

13. The aircraft assembly of claim 12 , wherein the oxidation is a sulfur anode oxidation.

14. The aircraft assembly of claim 13 wherein the anode oxidation is substantially 0.5 microns thick.

15. The aircraft assembly of claim 13 wherein the lubricant coating is substantially 5 microns thick.

16. The aircraft assembly of claim 13 wherein the metal rod is titanium.

17. A method for treating a fixing element that secures an aircraft assembly, the fixing assembly including a rod comprised of a cylindrical shaft extending between a head and an end, the method comprising:
surface treating at least a portion of the cylindrical shaft by means of anode oxidation;
coating at least a first region of the cylindrical shaft with a lubricant to provide a first region and a second region on the cylindrical shaft and between the head and the end,
wherein the first region comprises a first annular ring surface-treated by the anode oxidation, and,
wherein the second region corpses a second annular ring coated with the lubricant.

18. A fixing element for securing components of an assembly, comprising:
a metal rod comprising a cylindrical shaft extending between a head and an end, and further comprising:
a first region that is surface-treated by means of anode oxidation; and
a second region coated with a lubricating coating,

wherein the end of the metal rod comprises a threaded end, and,
wherein the first region comprises a first annular ring about the cylindrical shaft and between the head and the threaded end, and,
wherein the second region comprises a second annular ring about the cylindrical shaft and between the head and the threaded end.

Assignees

• Airbus Operations Sas
• Airbus Operations Sas

Inventors

• Maurel Jean-Philippe
• Labal Frederic
• Martres Jean-Luc

Classifications

• F16B33/06 Primary

  Surface treatment of parts furnished with screw-thread, e.g. for preventing seizure {or fretting (corrosion preventing means F16B33/008; settable coatings for locking threaded members F16B39/225; deformable coatings for locking threaded members F16B39/34)} · CPC title

• F16B33/008 Primary

  Corrosion preventing means · CPC title

• F16B4/004

  Press fits, force fits, interference fits, i.e. fits without heat or chemical treatment (F16B4/002 takes precedence) · CPC title

• F16B35/00

  Screw-bolts; Stay-bolts; Screw-threaded studs; Screws; Set screws ({F16B33/008 takes precedence; joining sheets or plates using screws with two separate threads F16B5/0275; using screws with adjustment sleeves F16B5/0283}; thread cutting screws F16B25/00) · CPC title

• B64C1/00

  Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like · CPC title