Aircraft assembly

Patent metadata

Field	Value
Publication number	US-11111948-B2
Application number	US-201916392721-A
Country	US
Kind code	B2
Filing date	Apr 24, 2019
Priority date	Apr 25, 2018
Publication date	Sep 7, 2021
Grant date	Sep 7, 2021

Abstract

An aircraft assembly having a titanium rod comprising a first threaded portion, and a titanium nut comprising a second threaded portion conforming with the first threaded portion for mating engagement with it. One of the first and second threaded portions defines a male thread and the other one of the first and second threaded portions defines a female thread such that the nut can be wound in threading engagement along the rod. A threaded insert formed from a first metal of different hardness in comparison to titanium is coupled to the rod or the nut to define the first threaded portion or the second threaded portion respectively such that one of the first and second threaded portions is formed from titanium and the other one of the first and second threaded portions is formed from the first metal.

First claim

The invention claimed is:

1. An aircraft assembly comprising:
a titanium rod comprising a first threaded portion;
a titanium nut comprising a second threaded portion conforming with the first threaded portion for mating engagement with the first threaded portion, wherein one of the first threaded portion and the second threaded portion defines a male thread and the other one of the first threaded portion and the second threaded portion defines a female thread such that the nut can be wound in threading engagement along the rod; and
a threaded insert formed from a first metal of different hardness in comparison to titanium, the threaded insert being coupled to the rod or the nut to define the first threaded portion or the second threaded portion respectively such that one of the first threaded portion and the second threaded portion is formed from titanium and the other one of the first threaded portion and the second threaded portion is formed from the first metal;
wherein the rod defines a bore, the first threaded portion defines the female threaded portion within the bore and the nut is a gland nut defining the male threaded portion, wherein the titanium rod comprises an outer cylinder of an aircraft landing gear shock absorbing strut.

2. The aircraft assembly according to claim 1 , wherein the one of the first threaded portion and the second threaded portion that is formed from titanium comprises threads formed by a cold forging thread rolling process.

3. The aircraft assembly according to claim 1 , wherein the body of the nut or rod to which the insert is coupled is at least 80% of the volume of the nut or rod respectively.

4. The aircraft assembly according to claim 1 , wherein the insert defines the female threaded portion.

5. The aircraft assembly according to claim 1 , wherein the insert comprises a self-locking thread insert.

6. The aircraft assembly according to claim 1 , wherein the insert is formed from die drawn wire.

7. The aircraft assembly according to claim 1 , wherein the insert is formed from a copper nickel tin alloy comprising at least 75% by weight copper and at least 15% nickel and at least 5% tin.

8. The aircraft assembly according to claim 1 , wherein the first threaded portion, defined by the rod, defines the male threaded portion and the nut body defines a bore, the insert being located within the bore and defining the female threaded portion.

9. The aircraft assembly according to claim 1 , wherein the titanium rod comprises an outer cylinder of an aircraft landing gear shock absorbing strut.

10. The aircraft assembly according to claim 1 , wherein the insert is coupled to the rod.

11. An aircraft assembly comprising:
a titanium rod comprising a first threaded portion;
a titanium nut comprising a second threaded portion conforming with the first threaded portion for mating engagement with the first threaded portion, wherein the first threaded portion defines a male thread and the second threaded portion defines a female thread such that the nut can be wound in threading engagement along the rod; and
a threaded insert formed from a first metal of different hardness in comparison to titanium, the threaded insert being coupled to the nut to define the second threaded portion such that the first threaded portion is formed from titanium and the second threaded portion is formed from the first metal,
wherein the nut body defines a bore, the insert being located within the bore and defining the female threaded portion and wherein the titanium rod comprises an aircraft landing gear axle.

12. An aircraft assembly comprising:
a titanium rod comprising a first threaded portion;
a titanium nut comprising a second threaded portion conforming with the first threaded portion for mating engagement with the first threaded portion, wherein one of the first threaded portion and the second threaded portion defines a male thread and the other one of the first threaded portion and the second threaded portion defines a female thread such that the nut can be wound in threading engagement along the rod; and
a threaded insert formed from a first metal of different hardness in comparison to titanium, the threaded insert being coupled to the rod or the nut to define the first threaded portion or the second threaded portion respectively such that one of the first threaded portion and the second threaded portion is formed from titanium and the other one of the first threaded portion and the second threaded portion is formed from the first metal;
wherein the insert is formed from a copper nickel tin alloy comprising at least 75% by weight copper and at least 15% nickel and at least 5% tin.

Assignees

• Safran Landing Systems Uk Ltd

Inventors

• Hilliard Matthew

Classifications

• B64C25/36

  Arrangements or adaptations of wheels, tyres or axles in general · CPC title

• B64C25/58

  Arrangements or adaptations of shock-absorbers or springs (shimmy-dampers B64C25/50) · CPC title

• B21H3/02

  external screw-threads {; Making dies for thread rolling} · CPC title

• F16B7/18

  using screw-thread elements {(F16B7/025 takes precedence; for turnbuckles F16B7/06)} · CPC title

• F16B33/00

  Features common to bolt and nut · CPC title