Adjustable support links for aircraft

Patent metadata

Field	Value
Publication number	US-11858645-B2
Application number	US-202217752450-A
Country	US
Kind code	B2
Filing date	May 24, 2022
Priority date	May 24, 2022
Publication date	Jan 2, 2024
Grant date	Jan 2, 2024

Abstract

Adjustable support links for aircraft are disclosed herein. An adjustable support link includes a first rod end including a first shaft with first external threads, a second rod end including a second shaft with a bore having first internal threads, and a barrel nut at least partially disposed in the bore of the second rod end. The barrel nut has second external threads engaged with the first internal threads. The barrel nut having a channel. The first shaft is at least partially disposed in the channel. The channel has second internal threads engaged with the first external threads of the first rod end, such that rotation of the barrel nut in a first direction causes the first and second rod ends to move toward each other and rotation of the barrel nut in a second direction causes the first and second rod ends to move away from each other.

First claim

What is claimed is:

1. An adjustable support link comprising:
a first rod end including a first shaft with first external threads;
a second rod end including a second shaft with a bore having first internal threads, the second shaft having a first opening;
a barrel nut at least partially disposed in the bore of the second rod end, the barrel nut having second external threads engaged with the first internal threads of the second rod end, the barrel nut having a channel, the first shaft at least partially disposed in the channel, the channel having second internal threads engaged with the first external threads of the first rod end, such that rotation of the barrel nut in a first direction causes the first and second rod ends to move toward each other and rotation of the barrel nut in a second direction causes the first and second rod ends to move away from each other;
a plug disposed in the bore of the second shaft and coupled to the second shaft, the plug including a disc-shaped portion and a post extending from the disc-shaped portion and into a notch in an end of the first shaft to prevent relative rotation of the first and second rod ends, the disc-shaped portion having a second opening aligned with the first opening; and
a pin extending through the first and second openings to prevent relative rotation of the plug and the second shaft.

2. The adjustable support link of claim 1 , wherein the first and second rod ends are aligned along a longitudinal axis, and wherein at least a portion of the first and second shafts overlap in a radial direction extending from the longitudinal axis.

3. The adjustable support link of claim 1 , wherein the barrel nut has a head disposed outside of the bore.

4. The adjustable support link of claim 3 , wherein a portion of an external surface of the second shaft is faceted.

5. The adjustable support link of claim 1 , wherein the second shaft has a third opening extending in a direction that is perpendicular to a longitudinal axis of the adjustable support link, such that at least a portion of the barrel nut that is disposed in the bore is viewable through the third opening.

6. The adjustable support link of claim 1 , wherein the first external threads and the second internal threads have a first thread pitch, and the first internal threads and the second external threads have a second thread pitch different than the first thread pitch.

7. The adjustable support link of claim 1 , wherein the second rod end and the barrel nut include wire openings to receive a wire to prevent rotation of the barrel nut relative to the first and second rod ends.

8. The adjustable support link of claim 1 , wherein the first rod end has a first end portion with a first end portion opening to receive a first bolt, and the second rod end has a second end portion with a second end portion opening to receive a second bolt.

9. The adjustable support link of claim 8 , wherein a distance between the first end portion opening and the second end portion opening is less than about 3.5 inches.

10. The adjustable support link of claim 8 , wherein the first end portion opening is oriented parallel to the second end portion opening.

11. An aircraft comprising:
an airframe;
an engine; and
an adjustable support link coupled between the airframe and the engine, the adjustable support link including:
a first rod end coupled to the engine, the first rod end having a first shaft;
a second rod end coupled to the airframe, the first and second rod ends aligned along a longitudinal axis, the second rod end having a second shaft with a bore, the first shaft of the first rod end extending into the bore of the second shaft such that at least a portion of the first shaft and the second shaft overlap in a radial direction;
a barrel nut at least partially disposed in the bore of the second shaft and between the first shaft and the second shaft;
a plug disposed in the bore of the second shaft and coupled to the second shaft, a portion of the plug extending into a notch in an end of the first shaft to prevent relative rotation of the first and second rod ends, wherein the second shaft has a first opening and the plug has a second opening aligned with the first opening; and
a pin disposed in the first and second openings to prevent relative rotation of the plug and the second shaft, wherein the barrel nut is rotatable in the bore of the second shaft while the pin is disposed in the first and second openings.

12. The aircraft of claim 11 , wherein:
the first shaft has first external threads,
the second shaft has first internal threads,
the barrel nut has second external threads engaged with the first internal threads of the second rod end, and
the barrel nut has a channel, the first shaft at least partially disposed in the channel, the channel having second internal threads engaged with the first external threads of the first rod end.

13. The aircraft of claim 12 , wherein the barrel nut has a head disposed outside of the bore of the second shaft.

14. The aircraft of claim 11 , wherein the bore extends into an end of the second shaft, wherein the first shaft extends into the bore such that the end of the first shaft is a first distance from the end of the second shaft, and wherein the first opening in the second shaft is a second distance from the end of the second shaft, the second distance being greater than the first distance.

15. The aircraft of claim 11 , wherein the plug includes a disc-shaped portion and a post, the second opening formed in the disc-shaped portion, and the post extending from the disc-shaped portion and into the notch in the end of the first shaft.

16. A method comprising:
coupling an engine to an airframe of an aircraft at a forward mount;
coupling the engine to the airframe at a rear mount by coupling an adjustable support link between the engine and the airframe; and
adjusting a length of the adjustable support link to move the engine relative to the airframe, the adjustable support link including:
a first rod end, the first rod end having a first shaft;
a second rod end, the first and second rod ends aligned along a longitudinal axis, the second rod end having a second shaft with a bore, the first shaft of the first rod end extending into the bore of the second shaft such that at least a portion of the first shaft and the second shaft overlap in a radial direction;
a barrel nut at least partially disposed in the bore of the second shaft and between the first shaft and the second shaft;
a plug disposed in the bore of the second shaft and coupled to the second shaft, a portion of the plug extending into a notch in an end of the first shaft to prevent relative rotation of the first and second rod ends, wherein the second shaft has a first opening and the plug has a second opening aligned with the first opening; and
a pin disposed in the first and second openings to prevent relative rotation of the plug and the second shaft, wherein the barrel nut is rotatable in the bore of the second shaft while the pin is disposed in the first and second openings.

17. The method of claim 16 , wherein coupling the adjustable support link between the engine and the airframe includes coupling the first rod end of the adjustable support link to a first attachment portion of the engine and coupling the second rod end of the adjustable support link to a second attachment portion of the airframe.

18. The method of claim 17 , wherein the barrel nut is threadably engaged with the first shaft and threadably engaged with the second shaft, and wherein ad

Assignees

• Boeing Co

Inventors

• Boas Jonathan P

Classifications

• B64D27/402

  comprising box like supporting frames, e.g. pylons or arrangements for embracing the power plant · CPC title

• F16B7/06 Primary

  Turnbuckles (for cables, ropes, or wire F16G11/12) · CPC title

• B64D27/26 Primary

  Operations & Transport · mapped topic

• F02C7/20

  Mounting or supporting of plant; Accommodating heat expansion or creep · CPC title

• F16G11/12

  Connections or attachments, e.g. turnbuckles, adapted for straining of cables, ropes, or wire (straining wire in general B21F9/00) · CPC title