Quickly adjustable fail-safe link bar assemblies especially useful for connecting structural components of an aircraft

Patent metadata

Field	Value
Publication number	US-11820510-B2
Application number	US-202016807521-A
Country	US
Kind code	B2
Filing date	Mar 3, 2020
Priority date	Mar 26, 2019
Publication date	Nov 21, 2023
Grant date	Nov 21, 2023

Abstract

Link bar assemblies are provided to connect adjacent structural components (e.g., components of an aircraft such as connecting an underwing engine to the wing structure) having respective connection lugs. The link bar assemblies will include a link bar having opposed terminal ends which include circular bearings, bushings operatively received by the circular bearings of the link bar, and a bolt and pin assembly inserted through the bushings to connect the terminal ends of the link bar to the respective connection lugs of the adjacent structural components. At least one of the bushings includes a multi-faceted flange and defines an eccentric aperture (e.g., an elliptical aperture having major and minor axes) such that rotation of the bushing allows the eccentric aperture to become aligned with the mounting opening of a respective connection lug.

First claim

What is claimed is:

1. A link bar assembly to connect adjacent structural components having connection lugs defining respective mounting openings, the link bar assembly comprising:
a link bar having opposed terminal ends which include circular bearings;
bushings operatively received by the circular bearings of the link bar; and
a bolt and pin assembly inserted through the bushings to connect the terminal ends of the link bar to the respective connection lugs of the adjacent structural components, wherein
at least one of the bushings includes a multi-faceted flange and defines an eccentric aperture such that rotation of the bushing allows the eccentric aperture to become aligned with the mounting opening of a respective connection lug, and wherein
the link bar further comprises at least one lock ring which includes an interior circular toothed surface for engagement with the multi-faceted flange of the at least one bushing.

2. The link bar assembly according to claim 1 , wherein the at least one lock ring includes a radially extending lobe which defines a locking aperture that is alignable with a receiving aperture defined by the respective connection lug, and a locking bolt assembly operatively inserted in the locking and receiving apertures to positionally lock the lock ring and the at least one bushing relative to the respective connection lug.

3. The link bar assembly according to claim 1 , which comprises an opposed pair of the bushings wherein each of the opposed pair of bushings includes a multi-faceted flange and defines an eccentric aperture.

4. The link bar assembly according to claim 3 , further comprising a pair of lock rings each of which includes the interior circular toothed surface for engagement with the multi-faceted flange of a respective one of the bushings.

5. The link bar assembly according to claim 4 , wherein each of the lock rings includes a radially extending lobe which defines a locking aperture that is alignable with a receiving aperture defined by the respective connection lug, and a locking bolt assembly operatively inserted in the locking and receiving apertures to positionally lock the lock ring and the at least one bushing relative to the respective connection lug.

6. The link bar assembly according to claim 1 , wherein the eccentric aperture is an elliptical aperture having major and minor axes.

7. The link bar assembly according to claim 1 , wherein the bolt and pin assembly comprises a castle nut, and includes a threaded shank portion on the bolt of the bolt and pin assembly to threadably receive the castle nut.

8. The link bar assembly according to claim 1 , wherein the link bar is axially elongate.

9. The link bar assembly according to claim 8 , wherein the link bar has a cruciform cross-section.

10. An aircraft which comprises the link bar assembly according to claim 1 .

11. An aircraft comprising separated adjacent structural components having respective connection lugs, and a link bar assembly connecting the separated structural components to one another, wherein the link bar assembly comprises:
a link bar having opposed terminal ends which include circular bearings;
bushings operatively received by the circular bearings of the link bar; and
a bolt and pin assembly inserted through the bushings to connect the terminal ends of the link bar to a respective one of the connection lugs of the adjacent structural components, wherein
at least one of the bushings includes a multi-faceted flange and defines an eccentric aperture such that rotation of the bushing allows the eccentric aperture to become aligned with the mounting opening of a respective connection lug, and wherein
the link bar assembly further comprises at least one lock ring which includes an interior circular toothed surface for engagement with the multi-faceted flange of the at least one bushing.

12. The aircraft according to claim 11 , wherein the at least one lock ring includes a radially extending lobe which defines a locking aperture that is alignable with a receiving aperture defined by the respective connection lug, and a locking bolt assembly operatively inserted in the locking and receiving apertures to positionally lock the lock ring and the at least one bushing relative to the respective connection lug.

13. The aircraft according to claim 11 , wherein the link bar assembly comprises an opposed pair of the bushings wherein each of the opposed pair of bushings includes a multi-faceted flange and defines an eccentric aperture.

14. The aircraft according to claim 13 , further comprising a pair of lock rings each of which includes the interior circular toothed surface for engagement with the multi-faceted flange of a respective one of the bushings.

15. The aircraft according to claim 14 , wherein each of the lock rings includes a radially extending lobe which defines a locking aperture that is alignable with a receiving aperture defined by the respective connection lug, and a locking bolt assembly operatively inserted in the locking and receiving apertures to positionally lock the lock ring and the at least one bushing relative to the respective connection lug.

16. The aircraft according to claim 11 , wherein the eccentric aperture is an elliptical aperture having major and minor axes.

17. The aircraft according to claim 11 , wherein the bolt and pin assembly comprises a castle nut, and includes a threaded shank portion on the bolt of the bolt and pin assembly to threadably receive the castle nut.

18. The aircraft according to claim 11 , wherein the link bar is axially elongate and has a cruciform cross-section.

Assignees

• Embraer Sa
• Yabora Ind Aeronautica S A

Inventors

• Padovani André
• Costa Gomes Jonathas Fellipe
• Barros Soares Pedro Henrique

Classifications

• B64D27/402

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

• Y10T403/32893

  including distinct pin retainer · CPC title

• F16C11/045

  with at least a pair of arms pivoting relatively to at least one other arm, all arms being mounted on one pin (crank-pins F16C11/02) · CPC title

• B64C1/22 Primary

  Other structures integral with fuselages to facilitate loading {, e.g. cargo bays, cranes} · CPC title

• B64C7/00 Primary

  Structures or fairings not otherwise provided for · CPC title