Helical connecting link and method for energy absorption using the same

Patent metadata

Field	Value
Publication number	US-12565317-B2
Application number	US-202318199132-A
Country	US
Kind code	B2
Filing date	May 18, 2023
Priority date	Aug 4, 2022
Publication date	Mar 3, 2026
Grant date	Mar 3, 2026

Abstract

A connecting link for connecting first and second components such as an aircraft seat leg and a track fastener. The link includes a helical middle portion forming an interior space in which an energy attenuator is positioned. In embodiments, the energy attenuator includes inner and outer cylindrical bodies that operate in translation upon a deformation of a lattice structure configured to deform when at least one of a compressive threshold and a tensive threshold is met. In embodiments, the energy attenuator receives part of one of the first and second components. The connecting link may be manufactured by an additive manufacturing process and used in an aircraft leg assembly to save weight and absorb impact energy on the leg.

First claim

What is claimed is:

1 . A connecting link, comprising:
a housing having a first axial end portion attachable to a first component, a second axial end portion attachable to a second component, and a helically shaped middle portion extending from the first axial end portion to the second axial end portion and forming an interior space; and an energy attenuator positioned in the interior space, the energy attenuator comprising:
an inner cylindrical member extending axially from one end of the first axial end portion;
an outer cylindrical member extending axially from one end of the second axial end portion and circumferentially surrounding a portion of the first cylindrical member; and
an annular lattice structure positioned between one end of the second cylindrical member and the first axial end portion and circumferentially surrounding a portion of the first cylindrical member; wherein at least one of the helically shaped middle portion and the energy attenuator is configured to undergo plastic deformation when a threshold force on the connecting link is met.

2 . The connecting link according to claim 1 , wherein:
the annular lattice structure is configured to compress when a compressive threshold on the connecting link is met and break into at least two parts when a tensive threshold on the connecting link is met; compression or breakage of the annular lattice structure causes relative movement between the first and second cylindrical members; and compression or breakage of the annular lattice structure causes deformation of the helically shaped middle portion.

3 . The connecting link according to claim 1 , wherein deformation of the helically shaped middle portion includes at least one of elongation, contraction, twisting and bending of the helically shaped middle portion.

4 . The connecting link according to claim 1 , wherein an axial passage is formed through the first cylindrical member.

5 . The connecting link according to claim 1 , wherein an interface between the inner and outer cylindrical members comprises an annular recess formed in the inner cylindrical member and an annular collar formed on the outer cylindrical member and engaged in the annular recess, wherein when a tensive threshold on the connecting link is met, the annular collar is configured to compress the inner cylindrical member radially inward.

6 . The connecting link according to claim 1 , wherein each of the first and second axial end portions is divided into two leg portions including aligned transverse openings.

7 . The connecting link according to claim 1 , wherein the energy attenuator comprises a rectangular cylindrical body configured to receive a portion of the second component.

8 . The connecting link according to claim 1 , manufactured by an additive manufacturing process.

9 . An aircraft seat leg assembly, comprising:
a leg; a track fastener; and a connecting link connecting the leg to the track fastener, the connecting link comprising:
a housing having a first axial end portion attached to the first component, a second axial end portion attached to the second component, and a helically shaped middle portion extending from the first axial end portion to the second axial end portion and forming an interior space; and
an energy attenuator positioned in the interior space;
wherein at least one of the helically shaped middle portion and the energy attenuator is configured to undergo plastic deformation when a threshold force on the connecting link is met.

10 . The aircraft seat leg assembly according to claim 9 , wherein the energy attenuator comprises:
an inner cylindrical member extending axially from one end of the first axial end portion; an outer cylindrical member extending axially from one end of the second axial end portion and circumferentially surrounding a portion of the first cylindrical member; and an annular lattice structure positioned between one end of the second cylindrical member and the first axial end portion and circumferentially surrounding a portion of the first cylindrical member.

11 . The aircraft seat leg assembly according to claim 10 , wherein:
the annular lattice structure is configured to compress when a compressive threshold on the connecting link is met and break into at least two parts when a tensive threshold on the connecting link is met; compression or breakage of the annular lattice structure causes relative movement between the first and second cylindrical members; compression or breakage of the annular lattice structure causes deformation of the helically shaped middle portion; and deformation of the helically shaped middle portion includes at least one of elongation, contraction, twisting and bending of the helically shaped middle portion.

12 . The aircraft seat leg assembly according to claim 11 , wherein an interface between the inner and outer cylindrical members comprises an annular recess formed in the inner cylindrical member and an annular collar formed on the outer cylindrical member and engaged in the annular recess, wherein when a tensive threshold on the connecting link is met, the annular collar is configured to compress the inner cylindrical member radially inward.

13 . The aircraft seat leg assembly according to claim 9 , wherein each of the first and second axial end portions is divided into two leg portions including aligned transverse openings.

14 . The aircraft seat leg assembly according to claim 9 , wherein the energy attenuator comprises a rectangular cylindrical body configured to receive a tang extending from the leg.

15 . A connecting link, comprising:
a housing having a first axial end portion attachable to a first component, a second axial end portion attachable to a second component, and a helically shaped middle portion extending from the first axial end portion to the second axial end portion and forming an interior space; and an energy attenuator positioned in the interior space, the energy attenuator comprising a rectangular cylindrical body configured to receive a portion of the second component; wherein at least one of the helically shaped middle portion and the energy attenuator is configured to undergo plastic deformation when a threshold force on the connecting link is met.

16 . The connecting link according to claim 15 , wherein the energy attenuator comprises:
an inner cylindrical member extending axially from one end of the first axial end portion; an outer cylindrical member extending axially from one end of the second axial end portion and circumferentially surrounding a portion of the first cylindrical member; and an annular lattice structure positioned between one end of the second cylindrical member and the first axial end portion and circumferentially surrounding a portion of the first cylindrical member.

17 . The connecting link according to claim 16 , wherein:
the annular lattice structure is configured to compress when a compressive threshold on the connecting link is met and break into at least two parts when a tensive threshold on the connecting link is met; compression or breakage of the annular lattice structure causes relative movement between the first and second cylindrical members; and compression or breakage of the annular lattice structure causes deformation of the helically shaped middle portion.

18 . The connecting link according to claim 16 , wherein an axial passage is formed through the first cylindrical member.

19 . The connecting link according to claim 15 , wherein each of

Assignees

• Be Aerospace Inc

Inventors

• Acharya Pradeep
• Rao Sreekanth
• Dempah Maxime

Classifications

• B64D11/0648

  Lower frame constructions · CPC title

• B64D11/0619 Primary

  with energy absorbing means specially adapted for mitigating impact loads for passenger seats, e.g. at a crash · CPC title