Motion control system for an aircraft seat

Patent metadata

Field	Value
Publication number	US-12428162-B2
Application number	US-202318218404-A
Country	US
Kind code	B2
Filing date	Jul 5, 2023
Priority date	Jul 25, 2022
Publication date	Sep 30, 2025
Grant date	Sep 30, 2025

Abstract

An aircraft seat may include an integrated motion control system. The motion control system may include one or more user controlled sub-systems. Each sub-system may include at least one of a user control device, a lever arm, and a metering pin assembly. The lever arm may couple to the user control device and synchronously transmit a force to one or more cables in response to an actuation of the user control device. The metering pin assembly may include a metering pin which may be configured to attach to an end portion of the one or more cables and receive a force from the one or more cables causing the respective control sub-system to execute an adjustment control operation. The adjustment control operation may include a vertical position adjustment, a swivel position adjustment, or a track position adjustment.

First claim

What is claimed is:

1. A motion control system for an aircraft seat, the motion control system comprising:
one or more control sub-systems, each control sub-system comprising:
a user control device;
a lever arm coupled to the user control device, the lever arm configured to synchronously transmit a force to one or more cables in response to an actuation of the user control device; and
a metering pin assembly, the metering pin assembly including a metering pin, the metering pin configured to attach to an end portion of the one or more cables and receive a force from the one or more cables causing the respective control sub-system to execute an adjustment control operation.

2. The system of claim 1 , wherein the metering pin assembly further comprises:
a metering pin housing; and
a spring contained within the metering pin housing, wherein the spring is coupled to the metering pin.

3. The system of claim 2 , wherein at least a top portion of the metering pin housing is configured as a cable length adjustment feature.

4. The system of claim 1 , further comprising one or more cable fastening assemblies, the one or more cable fastening assemblies comprising:
an adjustment fitting configured to attach to at least a portion of the one or more cables, wherein at least a portion of the adjustment fitting is threaded; and
one or more fasteners configured to couple to the threaded portion of the adjustment fitting, wherein the one or more fasteners are configured to secure the adjustment fitting and one or more cables in place.

5. The system of claim 1 , wherein the one or more control sub-systems includes a stop mechanism, wherein the stop mechanism is positioned at a select location along an angular path of the lever arm, wherein the lever arm is configured to rotate along the angular path until it reaches the stop mechanism.

6. The system of claim 1 , wherein the one or more control sub-systems includes a vertical adjustment control sub-system configured to allow a user to adjust a vertical position of the aircraft seat.

7. The system of claim 1 , wherein the one or more control sub-systems includes a track adjustment control sub-system configured to allow a user to adjust a track position of the aircraft seat.

8. The system of claim 1 , wherein the one or more control sub-systems includes a swivel adjustment control sub-system configured to allow a user to adjust a swivel position of the aircraft seat.

9. The system of claim 1 , wherein at least one of the one or more control sub-systems are configured to couple to a side portion of the seat pan.

10. The system of claim 1 , wherein at least one of the one or more control sub-systems includes one or more interchangeable parts.

11. An aircraft seating system comprising:
an aircraft seat including at least one of a seat frame, seatback structure and a seat pan structure; and
one or more motion control systems, each motion control system comprising:
one or more control sub-systems, each control sub-system comprising:
a user control device;
a lever arm coupled to the user control device, the lever arm configured to synchronously transmit a force to one or more cables in response to an actuation of the user control device; and
a metering pin assembly, the metering pin assembly including a metering pin, the metering pin configured to attach to an end portion of the one or more cables and receive a force from the one or more cables causing the respective control sub-system to execute an adjustment control operation.

12. The system of claim 11 , wherein the metering pin assembly further comprises:
a metering pin housing; and
a spring contained within the metering pin housing, wherein the spring is coupled to the metering pin.

13. The system of claim 12 , wherein at least a top portion of the metering pin housing is configured as a cable length adjustment feature.

14. The system of claim 11 , further comprising one or more cable fastening assemblies, the one or more cable fastening assemblies comprising:
an adjustment fitting configured to attach to at least a portion of the one or more cables, wherein at least a portion of the adjustment fitting is threaded; and
one or more fasteners configured to couple to the threaded portion of the adjustment fitting, wherein the one or more fasteners are configured to secure the adjustment fitting and one or more cables in place.

15. The system of claim 11 , wherein the one or more control sub-systems includes a stop mechanism, wherein the stop mechanism is positioned at a select location along an angular path of the lever arm, wherein the lever arm is configured to rotate along the angular path until it reaches the stop mechanism.

16. The system of claim 11 , wherein the one or more control sub-systems includes a vertical adjustment control sub-system configured to allow a user to adjust a vertical position of the aircraft seat.

17. The system of claim 11 , wherein the one or more control sub-systems includes a track adjustment control sub-system configured to allow a user to adjust a track position of the aircraft seat.

18. The system of claim 11 , wherein the one or more control sub-systems includes a swivel adjustment control sub-system configured to allow a user to adjust a swivel position of the aircraft seat.

19. The system of claim 11 , wherein at least one of the one or more control sub-systems are configured to couple to a side portion of the seat pan.

20. The system of claim 11 , wherein at least one of the one or more control sub-systems includes one or more interchangeable parts.

Assignees

• Ami Ind Inc

Inventors

• Marutzky Kyler J

Classifications

• B60N2/0881

  Activation of the latches by the control mechanism · CPC title

• B60N2/0862

  sliding · CPC title

• B60N2002/971

  the locking system being an element distinct from articulation means, retaining the seat or seat part in its folded position, e.g. controlled by a wire · CPC title

• B60N2/305

  the cushion being hinged on the vehicle frame · CPC title

• B60N2/3047

  the cushion being hinged at the back-rest · CPC title