Force application device for an aircraft control column and method for using such a control column

Patent metadata

Field	Value
Publication number	US-2023028481-A1
Application number	US-202017757625-A
Country	US
Kind code	A1
Filing date	Nov 30, 2020
Priority date	Dec 20, 2019
Publication date	Jan 26, 2023
Grant date	—

Abstract

The invention relates to a force application device for an aircraft control column, the control column comprising a control lever configured to rotate a first shaft and a second shaft, the force application device comprising a first force feedback member configured to exert a resistive force opposing the rotation of the first shaft, a second force feedback member configured to exert a resistive force opposing the rotation of the second shaft and a common braking device comprising a housing, a first braking member and a second braking member which are coaxial and mounted rotatably inside the housing and configured to engage with the first shaft and the second shaft, respectively, so as to brake them, preferably simultaneously.

First claim

1 - 12 . (canceled)

13 . A force application device for a control column for an aircraft, the control column comprising a first shaft, a second shaft and a control lever configured to rotatably drive the first shaft about a first axis and the second shaft about a second axis, the force application device comprising:
a first force feedback member configured to exert a resistive force opposing the rotation of the first shaft about the first axis and a second force feedback member configured to exert a resistive force opposing the rotation of the second shaft about the second axis, the force application device being comprising a common braking device comprising a casing, a first braking member and a second braking member which are coaxial and rotatably mounted in the casing and are configured to cooperate respectively with the first shaft and the second shaft so as to brake them, simultaneously

14 . The force application device according to claim 13 , wherein, each braking member comprises a drive portion projecting from the casing and a brake portion mounted in the casing.

15 . The force application device according to claim 14 , wherein, the common braking device comprises a first volume and a second volume in which the brake portions of the braking members are respectively mounted, each volume comprising a magnetorheological fluid whose shear strength is variable as a function of a magnetic field applied to said magnetorheological fluid.

16 . The force application device according to claim 13 , wherein the braking members respectively cooperate with the shafts at a reduction ratio greater than 1.

17 . The force application device according to claim 13 , wherein the first braking member cooperates with the first shaft via a first gear connection.

18 . The force application device according to claim 13 , wherein the second braking member cooperates with the second shaft via a second gear connection.

19 . The force application device according to claim 13 , wherein the second braking member cooperates with the second shaft via a second connecting rod.

20 . The force application device according to claim 13 , wherein the first braking member cooperates with the first shaft via a first connecting rod.

21 . The force application device according to claim 14 , wherein the drive portions of the braking members extend projecting from said casing in the same direction.

22 . The force application device according to claim 14 , wherein, the drive portions of the braking members extend projecting from said casing in opposite directions.

23 . A control column for an aircraft, the control column comprising a first shaft, a second shaft and a control lever configured to rotatably drive the first shaft about a first axis and the second shaft about the second axis, the control column comprising the force application device according to claim 13 connected to the first shaft and the second shaft.

24 . A method for using the control column according to claim 23 , wherein, in a nominal operating mode, the common braking device being inactive so as to allow free rotation of the first shaft and the second shaft, the method comprises a step of activating the common braking device in an emergency operating mode in which the common braking device brakes the first shaft and the second shaft, simultaneously.

Assignees

• Safran Electronics & Defense

Inventors

• Joncour Yvon
• Lawniczak Rémi-Louis
• Bezivin Philippe
• Guillon Clément

Classifications

• B64C13/0421 Primary

  control sticks for primary flight controls · CPC title

• G05G2009/04766

  providing feel, e.g. indexing means, means to create counterforce · CPC title

• G05G9/047

  the controlling member being movable by hand about orthogonal axes, e.g. joysticks {(for switches H01H25/04)} · CPC title

• B64C13/10

  comprising warning devices · CPC title