Aircraft control comprising a pedal coupled to a cylinder and associated control device

Patent metadata

Field	Value
Publication number	US-10822073-B2
Application number	US-201615377646-A
Country	US
Kind code	B2
Filing date	Dec 13, 2016
Priority date	Dec 14, 2015
Publication date	Nov 3, 2020
Grant date	Nov 3, 2020

Abstract

An aircraft control comprises a mobile pedal and comprises a cylinder coupled to the pedal such that a displacement of the pedal according to at least a first direction reduces the volume of a first chamber of the cylinder. A control device comprises a fluid type bus system connecting two aircraft controls. Additionally, an aircraft is equipped with such a control device.

First claim

The invention claimed is:

1. A control device comprising:
at least one bus system;
a first control associated with a first set of controls; and
a second control associated with a second set of controls,
wherein each control comprises:
a mobile pedal; and
a cylinder comprising a body;
a piston attached to a rod that passes through a first longitudinal end of the cylinder, so that the piston is slidable within the cylinder;
wherein the cylinder comprises a first chamber and a second chamber, the first chamber being located on an opposite side of the piston from the second chamber and the second chamber being located between the piston and the first longitudinal end of the cylinder; and
wherein the cylinder is coupled to the pedal such that a displacement of the pedal in at least a first direction reduces a volume of the first chamber of the cylinder; and

wherein the bus system comprises:
a first line that connects the first chamber of the first control to the second chamber of the second control, and
a second line that connects the second chamber of the first control to the first chamber of the second control.

2. The control device according to claim 1 , wherein the first and second chambers of the cylinders and the first and second lines of the bus system are filled with an incompressible fluid.

3. The control device according to claim 2 , wherein the incompressible fluid is at atmospheric pressure.

4. The control device according to claim 1 , wherein the first and second chambers are separated from each other on opposite sides of the piston.

5. An aircraft comprising a control device, which comprises:
a first aircraft control comprising:
a first mobile pedal; and
a first cylinder comprising a body;
a first piston attached to a first rod that passes through a first longitudinal end of the first cylinder, so that the first piston is slidable within the first cylinder;
wherein the first cylinder comprises a first chamber and a second chamber, the first chamber of the first cylinder being located on an opposite side of the first piston from the second chamber of the first cylinder and the second chamber of the first cylinder being located between the first piston and the first longitudinal end of the first cylinder; and
wherein the first cylinder is coupled to the first pedal such that a displacement of the first pedal according to at least a first direction reduces a volume of the first chamber of the first cylinder;

a second aircraft control comprising:
a second mobile pedal; and
a second cylinder comprising a body;
a second piston attached to a second rod that passes through a first longitudinal end of the second cylinder, so that the second piston is slidable within the second cylinder;
wherein the second cylinder comprises a first chamber and a second chamber, the first chamber of the second cylinder being located on an opposite side of the second piston from the second chamber of the second cylinder and the second chamber of the second cylinder being located between the second piston and the first longitudinal end of the second cylinder; and
wherein the second cylinder is coupled to the second pedal such that a displacement of the second pedal according to at least the first direction reduces a volume of the first chamber of the second cylinder; and

a bus system which connects the first aircraft control and the second aircraft control, the bus system comprising:
a first line that connects the first chamber of the first cylinder to the second chamber of the second cylinder, and
a second line that connects the second chamber of the first cylinder to the first chamber of the second cylinder.

6. The aircraft according to claim 5 , wherein the first and second chambers of the first cylinder are separated from each other on opposite sides of the first piston, and wherein the first and second chambers of the second cylinder are separated from each other on opposite sides of the second piston.

Assignees

• Airbus Operations Sas

Inventors

• Guering Bernard
• Saint-Marc Laurent

Classifications

• Y02T50/40

  Weight reduction · CPC title

• B64C13/044 Primary

  operated by feet, e.g. pedals · CPC title

• B64C13/36

  fluid · CPC title

• B64C25/44 Primary

  Actuating mechanisms · CPC title

• B64C13/44

  overriding of personal controls; with automatic return to inoperative position · CPC title