Curvilinear Rudder Bar For An Aircraft And Aircraft Comprising Such A Curvilinear Rudder Bar

Patent metadata

Field	Value
Publication number	US-2017166296-A1
Application number	US-201615370037-A
Country	US
Kind code	A1
Filing date	Dec 6, 2016
Priority date	Dec 11, 2015
Publication date	Jun 15, 2017
Grant date	—

Abstract

The rudder bar includes two actuation arrangements, each provided with two pedals, each actuation arrangement having a frame provided with two rails arranged on either side of said frame and being in the form of a concave curve, and, associated with each one of said rails, a movable carriage, each one of said movable carriages bearing one of said pedals, each one of said movable carriages being configured such that it can be moved on the associated rail, for a direction command, under an action exerted by at least one foot of a pilot on at least one of said pedals.

First claim

1 . A rudder bar for an aircraft, said rudder bar comprising at least one actuation arrangement having first and second pedals,
wherein said actuation arrangement comprises: at least one frame, said frame having first and second rails, each one of said first and second rails being in the form of a concave curve; and associated with said first and second rails, a first and second movable carriage, respectively, each one of said first and second movable carriages bearing one of said first and second pedals, each one of said first and second movable carriages being configured to be moved on the associated rail, for a direction command, under an action exerted by at least one foot of a pilot on at least one of said first and second pedals.

2 . The rudder bar as claimed in claim 1 , wherein said frame has an elongate general shape.

3 . The rudder bar as claimed in claim 1 , wherein each one of said first and second movable carriages is connected to a cylinder arranged along the associated rail.

4 . The rudder bar as claimed in claim 1 , wherein each one of said first and second movable carriages has an arrangement of rollers mounted so as to be able to rotate and are configured so as to be able to move on the associated rail.

5 . The rudder bar as claimed in claim 1 , wherein said frame is provided with structural tubes.

6 . The rudder bar as claimed in claim 1 , wherein said actuation arrangement comprises an adjustment arrangement configured so as to allow an operator to modify the neutral positions of the pedals.

7 . The rudder bar as claimed in claim 1 , wherein said frame has an attachment arrangement, said attachment arrangement comprising two rods secured at right angles with respect to one another at one end, referred to as the front end, of the frame, and a connecting fitting provided with a stiffening rod and is secured to the other end, referred to as the rear end, of the frame.

8 . The rudder bar as claimed in claim 1 , wherein each one of said first and second pedals is mounted so as to be able to rotate on the associated movable carriage for a braking command.

9 . The rudder bar as claimed in claim 8 , wherein each one of said first and second pedals is connected to a hydraulic cylinder and to a connecting arm, forming an articulated triangle.

10 . The rudder bar as claimed in claim 1 , wherein said actuation arrangement comprises hydraulic fluid-transfer devices for at least one of the following commands: a direction command and a braking command.

11 . An aircraft, comprising a rudder bar comprising:
at least one actuation arrangement having first and second pedals, wherein said actuation arrangement comprises: at least one frame, said frame having first and second rails, each one of said first and second rails being in the form of a concave curve; and associated with said first and second rails, a first and second movable carriage, respectively, each one of said first and second movable carriages bearing one of said first and second pedals, each one of said first and second movable carriages being configured to be moved on the associated rail, for a direction command, under an action exerted by at least one foot of a pilot on at least one of said first and second pedals

12 . The aircraft as claimed in claim 11 , comprising a cockpit having a floor, wherein said frame is positioned such that a rear end thereof, located to the rear with respect to the direction of flight of the aircraft, is raised above the floor of the cockpit.

13 . The aircraft as claimed in claim 12 , wherein said frame is secured at a front end thereof, via two rods arranged at right angles with respect one another, to at least one structural element, and at a rear end thereof, via a connecting fitting, to a joist of the floor of the cockpit, the connecting fitting being provided with a stiffening rod.

Assignees

• Airbus Operations Sas

Inventors

• Guering Bernard
• Saint-Marc Laurent

Classifications

• G05G1/405

  infinitely adjustable · CPC title

• B64C13/12 Primary

  Dual control apparatus · CPC title

• G05G1/36

  Mounting units comprising an assembly of two or more pedals, e.g. for facilitating mounting · CPC title

• B64C25/44

  Actuating mechanisms · CPC title

• B64C13/42

  having duplication or stand-by provisions · CPC title