Aircraft attitude indicator device

Patent metadata

Field	Value
Publication number	US-9643732-B2
Application number	US-201514736526-A
Country	US
Kind code	B2
Filing date	Jun 11, 2015
Priority date	Jun 12, 2014
Publication date	May 9, 2017
Grant date	May 9, 2017

Abstract

An aeroplane attitude indicator device includes a mobile rod which includes a first end connected by a link to a support fastened to the aeroplane and a second end to which is connected a moving body, at least one actuator for controlling the motions of the rod, and a system for piloting the at least one actuator as a function of information originating from an attitude detection system of the aeroplane, so as to orient the rod in a vertical direction. The assembly of rod and moving body correspond to a pendulum-like artifact. Also described is an aeroplane cockpit equipped with an attitude indicator device.

First claim

The invention claimed is:

1. An attitude indicator device of an aeroplane, the device comprising:
a mobile rod comprising a first end connected by a link to a support fastened to the aeroplane and a second end to which is connected a moving body;
at least one actuator for controlling the motions of the rod;
a system for piloting said at least one actuator as a function of information originating from an attitude detection system of the aeroplane, so as to orient the rod in a vertical direction,
wherein the assembly of rod and moving body correspond to a pendulum-like artefact.

2. The attitude indicator device of an aeroplane according to claim 1 , further comprising at least one luminous element with at least one of a luminous intensity and a colour which varies as a function of a signal, of an alarm or of a parameter of the aeroplane.

3. The attitude indicator device of an aeroplane according to claim 2 , wherein the at least one of the luminous intensity and the colour change when the aeroplane has at least one of a trim and a bank exceeding a given threshold.

4. The attitude indicator device of an aeroplane according to claim 2 , wherein the at least one of the luminous intensity and the colour vary as a function of the vertical speed of the aeroplane.

5. The attitude indicator device of an aeroplane according to claim 1 , wherein the mobile rod is telescopic and wherein the attitude indicator device comprises an actuator for controlling the length of the telescopic rod as a function of a parameter of the aeroplane.

6. The attitude indicator device of an aeroplane according to claim 5 , wherein the length of the telescopic rod varies as a function of the vertical speed of the aeroplane.

7. The attitude indicator device of an aeroplane according to claim 1 , further comprising a cowling in the form of an aeroplane mockup.

8. The attitude indicator device of an aeroplane according to claim 1 , wherein the link comprises:
a first pivoting axis parallel to an aeroplane longitudinal axis (X 1 ) which pivots on itself with respect to an intermediate support;
a first actuator configured to control a pivoting motion of the first pivoting axis;
a second pivoting axis parallel to an aeroplane transverse axis (Y 1 ) which pivots on itself with respect to the support;
a second actuator configured to control a pivoting motion of the second pivoting axis;
wherein the intermediate support is fastened to the second pivoting axis.

9. An aeroplane cockpit comprising an attitude indicator device comprising:
a mobile rod comprising a first end connected by a link to a support fastened to the aeroplane and a second end to which is connected a moving body;
at least one actuator for controlling the motions of the rod;
a system for piloting said at least one actuator as a function of information originating from an attitude detection system of the aeroplane, so as to orient the rod in a vertical direction,
wherein the assembly of rod and moving body correspond to a pendulum-like artefact, and
wherein the attitude indicator device is positioned in a cockpit zone situated in a peripheral field of vision of a pilot who is installed in a piloting station and who is looking straight ahead.

Assignees

• Airbus Operations Sas

Inventors

• Laine Franck
• Sapin Olivier
• Renault Leberquer Charles

Classifications

• G01C21/16

  by integrating acceleration or speed, i.e. inertial navigation · CPC title

• B64D43/02 Primary

  for indicating aircraft speed or stalling conditions · CPC title

• G01C21/18

  Stabilised platforms, e.g. by gyroscope · CPC title

• G01C19/44

  for indicating the vertical · CPC title

• G01D13/22 Primary

  Pointers, e.g. settable pointer · CPC title