Method and device for activating the display of at least one stall margin indicator of an aircraft

Patent metadata

Field	Value
Publication number	US-9840337-B2
Application number	US-201615164213-A
Country	US
Kind code	B2
Filing date	May 25, 2016
Priority date	Jun 1, 2015
Publication date	Dec 12, 2017
Grant date	Dec 12, 2017

Abstract

An activation device comprising a computation unit configured to compute a stall margin of the aircraft, an information reception unit configured to receive information indicating if an automatic angle-of-attack protection system of the aircraft is active or inactive, and an activation unit configured to activate the display of the stall margin indicator only if the automatic angle-of-attack protection system is inactive.

First claim

The invention claimed is:

1. A method for activating the display of at least one stall margin indicator on at least one screen of a cockpit of an aircraft, said method comprising:
A) computing a stall margin of the aircraft;
B) receiving information indicating if an automatic angle-of-attack protection system of the aircraft is active or inactive; and
C) activating the display of the stall margin indicator, only if the automatic angle-of-attack protection system is inactive, the displayed stall margin indicator being positioned on the screen at a distance from a symbol illustrating a parameter of the aircraft, which is representative of said stall margin, the stall margin being materialized by the distance.

2. The method as claimed in claim 1 , wherein the activation of the display of the stall margin indicator is disabled if step A) does not have sufficient information to perform the computation of the stall margin.

3. The method as claimed in claim 1 , said method comprising a first auxiliary step comprising computing a consolidated angle-of-attack, said step A) using said consolidated angle-of-attack computed in the first auxiliary step for the implementation thereof.

4. The method as claimed in claim 3 , wherein said consolidated angle-of-attack is deduced from a monitored angle-of-attack obtained by at least one of checking the validity of a plurality of angle-of-attack computation sources of the aircraft or an estimated angle-of-attack.

5. The method as claimed in claim 1 , said method comprising a second auxiliary step comprising computing a consolidated Mach number of the aircraft, said step A) using said consolidated Mach number for the implementation thereof.

6. The method as claimed in claim 5 , wherein said consolidated Mach number is deduced from a monitored Mach number obtained by checking at least one of the validity of a plurality of Mach number computation sources of the aircraft or an estimated Mach number.

7. The method as claimed in claim 3 , said method further comprising a second auxiliary step comprising computing a consolidated Mach number of the aircraft, wherein step A) comprises computing the stall margin from the consolidated angle-of-attack and from the consolidated Mach number.

8. The method as claimed in claim 1 , said method comprising an additional step of management of at least one stall prevention device, said additional management step using, for the implementation thereof, the stall margin computed in step A).

9. The method as claimed in claim 8 , wherein said stall prevention device corresponds to at least one of the following elements: a stall audio alert, a stall text alert, an anti-stall stick shaker, an anti-stall stick pusher and a stall limit speed indicator.

10. The method as claimed in claim 1 , wherein the activation of the display of said stall margin indicator is disabled if the current Mach number of the aircraft is outside of a predetermined range.

11. The method as claimed in claim 1 , wherein a symbology of the stall margin indicator is variable and a function of the stall margin value.

12. A device for activating the display of at least one stall margin indicator on at least one screen of a cockpit of an aircraft, said activation device comprising:
a unit for computing a stall margin of the aircraft;
an information reception unit configured to receive information indicating whether an automatic angle-of-attack protection system of the aircraft is active or inactive; and
an activation unit configured to activate the display of the stall margin indicator only if the automatic angle-of-attack protection system is inactive, the displayed stall margin indicator being positioned on the screen at a distance from a symbol illustrating a parameter of the aircraft, which is representative of said stall margin, the stall margin being materialized by the distance.

13. A stall management assembly, comprising:
at least one display system, and a device for activating the display of at least one stall margin indicator on at least one screen of a cockpit of an aircraft, said activation device comprising:
a unit for computing a stall margin of the aircraft;
an information reception unit configured to receive information indicating whether an automatic angle-of-attack protection system of the aircraft is active or inactive; and
an activation unit configured to activate the display of the stall margin indicator only if the automatic angle-of-attack protection system is inactive, the displayed stall margin indicator being positioned on the screen at a distance from a symbol illustrating a parameter of the aircraft, which is representative of said stall margin, the stall margin being materialized by the distance.

14. An aircraft comprising a stall management assembly as claimed in claim 13 .

Assignees

• Airbus Operations Sas
• Airbus Operations Sas

Inventors

• Tanguy Alain
• Bourret Thierry
• Lanterna Florent
• Boitrel Matthieu

Classifications

• G01C1/00

  Measuring angles · CPC title

• B64D43/02 Primary

  for indicating aircraft speed or stalling conditions · CPC title