Device for confirming the engine thrust of an aircraft

• US 8,384,563 B2
• Filed: 05/28/2010
• Issued: 02/26/2013
• Est. Priority Date: 06/02/2009
• Status: Expired due to Fees

• Current Assignee: Airbus Operations (European Aeronautic Defence and Space Company EADS NV)
• Original Assignee: Airbus Operations (European Aeronautic Defence and Space Company EADS NV)
• Inventors: Fernandez, Brice
• Primary Examiner(s): Nguyen, Tai T
• Application Number:
  US12/790,032
• Publication Number:
  US 20100302073A1
• Time in Patent Office: 1,005 Days
• Field of Search: 340/959, 340/963, 340/966, 340/969, 340/945, 340/971, 340/973, 701/3, 701/14, 701/15, 701/29, 701/33, 701/99
• US Class Current: 340/959
• CPC Class Codes: B64D 31/00 Power plant control systems; Arrangement of power plant control systems in aircraft
• CPC Class Codes: G01D 2207/10 Displays which are primarily used in aircraft or display aircraft-specific information
• CPC Class Codes: G01D 2207/30 Displays providing further information, in addition to measured values, e.g. status
• CPC Class Codes: G01D 7/002 giving both analog and numerical indication

Abstract

A device for confirming the engine thrust of an aircraft is disclosed. The device, via an operating logic unit (14) of each engine processing different information, including a warning indicator (15) connected to the unit (14) delivers or not thrust confirmation information at the level of the cockpit.

Claims

1. A device for confirming a thrust of at least one engine of an aircraft while it is running on a ground surface, upon a take-off phase thereof, such a device comprising:

at least one display screen (2) in a cockpit of the aircraft permanently displaying at least one control parameter of each engine allowing to check the thrust delivered by one of them;

an operating logic unit (14) for each engine, receiving at least information on said control parameter of said engine when said thrust is reached, on the take-off mode position of a throttle lever corresponding to said engine and on a ground position of said aircraft; and

a warning indicator connected at an outlet of said logic unit and able to display, at a level of said cockpit, thrust confirmation information when said information received by said logic unit is validated,

wherein said logic unit (14) comprises, for each engine, at least an AND gate (24) receiving, at respective inlets thereof, said information on the control parameter of said engine, on the take-off mode position of said throttle lever, and on the ground position of said aircraft, and, when said information is gathered and validated, delivers, at the outlet thereof, said thrust confirmation information in a direction of said warning indicator (15), and

wherein said logic unit (14) further comprises, for each engine;

an OR gate (34) receiving at the respective inlets thereof at least information on a lack of thrust by said engine, on a position of the throttle lever other than that relating to the take-off mode, on a flight position of the aircraft and on a velocity of the aircraft higher than a take-off decision velocity; and

a toggle (28) at the inlets of which there are received said outlet information delivered by said AND gate (24) and said outlet information delivered by said OR gate (34), and the outlet of which is connected to said warning indicator (15).

2. A device according to claim 1, wherein said control parameter of said engine relates to at least one of those relating to a rotation speed of the engine, to a pressure ratio of said engine or to the thrust ratio of said engine with respect to a maximum thrust thereof.

3. A device according to claim 1, wherein said warning indicator (15) is integrated into said display screen (2).

4. A device according to claim 1, wherein said warning indicator (15) displays a light message.

5. A device according to claim 1, wherein an individual warning indicator (15) is associated with each engine.

6. A device according to claim 1, wherein a common warning indicator (15) is associated with all of said engines.

7. A device according to claim 6, wherein said thrust confirmation information coming out of said logic units (14) is sent to an AND gate (40), the outlet of which delivers said common overall confirmation information to all the engines in the direction of said common warning indicator.

8. A device according to claim 1, wherein, after said confirmation information has been displayed, a piece of information is addressed to said warning indicator (15) for cancelling the display of said thrust confirmation information.