SYSTEM FOR CONTROLLING AT LEAST ONE AIRCRAFT ENGINE AND AN AIRCRAFT COMPRISING SUCH A CONTROL SYSTEM

• US 20100301174A1
• Filed: 05/25/2010
• Published: 12/02/2010
• Est. Priority Date: 05/29/2009
• Status: Abandoned Application

• 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, Lamonzie, Vincent
• Application Number:
  US12/787,272
• Publication Number:
  US 20100301174A1
• Time in Patent Office: Days
• US Class Current: 244/234
• CPC Class Codes: B64D 31/04 actuated personally
• CPC Class Codes: B64D 31/06 actuated automatically

Abstract

A system for controlling at least one aircraft engine and an aircraft comprising such a control system. The system (4) comprises a control lever (5) of the engine, the intermediary range of automatic regulation thereof of the engine speed of which comprises a single marked position (II) with which there is associated a plurality of speeds, corresponding to each one of the flight phases of the aircraft (AC) such as take-off and climbing phases.

Claims

1. A system for controlling at least one engine (1) of an aircraft (AC) by means of a specific moving control lever (5), comprising:

a control lever (5) being able to occupy two extreme positions (I, III) corresponding to the idle speed (1) and to the maximum speed (III) of said engine (1), as well as an intermediary range of automatic regulation of the speed of said engine (1), the lower limit of said intermediary range being defined by the extreme position (I) corresponding to the idle speed, wherein;

said intermediary range (6) comprises a single marked position (II), corresponding to the upper limit thereof;

a plurality of speeds of said engine (1), corresponding to each one of the flight phases of said aircraft (AC), such as the take-off and climbing phases, is associated with said marked position (II) of the intermediary range (6); and

said system (4)comprising;

means (7) for determining the usual flight phase of said aircraft (AC); and

means (8) for automatically controlling speeds of said engine (1) associated with said marked position (H) of the intermediary range (6), from information received from said determination means (7).

2. A system according to claim 1, wherein said plurality of speeds of said engine (1) associated with said marked position (II) of the intermediary range (6) is automatically determined.

3. A system according to claim 1, wherein said plurality of speeds of said engine (1) associated with said marked position (11) of the intermediary range (6) is manually determined by the pilot.

4. A system according to claim 1, wherein said automatic control means (8) automatically manage the speed transitions between said successive flight phases of said aircraft (AC).

5. A system according to claim 1, wherein said automatic control means (8) automatically manage the speed transitions within one single phase of said aircraft (AC).

6. A control lever of an engine (1) of an aircraft (AC) belonging to a control system according to claim 1, said control lever (5) being able to occupy two extreme positions (1, III) corresponding to the idle speed (I) and to the maximum speed (III) of said engine (1), as well as an intermediary range of automatic regulation of the speed of said engine (1), the lower limit of said intermediary range being defined by the extreme position (I) corresponding to the idle speed,

wherein said intermediary range (6) comprises a single marked position (II), corresponding to the upper limit thereof and with which there is associated a plurality of speeds of said engine (1), corresponding to each one of the flight phases of said aircraft (AC) such as the take-off and climbing phases.

7. An aircraft, comprising at least one control system (4) according to claim 1.