Method and device for generating an optimum aerodynamic configuration of an aircraft during a flight

1. A process for automatic flight optimisation of an aerodynamic configuration of an aircraft (A) equipped with wings ( 3 ) which are provided with spoilers ( 6 ), process according to which, in an automatic fashion,

I) the aircraft (A) is monitored to determine a current flight phase, and if the current flight phase corresponds to a particular predetermined flight phase, the following operations are performed:

II/a) an optimum engine angle commands are taken into account, each of which relates to the deflection of spoilers ( 6 ) and is optimised to provide the aircraft (A) with an aerodynamic configuration for optimising a particular parameter in said particular flight phase;

b) a current value of incidence (a) of the aircraft (A) is determined; and

c) using this current value and said optimum engine angle commands, a correct engine angle command is determined which, when applied to said spoilers ( 6 ), provides the aircraft (A) with an optimum aerodynamic configuration for the current situation of the aircraft (A), said current engine angle command being determined using said current value of incidence (a) and a predetermined curve which shows the engine angle command as a function of incidence, said curve including optimum engine angle commands and transitions between such optimum engine angle commands, wherein, when said particular flight phase is an approach phase, the following is determined as the correct engine angle command:

for an incidence lower than a first predetermined value (α 1 ), a first optimum engine angle command providing the aircraft (A) with an aerodynamic configuration for optimising noise;

for an incidence higher than a second predetermined value (α 2 ) which is higher than said first predetermined value (α 1 ), a second optimum engine angle command providing the aircraft (A) with an aerodynamic configuration for optimising airlift; and

for an incidence between said first and second predetermined values (α 1 , α 2 ), a command which is between said first and second optimum engine angle commands, and

wherein, when said particular flight phase is a takeoff phase, the following is determined as the correct engine angle command:

for an incidence lower than a first predetermined value (α 3 ), a first optimum engine angle command providing the aircraft (A) with an aerodynamic configuration for

optimising noise, in the absence of any engine breakdown; and

optimising fineness upon a breakdown of an engine of the aircraft (A);

for an incidence higher than a second predetermined value (α 4 ) which is higher than said first predetermined value (α 3 ), a second optimum engine angle command providing the aircraft (A) with an aerodynamic configuration for optimising airlift; and

for an incidence between said first and second predetermined values (α 3 , α 4 ), a command which is between said first and second optimum engine angle commands.

2. The process according to claim 1 , wherein a step II/d) is further carried out, in which said correct engine angle command, determined in step II/c), is automatically applied to actuators ( 10 ) of the spoilers ( 6 ) of the aircraft (A).

3. The process according to claim 1 , wherein:

the engines of the aircraft (A) are monitored in order to be able to detect a possible breakdown; and

in case a breakdown of an engine of the aircraft (A) is detected, a particular optimum engine angle command is taken into account in step II/a).

4. The process according to claim 1 , wherein said transitions are continuous and monotonic.