Method and system for aiding the piloting of an aircraft, during a maneuver bringing about an increase in the attitude of the aircraft

1. A method of aiding the piloting of an aircraft during a maneuver bringing about an increase in the attitude of the aircraft, according to which method the following steps are carried out automatically and repeatedly:

a) a first value of attitude of the aircraft is taken into account;

b) the current attitude of the aircraft is determined;

c) an attitude deviation is determined by subtracting said first value of attitude from said current attitude; and

d) at least one horizon line is presented on a display screen of a head-up display device, superimposed with the environment seen in front of the aircraft, wherein:

in step d), a first section of indication which indicates said attitude deviation is moreover presented on said display screen,

said first value of attitude corresponds to an optimal value of attitude at the end of the maneuver, and

said first section of indication is presented on said display screen at a fixed position and said horizon line is presented on said display screen in a moveable manner.

2. The method as claimed in claim 1 , wherein said first section of indication is presented on an attitude scale, on which is also presented a second section of indication indicating said current attitude of the aircraft.

3. The method as claimed in claim 1 , wherein in step d), a symbol of protection against a rear collision is moreover presented on the display screen.

4. An aircraft, which comprises a system able to implement the method specified under claim 1 .

5. A method of aiding the piloting of an aircraft during a maneuver bringing about an increase in the attitude of the aircraft, according to which method the following steps are carried out automatically and repeatedly:

a) a first value of attitude of the aircraft is taken into account;

b) the current attitude of the aircraft is determined;

c) an attitude deviation is determined by subtracting said first value of attitude from said current attitude; and

d) at least one horizon line is presented on a display screen of a head-up display device, superimposed with the environment seen in front of the aircraft, wherein:

in step d), a first section of indication which indicates said attitude deviation is moreover presented on said display screen, and

said first value of attitude corresponds to the minimum value between, on the one hand, an optimal value of attitude at the end of the maneuver and, on the other hand, a value of attitude of protection against a rear collision.

6. The method as claimed in claim 5 , wherein said first section of indication is presented on an attitude scale, on which is also presented a second section of indication indicating said current attitude of the aircraft.

7. The method as claimed in claim 5 , wherein, during a phase of takeoff of the aircraft, said minimum value corresponds:

to said value of attitude of protection, which is constant, when the aircraft is rolling on the ground;

to said value of attitude of protection, which becomes variable and increasing, when the main landing gear of the aircraft leaves the ground, doing so until this value of attitude of protection becomes equal to the optimal value of attitude; and

to said optimal value of attitude thereafter.

8. A system for aiding piloting for an aircraft, said system comprising:

a set of information sources, comprising at least one information source which determines a current attitude of the aircraft;

a first section that transmits a first value of attitude;

a second section that determines an attitude deviation, by subtracting said first value of attitude from said current attitude;

a calculation unit which is connected to said set of information sources; and

a head-up display device, which is connected to said calculation unit and which is able to present, on a display screen, superimposed with the environment seen in front of the aircraft, at least one horizon line, wherein:

said display device moreover presents on said display screen, superimposed with the environment seen in front of the aircraft, at least one first section of indication indicating said attitude deviation determined by said second section, and

said first section is formed so as to transmit, as the first value of attitude, the minimum value between, on the one hand, an optimal value of attitude at the end of the maneuver and, on the other hand, a value of attitude of protection against a rear collision.

9. The system as claimed in claim 8 , wherein said display device is formed in such a way as to moreover present, on said display screen, an attitude scale and a second section of indication which is associated with said attitude scale and which indicates the current attitude of the aircraft.

10. The system as claimed in claim 8 , wherein it furthermore comprises a section of input making it possible for an operator to input at least one value corresponding to said optimal value of attitude.

11. An aircraft, which comprises a system such as that specified under claim 8 .