Method and device for generating a speed for an aircraft during a taxiing

1. A method of generating a controlled speed for an aircraft along a ground trajectory, comprising the steps of:

a) receiving a ground trajectory comprised of a series of successive elements and receiving a speed profile which defines, for each element of the ground trajectory, associated speed values;

b) measuring a current position of the aircraft;

c) calculating an interpolated speed of the speed profile that corresponds to the current position of of the aircraft, wherein the interpolated speed is calculated on the basis of said ground trajectory, said speed profile and said current position;

d) calculating, by a weighting factor calculation unit, a weighting factor from an angular deviation, wherein the angular deviation is calculated by an angular deviation calculation unit from a measured current aircraft heading and the ground trajectory;

e) determining an auxiliary speed from said interpolated speed; and

f) multiplying the determined auxiliary speed by said weighting factor to generate said controlled speed which represents a longitudinal speed command that commands the aircraft to move along said ground trajectory while complying with said speed profile.

2. The method as claimed in claim 1 , wherein said auxiliary speed corresponds to said interpolated speed.

3. A method of generating a controlled speed for an aircraft along a ground trajectory, comprising the steps of:

a) receiving a ground trajectory comprised of a series of successive elements and receiving a speed profile which defines, for each element of the ground trajectory, associated speed values;

b) measuring a current position of the aircraft;

c) calculating an interpolated speed of the speed profile that corresponds to the current position of the aircraft, wherein the interpolated speed is calculated on the basis of said ground trajectory, said speed profile and said current position;

d) calculating, by a weighting factor calculation unit, a weighting factor from an angular deviation, wherein the angular deviation is calculated by an angular deviation calculation unit from a measured current aircraft heading and the ground trajectory;

e) determining an auxiliary speed from:

a first predicted speed, which is determined from the speed profile at a first prediction horizon, wherein the first prediction horizon is based on a response time of the aircraft engines,

a first predictive speed control, which is calculated from the first predicted speed,

a second predicted speed, which is determined from the speed profile at a second prediction horizon, wherein the second prediction horizon is based on a response time of the brakes of the aircraft, and

a second predictive speed control, which is calculated from the second predicted speed; and

f) multiplying the determined auxiliary speed by said weighting factor to generate said controlled speed which represents a longitudinal speed command that commands the aircraft to move along said ground trajectory while complying with said speed profile.

4. The method as claimed in claim 3 , wherein said first predicted speed is determined from:

a curvilinear abscissa attained at said first prediction horizon, wherein the curvilinear abscissa is determined from said ground trajectory; and

a speed profile corresponding to the determined curvilinear abscissa.

5. The method as claimed in claim 3 , wherein said second predicted speed is determined from:

a curvilinear abscissa attained at said second prediction horizon, wherein the curvilinear abscissa is determined from said ground trajectory; and

a speed profile corresponding to the determined curvilinear abscissa.

6. A method of generating a controlled speed for an aircraft along a ground trajectory, comprising the steps of:

a) receiving a ground trajectory comprised of a series of successive elements and receiving a speed profile which defines, for each element of the ground trajectory, associated speed values;

b) measuring a current position of the aircraft;

c) calculating an interpolated speed of the speed profile that corresponds to the current position of the aircraft, wherein the interpolated speed is calculated on the basis of said ground trajectory, said speed profile and said current position;

d) calculating, by a weighting factor calculation unit, a weighting factor from an angular deviation, wherein the angular deviation is calculated by an angular deviation calculation unit from a measured current aircraft heading and the ground trajectory;

e) determining an auxiliary speed from the calculated interpolated speed; and

f) multiplying the determined auxiliary speed by said weighting factor to generate said controlled speed which represents a longitudinal speed command that commands the aircraft to move along said ground trajectory while complying with said speed profile, wherein the controlled speed is generated by measuring current yaw rate rmes of the aircraft, and generating the controlled speed Vc from the following relation:

Vlim =min( Vc ,( Ny·g )/ rmes,Vreg,Vtr,Vadh )

wherein

Vlim is a limit for the controlled speed,

Ny is a lateral load factor,

g is acceleration due to gravity,

Vreg is maximum regulatory speed on the airport domain,

Vtr is maximum load speed of the aircraft, and

Vadh is maximum tire grip speed of the aircraft.