Automatic take-off method and device for an airplane
First Claim
Patent Images
1. An automatic take-off method for an airplane, whereby, for an elevation guidance of the airplane on a take-off, the following successive series A of steps is performed, automatically and repetitively, on said take-off, comprising:
- A, a) determining an elevation guidance objective, using a flight management system, which represents an angular profile along the pitch axis of the airplane, said angular profile being expressed according to a first parameter;
A. b) measuring, using a standard trim device, the current value of said first parameter on the airplane;
A. c) from said elevation guidance objective and said measured current value of said first parameter, determining, using an automatic piloting device, a vertical piloting objective which is expressed as rate of pitch;
A. d) from said vertical piloting objective, determining, using a flight control computer, elevator deflection commands for the airplane; and
A. e) the determined elevator deflection commands are applied to operators of said elevators, wherein, in the step A. c), determining said vertical piloting objective QcPA from the following expression;
QcPA=k1·
(θ
c−
θ
eff)in which;
k1 is a predetermined gain;
θ
c represents said angular profile which can be used to obtain optimized performance levels according to take-off conditions; and
θ
eff represents a measured current value of said first parameter,wherein for a lateral guidance of the airplane on the take-off, the following successive series of steps B is performed, automatically and repetitively, on said take-off, comprising;
B. a) determining a lateral guidance objective which represents a particular guidance reference and which is expressed according to at least one second parameter;
B. b) measuring the current value of said second parameter on the airplane;
B. c) from said lateral guidance objective and said measured current value of said second parameter, determining a lateral piloting objective which is expressed as rate of yaw;
B. d) from said lateral piloting objective, determining actuation commands to control elements acting on the yaw of the airplane; and
B. e) applying said determined elevator actuation commands to operators of said elements,wherein said guidance reference concerns a second parameter which is defined for the runway used by the airplane for the take-off,wherein said second parameter is the heading of the runway, andwherein, in the step B. c), said lateral piloting objective re is determined from the following expression;
rc=reff+[k2−
reff+k3·
(ψ
c−
ψ
eff)]/k4in which;
k2, k3 and k4 are predetermined gains,reff is a measured current value of the rate of yaw of the airplane,ψ
c represents said guidance reference which corresponds to the geographic heading of the runway, andψ
eff is a measured current value of the heading of the airplane.
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Abstract
Automatic take-off method and device for an airplane. The device includes a device for automatically determining, using an elevation guidance objective, a vertical piloting objective which is expressed as rate of pitch, and a device for automatically determining, using the vertical piloting objective, deflection commands for elevators of the airplane.
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Citations
26 Claims
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1. An automatic take-off method for an airplane, whereby, for an elevation guidance of the airplane on a take-off, the following successive series A of steps is performed, automatically and repetitively, on said take-off, comprising:
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A, a) determining an elevation guidance objective, using a flight management system, which represents an angular profile along the pitch axis of the airplane, said angular profile being expressed according to a first parameter; A. b) measuring, using a standard trim device, the current value of said first parameter on the airplane; A. c) from said elevation guidance objective and said measured current value of said first parameter, determining, using an automatic piloting device, a vertical piloting objective which is expressed as rate of pitch; A. d) from said vertical piloting objective, determining, using a flight control computer, elevator deflection commands for the airplane; and A. e) the determined elevator deflection commands are applied to operators of said elevators, wherein, in the step A. c), determining said vertical piloting objective QcPA from the following expression;
QcPA=k1·
(θ
c−
θ
eff)in which; k1 is a predetermined gain; θ
c represents said angular profile which can be used to obtain optimized performance levels according to take-off conditions; andθ
eff represents a measured current value of said first parameter,wherein for a lateral guidance of the airplane on the take-off, the following successive series of steps B is performed, automatically and repetitively, on said take-off, comprising; B. a) determining a lateral guidance objective which represents a particular guidance reference and which is expressed according to at least one second parameter; B. b) measuring the current value of said second parameter on the airplane; B. c) from said lateral guidance objective and said measured current value of said second parameter, determining a lateral piloting objective which is expressed as rate of yaw; B. d) from said lateral piloting objective, determining actuation commands to control elements acting on the yaw of the airplane; and B. e) applying said determined elevator actuation commands to operators of said elements, wherein said guidance reference concerns a second parameter which is defined for the runway used by the airplane for the take-off, wherein said second parameter is the heading of the runway, and wherein, in the step B. c), said lateral piloting objective re is determined from the following expression;
rc=reff+[k2−
reff+k3·
(ψ
c−
ψ
eff)]/k4in which; k2, k3 and k4 are predetermined gains, reff is a measured current value of the rate of yaw of the airplane, ψ
c represents said guidance reference which corresponds to the geographic heading of the runway, andψ
eff is a measured current value of the heading of the airplane. - View Dependent Claims (2, 3, 4, 5, 6, 7, 8, 9, 10, 11, 12)
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13. An automatic take-off method for an airplane, whereby, for an elevation guidance of the airplane on a take-off, the following successive series A of steps is performed automatically and repetitively, on said take-off, comprising:
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A. a) determining an elevation guidance objective, using a flight management system, which represents an angular profile along the pitch axis of the airplane, said angular profile being expressed according to a first parameter; A. b) measuring, using a standard trim device, the current value of said first parameter on the airplane; A. c) from said elevation guidance objective and said measured current value of said first parameter, determining, using an automatic piloting device, a vertical piloting objective which is expressed as rate of pitch; A. d) from said vertical piloting objective, determining, using a flight control computer, elevator deflection commands for the airplane; and A. e) the determined elevator deflection commands are applied to operators of said elevators, wherein, in the step A. c), determining said vertical piloting objective QcPA from the following expression;
QcPa=k1·
(θ
c−
θ
eff)in which; k1 is a predetermined gain; θ
c represents said angular profile which can be used to obtain optimized performance levels according to take-off conditions; andθ
eff represents a measured current value of said first parameter, whereinfor a lateral guidance of the airplane on the take-off, the following successive series of steps B is performed, automatically and repetitively, on said take-off, comprising; B. a) determining a lateral guidance objective which represents a particular guidance reference and which is expressed according to at least one second parameter; B. b) measuring the current value of said second parameter on the airplane; B. c) from said lateral guidance objective and said measured current value of said second parameter, determining a lateral piloting objective which is expressed as rate of yaw; B. d) from said lateral piloting objective, determining actuation commands to control elements acting on the yaw of the airplane; and B. e) applying said determined elevator actuation commands to operators of said elements, wherein, in the step B. c), said lateral piloting objective rc is determined from the following expressions;
rc=reff−
[Y3+(V2·
Δ
ψ
+2·
V1·
reff)]/Vground·
k5
Y3=k6·
[k7·
(k8·
[Yd−
Y]−
Vy)+(V1·
Δ
ψ
+Vground·
r)]in which; k5, k6, k7 and k8 are predetermined gains; reff is a measured current value of the rate of yaw of the airplane; V2 is a measured derivative of the longitudinal acceleration of the airplane; V1 is a measured longitudinal acceleration of the airplane; Vground is a measured ground speed of the airplane; Δ
ψ
is a current heading clearance error;Yd is a lateral position to be followed in a runway check-point; Y is a lateral position of the airplane in the runway check-point; and Vy is a lateral speed of the airplane in the runway cheek-point. - View Dependent Claims (14, 15)
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16. An automatic take-off method for an airplane, whereby, for an elevation guidance of the airplane on a take-off, the following successive series A of steps is performed, automatically and repetitively, on said take-off, comprising:
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A. a) determining an elevation guidance objective, using a flight management system, which represents an angular profile along the pitch axis of the airplane, said angular profile being expressed according to a first parameter; A. b) measuring, using a standard trim device, the current value of said first parameter on the airplane; A. c) from said elevation guidance objective and said measured current value of said first parameter, determining, using an automatic piloting device, a vertical piloting objective which is expressed as rate of pitch; A. d) from said vertical piloting objective, determining, using a flight control computer, elevator deflection commands for the airplane; and A. e) the determined elevator deflection commands are applied to operators of said following expression;
QcPA=k1·
(θ
c−
θ
eff)in which; k1 is a predetermined gain; θ
c represents said angular profile which can be used to obtain optimized performance levels according to take-off conditions; andθ
eff represents a measured current value of said first parameter,wherein, for a lateral guidance of the airplane on the take-off, the following successive series of steps B is performed automatically and repetitively on said take-off, comprising; B. a) determining a lateral guidance objective which represents a particular guidance reference and which is expressed according to at least one second parameter; B. b) measuring the current value of said second parameter on the airplane; B. c) from said lateral guidance objective and said measured current value of said second parameter, determining a lateral piloting objective which is expressed as rate of yaw; B. d) from said lateral piloting objective, determining actuation commands to control elements acting on the yaw of the airplane; and B. e) applying said determined elevator actuation commands to operators of said elements, and wherein the alignment of the airplane is automatically monitored so as to ensure that it is on a runway authorized for the take-off. - View Dependent Claims (17, 18, 19)
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20. An automatic take-off device for an airplane, said device including a first automatic piloting assembly, comprising:
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a first device configured for automatically determining an elevation guidance objective which represents an angular profile along the pitch axis of the airplane, said angular profile being expressed according to a first parameter; a second device configured for to automatically measuring the current value of said first parameter on the airplane; a third device configured for automatically determining, from said elevation guidance objective and said measured current value of said first parameter, a vertical piloting objective which is expressed as rate of pitch; a fourth device configured for automatically determining, from said vertical piloting objective, deflection commands for elevators of the airplane; and operators of said elevators, to which are automatically applied the deflection commands determined by said fourth device, wherein said third device includes a unit determining said vertical piloting objective QcPA, from the following expression;
QcPA=k1·
(θ
c−
θ
effin which; k1 is a predetermined gain; θ
c represents said angular profile which can be used to obtain optimized performance levels according to take-off conditions;θ
eff represents the measured current value of said first parameter,a second automatic piloting assembly which comprises; a fifth device automatically determining a lateral guidance objective which represents a particular guidance reference and which is expressed according to at least one second parameter; a sixth device automatically measuring the current value of said second parameter on the airplane; a seventh device automatically determining, from said lateral guidance objective and said measured current value of said second parameter, a lateral piloting objective which is expressed as rate of yaw; an eighth device automatically determining, from said lateral piloting objective, actuation commands for controlling elements acting on the yaw of the airplane; and operators of said elements acting on the yaw of the airplane, to which are automatically applied the actuation commands determined by said eighth device, wherein said guidance reference concerns a second parameter which is defined for the runway used by the airplane for the take-off, wherein said second parameter is the heading of the runway, and wherein said seventh device determines said lateral piloting objective re from the following expression;
rc=reff+[k2−
reff+k3·
(ψ
c−
ψ
eff)]/k4in which; k2, k3 and k4 are predetermined gains, reff is a measured current value of the rate of yaw of the airplane, ψ
c represents said guidance reference which corresponds to the geographic heading of the runway, andψ
eff is a measured current value of the heading of the airplane. - View Dependent Claims (21, 22, 23, 24, 25)
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26. An automatic take-off method for an airplane, whereby, for an elevation guidance of the airplane on a take-off, the following successive series A of steps is performed, automatically and repetitively, on said take-off, comprising:
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A. a) determining an elevation guidance objective, using a flight management system, which represents an angular profile along the pitch axis of the airplane, said angular profile being expressed according to a first parameter; A. b) measuring, using a standard trim device, the current value of said first parameter on the airplane; A. c) from said elevation guidance objective and said measured current;
value of said first parameter, determining a vertical piloting objective, using an automatic piloting device, which is expressed as rate of pitch;A. d) from said vertical piloting objective, determining, using a flight control computer, elevator deflection commands for the airplane; and A. e) the duly determined deflection commands are applied to operators of said elevators, wherein, in the step A. c), determining said vertical piloting objective QcPA from the following expression;
QcPA=k1·
(θ
c−
θ
eff)in which; k1 is a predetermined gain; θ
c represents said angular profile which can be used to obtain optimized performance levels according to take-off conditions; andθ
eff represents a measured current value of said first parameter,wherein, for a lateral guidance of the airplane on the take-off, the following successive series of steps B is performed, automatically and repetitively, on said take-off, comprising; B. a) determining a lateral guidance objective which represents a particular guidance reference and which is expressed according to at least one second parameter; B. b) measuring the current value of said second parameter on the airplane; B. c) from said lateral guidance objective and said measured current value of said second parameter, determining a lateral piloting objective which is expressed as rate of yaw; B. d) from said lateral piloting objective, determining actuation commands to control elements acting on the yaw of the airplane; and B. e) applying said duly determined actuation commands to operators of said elements, wherein said guidance reference concerns a second parameter which is defined for the runway used by the airplane for the take-off wherein said second parameter is the heading of the runway, wherein, in the step B. c), said lateral piloting objective rc is determined from the following expression;
rc=reff+[k2−
reff+k3·
(ψ
c−
ψ
eff)]/k4in which; k2, k3 and k4 are predetermined gains; reff is a measured current value of the rate of yaw of the airplane; ψ
e represents said guidance reference which corresponds to the geographic heading of the runway; andψ
eff is a measured current value of the heading of the airplane.
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Specification