초록 ▼

Method and device for an optimal management of the energy of an aircraft. The device (1) includes means (5) for determining, in an iterative manner, according to a predicted energy state and according to a management strategy, optimal commands of means (S1,S2, S3, S4, S5, S6) for controlling the ene

Method and device for an optimal management of the energy of an aircraft. The device (1) includes means (5) for determining, in an iterative manner, according to a predicted energy state and according to a management strategy, optimal commands of means (S1,S2, S3, S4, S5, S6) for controlling the energy of the aircraft, which allow the aircraft to reach a given point of a trajectory in a given operational state.

대표청구항 ▼

1. An optimized energy management method for an aircraft, upon a flight along a predetermined trajectory so as to join a given point of said trajectory in a given operational state characterized by a set of constraints, a method wherein, upon the flight of the aircraft along said trajectory until sa

1. An optimized energy management method for an aircraft, upon a flight along a predetermined trajectory so as to join a given point of said trajectory in a given operational state characterized by a set of constraints, a method wherein, upon the flight of the aircraft along said trajectory until said given point, automatically and repetitively, the sequence of successive steps is implemented as follow: a) the current values of parameters of the aircraft are determined;b) the predicted energy state of the aircraft at said point is calculated with the help of at least one prediction module (12) as a function of these current values and predetermined models, and iteratively as a function of the predicted energy state, optimized command orders of means (S1, S2, S3, S4, S5, S6) for controlling the aircraft energy are determined with the help of at least one optimization module (Cn), according to a management strategy, said optimized command orders being such that they allow the aircraft to reach said given point in the given operational state; andc) the optimized command orders being thus determined are applied to said energy control means (S1, S2, S3, S4, S5, S6) for the aircraft,a method according to which a plurality of different modes is provided, each of which is associated with particular energy control means and, as a function of the management strategy used at step b), a priority order of said modes enabling the selection of the mode being used is determined through a mode management module (11). 2. The method according to claim 1, wherein the management strategy used at step b) corresponds to a selected strategy and in the absence of selection, to a default strategy. 3. The method according to claim 1, wherein at step b), at least one of the following management strategies can be used:a noise reduction strategy;a fuel consumption reduction strategy;a comfort management strategy for the passengers;a maximum efficiency strategy;a destination distance management strategy; andat least one mixed strategy combining at least two of the preceding strategies. 4. The method according to claim 1, wherein at step c), information relative to the control of the energy control means is presented to a pilot of the aircraft on a viewing screen (19). 5. The method according claim 1, wherein for a control mode for slats and flaps and for the landing gear of the aircraft, the following operations are performed at step b): α 1) a predicted energy profile is calculated thru the prediction module (12);α 2) for such predicted energy profile, an energy error is calculated;α 3) if the energy error is not stabilized, iteratively the following operations are performed, consisting in: calculating the efficiency of the command orders on the objective to be reached;calculating the correction to be applied to the command orders; andupdating the command orders;and then back to step α 1); andα 4) if the energy error is stabilized and minimized, said optimized command orders looked at are obtained. 6. The method according to claim 5, wherein said prediction module (12) predicts the energy at the given point by progressive calculations for a plurality of successive segments along the trajectory until the given point, each segment corresponding to a constant aerodynamic configuration phase or to an aerodynamic configuration transient phase, parameters predicted at the end of any segment being used as initial parameters for the segment following directly, and in that said optimization module (C1) calculates correction to be applied to the command orders so as to be able to cancel the energy error. 7. The method according to claim 1, wherein at least some of the following modes are taken into account: a control mode for the slats and flaps;a control mode for the airbrakes;a control mode for the engines;a control mode for means modifying the planned vertical trajectory of the aircraft;a control mode for means modifying the planned lateral trajectory of the aircraft; anda control mode for means modifying the setpoint speed servo-controlled by the self-thrust. 8. The method according to claim 5, wherein, for each mode, a prediction module (12) and an optimization module (Cn) are provided for the command orders to be applied to the energy control means associated with said mode, and said modules (12, Cn) are implemented at step b) to determine said optimized command orders. 9. The method according to claim 1, wherein said models comprise at least some of the following elements: a wind model, performance models for the aircraf, an indication of the dynamics of actuators associated with energy control means and an indication of operational constraints. 10. The method according to claim 1, wherein in the case of a failure of the energy control means, a reconfiguration is performed on un failing energy control means. 11. An optimized energy management device for an aircraft upon a flight along a trajectory so as to join a given point of said trajectory in a given operational state characterized by a set of constraints, said device (1) comprising: means (2) to determine the current values of parameters of the aircraft upon the flight of the aircraft along said trajectory until the given point;means (5) comprising at least one prediction module (12) to calculate the predicted energy state at said point, as a function of these current values and predetermined models, and at least one optimization module (Cn) to determine iteratively as a function of the predicted energy state, according to a management strategy, optimized command orders of energy control means of the aircraft, said optimized command orders being such that they allow the aircraft to reach said given point in said given operational state;means (S1, S2, S3, S4, S5, S6) for controlling the energy of the aircraft, to which the optimized command orders being so determined are applied, a plurality of different modes being provided, each of which is associated with particular energy control means; anda mode management module (11) determining for each management strategy a mode priority order enabling to select the mode to be used. 12. The device according to claim 11, wherein it comprises in addition display means (17) to present the pilot of the aircraft, on a viewing screen (19), information relative to the command of the energy control means. 13. The device according to claim 11. wherein it comprises in addition interface means (4) enabling an operator to enter data into said device (1). 14. An aircraft, wherein it comprises a device (1) such the one specified in claim 11.