METHOD AND SYSTEM FOR AUTOMATICALLY DETERMINING AN OPTIMIZED DESCENT AND APPROACH PROFILE FOR AN AIR

专利摘要:
A method for automatically determining a descent and approach profile for an aircraft is based on a back calculation of propagation of a state of the aircraft along S (i) segments from a back calculation start point. to the starting point DECEL for implementing the deceleration of the aircraft. The automatic determination method comprises for each segment S (i) a determination step (112) of an optimal speed VOPT (i) of the aircraft on the speed range of the next aerodynamic configuration C (j + 1) to implement according to a predetermined deceleration strategy and / or predetermined constraints inherent in the flight procedure or introduced by the pilot in his flight plan.
公开号:FR3037411A1
申请号:FR1501219
申请日:2015-06-12
公开日:2016-12-16
发明作者:Johan Boyer；Wright Benoit Dacre
申请人:Thales SA；
IPC主号:

专利说明:

[0001] The present invention relates to a method for automatically determining an approach profile that optimizes the management of the aerodynamic configuration of an aircraft. BACKGROUND OF THE INVENTION The present invention also relates to a system configured to implement the method of automatically determining an approach profile optimizing the management of the aerodynamic configuration of the aircraft. The present invention also relates to means for displaying and / or inputting input parameters of the automatic determination method. The present invention also relates to display means of the approach profile, determined by the automatic determination method and optimizing the management of the aerodynamic configuration of the aircraft. Today, civilian aircraft determine their vertical descent profile from navigation databases, data entered in the active flight plan, and aircraft performance data. The vertical profile is established by the flight management system (FMS) which calculates the trajectory associated with the performance of the aircraft to best respect the operational constraints. The vertical profile predicted downhill and approach, considers some assumptions about the instants of extension of the actuators affecting the deceleration of the aircraft that are the beaks, the flaps, the landing gear and the airbrakes, these moments being also subsequently called the instants of setting aerodynamic configurations. Today, these instants of setting aerodynamic configurations are defined by speeds provided directly by a performance database. The speeds conventionally used are the maneuvering speeds, that is to say the minimum speeds of setup in automatic management mode. These moments do not vary except for the airbrakes that depend on the performance of the aircraft and predicted slopes.
[0002] This means that these moments do not take into account actual weather conditions or the procedure. These moments are however essential for the calculation of the deceleration profile, the flight time, the fuel consumption and the noise level perceived on the ground. For example, the spouts and flaps are extended at maneuvering speeds, otherwise known as F / S / 0 respectively for the so-called FULL (or 3) aerodynamic configuration in which the spouts and flaps are extended to a high degree, so-called landing. , the so-called aerodynamic configuration 2 in which the nozzles and the flaps are extended to a lesser degree, and the so-called configuration 1. These speeds are the minimum speeds Vmin at which the aerodynamic configurations can be extended when the aircraft is in management mode automatic by the FMS flight management system. In addition, the maximum setting speeds Vmax are called the VFEs and ensure that the loads on the wing remain acceptable. These last speeds are provided to the pilots in the cockpit. In addition, the vertical slopes of the current procedures are often fixed for simplifying reasons (calculation of geometric profile based on altitude constraints of the procedure for example). In the current economic and ecological context, airlines are seeking to reduce the operational costs of flights and reduce their environmental footprint, ie to reduce environmental pollution such as noise or greenhouse gas emissions. through the reduction of fuel consumption. To achieve these objectives, new approach procedures (lower noise - no-stop) of the type CDA (English Continuous Descent Approach) / CDO (English Continuous Descent Approach) are proposed. They must both bring environmental benefits and ensure better determinism, especially on the predicted end-of-procedure time for flow separation problems in approach by air traffic control. In general, the so-called CDA / CDO flight procedures consist in flying higher with a neutral energy profile, that is to say with a minimum thrust, without using the airbrakes, and with instants of setting configuration optimized in terms of energy stabilization and noise pollution.
[0003] Thus, the implementation of the CDA / CDO procedures leads to highly optimized vertical profile constructions where the margin of maneuver to catch up with the vertical plane in case of deviation is reduced. Taking into account this problem, the instants of extension of the spouts and flaps thus play a major role in the calculation of descent and approach profiles in the field of so-called CDA / CDO flight procedures. However, the current solutions for which the choice of configuration change speeds is fixed at a single value are very conservative in this respect, and do not favor the reduction of operational costs as one of the objectives set by said CDA procedures. / CDO. Current solutions include higher fuel consumption. In addition, setting configuration change rates to a single value amounts to setting the deceleration profile and does not adjust to the speed constraints to be satisfied. Moreover, the current solutions do not correspond to the pilot's operational practices, which makes it impossible to reliably and accurately predict fuel consumption and flight time until landing. In general, there is currently no adaptive method for adapting the configuration speeds for each flight, depending on the particularities of the procedures, weather conditions, speed constraints, time, noise and other parameters. , even if the patent application FR 3005759 A1 describes a method of automatically determining an optimized descent and approach profile which makes it possible to modify the instants of configuration in order to overcome non-flightable slope problems. However, the method described does not make it possible to deal with the optimization of layouts in aerodynamic configurations in a richer and more complex set of contexts. The adjustment of the configurations is a major element to adapt the trajectory of the aircraft and its speed profile to the various operational constraints. Nowadays, a simplified modeling of the aerodynamic setup sequence whose instants are generally based on fixed and minimum speeds, does not make it possible to cover the variability of the operating procedures, called "Dive and Drive" or "CDA / CDO", and therefore does not represent current pilots' practices. The technical problem is to provide a method for the automatic determination of an optimized descent and approach profile for an aircraft making it possible to calculate speeds of setting in optimized configurations and correspondingly the instants of change of aerodynamic configurations, considering the wing and structure loads, maneuvering speeds, procedure (speed constraints, time, noise, slope) and operational costs (fuel consumption, noise). The technical problem is to provide a method of automatically determining an optimized descent and approach profile for an aircraft that allows the pilot to have the choice of an early or late deceleration according to the usual practices while ensuring a capacity sufficient deceleration for the stabilization of the aircraft at 1000 ft AGL (in English Above Ground Level) in IFR (in English Instrument Flight Rule) or 500 ft AGL in VFR (in English Visual Flight Rule). To this end, the subject of the invention is a method of automatically determining a descent and approach profile for an aircraft, implemented from a flight management system based on one or more electronic computers, the descent and approach profile evolving from a starting point DECEL for implementing the deceleration of the aircraft to a stabilization point, comprising a sequence of segments defined between successive characteristic points including aerodynamic configuration change points taken from a discrete set of predetermined aerodynamic configurations; the automatic determination method being based on a back calculation of propagation of a state of the aircraft along the segments of the sequence from the stabilization point to the starting point DECEL of the implementation of the deceleration of the aircraft; and the automatic determination method comprising for each current segment S (i) traversed of the profile delimited between a corresponding starting current characteristic point SP (i) of back calculation and a current arrival characteristic point SP (i + 1) associated back calculation method: 3037411 5 .- a step of determining one or more forthcoming aerodynamic configurations C (j + 1) of the aircraft from a current configuration C (j) active at the starting current characteristic point SP (i) back calculation and a nominal sequence of change of aerodynamic configurations; and a determining and supplying step for the next aerodynamic configuration or configurations (Cj + 1) of a possible range of speeds of use of said next aerodynamic configuration C (j + 1) delimited by a minimum speed Vmm (j +1) and a maximum speed Vmax (j + 1); The automatic determination method being characterized in that it comprises for each current running segment S (i), a step of determining an optimum speed Vop-r (i) of the aircraft over the speed range of the next aerodynamic configuration C (j + 1), said optimum speed VopT (i) of the aircraft being a function of a predetermined deceleration strategy and / or predetermined constraints, inherent in the flight procedure or introduced by the pilot in his flight plan. According to particular embodiments, the automatic determination method comprises one or more of the following characteristics: the deceleration strategy is a single-criteria optimization strategy that minimizes a parameter taken from a fuel consumption by the aircraft , an acoustic noise level generated by the aircraft, a journey time, or a multi-criteria optimization strategy that optimizes a combination of several criteria, at least one of them being included in the set formed by fuel consumption, acoustic noise level and travel time; the predetermined constraints inherent in the flight procedure or introduced by the pilot into his flight plan are included in the set of constraints formed by: velocity constraints reached at a point characteristic of a segment greater than or equal to a predetermined threshold value (AT OR ABOVE), or equal to a predetermined threshold value (AT), or less than or equal to a predetermined threshold value (AT OR BELOW), or included in a window of predetermined speeds (WINDOW); and arrival time constraints at a point characteristic of a segment greater than or equal to a predetermined threshold value (AT OR AFTER), or equal to a predetermined threshold value (AT), or less than or equal to one predetermined threshold value (AT OR BEFORE), or included in a predetermined time window (WINDOW); and noise constraints observed from a point characteristic of a segment; and altitude constraints reached at a characteristic end point of a segment greater than or equal to a predetermined threshold value (AT OR ABOVE), or equal to a predetermined threshold value (AT), or less than or equal to a value predetermined threshold (AT OR BELOW), or included in a predetermined velocity window (WINDOW); and fuel consumption constraints; the automatic determination method furthermore comprises for each current segment S (i) traversed, a digital integration step of said segment S (i), making it possible to propagate the state of the aircraft along the current segment S (i) from the associated back calculation characteristic starting point SP (i) to the associated backward calculation characteristic point SP (i + 1), and performed according to the type of the current segment S (i ), defined by the sequencer, and a stopping condition, defined by either reaching the optimum speed of the aircraft in the current segment, or reaching the associated calculation current arrival characteristic point. without having reached the optimum speed of the aircraft; the type of segment is comprised in the set formed by: the Flight Path Angle (FPA) type segment consisting in setting a slope with respect to the ground; and the OPEN type segment of setting a motor speed; and the VS-type segment of setting a vertical speed; and the LEVEL type segment of setting an altitude; the FPA, OPEN, VS, LEVEL type segments being able to be implemented optionally in decelerated mode, in constant speed mode or in accelerated mode; the automatic determination method comprises a flightability test step, performed when the optimum speed of the aircraft is reached, consisting of: determining a limiting slope FPAlin associated with the deployment of the new configuration C (j-F1) as a maximum slope in absolute value to maintain the speed of the aircraft in "idle" thrust without airbrake and without acceleration, and compare the slope of the current segment S (i) to the limit slope FPAlin, determined; When the characteristic point forming the associated back calculation current arrival point is reached without having reached the optimum speed of the aircraft, the performances are compared in terms of optimization according to the DECEL strategy chosen between a first solution. anticipating the aerodynamic configuration change at the arrival point of the current segment S (i), and a second solution of not anticipating the current aerodynamic configuration change; and in the case where the performance in terms of optimization according to the chosen DECEL strategy of the first solution is better than that of the second solution, a limiting slope FPAlim, associated with the deployment of the new aerodynamic configuration is determined as a maximum slope. allowing the speed of the aircraft to be maintained in "idle" thrust without airbrake and without acceleration, then the slope of the current segment S (i) is compared with the limiting slope FPAlim; 15 .- when the slope of the current segment S (i) is greater than or equal to the limit slope FPAum on the new nominal configuration, it is investigated whether an alternative aerodynamic configuration of the new nominal aerodynamic configuration exists, and if it is determined that a new alternative aerodynamic configuration exists, for this alternative performances are compared in terms of optimization according to the DECEL strategy chosen between a first solution of anticipating the aerodynamic configuration change at the arrival point of the current segment with this alternative, and a second solution of not anticipating the current aerodynamic configuration change; And in the case where for this alternative the performance in terms of optimization according to the chosen DECEL strategy of the first solution is better than that of the second solution, then a limiting slope FPAlim associated with the deployment of the new alternative aerodynamic configuration is determined as a maximum slope in absolute value 30 for maintaining the speed of the aircraft in thrust "idle" without airbrake and without acceleration, then the slope of the current segment S (i) is compared to the limit slope FPAim determined; then in the case where the slope of the current segment S (i) is strictly less than or equal in absolute value to the determined limiting slope FPAiim, in a step of modifying the current aerodynamic configuration, the current aerodynamic configuration change in the new alternative aerodynamic configuration is realized; and in the case where there is no new alternative aerodynamic configuration for which the slope of the current segment S (i) is strictly less than or equal in absolute value to the limiting slope FPAlim determined the current aerodynamic configuration is maintained for the integration of the next segment S (i + 1); when the slope of the current segment S (i) is strictly less than or equal to the limiting slope FPAIim for the new aerodynamic configuration C (j + 1), in a step of modifying the current aerodynamic configuration, the configuration change current aerodynamics in the new nominal aerodynamic configuration according to the nominal sequence of the sequencer is realized; when the associated backcalculating current characteristic point is reached without having reached the optimum speed of the aircraft, the performances are compared in terms of optimization according to the DECEL strategy chosen between a first solution consisting in anticipating the aerodynamic configuration change at the characteristic arrival point of the current segment, and a second solution of not anticipating the current aerodynamic configuration change; and in the case where the performance in terms of optimization according to the chosen DECEL strategy of the second solution is better than that of the first solution, it is sought if an alternative aerodynamic configuration of the nominal aerodynamic configuration exists, and if It is determined that an alternative aerodynamic configuration exists, for this alternative the performances are compared in terms of optimization according to the DECEL strategy chosen between a first solution of anticipating the aerodynamic configuration change at the arrival point of the current segment with this alternative, and a second solution of not anticipating the current aerodynamic configuration change.
[0004] The invention also relates to a method for automatically determining a descent and approach profile for an aircraft, implemented from a flight management system based on one or more electronic computers, the descent and approach profile evolving from a DECEL starting point of the deceleration of the aircraft to a stabilization point, comprising a sequence of 3037411 9 horizontal and vertical flight phases passing through successive characteristic points including aerodynamic configuration change points taken from a discrete set of predetermined aerodynamic configurations C (j); the automatic determination method being based on an optimized trajectory calculation which directly integrates the coupling of horizontal and vertical flight phases into the flight plan and being characterized in that it comprises: a step of providing aerodynamic configurations C (j) and calculating for each aerodynamic configuration a range of speeds 10 possible use of said aerodynamic configuration, delimited by a minimum speed Vram (j) and a maximum speed Vmax (j); and .- a step of formulating a problem of computing an overall trajectory from the starting point DECEL to the stabilization point in the form of an optimal control problem; and 15 .- a step of solving the optimal control problem with an arbitration between the constraints of use of the aerodynamic configurations to determine their optimal sequence, a calculation of the characteristic points and a calculation of the VopT (j) optimized configuration speeds. according to a predetermined deceleration strategy and / or predetermined constraints inherent in the flight procedure or introduced by the pilot in his flight plan. The invention also relates to a system for automatically determining a descent and approach profile for an aircraft comprising a flight management system based on one or more electronic computers, data acquisition means for allow a pilot to enter data into the flight management system, one or more displays to display one or more descent profiles of the aircraft, and wherein: .- the descent profile and approach of the aircraft. The aircraft is intended to evolve from a DECEL starting point of the deceleration of the aircraft to a back calculation start point, and comprises a sequence of segments defined between successive characteristic points and positions. changing aerodynamic configurations taken from an integer number of predetermined aerodynamic configurations; and 3037411 10 .- the flight management system (10) is configured to implement an automatic determination method, based on a back calculation of propagation of a state of the aircraft along the segments of the suite since the starting point of calculation back to the starting point DECEL of the implementation of the deceleration of the aircraft; and implement for each current segment S (i) traversed of the profile, delimited between a starting current characteristic point SP (i) associated with calculation back and a current arrival characteristic point SP (i + 1) associated back calculation a step of determining one or more next aerodynamic configurations C (j + 1) of the aircraft from a current configuration C (j) active at the starting current characteristic point SP (i) of back calculation and a nominal sequence of aerodynamic configuration changes; and a step of determining and providing for the next aerodynamic configuration (Cj + 1) a range of possible speeds of use of said aerodynamic configuration C (j + 1), delimited by a minimum speed Vrnin (j + 1) and a maximum speed Vmax (j + 1); the system for automatically determining a descent and approach profile being characterized in that: the capture means and the flight management system are configured to allow the pilot to enter and select a strategy deceleration; and .- the flight management system is configured to determine for each current running segment S (i) an optimum speed VopT (j + 1) of the aircraft 25 over the speed range of the next aerodynamic configuration C (j + 1) according to the chosen deceleration strategy and / or predetermined constraints inherent in the flight procedure or introduced by the pilot in his flight plan. According to particular embodiments, the automatic determination system comprises one or more of the following characteristics: the flight management system is configured to provide the pilot through one or more displays the optimal speeds of change aerodynamic configuration and / or pseudo-points of passage on the predicted trajectory where to perform the aerodynamic configuration changes and / or to provide an autopilot with the optimum aerodynamic configuration change speeds and / or the times of change of aerodynamic configuration; aerodynamic configuration for actuating the corresponding actuator (s); 5 .- the system for automatically determining a descent and approach profile for an aircraft further comprises a set of actuators, formed by nozzles, flaps, airbrakes, a landing gear of the aircraft. to implement the different aerodynamic configurations allowed by the sequencer; each aerodynamic configuration being characterized by a combination of deployment states of the actuators among the nozzles, the flaps, the air brakes, the landing gear, the deployment states of the actuators being each provided by a parameter representative of a first angle formed by the nozzles with a first predetermined direction, a second angle formed by the flaps with a second predetermined direction, a third angle formed by the airbrakes with a third predetermined direction; and the landing gear output status. The invention also relates to a display of aerodynamic configuration changes determined according to the automatic determination method described above comprising: a first display screen of a lateral navigation profile and / or a profile vertical descent in altitudes and / or speeds including each of the pseudo-points of passage in each of which a change of aerodynamic configuration takes place, the geographical positions of the pseudo-points of passage varying according to the chosen deceleration strategy; and / or a second screen for displaying a band of possible speeds of use of a selected aerodynamic configuration and / or an optimized speed of extension of the aerodynamic configuration corresponding to a choice of flight strategy. deceleration and a flight plan entered. The invention will be better understood upon reading the following description of several embodiments, given by way of example only and with reference to the drawings in which: FIG. 1 is a view of a system FMS-type flight management system for an aircraft configured to implement the automatic determination method of the invention; Figure 2 is a flow chart of an automatic determination method according to the invention implemented by the flight management system of Figure 1; FIGS. 3A and 3B are respective views of a display of the selection of the selection of a deceleration strategy, here nominal, and of a navigation display including points of change of aerodynamic configurations corresponding to the strategy of rated deceleration selected; FIGS. 4A and 4B are respective views of a display of the selection of the selection of a deceleration strategy, here delayed, and of a navigation display including points of change of aerodynamic configurations corresponding to the strategy of delayed deceleration selected; FIGS. 5A and 5B are respective views of a display of the input of the validated selection of a deceleration strategy, here delayed, and of a validated navigation display including aerodynamic configuration change points corresponding to the delayed deceleration strategy selected; Figure 6 is a view of a vertical display in altitudes and comparative speeds of the profiles respectively associated with a nominal deceleration strategy and a delayed deceleration strategy; FIG. 7 is a view of a speed information display allowing changes in aerodynamic configurations determined by the automatic determination method of FIG. 2.
[0005] Generally and conventionally, during the preparation of the flight or during a diversion, the crew enters its flight plan into a flight management system, commonly called FMS, according to the English expression "Flight Management System". In known manner, from the flight plan defined by the pilot in the form of a list of waypoints called "waypoints" and 3037411 13 departure procedures, arrival airways (English airways) The missions, the lateral trajectory is calculated according to the geometry of sections between the crossing points (commonly called LEG) and / or altitude and speed conditions which are used for the calculation of the turning radius. On this lateral trajectory, the FMS optimizes a vertical trajectory, respecting possible constraints of altitude, speed, time, slope. To predict the behavior of the aircraft and thus determine the trajectory, the FMS uses a performance database that makes it possible to predict the behavior of the aircraft for a given state. Conventionally, when the aircraft is an airplane, a state of the aircraft called "airplane state" is defined as the set formed by all the parameters influencing the flight mechanics of the aircraft: in particular the slope, but also thrust, halftone, mass, speed, altitude, aerodynamic configuration, etc. According to FIG. 1 and a functional representation of a flight management system for an aircraft, an FMS flight management system 10, based on one or more electronic computers, has a man-machine interface 12 comprising means for input, for example formed by a keyboard, and display means, for example formed by a display screen, or simply a touch screen display, and modules fulfilling the various functions described in the ARINC standard 702 entitled "Advanced Flight Management Computer System", December 1996. The method according to the invention can be realized within the framework of a comparable architecture, but not restricted to it. The flight management system FMS 10 FMS is configured to implement all or part of the functions of the ARINC 702 standard through the following different modules: a navigation module 14, called LOCNAV, to perform the optimal location of the aircraft according to geolocation means 16 such as geo-positioning by satellites or GPS, GALILEO, VHF radionavigation beacons (English Very High Frequency), inertial units. This module communicates with the aforementioned geolocation devices; 3 0 3 74 1 1 14 .- a flight plan determination module 18, called "FPLN", to enter the geographical elements constituting the skeleton of the route to be followed, such as the points imposed by the departure and departure procedures. arrival, the waypoints or waypoints referred to in English 5 "waypoints", the air corridors, commonly referred to as "airways" according to English terminology; a navigation database 20, called NAVDB, for constructing geographic routes and procedures from data included in the bases relating to points, beacons, and portions of 10 trajectories, also called "bequests" of interception or altitude ...; a performance database 22, called PRF DB, containing information relating to the aerodynamic parameters and engine performance of the aircraft, as well as to its field of use or flight model; A lateral path determination module 24, called TRAJ, for constructing a continuous trajectory from the points of the flight plan, respecting the aircraft performance and the confinement constraints (RNP); a prediction module 26, called PRED, for constructing an optimized vertical profile on the lateral trajectory, and giving the estimates of distance, time, altitude, speed, fuel and wind in particular on each point, at each change of parameter of pilot and at each change of destination, which will be displayed to the crew. The functions which are the subject of the invention in particular affect this part of the computer and it should be noted that the modules 24 and 26 can be integrated into a single TRAJ-PRED module which generally supports lateral and vertical calculations; a guide module 28, called GUIDANCE, for guiding the aircraft in its lateral course and the vertical plane on its three-dimensional trajectory, while respecting the speed, with the aid of the information calculated by the prediction module 26. In an aircraft equipped with an automatic piloting device 30, the latter exchanges information with the guiding module 28; a digital data transport link 32, called DATALINK, for exchanging flight information between the flight plan and prediction modules and the control centers or the other aircraft 34. According to FIG. and a preferred embodiment, a method for automatically determining an optimized descent and approach profile for an aircraft according to the invention is initialized by the pilot, when entering a flight plan and the choice of a DECEL strategy. In general, the automatic determination method 102 is based on the calculation of the FMS predictions and consists in calculating an optimal late deceleration of an aircraft on approach. This calculation includes a calculation of the achievable set-up speeds, minimum and maximum, a calculation of the characteristic points of the trajectory and a computation of the speeds of setting configuration optimized taking into account the various constraints (fuel, time, noise, loads , etc). The automatic determination method 102 is based on a sequencer, which corresponds to a conventional state machine, the variants of which are well known to those skilled in the art. This sequencer defines the sequence of segments to be used and contains a predefined strategy for concatenation of integrations of different types of segments. The segments used can translate the various modes of guidance of the aircraft, relying for example on four types of segments. The slope segments, called Flight Path Angle (FPA), consist of setting a slope with respect to the ground; OPEN segments consist of setting engine speed; the vertical speed segments, called VS (Vertical Speed), consist in setting a vertical speed; the 25 segments of level of altitude or bearings, denominated LEVEL consist in fixing an altitude. Each of these four types of segments is divided into two categories, the acceleration (or deceleration) segments and the constant CAS or MACH segments. The sequencer thus assembles, according to the predefined strategy, these different segments to construct the trajectory of the aircraft from a state of the initial aircraft, referred to as the initial "airplane state". The airplane state is thus propagated by digital integration along a given type segment until one or more of the exit conditions are reached, marking the end of the current segment, and the beginning of a new segment. . The output conditions can be defined by a speed, an altitude and / or a distance depending on the type of segment considered.
[0006] For example, a constant speed LEVEL segment can end only on a distance condition, while a constant speed FPA segment can end on an altitude or distance condition. The final aircraft state at the end of the segment constitutes the initial airplane state of the next segment 5 and is thus propagated until the final conditions of the calculation are reached. Variations in acceleration and deceleration can also be used. The invention is described in close connection with the sequencing and digital integration mechanism since it involves the definition of an updated optimized VopT speed, replacing the existing VCCs, and which constitutes an exit condition of the integration segments. digital. In addition, it possibly involves iterations so as to optimize the aerodynamic configuration of the aircraft on the segments considered. However, the same logic can be applied analogously by formulating formal constraints equivalent to these output conditions. The automatic determination method 102 according to the invention is based on prediction calculation algorithms conventionally used by current FMS flight management systems. According to the preferred embodiment of the invention, the automatic determination method 102 is applied by means of a backward trajectory calculation, called backward in English, and makes it possible successively to establish various aerodynamic configurations up to the establishment. the smooth configuration according to an order predefined by the sequencer of the state machine and depending on the deceleration strategy chosen by the driver. An aerodynamic configuration is here defined in a broad sense as being an aerodynamic configuration corresponding to a permissible combination of the deployment states of the deceleration elements or actuators of the aircraft which are the nozzles, the flaps, the landing gear and possibly the airbrakes. The deployment states of the actuators are each provided by a parameter representative of a first angle formed by the nozzles with a first predetermined direction, a second angle formed by the flaps with a second predetermined direction, a third angle formed by The airbrakes with a predetermined third direction, and the landing gear landing state. Thus an aerodynamic configuration of the aircraft can be defined and identified by an associated vector of the deployment states of the various actuators of the aircraft. The automatic determination method 102 comprises a set of steps. In a first initialization and inputting step 104, the pilot classically enters an FPLN flight plan through his flight management display FMD. In the same first step 104, the pilot enters and selects a DECEL deceleration strategy in a menu of at least two different deceleration strategies, including a first nominal deceleration strategy, designated by NOMINAL. For example, a second deceleration strategy, designated by LATE, implements the deceleration of the aircraft later than the first nominal deceleration strategy.
[0007] According to a variant of step 104, the second LATE optimization strategy is systematically preselected without seeking the opinion of the pilot. Then, in a second back calculation initialization step 106, a current segment counter S (i) is set to 1 to implement the method 102 according to the invention and the integration of a first segment noted S (1). In general, the descent and approach profile evolves from a departure point, designated by DECEL, from the beginning of the implementation of the deceleration of the aircraft to a starting point of back calculation which corresponds to a stabilization point of the aircraft before the landing phase is engaged. In a general manner, the descent and approach profile comprises a sequence or sequence of an integer number N of segments S (i), defined between successive characteristic points SP (i), SP (i + 1) and positions of aerodynamic configuration changes taken from among a set of 30 aerodynamic configurations. Since the integer i denotes an index or a rank of numbering and of course of the segments along the profile, a segment S (i) is delimited by a starting point of back calculation and a characteristic point of arrival of back calculation, designated respectively by SP (i) and SP (i + 1).
[0008] The automatic determination method 102 is based on a back calculation of propagation of a state of the aircraft along the segments S (i) of the sequence, i ranging from 1 to N from the back calculation start point. SP (1), also called stabilization point, to the starting point SP (N + 1) DECEL 5 of the implementation of the deceleration of the aircraft. The starting calculation point SP (1) is the starting characteristic point of the first segment S (1) and constitutes a stabilization point of the aircraft at least 1000 feet above the ground level AGL (" Above Ground Level ") in Instrument Flight Rule (IFR) instrument flight mode or at least 500 feet above ground level in Visual Flight Mode (VFR) visual flight mode (AGL), an operating margin possibly added to these minima. The current segment being initialized by the first segment S (1) with a first aerodynamic configuration, called landing (3 or FULL) 15 selectable by the control, associated with its characteristic point of departure, in the same second initialization step 106, the next aerodynamic configuration of the aircraft is determined according to the various actuators available and the sequence of aerodynamic configurations planned or programmed by the sequencer of the state machine, according to the information provided by the database 22 PERF DB . Then in the same second initialization step 106, for the next aerodynamic configuration provided for the first segment S (1), a range of speeds of possible use of said next aerodynamic configuration is calculated and provided, the speed range being 25. delimited by a minimum speed Vmin and a maximum speed Vmax. The authorized speed range notably takes into account the maximum permissible loads on the wing of the aircraft and provided in a database detailing the performance of the aircraft, and the mass of the aircraft at the starting characteristic point SP (1 ) of the first segment S (1) provided by the airplane state at this point SP (1). Then, in a loop 108 of travel of the segments S (i) described by the index i of course of the segments, in a third step 110 of calculation of the next characteristic conditions, the characteristic conditions of the arrival characteristic point SP (i + 1) of the current segment S (i) are determined. In this third step 110, the next characteristics of the arrival characteristic point are stopping conditions for the digital integration of the current segment S (i). The next stop point or points that may form the characteristic point of arrival are determined in particular from the flight plan and the stolen procedure, and 5 may be: .- either waypoints, referred to as English waypoints, which may be associated with constraints; or .- points defined by a floating latitude / longitude along the trajectory (pseudo-waypoints called in English pseudo-waypoints, entry of constrained noise zone, etc.); or .- characteristic altitudes with speed limit for example. Then, in a fourth optimized speed calculation step Vop-r (i) 112, for the current segment S (i) an optimum aircraft speed is determined over the range of speeds of the next aerodynamic configuration associated with the segment. current S (i) according to a predetermined deceleration strategy and / or predetermined constraints inherent in the flight procedure or introduced by a pilot in his flight plan. The deceleration strategy is a single-criteria optimization strategy that minimizes a parameter taken from a fuel consumption, an acoustic noise level, an acoustic noise power template, a descent time, or a multi-criteria optimization strategy that optimizes a combination of several criteria, one of them being included in the set formed by the fuel consumption, the acoustic noise level and the descent time. The predetermined constraints inherent in the flight procedure or introduced by the pilot in his flight plan are included in the set of constraints formed by:. Velocity constraints reached at a point characteristic of a segment greater than or equal to a predetermined threshold value (AT OR ABOVE), or equal to a predetermined threshold value (AT), or less than or equal to a predetermined threshold value (AT OR BELOW), or included in a predetermined speed window (WINDOW); and time-of-arrival constraints at a characteristic point of a segment greater than or equal to a predetermined threshold value (AT OR 3037411 AFTER), or equal to a predetermined threshold value (AT), or less than or equal to at a predetermined threshold value (AT OR BEFORE), or included in a predetermined time window (WINDOW); and .- maximum noise constraints observed from a point characteristic of a segment or at a given altitude; and .- Altitude constraints reached at a characteristic end point of a segment greater than or equal to a predetermined threshold value (AT OR ABOVE), or equal to a predetermined threshold value (AT), or less than or equal to a predetermined threshold value (AT OR 10 BELOW), or included in a predetermined velocity window (WINDOW); and .- fuel consumption constraints. Then, in a fifth current segment digital integration step 114, the digital integration of the current segment S (i) is performed to allow propagation of the state of the aircraft along the current segment S (i). from the associated back calculation characteristic starting point SP (i) to the associated backward calculation characteristic point SP (i-F1) according to the type of the current segment, defined by the sequencer, and a stopping condition, defined by: 20 .- the attainment of the optimum speed VopT (i) of the aircraft in the current segment S (i); .- or reaching the point of arrival common arrival SP (i + 1) associated calculation back without having reached the optimal speed of the aircraft. In a seventh routing step 116, an eighth step 118 of checking not exceeding a permitted limit slope threshold for the current segment S (i) is executed when the optimum speed Vop-r (i) of the aircraft is reached in the current segment S (i), or a ninth evaluation step 120 of interest to anticipate an aerodynamic configuration change is implemented when the associated current arrival point SP (i + 1) of back calculation is achieved without having reached the optimum speed Vopi- (i) of the aircraft. In the eighth step 118, a limiting slope FPAlim (i) associated with the deployment of the next aerodynamic configuration is determined as being the maximum slope followed by the aircraft making it possible to maintain the speed of the aircraft in "idle" thrust without airbrake and without acceleration, and the associated slope of the current segment S (i) is then compared to the previously determined limit slope FPAlim (i). The purpose of this maintenance function is to avoid steep descent, commonly known in English as "TOO STEEP PATH".
[0009] In the ninth step 120, the performances, in terms of optimization according to the chosen DECEL strategy, of a first solution consisting in anticipating the change in aerodynamic configuration at the arrival point of the current segment, and a second solution of not anticipating the current aerodynamic configuration change are compared Then in a tenth routing step 122, the eighth step 118 is executed when the performance of the first solution in terms of optimization according to the selected DECEL strategy is better than that of the second solution, or else an eleventh step 124 is executed.
[0010] In the eleventh step 124, it is investigated whether an alternative aerodynamic configuration of the nominal aerodynamic configuration exists, being equivalent in rank in the nominal sequence of sequence of the nominal aerodynamic configurations. In a twelfth switching step 126, at least the ninth and tenth steps 120, 122 are performed when there is an alternative and equivalent aerodynamic configuration of the nominal aerodynamic configuration provided by the sequencer, or a thirteenth step 128 of maintaining the aerodynamic configuration. the current or current aerodynamic configuration is executed when there is no or no alternative and equivalent aerodynamic configuration of the nominal aerodynamic configuration provided by the sequencer. The implementation of the thirteenth step 128 is a consequence of the refusal by step 118 or step 120 to activate the next predicted aerodynamic configuration at the arrival point of arrival SP (i + 1) of the current segment S (i). The activation of the current aerodynamic configuration actuator (s) being maintained for the current segment S (i), the next nominal aerodynamic configuration to be provided for the next segment S (I + 1) will be identical to the next nominal aerodynamic configuration determined for the segment. current S (i).
[0011] In a fourteenth switching step 130, following the eighth step 118, the eleventh step 124 is executed when the slope associated with the current segment S (i) is greater than or equal to the limit slope (i), or one fifteenth step 132 of changing the aerodynamic configuration of the arrival characteristic point SP (i + 1) of the current segment is executed when the slope associated with the current segment S (i) is strictly less than the limit slope FPAIim (0. In the step 152. The aerodynamic configuration of the aircraft is modified by activating the new configuration at the arrival characteristic point of the current segment S (i), then in a sixteenth step 134, the next configuration or configurations (at least the next nominal configuration and alternative configurations where appropriate) are determined according to the different actuators available and the sequence of aerodynamic configurations. They are provided or programmed by the sequencer of the state machine according to the information provided by the database 22 PERF DB. In a seventeenth step 136, for the next aerodynamic configuration planned for the next segment S (i + 1), a range of possible speeds of use of said next aerodynamic configuration is calculated and provided, the speed range being delimited. by a minimum speed Vrnin (i + 1) and a maximum speed Vmax (i + 1). The authorized speed range notably takes into account the maximum permissible loads on the wing of the aircraft and provided in a database detailing the performance of the aircraft, and the mass of the aircraft at the point of arrival characteristic SP (i + 1) of the current segment S (i) provided by the airplane state at this point calculated in the step of integrating the current segment S (i). In an eighteenth step 138, following step 128 or step 136, as long as the deceleration phase is not completed or more restricted as long as the aircraft is not in a smooth configuration , The current index i of travel of the segments is incremented by one unit. The aerodynamic configuration maintained in step 128 or the new configuration activated in step 132 becomes the active aerodynamic configuration of the starting characteristic point SP (i) of the current segment S (i) after incrementing the current index i. In addition, the next aerodynamic configuration or configurations determined in step 134 in the case of a modification of the preceding segment, or the next configuration or configurations determined previously to step 128 in the case of maintenance of the configuration. current, constitute the next aerodynamic configuration or configurations to be activated if this is possible for the current segment 5 or current S (i) obtained at the output of the eighteenth stage 138. The algorithm of the loop 108 stops when the phase deceleration is completed or more restricted when the aircraft is in a smooth configuration trains retracted. A descent and approach profile is obtained by assembling the segments in a direction opposite to that of the back calculation. The automatic determination method 102 as described above makes it possible to predict and present to the crew points of configuration or activation of various aerodynamic configurations, optimized with regard to various criteria considered alone or in combination that are: one or more speed constraints, one or more time constraints, an optimization of the fuel consumption, a minimization of the acoustic noise, and loads on the wing. It should be noted that the profilability of the profile will always be combined with one of the above criteria. The automatic determination method 102 as described above has the following advantages: - to generate fuel and time savings over a nominal deceleration strategy; .- widening ETA ranges min / max (in English Estimated Time of Arrival) for the functions of type RTA (adjustment of the arrival time) 30 .- the improvement of the accuracy of the predictions of the FMS and therefore the reinforcement of the confidence of the crews in the system: .- through a modeling closer to operational practices (anticipation elements to stabilize the aircraft in energy according to the chosen strategy), 3037411 24 .- by limiting the deceleration phase and therefore the flight time exposed to the application of possible non-optimal deceleration margins. 3A and an example of a cockpit flight control display and entry means, a flight control display 202, called FMD (Flight Management Display), comprises a graphic display object. type menu box 204 for displaying a DECEL menu of commands for selecting a deceleration strategy or a type of deceleration in a set comprising at least two different deceleration strategies, among which a nominal nominal strategy 10, called NOMINAL, and a delayed deceleration strategy compared to that of the nominal strategy, called LATE. Here, the nominal NOMINAL strategy has been selected. According to FIG. 3B and an example of display 208 of the lateral trajectory or navigation, denominated ND (Navigation 15 Display), the lateral trajectory 212 associated with the selected nominal deceleration strategy includes pseudo-points of passage ( in English pseudo waypoints) 214, 216, 218, 220, 222, here only change of speed and phase or aerodynamic configurations, designated respectively by D, 1, 2, 3, 4 or F, respectively corresponding to the starting point the implementation of the deceleration, marking the beginning of the approach phase, or characteristic point of arrival of back calculation with smooth configuration and change of speed, at a first characteristic point of extension of the nozzles at a first angle of spouts formed by the spouts and a predetermined beak reference direction, at a second characteristic point of spout and flap extension after a second year and a second flap angle formed by the flaps and a predetermined flap reference direction, at a third characteristic point of extension of the flaps and flaps at a third beak angle and a third flap angle, and a fourth characteristic point 30 extending beaks and flaps at a fourth beak angle and a fourth flap angle, the fourth characteristic point also forming the starting point of back calculation. The present invention is not limited to a particular number of nozzle and flap configurations and may be in discrete extension logic to any predetermined number of configurations.
[0012] In general, the aerodynamic configurations of a given aircraft type are identified by an integer index j different from the numbering of the aerodynamic configuration, j varying from 1 to JN, and JN denoting the total number of aerodynamic configurations allowed by the sequencer. Each aerodynamic configuration is characterized by a combination of actuator deployment states among the nozzles, flaps, airbrakes, landing gear. The deployment states of the actuators are for example: a first angle Obe 'representative of a degree of deployment of the nozzles; a second Orolets angle representative of a degree of deployment of the shutters. a third angle representative of a degree of deployment of brake shoes of the air brakes; and 15 .- the state of exit of the landing gear. A choice will be available for the crew in the cockpit, so that they can choose a method of calculating the deceleration so that it is nominal, adjusted and optimized, or late, depending on the conditions of the flight and the criteria defining the flight strategy.
[0013] According to Figure 4A, the deceleration strategy LATE is selected in the menu box 204 of choice of the deceleration strategy. Following the activation of the LATE delayed deceleration strategy, an eclair flight plan is created. The setup times are adjusted accordingly according to the automatic determination method 202 of Fig. 2, and this adjustment is visible on a secondary side path 232, shown in Fig. 4B. According to FIG. 4B and the secondary trajectory 232, the characteristic points 214, 216, 218, 220, 222 of the nominal trajectory 212, associated respectively with the deceleration point and the aerodynamic configuration change points D, 1, 2, 3, 4 are replaced by characteristic points 234, 236, 238, 240 respectively associated with the aerodynamic configurations D, 1, 3, 4. It appears on the secondary trajectory 232 that the deceleration point D is delayed and the aerodynamic configuration 1 has been 3037411 26 removed, the aerodynamic configuration 2 being activated consecutively to the smooth aerodynamic configuration. According to FIGS. 5A and 5B, the pilot maintains his choice to implement the delayed deceleration strategy LATE, and inserts the corresponding temporary flight plan, determined by the automatic determination method 102 and displayed in FIG. 4B by the trajectory temporary side colored in a first color and / or represented by a first pattern (here in broken lines), by inserting said temporary plane, which results in the display of the lateral trajectory 232 in a second color and / or a second reason (here in unbroken line). According to FIG. 6, the profiles in altitudes 252, 254 and in speeds 262, 264, associated respectively with the deceleration strategies NOMINAL and LATE, are superimposed according to a vertical display VD, called in English Vertical Display.
[0014] The profiles 252, 254, 262, 264 illustrate the differences in velocities and the differences between the pseudo-run-points of aerodynamic configuration existing between the deceleration strategies NOMINAL and LATE. In general, a pseudo-waypoint, in English pseudo waypoint, is defined as a floating point, that is to say a point whose geographical position is variable on a lateral trajectory set according to predetermined constraints. In accordance with Figure 7 and a display example, a primary flight display 272 PFD is configured to display optimized speeds Vop-r, calculated according to the automatic determination method 102 for each of the configurations for implementation of a selected DECEL deceleration strategy. The main flight display 272 is configured to display a speed band each corresponding to an aerodynamic configuration j.
[0015] Here, in FIG. 7, four aerodynamic configurations 282, 284, 286, 288 are represented by their respective speed bands 292, 294, 296, 298. The first configuration 282, corresponding to the identification index j equals 1, for example, is characterized by the first speed band 292, delimited by the value of the minimum deployment speed Vmm (1) equal to 210 kts and the value of the deployment speed Vmax (1) equal to 230 kts. A first mark 302 points to the minimum value Vmin (1) and highlights it by a first geometric shape and / or a distinctive clean color and a second mark 304 points to the maximum value 5 Vmax (1) and highlights it by a second geometric form and / or a second distinctive clean color. The value of the optimized speed VopT (1), calculated by the automatic determination method 102 and lying between the minimum deployment speed Vmm (1) and the maximum deployment value Vmax (1), here equal to 213 kts, is pointed by a third mark 306 disposed next to the index j of the aerodynamic configuration here set to 1. The second configuration 284, corresponding to the identification index j equal to 2, is characterized by the second speed band 294 delimited by the value of the minimum deployment speed 15 Vmm (2) equal to 185 kts and the value of the deployment speed Vmax (2) equal to 200 kts. A first mark 302 points to the minimum value Vmm (2) and emphasizes it by a first geometrical shape and / or a distinctive clean color and a second mark 304 points to the maximum value Vmax (2) and highlights it by a second geometric form and / or a second distinctive clean color. The value of the optimized speed VopT (2) calculated by the automatic determination method 102 and ranging between the minimum deployment speed Vmm (2) and the maximum deployment value Vmax (2), here equal to 195 kts, is pointed by a third mark 306 disposed next to the index j of the aerodynamic configuration here set to 2. The third configuration 286, corresponding to the identification index j equal to 3, is characterized by the third speed band 296 delimited by the value of the minimum deployment speed Vmm (3) equal to 148 kts and the value of the deployment speed Vmax (3) equal to 186 kts. A first mark 302 points to the minimum value Vmm (3) and highlights it by a first geometric shape and / or a distinctive clean color and a second mark 304 points the maximum value Vmax (3) and highlights it by a second Geometric shape and / or a distinctive second color. The value of the optimized speed VopT (3) calculated by the automatic determination method 102 and 3037411 28 between the minimum deployment speed Vmm (3) and the maximum deployment value V. (3), here equal to 176 kts , is pointed by a third mark 306 disposed next to the index j of the aerodynamic configuration here set to 3.
[0016] The fourth configuration 288, corresponding to the identification index j equal to 4, is characterized by the fourth speed band 298, delimited by the value of the minimum deployment speed Vmh (4) equal to 148 kts and the value the deployment speed Vmax (4) equal to 176 kts. A first mark 302 points to the minimum value Vnlin (4) 10 and highlights it by a first geometric shape and / or a distinctive clean color and a second mark 304 points the maximum value V. (4) and highlights it by a second geometric form and / or a second distinctive clean color. The value of the optimized speed Vop-1- (4) calculated by the automatic determination method 102 and 15 between the minimum deployment speed Vmh (4) and the maximum deployment value Vmax (4), here equal to 158 kts , is pointed by a third mark 306 disposed next to the index j of the aerodynamic configuration here set to 4. The display of the speed bands is complementary to the display on the navigation display ND of the pseudo-points passage where the aerodynamic configuration changes and / or display on the vertical display VD of the same pseudo-points of passage where the aerodynamic configuration changes. The display of the speed bands is also complementary to the possible textual messages displayed on the main flight display PFD or on any equivalent means, for example those displayed by an Airbus aircraft of type A350 and designated "EXTEND CONFx". In general, the optimized speed Vop-r (j) is the speed at which it is envisaged to change aerodynamic configuration in the aerodynamic configuration of index j to the pseudo-point of change of configuration if such a point exists. . It should be noted that no function currently present in an FMS-type system or equivalent is intended to optimize the instants of setting configurations by considering multiple criteria such as the 3037411 29 constraint of speed / time / noise / slope, respecting the loads on the wing. In general, there is currently no adaptive multi-criteria method for adapting configuration speeds for each flight, depending on the particularities of the procedures, predicted or actual weather conditions, speed constraints, time , noise and other parameters. The speeds conventionally used today are the maneuvering speeds or the maximum limit speeds, and therefore the minimum or maximum speeds of setups. It should also be noted that various elements and arguments play in favor of energy management, and more specifically of deceleration during the approach phase, by adjusting the instants of configuration.
[0017] First of all, the configuration of the aircraft generally makes it possible to increase the deceleration capacity, and to enlarge the flight range in speed, thus making it possible to reach lower speeds, progressively up to final approach speed. It is therefore used by the pilots as an approach energy management means to stabilize, the objective being to reach the approach speed on the Glide, at the latest 500ft or 1000ft AGL. Since it is favorable to decelerate as late as possible to reduce fuel consumption, this is a first argument to recalculate the speed of extension of the beaks and flaps.
[0018] Then, the adjustment of the instants of setting configuration is also a lever to comply with speed constraints of all types (AT, AT OR ABOVE, AT OR BELOW), as required by the standard DO-236C entitled "Minimum Aviation System Performance Standards: Required Navigation Performance for Area. In addition, these speeds, having an impact on the stolen deceleration profile, have a direct impact on the flight time, and therefore allow to respect a time constraint fixed by the air traffic control for example, and thus to widen the range. ETAmin / ETA., Thereby enhancing the aircraft's ability to meet an approached RTA (English Required Time of Arrival). Finally, the settings in aerodynamic configurations have an impact on the speed profile and the aerodynamic configuration of the aircraft, and therefore on the noise emitted by the aircraft, and perceived on the ground by the populations or a microphone. This fourth argument reinforces the need to adjust setup speeds to find the best fuel / time / noise compromise. The proposed solution is therefore advantageous because it relies in part on existing calculation modules, and makes the system more close to the operational reality. In addition, it offers the possibility of reducing operational costs for companies through a reduction of systemized fuel consumption, since the optimal strategy can be displayed to the crew, which guarantees its application.
[0019] In addition, the solution also introduces a lever on the separation of the aircraft through a possible adjustment of the flight time on approach, and a possible respect of the speed constraints of the AT and AT OR ABOVE type. Finally, the solution has the advantage of taking into account the noise pollution associated with the aircraft, so as to obtain the best compromise between the comfort of the residents of the airport areas and the costs incurred for the company. It is applicable in any calculation of predictions present in an FMS. The invention is also applicable in any navigation means, embedded or not, managing the trajectory of an aircraft (drone for example). The automatic determination method according to the invention makes it possible to reliably inform the pilot (s) on his deceleration strategy as well as on the actions to be taken to decelerate according to the strategy previously chosen. On the other hand, always in order to reduce the environmental footprint of each flight, the invention makes it possible to limit the impact of the systematic use of margins degrading the optimality of the profile. In general, the invention also relates to an aircraft using the method of automatically determining an approach profile as described above and optimizing the management of the aerodynamic configuration of said aircraft. In general, the automatic determination method 102 is based on the calculation of the FMS predictions and consists of calculating an optimal late deceleration of an approaching aircraft. This calculation includes a calculation of the achievable setting speeds, minimum and maximum, a calculation of the characteristic points of the trajectory and a computation of the speeds of setting in configuration optimized taking into account the various constraints (fuel, time, noise, loads, etc.).
[0020] As a variant of the determination method of FIG. 2, a method of automatically determining an approach profile for an aircraft according to the invention optimizing the management of the aerodynamic configuration of the aircraft uses the described logic of the method of FIG. 2 in a trajectory calculation, defined in the French patent application registered under the filing number FR 14/02752, formulating them in the form of constraints. The trajectory calculation method, described in this French patent application, makes it possible to calculate an optimized trajectory by directly integrating the coupling of the horizontal and vertical flight phases in the calculation of the flight plan. This trajectory calculation method is based on an optimal control approach, for example through modeling into a Bolza problem. The trajectory is then determined by known tools of optimal control resolution, with arbitration according to the process between the constraints to determine their optimal sequence. Such a method allows for an overall determination of the trajectory that does not rely on segment integration.

权利要求:
Claims (15)
[0001]
REVENDICATIONS1. Method for automatically determining a descent and approach profile for an aircraft, implemented from a flight management system based on one or more electronic computers, the descent and approach profile evolving from a starting point DECEL for implementing the deceleration of the aircraft to a stabilization point, comprising a sequence of segments defined between successive characteristic points including aerodynamic configuration change points taken from a discrete set of predetermined aerodynamic configurations; The automatic determination method is based on a back calculation of propagation of a state of the aircraft along the segments of the sequence from the stabilization point to the starting point DECEL of the implementation of the deceleration of the aircraft. aircraft; and the automatic determination method comprising for each current segment S (i) traversed of the profile delimited between a corresponding starting current characteristic point SP (i) of back calculation and a current arrival characteristic point SP (i + 1) associated A calculation step (106; 134) of one or more forthcoming aerodynamic configurations C (j + 1) of the aircraft from a current configuration C (j) active at the starting current characteristic point SP (i) of back calculation and a nominal sequence of change of aerodynamic configurations; and a step of determining and supplying (106; 136) for the next aerodynamic configuration or configurations (Cj + 1) a possible range of speeds of use of said next aerodynamic configuration C (j + 1) delimited by a minimum speed VOE, i, -, (j + 1) and a maximum speed Vmax (j + 1); The automatic determination method being characterized in that it comprises for each running current segment S (i), a step (112) for determining an optimum speed V or (i) of the aircraft over the speed range of the next aerodynamic configuration C (j-F1), said optimum speed Vop-r (i) of the aircraft being a function of a predetermined deceleration strategy and / or predetermined constraints, inherent to the flight procedure or introduced by the pilot in his flight plan.
[0002]
A method of automatically determining a descent and approach profile according to claim 1, wherein the deceleration strategy is a single-criteria optimization strategy which minimizes a parameter taken from a fuel consumption by the aircraft, an acoustic noise level generated by the aircraft, a journey time, or a multi-criteria optimization strategy that optimizes a combination of several criteria, at least one of them being included in the set formed by a fuel consumption, acoustic noise level and travel time.
[0003]
A method of automatically determining a descent and approach profile according to claim 1, wherein the predetermined constraints inherent in the flight procedure or introduced by the pilot in his flight plan are included in all stresses formed by:. velocity constraints reached at a characteristic point of a segment greater than or equal to a predetermined threshold value (AT OR ABOVE), or equal to a predetermined threshold value (AT), or less than or equal to a predetermined threshold value (AT OR BELOW), or included in a window of predetermined speeds (WINDOW); and time-of-arrival constraints at a characteristic point of a segment greater than or equal to a predetermined threshold value (AT OR AFTER), or equal to a predetermined threshold value (AT), or less than or equal to one predetermined threshold value (AT OR BEFORE), or included in a predetermined time window (WINDOW); and. noise constraints observed from a characteristic point of a segment; and .- altitude constraints reached at a characteristic end point of a segment greater than or equal to a predetermined threshold value (AT OR ABOVE), or equal to a predetermined threshold value (AT), or less than or equal to a predetermined threshold value (AT OR BELOW), or included in a predetermined speed window (WINDOW); and 3037411 34 .- Fuel consumption constraints.
[0004]
A method of automatically determining a descent and approach profile according to claim 1, further comprising for each current segment S (i) traversed a digital integration step (114) of said segment S (i), to propagate the state of the aircraft along the current segment S (i) from the associated back calculation associated current starting point SP (i) to the associated current arrival point SP (i + 1) of back calculation, and performed according to the type of the current segment 10 S (i), defined by the sequencer, and a stopping condition, defined by: .- the achievement of the optimal speed of the aircraft in the current segment; .- or the achievement of the characteristic point of arrival associated current of calculation back without having reached the optimal speed of the aircraft. 15
[0005]
A method of automatically determining a descent and approach profile according to claim 4, wherein the segment type is comprised in the set consisting of: the FPA (Flight Path Angle) segment consisting of set a slope with respect to the ground; and 20 .- the OPEN-type segment consisting of setting an engine speed; and .- the VS type segment consisting of setting a vertical speed; and .- the LEVEL segment consisting of setting an altitude; The segments of the FPA, OPEN, VS, LEVEL type can be implemented optionally in decelerated mode, in constant speed mode or in accelerated mode.
[0006]
A method of automatically determining a descent and approach profile according to any one of claims 4 and 5, including a flightability test step (118), performed when the optimum speed of the aircraft is reached. , consisting of: .- determining a limiting slope FPAiin, associated with the deployment of the new configuration C (j + 1) as a maximum slope in absolute value allowing the maintenance of the speed of the aircraft in "idle" thrust without airbrake and without acceleration, and 3 0 3 7 4 1 1 35 .- compare the slope of the current segment S (i) to the determined limit slope FPAlim.
[0007]
A method of automatically determining a descent and approach profile according to any one of claims 4 and 5, wherein when the characteristic point forming the associated back calculation current arrival point is reached without having reached the optimum speed of the aircraft, the performances are compared (120) in terms of optimization according to the DECEL strategy chosen between a first solution of anticipating the aerodynamic configuration change at the arrival point of the current segment S (i ), and a second solution of not anticipating the current aerodynamic configuration change; and in the case where the performance in terms of optimization according to the chosen DECEL strategy of the first solution is better than that of the second solution, a limiting slope FPAIim, associated with the deployment of the new aerodynamic configuration is determined (118) as a maximum slope for maintaining the speed of the aircraft in "idle" thrust without airbrake and without acceleration, then the slope of the current segment S (i) is compared (118, 130) with the limiting slope FPAlim
[0008]
A method of automatically determining a descent and approach profile according to any one of claims 6 and 7, wherein when the slope of the current segment S (i) is greater than or equal to the limiting slope. FPAlim on the planned new nominal configuration, it is searched (124) if an alternative aerodynamic configuration of the new nominal aerodynamic configuration exists, and if it is determined that a new alternative aerodynamic configuration exists, for this alternative the performances are compared (120) in terms of optimization according to the DECEL strategy chosen between a first solution of anticipating the aerodynamic configuration change at the arrival point of the current segment with this alternative, and a second solution of not anticipating the change. current aerodynamic configuration; and 3037411 36 in the case where for this alternative the performance in terms of optimization according to the chosen DECEL strategy of the first solution is better than that of the second solution, then a limiting slope FPAlin, associated with the deployment of the new alternative aerodynamic configuration. is determined (118) as a maximum slope in absolute value allowing the aircraft speed to be maintained in "idle" thrust without airbrake and without acceleration, then the slope of the current segment S (i) is compared (130) with the limiting slope FPAlin, determined; then 10 in the case where the slope of the current segment S (i) is strictly less than or equal in absolute value to the determined limiting slope FPAlim, in a step of modifying the current aerodynamic configuration (132), the current aerodynamic configuration change in the new alternative aerodynamic configuration is realized; and in the case where there is no new alternative aerodynamic configuration for which the slope of the current segment S (i) is strictly less than or equal in absolute value to the limit slope FPAlim determined the current aerodynamic configuration is maintained for the integration of the next segment S (i-F1). 20
[0009]
9. A method of automatically determining a descent and approach profile according to any one of claims 6 and 7, wherein: when the slope of the current segment S (i) is strictly less than or equal to the limiting slope FPAfin, for the new aerodynamic configuration 25 C (j + 1), in a step of modifying the current aerodynamic configuration (132), the current aerodynamic configuration change to the new nominal aerodynamic configuration according to the nominal sequence of the sequencer is carried out. 30
[0010]
A method of automatically determining a descent and approach profile according to any one of claims 4 and 5, wherein when the associated backcalculating current characteristic point is reached without having reached the optimum speed of the aircraft, the performances are compared (120) in terms of optimization according to the strategy DECEL 35 chosen between a first solution of anticipating the change of aerodynamic configuration at the characteristic point of arrival of the current segment, and a second solution of not anticipating the current aerodynamic configuration change; and in the case where the optimization performance according to the chosen DECEL strategy of the second solution is better than that of the first solution, it is sought (124) if an alternative aerodynamic configuration of the nominal aerodynamic configuration exists, and if it is determined that an alternative aerodynamic configuration exists, for this alternative the performances are compared (120) in terms of optimization 10 according to the DECEL strategy chosen between a first solution of anticipating the aerodynamic configuration change at the point d arrival of the current segment with this alternative, and a second solution of not anticipating the current aerodynamic configuration change. 15
[0011]
11. A method for automatically determining a descent and approach profile for an aircraft, implemented from a flight management system based on one or more electronic computers, the descent profile and the descent profile. approach evolving from a starting point 20 DECEL for implementing the deceleration of the aircraft to a stabilization point, comprising a sequence of horizontal and vertical flight phases passing through successive characteristic points including change points of aerodynamic configurations taken from a discrete set of predetermined aerodynamic configurations C (j); The automatic determination method being based on an optimized trajectory calculation which directly integrates the coupling of horizontal and vertical flight phases in the flight plan and being characterized in that it comprises: A step of supplying aerodynamic configurations C ( j) and computing 30 for each aerodynamic configuration of a range of possible speeds of use of said aerodynamic configuration, delimited by a minimum speed Vrnin (j) and a maximum speed Vmax (j); A step of formulating a problem of computing an overall trajectory from the starting point DECEL to the stabilization point in the form of an optimal control problem; A step of solving the optimal control problem with an arbitration between the constraints of use of the aerodynamic configurations to determine their optimal sequence, a calculation of the characteristic points and a calculation of the speeds of configuration 5 Vop-r (j) optimized according to a predetermined deceleration strategy and / or predetermined constraints inherent in the flight procedure or introduced by the pilot in his flight plan. 10
[0012]
12. System for automatically determining a descent and approach profile for an aircraft comprising a flight management system (10) based on one or more electronic computers, data acquisition means (12; 202) to allow a pilot 15 to enter data into the flight management system; one or more displays (208) for displaying one or more descent profiles of the aircraft, and wherein the descent and approach profile of the aircraft is intended to evolve from a starting point DECEL of implementation the deceleration of the aircraft to a back calculation start point, and comprises a sequence of segments defined between successive characteristic points and aerodynamic configuration change positions taken from an integer number of predetermined aerodynamic configurations; and the flight management system (10) is configured to implement an automatic determination method, based on a back propagation calculation of a state of the aircraft along the segments of the train from the starting point. from back calculation to the starting point DECEL of the implementation of the deceleration of the aircraft; and implementing for each current segment S (i) traversed by the profile delimited between a corresponding starting current characteristic point SP (i) of back calculation and a current arrival characteristic point SP (i + 1) calculation associated rearward, a step of determining one or more forthcoming aerodynamic configurations C (j + 1) of the aircraft from a current configuration C (j) 3037411 39 active at the starting current characteristic point SP (i) rear calculation and a nominal sequence of aerodynamic configuration changes; and a step of determining and supplying for the next aerodynamic configuration or configurations (Cj + 1) a range of possible speeds of use of said aerodynamic configuration C (j + 1), delimited by a minimum speed Vrnin (j +1) and a maximum speed Vmax (j + 1); the system for automatically determining a descent and approach profile being characterized in that the input means (202) and the flight management system (10) are configured to allow the pilot to enter and select a deceleration strategy; and the flight management system (10) is configured to determine for each current running segment S (i) an optimum speed Vop-r (j + 1) of the aircraft 15 over the speed range of the next aerodynamic configuration C (j-F1) according to the chosen deceleration strategy and / or predetermined constraints inherent in the flight procedure or introduced by the pilot in his flight plan. 20
[0013]
A system for automatically determining a descent and approach profile for an aircraft according to claim 12 wherein the flight management system is configured to provide the pilot through one or more displays (12; 208). the optimal aerodynamic configuration change speeds and / or the pseudo-points of passage on the predicted trajectory where to perform the aerodynamic configuration changes and / or to provide an autopilot (30) with optimal aerodynamic configuration change speeds and / or or the moments of aerodynamic configuration change to actuate the corresponding actuator (s).
[0014]
14. System for automatically determining a descent and approach profile for an aircraft according to any one of claims 12 to 13 further comprising 3037411 A set of actuators, formed by nozzles, flaps, airbrakes, a landing gear of the aircraft, to implement the different aerodynamic configurations allowed by the sequencer, Each aerodynamic configuration being characterized by a combination of deployment states of the actuators among the nozzles, flaps, airbrakes, the landing gear, the deployment states of the actuators being each provided by a parameter representative of a first angle formed by the nozzles with a first predetermined direction; A second angle formed by the flaps with a second predetermined direction; A third angle formed by the airbrakes with a third predetermined direction; and the landing gear output state.
[0015]
15. An aerodynamic configuration change display determined according to the automatic determination method of any one of claims 1 to 9, comprising a first screen (208) for displaying a lateral navigation profile and / or a vertical descent profile at altitudes and / or velocities each including pseudo-points of passage in each of which a change of aerodynamic configuration takes place, the geographical positions of the pseudo-points of passage varying according to the chosen deceleration strategy and / or A second display screen (272) of a band of possible speeds of use of a selected aerodynamic configuration and / or an optimized speed of extension of the aerodynamic configuration corresponding to a choice of deceleration strategy and a flight plan entered. 30

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FR3037411B1|2019-12-20|

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优先权:

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申请号 | 申请日 | 专利标题

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FR1501219A|FR3037411B1|2015-06-12|2015-06-12|METHOD AND SYSTEM FOR AUTOMATIC DETERMINATION OF AN OPTIMIZED DESCENT AND APPROACH PROFILE FOR AN AIRCRAFT|

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FR1501219|2015-06-12|FR1501219A| FR3037411B1|2015-06-12|2015-06-12|METHOD AND SYSTEM FOR AUTOMATIC DETERMINATION OF AN OPTIMIZED DESCENT AND APPROACH PROFILE FOR AN AIRCRAFT|

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US15/176,003| US9963247B2|2015-06-12|2016-06-07|Method and system for automatic determination of an optimized descent and approach profile for an aircraft|

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CN201610689372.9A| CN106249592B|2015-06-12|2016-06-12|Method and system for the automatic determination of an optimized descent and approach profile for an aircraft|