法国专利FR3033908A1 SYSTEM AND METHOD FOR AIRCRAFT ASSISTING ASSISTANCE

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专利摘要:
System (3) for assisting the piloting of an aircraft (5) during piloting in manual mode, comprising a module (50) for monitoring, configured to compare an acceleration of the aircraft (5) with a range of a speed-dependent acceleration based on an aircraft speed (5), an acceleration control module (52), switchable between an on state and a deactivated state, and configured to, in the activated state, to the exclusion of the deactivated state, generating a control signal of at least one aircraft acceleration control device (7, 9, 11, 13, 17) (5) to smooth the acceleration from the aircraft (5) to said authorized acceleration range, to maintain the speed of the aircraft within a predefined operating speed range, said monitoring module (50) being configured to activate said module (52) of acceleration control when the acceleration of the aircraft (5) is not included in said acceleration range n allowed.
公开号:FR3033908A1
申请号:FR1500534
申请日:2015-03-18
公开日:2016-09-23
发明作者:Sebastien Lepage
申请人:Dassault Aviation SA；
IPC主号:

专利说明:

[0001] The present invention relates to a system for assisting the piloting of an aircraft during piloting in manual mode of said aircraft.
[0002] The invention aims in particular to assist a pilot during a manual mode control, so as to maintain the speed of the aircraft in a given speed range, for example to maintain the speed of the aircraft below a maximum authorized speed, corresponding to a structural limit of the aircraft, and above a minimum authorized speed, associated with an aerodynamic stall effect of the aircraft. In order to maintain the speed of an aircraft in such a speed range, it is known to provide the aircraft with a protection system configured to limit the incidence and attitude of the aircraft, in order to avoid to reach the stalling speed of the aircraft, and to gradually introduce, from a threshold speed, a nose-up control to avoid reaching the structural limit of the aircraft. Nevertheless, these solutions do not protect the aircraft against a loss of maneuverability. In particular, at low speed, the ability of the aircraft to pitch up decreases to zero. Under such conditions, the pilot no longer has sufficient maneuvering room in terms of incidence to increase the load factor of the aircraft and to quickly change the trajectory of the aircraft. Similarly, at high speed, the ability of the aircraft to sting decreases to zero, altering the maneuverability of the pilot to change the trajectory of the aircraft. To solve this problem, it has been proposed to provide the aircraft with a speed control system, activated as soon as the speed of the aircraft passes a predetermined threshold, and configured to enslave the speed of the aircraft by controlling the speed of the aircraft. throttle. This solution is not entirely satisfactory. Indeed, this solution is based on the control of the only thrust, regardless of the flight configuration of the aircraft, without intervening on the aircraft's screen, and is therefore not generally optimal. In addition, the implementation of the protection, which involves switching from a manual throttle control to an automatic control of this controller, can disrupt the manual piloting of the aircraft by the pilot. An object of the invention is therefore to propose an aircraft piloting assistance system which makes it possible to assist the pilot during a manual mode piloting in order to avoid reaching high speed limits and / or predetermined low while avoiding a loss of maneuverability of the aircraft, disrupting at least the manual steering of the aircraft. To this end, the subject of the invention is a system of the aforementioned type, characterized in that said system comprises: a monitoring module, configured to compare at each instant an acceleration of the aircraft at said instant to a range of authorized acceleration for the aircraft at said instant, said authorized acceleration range being a function of a speed of the aircraft at said instant, an acceleration control module, switchable between an activated state and a deactivated state, said an acceleration control module being configured to, in the activated state, excluding the deactivated state, generating a control signal of at least one aircraft acceleration control device in at least one a control moment in order to make the acceleration of the aircraft move towards said authorized acceleration range, in order to maintain or to make the speed of the aircraft in a predicted speed range defined, said monitoring module being configured to activate said acceleration control module at a given activation instant when the acceleration of the aircraft at said given activation time is not within said authorized acceleration range . In other aspects, the flight control system includes one or more of the following features: said monitoring module is configured to deactivate said acceleration control module at a given deactivation time, subsequent to said instant given activation, when the acceleration of the aircraft at said given deactivation time is within said authorized acceleration range. Said acceleration control device is comprised in the group consisting of a device for modifying the drag of the aircraft, a device for modifying the thrust of the aircraft, and a device for modifying the trajectory of the aircraft. aircraft; said range of operating speed is defined between an upper limit corresponding to a maximum speed of use of the aircraft, and a lower limit corresponding to a minimum speed of use of the aircraft; said authorized acceleration range is defined by at least one upper limit of acceleration allowed at said instant, said upper bound being a function of a difference between the speed of the aircraft at said instant and the maximum speed of use of the aircraft; Said authorized acceleration range is defined by at least one lower limit of acceleration allowed at said instant, said lower limit being a function of a difference between the speed of the aircraft at said instant and the minimum speed of use the aircraft; said range of operating speed is defined between an upper limit corresponding to a maximum maneuverability speed of the aircraft, and a lower terminal corresponding to a minimum maneuverability speed of the aircraft; the acceleration control module is configured to: compare a speed of the aircraft at said control instant to said range of operating speed, and to generate a control signal of a first type, if the speed the aircraft at said control time is within said operating speed range, in order to maintain the speed of the aircraft within said operating speed range, and to generate a control signal of a second type, different from the first type, if the speed of the aircraft at said control instant is not included in said range of operating speed, in order to make the speed of the aircraft approach the said speed range of employment; the control signal of the first type is a control signal of at least one device for modifying the drag or the thrust of the aircraft, and the control signal of the second type is a control signal of at least a device for modifying the trajectory of the aircraft; The system comprises an information display device relating to the flight of the aircraft, said information comprising information relating to an energy variation of the aircraft, said display device being configured to represent on a screen visualizing a symbol of energy variation representative of a current value of a total energy variation of the aircraft, and at least one energy variation terminal symbol 25 representative of a threshold value of said variation of total energy, corresponding to a terminal of said allowed acceleration range. The subject of the invention is also a method of assisting the piloting of an aircraft during manual flight control of said aircraft by means of an assistance system according to the invention, said method comprising: a step activation, in which said monitoring module detects that the acceleration of the aircraft at a given activation time is not included in said authorized acceleration range, and activates said acceleration control module, a step of generation, by said activated acceleration control module, of a control signal of at least one device for controlling the acceleration of the aircraft in at least one control moment with a view to making to extend the acceleration of the aircraft towards said authorized acceleration range, in order to maintain or to make the speed of the aircraft in or toward said range of operating speed. In other aspects, the piloting assistance method comprises one or more of the following features: said generating step comprises: a phase of comparing a speed of the aircraft at said control instant with said range of speed of use, and - a phase of generating a control signal of at least one device for controlling the acceleration of the aircraft of a first type, if the speed of the aircraft auditing control time is in said range of operating speed, in order to maintain the speed of the aircraft in said range of operating speed, or - a phase of generating a control signal of at least one an aircraft acceleration control device of a second type, different from the first type, if the speed of the aircraft at said control instant is not within said range of speed of use, with a view to to cause the speed of the aircraft to move towards said speed range of e mploi; the control signal of the first type is a control signal of at least one device for modifying the drag or the thrust of the aircraft, and the control signal of the second type is a control signal of at least a device for modifying the trajectory of the aircraft; the method further comprises a deactivation phase, subsequent to said generation step, during which said monitoring module detects that the acceleration of the aircraft is within said authorized acceleration range, at a given deactivation time after said given activation time, and deactivates said acceleration control module. The invention will be further understood with reference to embodiments of the invention which will now be described with reference to the appended figures in which: FIG. 1 schematically illustrates a steering assistance system according to a mode embodiment of the invention; FIG. 2 illustrates a representation mode by an information display device relating to the speed and acceleration of the aircraft of the system of FIG. 1; FIG. 3 illustrates an alternative representation by the display device 35 of information relating to the speed and acceleration of the aircraft; FIG. 4 is a block diagram illustrating the method according to one embodiment of the invention. FIG. 1 shows a system 3 for assisting the piloting of an aircraft 5 according to one embodiment of the invention.
[0003] The aircraft 5 comprises a propulsion system 7, for example a set of engines capable of exerting a thrust force on the aircraft. The aircraft 5 furthermore comprises devices 9 for modifying the drag force exerted by the air on the aircraft 5, hereinafter referred to as modification devices for the screen, for example control surfaces such as airbrakes. and spoilers 13. The airbrakes 11 are operable between a retracted position, in which the airbrakes 11 have no influence on the screen, and an extended position, in which the airbrakes 11 increase the screen of the aircraft 5. The spoilers 13 are also operable between a retracted position, in which the spoilers 13 exert no influence on the screen, and an out position, in which the spoilers 13 increase the screen of the aircraft 5. When the spoilers 13 are out they also reduce the lift of the aircraft 5. The aircraft 5 also comprises devices 17 for modifying the trajectory of the aircraft 5, for example a rudder r and fins.
[0004] The aircraft 5 furthermore comprises high lift devices, such as beaks and flaps, capable of modifying the lift of the aircraft 5. The propulsion system 7, the drag force modification devices 9 exerted by the aircraft air on the aircraft 5 and the devices 17 for modifying the trajectory of the aircraft 5 form devices for controlling the acceleration of the aircraft.
[0005] The aerodynamic configuration of the aircraft will subsequently be called the configuration of the spouts, flaps and control surfaces. The aircraft 5 furthermore comprises a plurality of sensors 21 making it possible to determine the flight parameter values of the aircraft 5, such as its position, its altitude z, its speed and its acceleration with respect to the air and to the ground. .
[0006] For example, an anemometer makes it possible to determine an indicated speed VI of the aircraft 5, which is the speed of the aircraft 5 with respect to the air, directly resulting from pressure measurements. The system 3 is configured to assist the crew of the aircraft 5 during a flight in manual mode, to maintain the speed of the aircraft 5 in a first speed range.
[0007] In the remainder of the description, unless otherwise indicated, the term "speed" of the aircraft 5 will be referred to as the indicated speed VI, and a variation in the indicated speed of the aircraft 5 will be referred to as acceleration. acts of a positive acceleration or a negative acceleration, also called deceleration.
[0008] Furthermore, a "range", in particular a speed or acceleration, is a range of speed or acceleration defined by at least one finite value terminal. The first speed range corresponds, for example, to a speed range attainable by the aircraft 5. The first speed range is preferably defined by a maximum speed, denoted Vmax, and a minimum speed, denoted Vmm. The speed Vmax corresponds to for example to a structural limit of the aircraft 5: it is for example a maximum speed that can take the aircraft 5 without risk to its structure, denoted VD, reduced by a reduced safety margin. For example, Vmax = VD - X, where X is of the order of a few meters per second, for example 0 <X 20 m / s.
[0009] Preferably, the speed Vmax has a fixed value, in particular independent of the aerodynamic configuration of the aircraft 5 and the flight phase of the aircraft 5. The minimum speed Vm1, -, is for example a stall speed of the aircraft 5, plus a safety margin. The minimum speed Vrmr thus corresponds to the stalling incidence of the aircraft 5, beyond which an aerodynamic stall of the aircraft 5 occurs. The speed V, ',,, depends on the aerodynamic configuration of the aircraft 5, the weight of the aircraft 5 and the load factor of the aircraft 5. The system 3 is configured to assist the crew of the aircraft. aircraft 5 during a flight in manual mode, to help the crew maintain the speed of the aircraft 5 in the first speed range, and if possible in a second speed range. In general, the second speed range is defined as a desired operating speed range for the aircraft 5. The second speed range is in the first speed range. This second speed range is for example a range of maneuverability of the aircraft, that is to say a speed range in which the aircraft 5 is considered maneuverable, and outside of which the maneuverability of the aircraft 5 is reduced. In another example, the second speed range is a speed range associated with a time of flight constraint, i.e., a speed range to ensure that the flight time of the aircraft will be well understood in a given flight time range.
[0010] According to another example, the second speed range is a speed range associated with a reduced flight range, for example in the event of a mechanical failure. In the remainder of the description, it will be considered, by way of example, that the second speed range is a range of maneuverability of the aircraft.
[0011] The second speed range is preferably defined by a maximum speed of use, which is in the example described a maximum speed of maneuverability, noted Vmmsup, and a minimum speed of use, which is in the example described a minimum speed of maneuverability, noted Vmminf. The maximum speed of maneuverability Vmmsup is a speed up to which minimum maneuverability of the aircraft 5 is guaranteed. The maximum maneuverability speed Vmmsup is preferably independent of the aerodynamic configuration of the aircraft 5 and the flight phase of the aircraft 5. For example, the maximum maneuverability speed Vmmsup is defined as a function of the speed VD, in particular as the speed VD decreased by a safety margin 15 increased. Thus, the maximum speed of maneuverability Vmmsup is always lower than the maximum speed Vmax- For example, Vmmsup = VD - X ', where X' is of the order of a few meters per second, for example 10 <X '5 30 m / s. The minimum maneuverability speed Vmminf is a speed of the aircraft 5 above which a minimum maneuverability of the aircraft 5 is guaranteed. For example, the minimum maneuverability speed Vmminf is proportional to the speed VS1g, which is the stall speed of the aircraft 5 under a load factor of 1g. The minimum speed of maneuverability Vmminf is then expressed by Vmminf = k * VS1g, where k is a proportionality factor. For example, 1 5. k 5. 1,2.
[0012] Preferably, the proportionality factor k depends on the flight phase of the aircraft 5. In particular, k may take a first value during takeoff, and a second value, distinct from the first value, notably greater than the first value. , during the rest of the flight. The minimum maneuverability speed Vmminf is generally greater than the minimum speed Vrnin. The system 3 comprises a computer 30 and man-machine interface means, in particular a device 34 for displaying information. The computer 30 includes a processor 40 and a memory 42. The processor 40 is adapted to execute applications contained in the memory 42, in particular an operating system allowing the conventional operation of a computer system.
[0013] The memory 42 comprises different areas of memory containing software modules adapted to be executed by the processor 40 and data sets. In particular, the memory 42 comprises an estimation module 48, a monitoring module 50 and an acceleration control module 52.
[0014] The estimation module 48 is configured to determine at each instant the first and second speed ranges. In particular, the estimation module 48 is configured to determine at each instant the speeds Vmin, Vmax, VMMInf and Vmmsup. The estimation module 48 is further configured to determine at each instant a third speed range included in the first and second ranges. This third speed range is preferably an operational speed range of the aircraft 5, defined between a lower bound, denoted Vmm0p, corresponding to a minimum operational speed of the aircraft 5, and an upper bound, denoted Vmax0p, corresponding to a maximum operational speed of the aircraft 5.
[0015] The minimum operational speed VmmOp is greater than the minimum speed of maneuverability Vmmmf. The minimum operational speed Vm, nop is for example proportional to the speed VS1g, and is expressed by Vff1n0p = k '* VS1g, where k' is a proportionality factor greater than k. For example, 1.2 5. k '5 1.5. Preferably, the proportionality factor k 'depends on the flight phase of the aircraft 5. In particular, k' takes a first value during take-off, and a second value, distinct from the first value, in particular greater than the first value. value, during the rest of the flight. The maximum operational speed V'xop is less than the maximum speed of maneuverability Vmmsup. The maximum operational speed Vmaxop is preferably fixed.
[0016] The estimation module 48 is furthermore configured to determine, at each instant, a total energy variation of the aircraft 5, homogeneous with a slope of the aircraft 5. At an altitude z, the aircraft 5 possesses an energy total mechanical Etotal, sum of its kinetic energy and potential energy, which can be expressed by: 1 (1) Etotale = m Vs201 + mgz where m denotes the mass of the aircraft 5 and Vau its speed relative to the ground. The variation of this total energy can be expressed by a total slope YT, according to the equation: T = 1 of Total Y = sol Y = Ysol (2) mgV ', where y / s, is the time derivative the speed V ', the aircraft 5 relative to the ground. This YT magnitude, homogeneous with a slope, is thus equal to the ground slope ysol of the aircraft 5 when its ground speed Vs01 remains constant. A variation of the total slope TT therefore results in a variation of the ground slope, so and / or a variation of the acceleration V, 1 of the aircraft with respect to the total slope. variation of the total energy of the aircraft 5. However, the critical speeds defined above are speeds of the aircraft 5 with respect to the air mass (and not with respect to the ground). The estimation module 48 is thus configured to determine a change in total energy derived from the total slope referred to above, called total pseudo slope and designated by the symbol Y *. This quantity corresponds to the ground slope which, under current conditions, leads to a constant conventional speed. Its expression is deduced from the equations of the mechanics of flight, and is expressed by: [have 15 The total pseudo-slope Y is thus a homogeneous quantity at a slope of the aircraft 5, and whose value is representative of the acceleration of the aircraft 5. Indeed, when the acceleration of the aircraft 5 is zero, the pseudo-total slope Y * is equal to the ground slope of the aircraft 5, and when the acceleration of the aircraft 5 is positive or negative, the total pseudo-slope Y is greater than or less than the ground slope of the aircraft 5 respectively. The surveillance module 50 is configured to monitor the speed and acceleration of the aircraft 5, and to activate or deactivate the acceleration control module 52, depending on the speed and acceleration of the aircraft 5. In particular, the monitoring module 50 is configured to determine at each instant an acceleration range allowed for the aircraft 5 at this time, and to compare at each instant the acceleration of the aircraft 5 to the authorized acceleration range. "Authorized acceleration range" means that the acceleration range is permitted for the aircraft without the need for modifying this acceleration, regardless of the physical capabilities for the aircraft to reach or not. Y = TSOI + Vsol avair g az JVc = cste = Ysoi ± A - - (3) gg 3033908 10 terminals of this acceleration range. The authorized acceleration range is thus not defined by minimum and maximum accelerations that the aircraft is able to achieve, but by minimum and maximum accelerations tolerated for the aircraft. In addition, the monitoring module 50 is configured to activate the acceleration control module 52 if the acceleration of the aircraft 5 is not within the allowed acceleration range, and to deactivate the module 52 of acceleration control if the acceleration of the aircraft 5 is within the allowed acceleration range. The authorized acceleration range is defined at each instant as a function of the speed of the aircraft 5, in particular as a function of the difference between the speed of the aircraft 5 at this instant and the second speed range, which is in the example described the range of maneuverability of the aircraft 5. Thus, the comparison of the acceleration to the authorized acceleration range makes it possible to detect situations in which, without the pilot's action, the speed of the aircraft 5 would exit or remain outside the maneuverability range, activate the acceleration control module 52 when such situations are detected and keep the acceleration control module 52 activated as long as this risk exceeds a threshold determined. In particular, an output of the acceleration of the authorized acceleration range corresponds to a situation in which, if no corrective action is taken to reduce the acceleration, taking into account the reaction times of the modification devices of the In the case of a raster, thrust and trajectory, an excursion of the speed of the aircraft 5 outside the range of maneuverability can no longer be avoided. Preferably, the allowed acceleration range is defined by an upper acceleration terminal, denoted ACCmax, and a lower acceleration terminal, denoted Accumn- The upper acceleration terminal), corresponds to a maximum acceleration allowed. given the speed of the aircraft 5, in particular the difference between the maximum maneuverability speed Vmmsup and the speed of the aircraft 5. The monitoring module 50 is configured to determine the upper acceleration acceleration terminal each moment according to the difference between the maximum maneuverability speed Vmmsup, as determined at this time by the estimation module 48, and the speed of the aircraft 5 at this time. In particular, the acc'x upper acceleration terminal is a strictly increasing function of the difference between the maximum maneuverability speed Vmmsup and the speed of the aircraft 5.
[0017] Thus, when the speed of the aircraft 5 approaches the maximum maneuverability speed Vmmsup, that is to say when the difference between the maximum maneuverability speed Vmmsup and the speed of the aircraft 5 decreases, the Acc'x acceleration upper limit decreases, which indicates a closer flight zone in which, without pilot action, taking into account the acceleration and the reaction time of the acceleration control devices, an excursion the speed of the aircraft 5 above the maximum maneuverability speed Vmmsup can not be avoided. Moreover, the upper acceleration terminal Accmax is positive as long as the speed of the aircraft 5 remains lower than the maximum maneuverability speed Vmmsup, and 10 becomes negative when the speed of the aircraft 5 becomes greater than the maximum speed of the aircraft. Vmmsup maneuverability. This reflects the fact that, when the speed of the aircraft 5 is greater than the maximum maneuverability speed Vmmsup, only a negative acceleration and less than the upper Accmax acceleration terminal makes it possible to set the speed towards the maneuverability range.
[0018] The upper acceleration terminal Acc, -na, is for example proportional to the difference between the maximum maneuverability speed Vmmsup and the speed of the aircraft 5, and is then expressed as: Accmax = K * (Vmmsup - V), where K is a strictly positive proportionality factor. For example, the factor 20 K is fixed, in particular independent of the aerodynamic configuration of the aircraft 5 and the flight phase of the aircraft 5. In a variant, the upper acceleration terminal Accmax is a nonlinear function of the aircraft. the difference between the maximum speed of maneuverability Vmmsup and the speed of the aircraft 5. The lower acceleration limit Acc, ',,, corresponds to a minimum acceleration allowed 25 taking into account the speed of the aircraft 5, in particular the difference between the speed of the aircraft 5 and the minimum maneuverability speed VMMInf- The monitoring module 50 is configured to determine the lower acceleration limit Acc ,,, n at each instant according to the difference between the minimum maneuverability speed Vmminf as determined by the estimation module 48 and the speed of the aircraft 5 at this time. In particular, the lower Accmin acceleration terminal is a strictly decreasing function of the difference between the speed of the aircraft 5 and the minimum maneuverability speed Vmminf. Thus, when the speed of the aircraft 5 decreases and approaches the minimum maneuverability speed Vmminf, the difference between the speed of the aircraft 5 and the minimum maneuverability speed Vmminf decreases, and the lower limit of acceleration Increased, 3033908 12 increases, which reflects a rapprochement of the flight zone in which, without action of the pilot, given the negative acceleration and the reaction time of the acceleration control devices, an excursion of the speed of the aircraft 5 below the minimum maneuverability speed Vmminf can not be avoided.
[0019] Moreover, the lower acceleration acceleration terminal is negative as long as the speed of the aircraft 5 remains greater than the minimum maneuverability speed V min, and becomes positive when the speed of the aircraft becomes lower than the speed. minimum maneuverability Vmminf. Indeed, when the speed of the aircraft 5 is less than the minimum maneuverability speed VMMInf, only a positive acceleration and greater than the lower acceleration limit Acc ,,,, n makes it possible to make the speed of the aircraft 5 to the maneuverability range. The lower acceleration terminal Accn ,,,, is for example proportional to the difference between the minimum maneuverability speed Vmminf and the speed of the aircraft 5, and is then expressed as: Acc ,,,,,, = K '* (Vmminf - V), where K' is a positive proportionality factor. For example, the factor K 'is fixed, in particular independent of the aerodynamic configuration of the aircraft 5 and the flight phase of the aircraft 5. In a variant, the lower acceleration terminal Acc ,,, is a non-functional function. linearly 20 of the difference between the minimum maneuverability speed VmmInf and the speed of the aircraft 5. The monitoring module 50 is furthermore configured to determine a total pseudo-slope threshold value yn, * ax associated with the acceleration Accmax, equal to: Ymax = Yu) / ± g and a threshold value iMin total pseudo-slope associated with acceleration Accmin, equal to: Accmin 25 Ymin = Yso / - g Moreover, the monitoring module 50 is configured to compare in each instant the acceleration of the aircraft 5, as determined from the sensors 21, lower terminals Accmk, and accmax acceleration higher. The monitoring module 50 is further configured to activate the acceleration control module 52 if the acceleration of the aircraft 5 at this time, then called the activation time, is greater than the upper Accmax acceleration terminal. or less than the lower Accmin acceleration limit.
[0020] The monitoring module 50 is also configured to deactivate the acceleration control module 52 if the acceleration of the aircraft 5 at this instant, then called the deactivation instant, is less than the upper acceleration acceleration terminal. greater than the lower acceleration terminal Accm ,,,.
[0021] The monitoring module 50 is furthermore configured to compare the speed of the aircraft 5 at each instant with the third speed range, in order to determine whether the speed of the aircraft 5 is within the operational speed range of the aircraft. 5, and to generate an alert, to the crew, if the speed at this time is greater than the maximum operational speed Vmax0p or less than the minimum operational speed V ',,,, op. Preferably, this alert is issued only if the absolute value of the difference between the speed of the aircraft 5 and the maximum or minimum operating speed is greater than a given threshold, corresponding to a tolerance, and if the The speed of the aircraft 5 remains outside the third speed range for a duration longer than a predetermined time. This alert is emitted for example by means 32 man interface machine. This alert is for example a hearing and / or visual alert. The monitoring module 50 is thus configured to generate an alert as soon as the speed of the aircraft 5 comes out of the operational speed range, therefore before the speed comes out of the range of maneuverability. Such an alert thus gives the opportunity to the crew to act on the manual controls of the aircraft 5 so that the speed of the aircraft 5 returns to the operational speed range, or at least remains within the range of maneuverability. . The acceleration control module 52 is switchable between an on state and a off state. The acceleration control module 52 is able to be activated and deactivated by the monitoring module 50. In the activated state, in particular when the acceleration control module 52 changes from the deactivated state to the activated state, the acceleration control module 52 is configured to generate an alarm signal destined for the first time. 'crew. This alarm signal 30 is intended to warn the crew that an action will be performed by the acceleration control module 52 in order to help the crew maintain the speed of the aircraft 5 in the range of maneuverability. . The acceleration control module 52 is also configured to generate a control signal of at least one aircraft acceleration control device 5, 35 in at least one control instant, with a view to maintaining or to make the speed of the aircraft 5 in the speed range of use.
[0022] In particular, the acceleration control module 52 is configured to generate a control signal of the propulsion system 7, in order to modify the thrust of the aircraft 5, and / or a control signal of the modification devices 9. of the screen, in particular of airbrakes 11 and spoilers 13, and / or devices 17 for modifying the trajectory of the aircraft 5. In particular, the acceleration control module 52 is configured to generate a control signal of FIG. a first type when the speed of the aircraft 5 at the control instant is within the range of maneuverability. The control signal of the first type is preferably a control signal of a device for modifying the drag or the thrust of the aircraft 5. In particular, when the acceleration of the aircraft 5 exceeds the upper limit acceleration system 52 is configured to first generate a thrust control signal of the aircraft 5, intended to reduce the thrust of the aircraft 5. Then, if the module 52 In spite of this action, the acceleration control remains activated, that is to say, if the acceleration of the aircraft 5 remains greater than the upper acceleration acceleration terminal, the acceleration control module 52 is configured to generating a control signal of the devices for modifying the screen, in particular an output signal of the airbrakes 11 and / or spoilers 13, in order to increase the drag of the aircraft 5.
[0023] Conversely, when the acceleration of the aircraft 5 becomes lower than the lower acceleration limit Accr ',,,, the acceleration control module 52 is configured to first generate a control signal of the 9 devices modification of the screen, including a return signal of the airbrakes 11 and / or spoilers 13, to reduce the drag of the aircraft 5. Then, if the acceleration control module 52 remains activated 25 despite this action, that is to say if the acceleration of the aircraft remains lower than the lower Accmin acceleration terminal, the acceleration control module 52 is configured to generate a control signal of the thrust of the aircraft 5, intended to increase the thrust of the aircraft 5. The acceleration control module 52 is moreover configured to generate a control signal of a second type, distinct from the first type, when the speed of the aircraft 5 at the moment of control is within the speed range achievable by the aircraft 5 but not in the range of maneuverability. The control signal of the second type is preferably a control signal of a device for modifying the trajectory of the aircraft 5.
[0024] Preferably, when the speed of the aircraft at the time of control is within the speed range achievable by the aircraft but not within the range of maneuverability, the acceleration control module 52 is also configured to generate a control signal of the first type, in particular to maintain control of the thrust and drag of the aircraft, or to generate an additional control signal of the thrust or drag of the aircraft. aircraft.
[0025] For example, when the acceleration of the aircraft 5 is lower than the lower accnn acceleration terminal and the speed of the aircraft 5 is not within the maneuverability range, the acceleration control module 52 is configured to prevent an exit of the airbrakes 11 and / or spoilers 13, which would increase the drag of the aircraft 5, and to prevent a decrease in the thrust of the aircraft 5.
[0026] Conversely, when the acceleration of the aircraft 5 is greater than the upper Acc'x acceleration terminal and the speed of the aircraft 5 is not within the range of maneuverability, the control module 52 acceleration is configured to prevent retraction of the airbrakes 11 and / or spoilers 13, which would reduce the drag of the aircraft 5, and to prevent an increase in the thrust of the aircraft 5.
[0027] Thus, when the acceleration of the aircraft 5 is out of the allowed acceleration range, the acceleration control module 52 is configured to generate an alarm signal for the attention of the crew and then to act. on the thrust and / or on the screen of the aircraft 5 as the speed of the aircraft 5 remains in the range of maneuverability, then to act on the trajectory of the aircraft 5 if the speed of the aircraft 5 out from the range of 20 maneuverability. In addition, at high speed, the acceleration control module 52 is configured to act on the thrust before acting on the drag, while at low speed, the acceleration control module 52 is configured to act on the screen, before acting on the thrust. This sequencing makes it possible to optimize the influence of the devices for modifying the screen and the thrust. In the deactivated state, the acceleration control module 52 is disconnected from any device for controlling the acceleration of the aircraft 5 and therefore does not exert any action on these devices. Thus, when the acceleration of the aircraft 5 is out of the allowable range given its speed, the acceleration control module 52 is configured to modify the acceleration of the aircraft 5 until the acceleration of the aircraft 5 is again within the authorized range. The acceleration control module 52 is then deactivated, and only the manual control commands of the aircraft 5 have an influence on the devices for controlling the acceleration of the aircraft 5. Thus, when the acceleration of the 5 is less than the lower accelerating terminal Acc, ',,, the control signals generated by the acceleration control module 52 are intended solely to increase the acceleration of the aircraft 5, but 3033908 under no circumstances to reduce this acceleration. Similarly, when the acceleration of the aircraft 5 is greater than the upper acceleration terminal Accmax, the control signals generated by the acceleration control module 52 are intended solely to reduce the acceleration of the aircraft 5 but in no case to increase this acceleration. In other words, the acceleration control module 52 is not configured to regulate the speed and acceleration of the aircraft 5, but only to provide one-off assistance in order to avoid the speed of the aircraft. aircraft 5 so as to avoid the range of maneuverability, and to prevent the speed of the aircraft 5 from the speed range achievable by the aircraft 5.
[0028] The information display device 34 comprises in particular a head-up display device and a head-up display device. The information display device 34 is configured to display, for the attention of the crew, information relating to the flight of the aircraft 5 during a flight of the aircraft 5. In particular, the device 34 information display is configured to display information representative of the current acceleration of the aircraft 5 and the acceleration range allowed for the aircraft 5. In particular, the information display device 34 is configured to represent at each moment a symbol representative of the total energy variation associated with the acceleration of the aircraft 5 at this instant, and to represent at least at certain times an energy variation terminal symbol 20 representative of a threshold value of variation of energy associated with the upper limit Acc, or with the lower limit Accnn of acceleration. Such a display allows the crew to visualize the variation of energy, in particular acceleration, still available for the aircraft 5, and, if necessary, to inform the crew when the acceleration of the aircraft 5 exits the allowed acceleration range 25. Preferably, the information display device 34 is configured to represent an upper energy variation terminal symbol, representative of a threshold value of energy variation associated with the upper acceleration terminal, only when the The difference between the upper acceleration bound and the current acceleration is less than a predetermined threshold deviation, i.e. when the current acceleration of the aircraft 5 approaches or exceeds the upper acceleration limit. Similarly, the information display device 34 is configured to represent a lower energy variation terminal symbol, representative of a threshold value of energy variation associated with the value of the lower bound of the energy. acceleration, only when the difference between the current acceleration and the lower ACCmin acceleration terminal is less than a predetermined threshold deviation, i.e. say when the current acceleration of the aircraft 5 approaches or exceeds the lower Accmm acceleration limit. Thus, an energy variation terminal symbol is displayed only when the acceleration of the aircraft 5 is near or exceeds the upper terminal Accm 'or the lower terminal 5 Accmin of acceleration. Thus, the energy variation terminal symbol is displayed only when this information is relevant, which makes it possible both to avoid overloading the information display device 34 and to attract the attention of the crew when the acceleration of the aircraft 5 is approaching the upper terminal Accmax or lower Accm ,, acceleration.
[0029] Furthermore, the information display device 34 is configured to display information representative of the current speed of the aircraft 5 and information relating to speed terminals for the aircraft 5, in particular at the first range and / or at the second speed range. In particular, the information display device 34 is configured to represent a graduated speed scale, along which is represented a speed symbol indicating the current speed of the aircraft 5. The display device 34 information is also configured to represent, along the speed scale, speed terminal symbols, including the maximum speeds Vmax and minimum V ,, p of the first speed range 20 and / or the maximum speeds and minimum of the second speed range, in the example describes the maximum speeds Vmmsup, and minimum Vmminf of maneuverability, and / or the maximum speeds Vmaxop and minimum Vmmop operational. Such a display makes it possible to inform the crew of the maneuvering room available to them in terms of speed.
[0030] In addition, the display device 34 is configured to display information relating to the actions performed by the acceleration control module 52, in particular to indicate a modification of the drag, the thrust and / or the trajectory by the Acceleration control module 52. Such a display makes it possible to keep the crew informed and thus to disrupt at least the piloting in manual mode.
[0031] FIG. 2 shows an example of representation of this information by the information display device 34. The information display device 34 comprises a display screen 68 dedicated to piloting the aircraft 5. FIG. 2 thus represents information projected on this screen, displayed in the form of symbols.
[0032] These symbols include in particular a model symbol 70 of the aircraft 5, occupying a fixed position on the screen, which materializes a projection at infinity of the longitudinal axis of the aircraft 5, and a line d artificial horizon 72, in the center of a graduated scale of slope 74. This artificial horizon 72 is inclined when the roll angle of the aircraft 5 is not zero, during a turn. A speed vector symbol 76 of the aircraft 5 indicates the direction of the speed vector of the aircraft 5.
[0033] 5 The vertical difference between the artificial horizon 72 and the speed vector symbol 76 of the aircraft 5 representing the ground slope ysol of the aircraft 5. Moreover, an energy variation symbol 80 indicates a variation of total energy of the aircraft 5, expressed by a magnitude representative of this variation of total energy.
[0034] In the example shown, the magnitude representative of the total energy variation is homogeneous with a slope of the aircraft 5. The symbol 80 of energy variation is offset laterally with respect to the speed vector symbol 76, the relative position of the symbol 80 of variation of energy with respect to the graduated scale of slope 74 corresponding to the value of the quantity representative of the variation of total energy.
[0035] Preferably, the magnitude representative of the total energy variation is the total pseudo-slope Y * of the aircraft 5. Thus, the relative position of the energy variation symbol 80 with respect to the speed vector symbol 76 indicates the sign of the acceleration of the aircraft 5: a horizontal alignment of the energy variation symbol 80 and the speed vector symbol 76 represents zero acceleration; when the acceleration of the aircraft 5 is negative, that is to say that the aircraft 5 decelerates, the energy variation symbol 80 is positioned below the speed vector symbol 76, whereas when the acceleration of the aircraft 5 is positive, the energy variation symbol 80 is positioned above the speed vector symbol 76.
[0036] In addition, the distance between the energy variation symbol 80 and the speed vector symbol 76 is representative of the absolute value of the acceleration of the aircraft 5. For example, as shown in FIG. 2, the symbol 80 The variation of energy is chevron-shaped, comprising a lower segment 80a and an upper segment 80b oblique joining to form a tip 80c, whose position along the vertical axis indicates, in accordance with the graduated scale of slope 74. , the value of the pseudo-total slope Y of the aircraft 5. Furthermore, a symbol 84 of energy variation terminal, representative of a threshold value of variation of energy associated with the upper acceleration terminal Accmax or at the lower acceleration terminal Accrnin, is displayed, preferably only when the distance between the upper terminal Accmax and the acceleration or the gap between the acceleration and the lower accra acceleration terminal, has is less than a predetermined threshold difference. The energy variation terminal symbol 84 thus indicates an upper or lower total pseudo-slope terminal associated with the upper Accmax acceleration terminal 5 or the lower Accrain acceleration terminal respectively, in view of the current ground slope. of the aircraft 5. Thus, the upper limit symbol of energy variation indicates a threshold value of total pseudo-slope ym * ax associated with acceleration Accmax, equal to: A CCmax Ymax = Ysol g 10 Similarly, the lower energy variation lower limit symbol indicates a total pseudo-slope threshold value ymin associated with the acceleration Accmin, equal to: Accmin Ym in = Ysol g The energy variation symbol 80 and the terminal symbol 84 energy variation is offset laterally with respect to the speed vector symbol 76, and vertically aligned. The distance between the energy variation terminal symbol 84 and the speed vector symbol 76 is representative of the absolute value of the upper limit Accmax or the lower limit Accmk of acceleration. In addition, the distance between the energy variation symbol 80 and the energy variation terminal symbol 84 is representative of a difference between the current acceleration and the Accmia or Accmax acceleration terminal, as long as the Accmin or Accmax acceleration terminal is not reached. Preferably, when the acceleration of the aircraft 5 is greater than the upper limit Accmax or lower than the lower limit Accm, a, the symbol 84 of the energy variation terminal remains superimposed on the symbol 80 of variation of energy . The energy variation terminal symbol 84 has a shape complementary to that of the energy variation symbol 80. For example, as illustrated in FIG. 2, the upper or lower energy variation limit symbol 84 comprises an oblique segment 84a inclined at the same inclination as the upper 80b or lower segment 80a respectively, and a vertical segment 84b. Alternatively, the symbol 84 may be chevron-shaped, similar to the symbol 80. The symbols 80 and 84 are then for example of different colors.
[0037] As long as the acceleration of the aircraft 5 is less than the upper acceleration acceleration terminal, the vertical distance between the symbol 84 and the symbol 80 is representative of the difference between the upper acceleration terminal Accmax and the acceleration of the aircraft 5.
[0038] When the acceleration of the aircraft 5 becomes equal to the upper acceleration acceleration terminal Accmax and then exceeds the upper Accmax acceleration terminal, the oblique segment 84a of the symbol 84 and the upper segment 80b of the symbol 80 are superimposed. Similarly, as long as the acceleration of the aircraft 5 is greater than the lower acceleration terminal Acdmin, the vertical distance between the symbol 84 and the symbol 80 is representative of the difference between the upper acceleration terminal Acc ,,,, n and the acceleration of the aircraft 5. When the acceleration of the aircraft 5 becomes equal and then lower than the lower acceleration terminal Adcmin, the oblique segment 84a of the symbol 84 and the lower segment 80a of the symbol 80 are superimposed.
[0039] Also shown is a graduated speed scale 90, along which is represented a speed symbol 92 indicating the current speed of the aircraft 5. As shown in FIG. 2, the speed symbol 92 is, for example, in the form of pentagon with one of the vertices pointing on the graduated speed scale 90 and indicates the current value of the speed of the aircraft 5 on this scale. The speed symbol 92 also forms a frame in which the value of the current speed of the aircraft 5 is given in numerical form. Preferably, the graduations of the speed scale 90 are movable relative to the Speed symbol 92. In addition, a second acceleration symbol 94, representative of the current acceleration 25 of the aircraft 5, is arranged opposite the speed scale 90. This symbol 94 is, for example, shaped. of arrow, which is oriented downward or upward depending on whether the acceleration of the aircraft 5 is negative or positive respectively, and whose length is representative of the value of the acceleration of the aircraft 5, according to a predetermined scale.
[0040] As a variant, the symbol 94 may be in the form of two parallel lines of the same length, this length being representative of the value of the acceleration of the aircraft 5, according to a predetermined scale. The symbol 94 is preferably colored, the color of the symbol 94 depending on the acceleration of the aircraft 5.
[0041] For example, the symbol 94 is green as long as the acceleration of the aircraft 5 is within the allowed acceleration range, and becomes amber when the acceleration of the aircraft 5 is outside the range of acceleration allowed. In addition, the symbol 94 turns red when the acceleration of the aircraft 5 reaches an upper or lower acceleration limit. The upper limit is for example defined as a function of the difference between the speed of the aircraft 5 and the maximum speed Vmax, while the lower limit is for example defined as a function of the difference between the speed of the aircraft 5 and the minimum speed Vmm. Thus, a red color of the symbol 94 signals a flight zone in which, without corrective action on the acceleration, the speed of the aircraft 5 will exit the attainable velocity range. On the other hand, stop symbols 95 arranged opposite the symbol 94 indicate the upper acceleration and acceleration Accmax, r, respectively. The position of the symbols 95 is representative of the value of the upper Accmax and lower Accm, a acceleration terminals, on the same scale as that used for the symbol 94. Thus, an overflow by the acceleration symbol 94 of a symbol 95 abutment means an overflow of the upper limit Accmax or lower Accmin acceleration. The speed scale 90 is furthermore provided with colored bands for signaling the critical speed ranges of the aircraft 5, and forming speed terminal symbols indicating the speed terminals Vmm, Vmax, Vmin0p, Vmax0p, VMMSup and Vmmmf. These strips comprise two first strips 98 for respectively signaling the speed interval between the maximum operational speed Vmax0p and the maximum maneuverability speed Vmmsup on the one hand, and the speed interval between the minimum operational speed Vmm0p and the minimum speed of 25 maneuverability Vmmmf on the other hand. In these speed ranges, the speed of the aircraft 5 remains within the maneuverability range but is outside the operational speed range. The strips 98 extend along the graduated speed scale between the maximum operational speed Vmaxop and the maximum maneuverability speed Vmmsup on the one hand, and between the minimum operational speed Vmmop and the minimum speed of maneuverability Vmminf of somewhere else. The strips 98 are for example amber. In Figure 2, only the strip 98 signaling the speed interval between the minimum operational speed Vmmop and the minimum speed of maneuverability Vmmmf is visible. Two second strips 100 are also intended to signal respectively the speed interval between the maximum maneuverability speed Vmmsup and the maximum achievable speed Vmax on the one hand, and between the minimum speed of 3033908 maneuverability Vmminf and the speed Vmjn stall on the other hand. In these speed ranges, the speed of the aircraft 5 is no longer within the minimum maneuverability range of the aircraft 5. The strips 100 extend along the graduated speed scale between the maximum speed of the aircraft. maneuverability Vmmsup and the maximum speed Vmax 5 on the one hand, and between the minimum speed of maneuverability Vmminf and the minimum speed V, ', n on the other hand. The strips 100 are for example amber. In Figure 2, only the strip 100 signaling the speed interval between the minimum speed of maneuverability Vmminf and the speed V, ', n stall is visible. Finally, two strips 102 indicate the non-attainable speed intervals for the aircraft 5, that is to say the speeds higher than the maximum speed Vmax or lower than the minimum speed Vn ,, n. These are the speeds that must in no case be reached by the aircraft 5. These bands are for example red in color. In Figure 2, only the strip 102 signaling speeds below the minimum speed Vmin is visible.
[0042] FIG. 3 illustrates an alternative representation of information by the information display device 34. This variant differs from the mode of the representation illustrated in FIG. 2 in that when the acceleration of the aircraft 5 becomes strictly lower (respectively strictly greater) than the lower limit Accm ,,, (respectively greater than the upper terminal 20 Accmax ), the vertical segment 84b of the energy variation terminal symbol 84 extends upwardly (respectively downwardly) relative to the oblique segment 84a, the elongation of the vertical segment 84b being proportional to the distance between the value of the lower bound Acc ,,,, acceleration and the current acceleration of the aircraft. According to another variant not illustrated, the vertical distance between the symbol 84 and the symbol 80 is always representative of the difference between the upper acceleration terminal Accmax and the acceleration of the aircraft 5, respectively of the difference between the lower Accmjn acceleration terminal and the acceleration of the aircraft 5, even when the acceleration of the aircraft 5 becomes greater than the upper Accmax acceleration terminal, respectively lower than the lower Accnn acceleration terminal.
[0043] FIG. 4 shows, in the form of a block diagram, an exemplary implementation of the method according to the invention, during a flight of the aircraft 5. This method comprises a step 120 of monitoring This monitoring step 120 is preferably implemented at each instant during the flight of the aircraft 5.
[0044] The monitoring step 120 comprises a phase 122 for determining, by the estimation module 48, the first, second and third speed ranges. In particular, during the phase 122, the estimation module 48 determines the minimum speed V, ',,, depending on the aerodynamic configuration of the aircraft 5, the weight of the aircraft 5 and the load factor of the aircraft 5. The estimation module 48 also determines the minimum maneuverability speed Vmminf, as a function of the flight phase of the aircraft 5. In addition, the estimation module 48 determines the minimum operational speed Vr, -No, depending on the flight phase of the aircraft 5 at this time.
[0045] The monitoring step 120 further comprises a phase 124 for determining, by the estimation module 48, a variation of energy of the aircraft 5, characterized by the total pseudo slope Y *, from the 5. The monitoring step 120 further comprises a phase 126 for determining, by the monitoring module 50, the authorized acceleration range for the aircraft 5 at this time. instant, depending on the speed of the aircraft 5 at this time, in particular as a function of the difference between the speed of the aircraft 5 at this time and the maneuverability range of the aircraft 5. During the phase 126, the monitoring module 50 determines the upper acceleration terminal 20 Acc'x as a function of the difference between the maximum speed of maneuverability Vmmsup, as determined during the phase 122 by the estimation module 48, and the speed of the aircraft 5 at this time. In addition, the monitoring module 50 determines the lower acceleration limit Accr '' as a function of the difference between the minimum maneuverability speed VmMInf as determined during the phase 122 by the estimation module 48 and the speed of the aircraft 5 at this time. The monitoring step 120 then comprises a comparison phase 130, during which the monitoring module 50 compares the acceleration of the aircraft 5 with the authorized acceleration range. In particular, the monitoring module 50 compares the acceleration of the aircraft 5 with the lower Accruin and upper Accmax accelerator terminals determined during the phase 126. At the end of the phase 130, if the acceleration of the 5 is within the allowed acceleration range, that is to say if the acceleration of the aircraft 5 is lower than the upper acceleration terminal Acc'x and greater than the lower terminal Acc ,, ,,, the monitoring module 50 does not activate the acceleration control module 52 or deactivates it if it had previously been activated, at a deactivation time, during a phase 132.
[0046] On the contrary, the acceleration of the aircraft 5 is not included in the authorized acceleration range, that is to say if the acceleration of the aircraft 5 is greater than the upper limit Accri, acceleration or lower than the lower acc Acceleration limit, the surveillance module 50 judges that without any action to influence the acceleration of the aircraft 5, an excursion of the speed of the aircraft 5 in -out of the range of maneuverability will be inevitable. The monitoring module 50 then activates the acceleration control module 52, at an activation time, during a phase 134. In parallel, during a phase 136 of the step 120, the monitoring module 50 compares the speed of the aircraft 5 with the third speed range, to determine if the speed of the aircraft 5 is within the operational speed range of the aircraft 5. If the speed of the aircraft 5 is outside the third speed range, that is to say if the speed of the aircraft 5 is strictly greater than the maximum operational speed Vmaxop or strictly less than the operational minimum speed V ,, op, the module 50 monitoring generates an alert to the driver.
[0047] Preferably, this alert is issued only if the absolute value of the difference between the speed of the aircraft 5 and the maximum or minimum operational speed is greater than a given threshold, corresponding to a tolerance margin, and if the speed of the aircraft 5 remains outside the third speed range for a duration greater than a predetermined time.
[0048] The alert is emitted for example by the means 32 of human machine interface. This alert is for example a hearing and / or visual alert. Thus, the monitoring module 50 generates an alert as soon as the speed of the aircraft 5 leaves the operational speed range, therefore before the speed exits the range of maneuverability, and this independently of the activation of the module 52 of acceleration control. Such an alert thus gives the opportunity to the crew to act on the manual controls of the aircraft 5 so that the speed of the aircraft 5 returns to the operational speed range, or at least remains within the range of maneuverability. . Following the phase 134, that is to say following an activation of the acceleration control module 52 by the monitoring module 50, the acceleration control module 30 implements a step 140 generation. an alarm signal to the crew, intended to warn the crew that an action will be performed by the acceleration control module 52 to change the acceleration of the aircraft 5 if no action is undertaken by the crew. If the acceleration control module 52 remains activated following the transmission of this alarm signal, that is to say if no action has been taken by the crew or if, despite action taken , the acceleration of the aircraft 5 remains outside the authorized acceleration range, the acceleration control module 52 implements a step 146 for generating a control signal of at least one an aircraft acceleration control device 5 for causing the acceleration of the aircraft 5 to move towards the authorized acceleration range, so that the speed of the aircraft 5 remains within the maneuverability range, and in any case within the attainable speed range. The control signal generated by the acceleration control module 52 depends on the speed of the aircraft 5. In particular, as long as the speed of the aircraft 5 remains within the range of maneuverability, the control module 52 acceleration acts on the devices for modifying the screen and the thrust of the aircraft 5, without affecting the trajectory of the aircraft 5. On the other hand, if the speed of the aircraft 5 leaves the range of maneuverability, the acceleration control module 52 modifies the trajectory of the aircraft 5 in order to make the speed of the aircraft 5 move towards the maneuverability range, while maintaining control over the devices for modifying the screen and the thrust of the aircraft 5, in particular to modify the drag and / or the thrust in order to make the acceleration of the aircraft 5 move towards the authorized acceleration range, if such a modification is still possible, and to prevent any modification of the drag and thrust that would maintain the acceleration of the aircraft 5 outside the allowed acceleration range. The generation step 146 thus comprises a phase 150 for comparing the speed of the aircraft 5 to the maneuverability range of the aircraft 5, that is to say at the minimum speeds Vmminf and maximum Vmmsup of maneuverability, as determined by the estimation module 48 at this time. If the speed of the aircraft 5 is within the maneuverability range, the acceleration control module 52 generates in a phase 152 a control signal of at least one drag modification device and / or the thrust of the aircraft 5, in order to maintain the speed of the aircraft 5 in the range of maneuverability. Preferably, if the acceleration of the aircraft 5 is greater than the upper acceleration terminal A''x, the acceleration control module 52 first generates, during a first phase 152, a signal thrust control device 5, in particular a control signal of the propulsion system 7, to reduce the thrust of the aircraft 5. Then, if the acceleration control module 52 remains activated despite this action, that is to say if the acceleration of the aircraft 5 remains greater than the upper Accmax acceleration terminal, the acceleration control module 52 generates in a second phase 152 a control signal of devices 9 for modifying the screen, in particular an output signal of the airbrakes 11 and / or spoilers 13, in order to increase the drag of the aircraft 5.
[0049] On the other hand, if the acceleration of the aircraft 5 is lower than the lower acceleration acceleration terminal Acc ', the acceleration control module 52 first generates, in a first step 152. , a control signal of the devices 9 for modifying the screen, in particular a retraction signal of the airbrakes 11 and / or spoilers 13, in order to reduce the drag of the aircraft 5. Then, if the control module 52 acceleration remains activated despite this action, that is to say if the acceleration of the aircraft 5 remains lower than the lower acceleration acceleration terminal, the acceleration control module 52 generates during a second phase 152 a control signal of the thrust of the aircraft, in particular a control signal of the propulsion system 7, in order to increase the thrust of the aircraft 5. If on the other hand the speed of the aircraft 5 is not within the maneuverability range, the access control module 52 Eleration generates in a phase 154 a control signal of at least one device for modifying the trajectory of the aircraft 5, in order to make the speed of the aircraft 5 move towards the maneuverability range.
[0050] In phase 154, the acceleration control module 52 also controls the thrust and drag of the aircraft. In particular, if the acceleration of the aircraft 5 is lower than the lower Accmjn acceleration terminal and the speed of the aircraft 5 is not within the range of maneuverability, the acceleration control module 52 prevents during the phase 154 20 an output of the airbrakes 11 and / or spoilers 13, which would increase the drag of the aircraft 5, and prevents a decrease in the thrust of the aircraft 5. If the acceleration of the aircraft 5 is greater than the Accmx upper acceleration terminal and the speed of the aircraft 5 not within the range of maneuverability, the acceleration control module 52 prevents during phase 154 a retraction of the airbrakes 11 and / or spoilers 13, which would decrease the drag of the aircraft 5, and prevent an increase in the thrust of the aircraft 5. As described above, as soon as the monitoring module 50 detects that the acceleration of the aircraft 5 is again included in the accelerated range the monitoring module 50 deactivates the acceleration control module 52 in a phase 132. In the deactivated state, the acceleration control module 52 is disconnected from any control device for accelerating the acceleration. 5 and no longer exerts any action on these devices. Thus, when the acceleration of the aircraft 5 leaves the authorized range given its speed, the acceleration control module 52 modifies the acceleration of the aircraft 35 until the acceleration of the aircraft 5 is again within the allowed range. The acceleration control module 52 is then deactivated, and only the manual control commands of the aircraft 5 have an influence on the acceleration control devices of the aircraft 5. In parallel, the device 34 information display displays during the flight of the aircraft 5 information relating to the flight of the aircraft 5, in particular relating to the speed and acceleration of the aircraft 5, as illustrated in FIG. 2 or 3. In particular, before each action performed by the acceleration control module 52, during the phases 152 and 154, the display device 34 displays a message intended for the pilot, in order to inform the pilot of the action about to be completed. The system and the method according to the invention thus make it possible to assist the crew 10 during a flight in manual mode, in order to prevent the speed of the aircraft 5 from reaching one of the terminals of the second speed range, in particular reaches values likely to compromise its maneuverability or even the integrity of its structure, without however going into an automatic mode in which the pilot would no longer have control of certain commands, for example a mode in which auto-joystick, automatically controlling the thrust of the aircraft, would be activated. In particular, the alarm signal generated as soon as the acceleration of the aircraft 5 is outside the authorized range makes it possible to warn the crew that an action will be performed by the acceleration control module 52, and the crew an opportunity to manually modify the drag, thrust or trajectory of the aircraft 5 before an action is performed by the acceleration control module 52. In addition, this alarm signal, as well as the information displayed by the display device 34, relating to the actions performed by the acceleration control module 52, makes it possible to inform the crew when a modification of the acceleration will be or is performed by the acceleration control module 52, and thus makes it possible to make the pilot 25 realize that a protection function is implemented and alters the manual steering. In addition, the implementation of a protection by the acceleration control module 52 even before the speed exits the range of maneuverability allows to have a certain margin of maneuver, and thus to change everything. first the thrust and the drag of the aircraft 5, in order to bend the acceleration of the aircraft 5, while retaining the possibility of modifying the trajectory of the aircraft 5 thereafter, if the modification of the thrust and the trail is insufficient. Indeed, when the speed of the aircraft 5 reaches the maximum or minimum speed of maneuverability, the trajectory of the aircraft 5 can still be changed. It should be understood that the embodiments presented above are not limiting.
[0051] In particular, in a particular embodiment, the system and method according to the invention are implemented only at high or low speed. This embodiment corresponds to the case where one of the limits of the allowed acceleration range is infinite.
[0052] In addition, the system and method according to the invention can be implemented independently of the display device. Furthermore, the second speed range may be a desired speed range for the aircraft other than a maneuverability range of the aircraft. For example, the second speed range may be defined according to the flight plan, such as a speed range to ensure passage of the aircraft at certain points within predefined time intervals.

权利要求:
Claims (14)
[0001]
CLAIMS1.- A system (3) for assisting the piloting of an aircraft (5) during manual flight control of said aircraft (5), said system (3) comprising: a surveillance module (50), configured to compare at each instant an acceleration of the aircraft (5) at said instant to an acceleration range ([Accmin; ACCmax]) authorized for the aircraft (5) at said instant, said authorized acceleration range ([Acc, ,,,; Accmax]) being a function of a speed (VI) of the aircraft (5) at said instant, - an acceleration control module (52), switchable between an activated state and a deactivated state, said module Control (52) being configured for, in the activated state, excluding the deactivated state, generating a control signal of at least one device (7, 9, 11, 13, 17). for controlling the acceleration of the aircraft (5) in at least one checking moment in order to make the acceleration of the aircraft (5) move towards said access range permissible release ([Accmin; Accmax]), in order to maintain or increase the speed of the aircraft in or to a predefined speed range ([Vmminf; Vmmsup]), said module (50) being configured to activate said acceleration control module (52) at a given activation time when the acceleration of the aircraft (5) at said given activation time is not within said allowed acceleration range ( [Accrnin; ACCMax]) -
[0002]
2. A system (3) for assistance according to claim 1, characterized in that said monitoring module (50) is configured to disable said acceleration control module (52) at a given deactivation time, subsequent to said instant given activation, when the acceleration of the aircraft (5) at said given deactivation time is within said allowed acceleration range ([Accm ,,,; Accmax]).
[0003]
3.- System (3) for assistance according to any one of claims 1 or 2, characterized in that said device (7, 9, 11, 13, 17) acceleration control is included in the group consisting of a device (9, 11, 13) for modifying the drag of the aircraft (5), a device (7) for modifying the thrust of the aircraft (5), and a device (17) for modifying the trajectory of the aircraft (5).
[0004]
4.- System (3) for assistance according to any one of claims 1 to 3, characterized in that said range of speed of use ([VMMInf; VMMSup]) is defined between an upper terminal (Vmmsup) corresponding to a maximum operating speed of the aircraft (5), and a lower limit (Vmminf) corresponding to a minimum speed of use of the aircraft (5).
[0005]
5.- System (3) for assistance according to claim 4, characterized in that said authorized acceleration range ([Accmin; Accmax]) is defined by at least one upper terminal (Accm ') acceleration allowed audit instant, said upper terminal (Acc, ') being a function of a difference between the speed (VI) of the aircraft (5) at said instant and the maximum speed of use (Vmmsup) of the aircraft (5).
[0006]
6. System (3) for assistance according to any one of claims 4 or 5, characterized in that said authorized acceleration range ([Acc, ', n; Accmax]) is defined by at least one terminal lower (Accn ,, n) acceleration allowed at said instant, said lower terminal (Accm, n) being a function of a difference between the speed (VI) of the aircraft (5) at said instant and the minimum speed of use (Vmminf) of the aircraft (5).
[0007]
7.- System (3) for assistance according to any one of claims 4 to 6, characterized in that said range of speed of use ([Vmminf; Vmmsup]) is defined between a corresponding upper bound (Vmmsup) at a maximum maneuverability speed of the aircraft (5), and a lower bound (Vmminf) corresponding to a minimum maneuverability speed of the aircraft (5).
[0008]
8. System (3) for assistance according to any one of claims 1 to 7, characterized in that the acceleration control module (52) is configured to: - compare a speed (V1) of the aircraft (5) at said control instant at said range of operating speed ([Vmminf; Vmmsup]), and for - generating a control signal of a first type, if the speed (VI) of the aircraft (5 ) at said control time is within said operating speed range 20 ([Vmminf; Vmmsup]), in order to maintain the speed of the aircraft (5) in said range of operating speed ([Vmminf; Vmmsup ]), and - generating a control signal of a second type, different from the first type, if the speed of the aircraft (5) at said control time is not within said range of operating speed ([ Vmminf; Vmmsup]), in order to make the speed of the aircraft (5) move towards said range of operating speed ([Vmminf; Vmmsupl).
[0009]
9.- System (3) for assistance according to claim 8, characterized in that the control signal of the first type is a control signal of at least one device (7, 9, 11, 13) for modifying the drag or thrust of the aircraft (5), and in that the control signal of the second type is a control signal from at least one aircraft trajectory modification device (17) (5). ).
[0010]
10. Assistance system according to any one of the preceding claims, characterized in that it comprises a device (34) for displaying information relating to the flight of the aircraft (5), said information comprising information relating to a variation of energy of the aircraft (5), said display device (34) being configured to represent on a display screen (68) an energy variation symbol (80) representative of a current value of a total energy variation of the aircraft, and at least one energy variation terminal symbol (84) representative of a threshold value (y, said total energy variation, corresponding to a terminal r * min vax -1M (Acc, ', n, Accmax) of said allowed acceleration range ([Accmin; Accmax].
[0011]
11. A method of assisting the piloting of an aircraft (5) during manual control of said aircraft (5) by means of a system (3) of assistance according to any one of claims 1 at 10, said method comprising: - an activation step (120, 134), during which said monitoring module (50) detects that the acceleration of the aircraft (5) at a given activation instant n ' is not within said allowable acceleration range ([ACCmin; ACCmaxD, and activates said acceleration control module (52), - a generation step (146), by said acceleration control module (52) activated, a control signal of at least one device (7, 9, 11, 13, 17) for controlling the acceleration of the aircraft (5) in at least one control moment with a view to softening the acceleration of the aircraft (5) towards said authorized acceleration range ([Accmin; Accmax1), in order to maintain or increase the speed of the aircraft in or to said speed range ([Vmminf; Vmmsup]).
[0012]
12. A support method according to claim 11, characterized in that said generating step (146) comprises: a phase (150) for comparing a speed of the aircraft (5) to said control time at said range of operating speed ([Vmminf; Vmmsup]), and - a phase (152) for generating a control signal of at least one device (7, 9, 11,
[0013]
13) for controlling the acceleration of the aircraft (5) of a first type, if the speed of the aircraft (5) at said control instant is in said range of speed of use ([Vmminf; Vmmsupp in order to maintain the speed of the aircraft (5) in said range of operating speed ([Vmminf; Vmmsup]), or - a phase (154) for generating a control signal of at least a device (17) for controlling the acceleration of the aircraft (5) of a second type, different from the first type, if the speed of the aircraft (5) at said control instant is not included in said operating speed range ([Vmminf; Vmmsup1), in order to make the speed of the aircraft 30 (5) approach the said operating speed range (Umminf; Vmmsupl) - 13. Assistance method according to the claim 12, characterized in that the control signal of the first type is a control signal of at least one device (7, 9, 11, 13) for modifying the drag or the thrust of the aircraft (5), and in that the control signal of the second type is a control signal of at least one device (17) for modifying the trajectory of the aircraft (5). 3033908 32
[0014]
14. A method of assistance according to claim 13, characterized in that it further comprises a phase (132) of deactivation, subsequent to said step (146) of generation, in which said module (50) monitoring detects the acceleration of the aircraft (5) is within said allowed acceleration range ([Accmin; Accm '])) at a given deactivation time, subsequent to said given activation time, and deactivates said module (52) acceleration control.

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公开号 | 公开日

FR3033908B1|2018-11-30|

US10209710B2|2019-02-19|

BR102016005723A2|2016-09-20|

US20160272336A1|2016-09-22|

CA2922616A1|2016-09-18|

引用文献:

公开号 | 申请日 | 公开日 | 申请人 | 专利标题

FR2677605A1|1991-06-14|1992-12-18|Aerospatiale|METHOD AND SIGNALING OF MANEUVERABILITY OF AN AIRCRAFT AND DEVICE IMPLEMENTING SAID METHOD.|

US20100078518A1|2008-09-26|2010-04-01|Tran Chuong B|Horizontal tail load alleviation system|

US4764872A|1986-07-16|1988-08-16|Honeywell Inc.|Vertical flight path and airspeed control system for aircraft|

FR2747204B1|1996-04-05|1998-06-12|Aerospatiale|DEVICE FOR MAINTAINING THE SPEED OF AN AIRCRAFT WITHIN A DETERMINED SPEED DOMAIN|

US5912627A|1997-10-17|1999-06-15|Alexander; William J.|Device and method for indicating if an airplane is operating within operating limits|

US5913627A|1997-12-11|1999-06-22|Pitney Bowes Inc.|Guide and support structure for a mailing machine|

US6246929B1|1999-06-16|2001-06-12|Lockheed Martin Corporation|Enhanced stall and recovery control system|

FR2864032B1|2003-12-19|2007-02-23|Airbus France|METHOD AND DEVICE FOR DETECTING ON AIRCRAFT AN EXCEEDING OF DIMENSIONING LOADS AT A PORTION OF STRUCTURE OF SAID AIRCRAFT.|

DE102005032849B4|2005-07-14|2009-09-03|Eads Deutschland Gmbh|An apparatus and method for transferring an aircraft from an out of a permissible flight condition range to a flight condition within the allowable flight condition range|

CA2789269C|2010-02-11|2015-12-29|Bell Helicopter Textron Inc.|Stall prevention/recovery system and method|EP2757350B1|2013-01-18|2015-09-16|Airbus Defence and Space GmbH|Display of aircraft attitude|

FR3033886B1|2015-03-18|2017-04-21|Dassault Aviat|DEVICE FOR DISPLAYING AN ENERGY VARIATION AND AN ENERGY VARIATION TERMINAL FOR AN AIRCRAFT|

US11263912B2|2019-08-15|2022-03-01|Gulfstream Aerospace Corporation|Aircraft taxi assistance avionics|

法律状态:
2016-03-21| PLFP| Fee payment|Year of fee payment: 2 |

2016-09-23| PLSC| Publication of the preliminary search report|Effective date: 20160923 |

2017-03-17| PLFP| Fee payment|Year of fee payment: 3 |

2018-02-27| PLFP| Fee payment|Year of fee payment: 4 |

2020-02-25| PLFP| Fee payment|Year of fee payment: 6 |

2021-02-10| PLFP| Fee payment|Year of fee payment: 7 |

2022-02-10| PLFP| Fee payment|Year of fee payment: 8 |

优先权:

申请号 | 申请日 | 专利标题

FR1500534|2015-03-18|

FR1500534A|FR3033908B1|2015-03-18|2015-03-18|SYSTEM AND METHOD FOR AIRCRAFT ASSISTING ASSISTANCE|FR1500534A| FR3033908B1|2015-03-18|2015-03-18|SYSTEM AND METHOD FOR AIRCRAFT ASSISTING ASSISTANCE|

CA2922616A| CA2922616A1|2015-03-18|2016-03-03|Aircraft piloting assistance system and method|

US15/063,940| US10209710B2|2015-03-18|2016-03-08|Aircraft piloting assistance system and method|

BR102016005723A| BR102016005723A2|2015-03-18|2016-03-16|aircraft pilot aid system and method|

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