• 专利附录
  • 专利说明
  • 权利要求
  • 类似技术
  • 同族专利
  • 引用文献
  • 法律状态
  • 优先权
    • 专利摘要:
    - Method and device for displaying a symbology for assisting the piloting of an aircraft during a landing phase. - The display device (12) allows a crew to anticipate or avoid the issuance of an exit alert, capable of being issued by a flight control unit (10), said device display device (12) comprising a display unit (1) capable of displaying a symbology, a module (21) for determining the characteristics of the track, a module (20) for determining a driving distance required by the aircraft to achieve a running speed, when the flight control unit (10) operates in a first mode, a transmission module (23) configured to transmit a set of signals (s23) allowing the unit d displaying (1) displaying a symbol representative of the driving distance and at least one symbol representative of the characteristics of the track.
    公开号:FR3049265A1
    申请号:FR1652559
    申请日:2016-03-24
    公开日:2017-09-29
    发明作者:Christine Charbonnier；Rodolphe Bonet；Laetitia Thenault
    申请人:Airbus Operations SAS；
    IPC主号:
    专利说明:

    TECHNICAL AREA
    The present invention relates to a method and a device for displaying a symbology for aiding the piloting of an aircraft during a landing phase on an airstrip.
    STATE OF THE ART
    There are currently methods and devices for assisting the piloting of an aircraft during a landing phase on an airstrip. US Pat. No. 8,275,501 B1 describes such a method or such a device. Such a method or device is a unit called runway overrun prevention system (or unit) or ROPS (or runway overrun prevention system).
    In general, these devices are intended to estimate the landing point of the aircraft on the landing runway on landing based on the ability of the aircraft to stop in nominal conditions. The adjective "nominal" qualifies the fact that there is no case of failure that could degrade the deceleration capacity of the aircraft.
    If, at any point during the landing phase, the method or device predicts that the aircraft will not be able to stop on the runway, at least one alert is triggered. Such an alert allows the crew to carry out a go-around maneuver if it is still possible to do so. If it is no longer possible to perform a go-around and the aircraft is on the ground, these alerts may also prompt the crew to use any deceleration means available, such as maximum braking and inversion. maximum of the thrust, in order to stop the aircraft on the remaining length of the runway.
    Thus, a unit of the RQPS type will issue an alert in the event of detection of a risk of leaving the runway, in order to encourage the crew to use any means of deceleration or to automatically trigger a deceleration means. For example, maximum braking can be triggered by the crew or triggered automatically and a maximum thrust reversal can be triggered by the crew. Such an alert represents a last safety net so that the pilot can trigger an urgent action.
    When the aircraft is in flight or on the ground, the ROPS unit calculates in real time a stopping distance which corresponds to a distance that an aircraft makes to stop on an airstrip. This stopping distance is continuously compared to the length of the remaining track in front of the aircraft. Thus, if the calculated stopping distance is greater than the length of the track, dedicated alerts are issued. These alerts may correspond to messages displayed on the main flight display (PFD for "Primary Flight Display" in English) and a loudspeaker sound alert. These dedicated alerts separate the world into a white region in which no alerts are issued and a black region in which dedicated alerts are issued. The ROPS unit has two sub-functions: a Runway Overrun Warning (ROW) function and a Runway Overrun Prevention (ROP) function. . The ROW function allows the generation of alerts prompting the crew to go back on the air while the ROP function allows the generation of alerts prompting the crew to activate deceleration devices. The ROW function is active from a predetermined height, for example 500 feet (152 m), and remains active until a decision point. From this decision point, the ROP function is active. The ROP function remains active until the aircraft AC reaches a running speed.
    Said decision point may correspond to the detection of a steady state condition, that is to say, a condition corresponding to the fact that the autobrake is activated and that the ground spoilers ( Ground spoilers) are deployed. This decision point can therefore be translated by the following logic: the decision point is confirmed if at least one of the following conditions is true: the main landing gear (MLG) or "Main Landing Gears"; the Nose Landing Gears (NLG) are compressed for 1 s, the total deployment of the ground spoilers has been requested.
    One of these two conditions can be true if automatic braking is activated.
    For some aircraft, there is no available means for the crew to anticipate an alert generated by the ROPS-type unit since no other indication than that of the alert is provided to the crew.
    For other aircraft, indications are provided to the crew via an airport navigation display ("airport navigation display" in English) but at least one action of the crew is necessary to access these indications. . In addition, the display of these indications may obscure the navigation and monitoring information that must be monitored during the landing phase.
    Therefore, continuous display of these indications is not possible during the landing phase.
    STATEMENT OF THE INVENTION
    The object of the present invention is to remedy this drawback by proposing a method and a device enabling the crew of an aircraft to anticipate or avoid issuing an exit warning. To this end, the invention relates to a method for displaying a symbology for assisting the piloting of an aircraft during the landing phase on an airstrip. Said symbology is displayed on a display unit in association with a landing aid assistance unit capable of operating in at least a first mode of operation when the aircraft is on the ground. The flight control unit is able to emit a signal representative of its mode of operation.
    According to the invention, the method comprises: a step of determining characteristics of the runway, implemented by a first determination module, consisting in determining characteristics of the runway; a first series of sub-steps when the piloting aid unit transmits to a second determination module a signal representative of the first mode of operation, the first series of steps comprising: O a first sub-step of determining distance , implemented repetitively by the second determination module, consisting in determining a rolling distance corresponding to a distance necessary for the aircraft to reach a rolling speed; O a sub-step of transmitting to the display unit a symbology of the first mode of operation, implemented by a first transmission module, of transmitting to the display unit a set of signals allowing the display unit displays a symbol representative of a driving distance and displaying at least one symbol representative of the characteristics of the track.
    Thus, thanks to the invention, the method allows a display to be always available to the crew without any action on its part so that it can implement the necessary actions to anticipate or avoid an exit alert issued by a ROPS type unit.
    In a preferred embodiment, the method further comprises a second series of substeps when the driving aid unit transmits to a third determining module a signal representative of a second operating mode when the aircraft is in flight, the second series of steps comprising: a second distance determining sub-step, repetitively implemented by the third determining module, of determining: O a stopping distance on a runway a stop distance on a track in a selected state, if the third determination module receives a signal representative of the selected track state, said signal being to be transmitted to the third determination module by a track state selection module; a sub-step of transmitting to the display unit a symbology of the second mode of operation, implemented by a second transmission module, of transmitting to the display unit a set of signals enabling the display unit to display at least one symbol representative of the characteristics of the track and to display: O is a symbol representative of the stopping distance on a dry track and a symbol representative of the stopping distance on a wet track, O is a symbol representative of the stopping distance on a track in the selected state.
    Advantageously, the step of determining the characteristics of the track consists in determining a length of the track and coordinates of a track release point in a reference frame linked to the track, from signals from a database airport.
    In addition, the first distance determination sub-step consists of determining coordinates of a running point from which the aircraft reaches a running speed in the reference point linked to the track, from signals coming from the flight aid unit.
    In addition, the substep of transmission of a symbology of the first mode comprises: a first substep of transmission of a track symbology, implemented by the first transmission module, of transmitting a set of signals allowing to the display unit displaying a representative symbol of the landing runway from the runway length and a symbol locating the runway release point from the runway clearing point coordinates in the runway landmark linked to the track; a first sub-step of transmission of a distance symbology, implemented repetitively by the first transmission module, of transmitting a set of signals enabling the display unit to display a symbol locating the point running from the coordinates of the rolling point, the display of this symbol being able to be refreshed by the display unit with each transmission of all the signals.
    In addition, the step of determining the characteristic of the track further comprises determining the coordinates of an end of track margin in the track-related mark corresponding to a predetermined margin before the downstream end of the track in the track. landing direction of the aircraft.
    In addition, the first sub-step of transmitting a track symbology further comprises transmitting, by the first transmission module, a set of signals allowing the display unit to display a symbol representative of the margin predetermined from the coordinates of the runway end margin.
    Advantageously, the second substep of determining distances also consists in determining from signals coming from the flight control unit: either coordinates of a stopping point of the aircraft on a dry runway according to the a runway-related fix and coordinates of a wet runway stop point in the runway-related fix, or coordinates of a breakpoint of the runway aircraft in the state selected in the reference linked to the track.
    According to a particularity, the substep of transmission of a symbology of the second mode comprises: a second substep of transmitting a track symbology, implemented by the second transmission module, of transmitting a set of signals allowing the display unit to display a representative symbol of the track from the length of the track and a symbol locating the track release point from the coordinates of the track release point in the coordinate system related to Track ; a second sub-step of transmitting a distance symbology, implemented repetitively by the second transmission module, of transmitting a set of signals allowing the display unit to display: O is a symbol representative of the stopping distance of the dry runway aircraft from the dry runway stop point coordinates and a wet runway stop distance symbol from the wet runway breakpoint coordinates in the track-related coordinate system, O is a symbol representative of the stopping distance of the aircraft on the track in the selected state from the coordinates of the runway stop point in the selected state, the display these symbols being able to be refreshed by the display unit with each transmission sets of these signals.
    Preferably, the method further comprises a reconfiguration step, implemented by a reconfiguration module, of performing at least one of the following substeps: a substep of transmitting a control signal to the a display unit controlling the erasure of the symbols displayed following the substep of transmitting a symbology of the first mode, when the control assistance unit changes from a first mode to a second operating mode; a sub-step of transmitting a control signal to the display unit controlling the erasure of the displayed symbols following the step of transmitting a symbology of the second mode, when the flight control unit passes from a second mode to a first mode of operation. The invention also relates to a device for displaying a symbology of assistance in piloting an aircraft during the landing phase on an airstrip in association with a landing aid piloting unit. The flight aid unit operates in at least one first mode when the aircraft is on the ground. The flight control unit is able to emit a signal representative of the operating mode.
    According to the invention, the device comprises: a display unit able to display said symbology, a first module for determining the characteristics of the landing runway configured to determine the characteristics of the runway, a second determination module configured to repeatedly determine a running distance corresponding to a distance necessary for the aircraft to reach a running speed, when the flight control unit transmits to the first determination module a signal representative of the first operating mode, a first transmission module configured to repetitively transmit a set of signals enabling the display unit to display a symbol representative of the driving distance and to display at least one symbol representative of the characteristics of the track.
    According to a preferred embodiment, the device further comprises: a third determination module configured to determine, repetitively, when the piloting assistance unit transmits to the third determination module a signal representative of the second mode of operation: either a stopping distance on a dry track and a stopping distance on a wet track, O a stopping distance on a track in a selected state, if the third determining unit receives a signal representative of the state selected track, said signal being adapted to be transmitted to the third determination module by a track state selection module; a second transmission module configured to repetitively transmit a set of signals enabling the display unit to display at least one symbol representative of the characteristics of the track and to display: O is a symbol representative of the distance d stopping on a dry runway and a symbol representing a stopping distance on a wet runway, O is a symbol representative of the stopping distance on a runway in the selected state.
    Furthermore, the second determination module is also configured to determine the coordinates of a runway margin corresponding to a predetermined margin before the downstream end of the runway in the landing direction of the aircraft, the first module transmission device being also configured to transmit a set of signals allowing the display unit to display a symbol representative of the predetermined margin from the coordinates of the end of the runway margin.
    Preferably, the device further comprises a reconfiguration module configured to perform at least one of the substeps of: transmitting a control signal to the display unit controlling the erasing of symbols displayed on the unit when the flight control unit changes from a first operating mode to a second operating mode, transmitting a control signal to the display unit controlling the erasing of the symbols displayed on the display unit. display unit, when the flight control unit changes from a second operating mode to a first operating mode. The invention also relates to a system for assisting the piloting of an aircraft during the landing phase on an airstrip. The system comprises a display device according to the invention and a piloting assistance unit during the landing phase. The system display unit corresponds to a navigation screen. The invention also relates to an aircraft, in particular a transport aircraft, which is provided with a device for displaying a steering assistance symbology such as that described above.
    BRIEF DESCRIPTION OF THE FIGURES The invention, with its features and advantages, will emerge more clearly from a reading of the description given with reference to the appended drawings, in which: FIG. 1 represents a synoptic view of a particular embodiment of a device for assisting the piloting of an aircraft during the landing phase on an airstrip, FIG. 2 is a block diagram of steps implemented by the device, and FIG. an aircraft comprising the device. FIG. 4 represents a first example of display on a display unit according to a symbology of a second mode of operation; FIG. 5 represents a second example of display on a display unit according to a symbology of a second mode of operation, - Figure 6 shows a third example of display on a display unit according to a symbology of a second mode of operation, - Figure 7 shows a first example of display on a unit of display according to a symbology of a first mode of operation, - Figure 8 shows a second example of display on a display unit according to a symbology of a first mode of operation.
    DETAILED DESCRIPTION
    The remainder of the description will refer to the figures cited above. The invention relates to a method and a device 12 for displaying a symbol for assisting the piloting of an aircraft AC during a landing phase on a landing strip T. The symbology is displayed on a display unit 1 in association with a landing aid control unit 10, such as a ROPS type unit. The piloting aid unit 10 during the landing phase can operate in a first mode of operation.
    Said first mode of operation is activated when the aircraft AC is on the ground. It corresponds, for example, to the ROP function for the ROPS unit.
    Furthermore, the flight control unit 10 can operate in a second mode of operation when the aircraft AC is in flight. It corresponds, for example, to the ROW function for the ROPS unit.
    The moment that separates the two modes of operation is, for example, the moment of the decision point. The AC aircraft is essentially in flight before the decision point. It is essentially ground after the decision point. The flight control unit 10 is able to send a signal slO representative of its operating mode. The crew can control the activation or deactivation of the flight aid unit 10. For example, this control can be performed by means of a button in the cockpit of the aircraft AC.
    In a particular embodiment of the flight control unit 10, if the flight control unit 10 is deactivated, said unit 10 only functions in the first embodiment when the aircraft AC is on the ground . In this case, the flight aid unit 10 does not operate in the second operating mode even if the aircraft AC is in flight.
    In this last particular embodiment, if the piloting aid unit 10 is activated, said unit 10 operates in the second mode of operation when the aircraft AC is essentially in flight and in the first mode of operation when the AC aircraft is basically ground.
    For example, below a certain altitude, for example below 500 feet (about 152 m), if the crew has activated the flight aid unit 10, said piloting aid unit 10 is activated in the first mode of operation. During the final approach of the T track, as long as the T track is detected and until the decision point is reached, the second mode remains activated.
    According to the invention, the display device 12 which is embarked on the aircraft AC comprises, as represented in FIG. 1: a display unit 1, a first determination module 21 COMP1 (COMP for "computation module") in English) characteristics of the landing runway T configured to determine the characteristics of the track T, a second determining module COMP2 configured to repeatedly determine a running distance corresponding to a distance required by the aircraft AC for to reach a running speed, when the piloting aid unit 10 transmits to the second determination module 20 a signal slO representative of the first mode of operation, a first transmission module 23 TRANSI (TRANS for transmission module) ) configured to repetitively transmit a set of signals s23 enabling the display unit 1 to display a symbol 7 representing entative of the driving distance and display at least one symbol 3 and 6 representative of the characteristics of the track T.
    Without limitation, the running speed corresponds to a speed of 10 knots (about 18.5 km / h).
    Advantageously, the characteristics of the track T determined by the first determination module 21 correspond to a length of the track T and the coordinates of a release point L of track T in a reference frame R linked to the track T (FIG. 3). . By way of example, the length of the track T may correspond to the coordinates of an upstream end B of the track T and to the coordinates of a downstream end G of the track T in the landing direction F of the aircraft AC. . Moreover, the coordinates of the upstream end B of the track T can be considered as the origin of the reference R linked to the track T. This determination can be made from signals if 4 coming from a database 14 an airport checkpoint such as a database of airstrips hosted on a warning system and warning of impact (TAWS for "Terrain Awareness and Warning System" in English). By way of example also, the release point L of the track T can define a distance between the upstream end B of the track T and the said release point L. This distance corresponds to a preselected distance intended for a braking unit allowing the release of the track T type BTV ("Brake To Vacate" in English). The BTV type braking unit indicates or controls the combination of brakes and thrust reversals necessary for the AC aircraft to be stopped, for example, at the release point at an exit ramp.
    According to one embodiment, the first determination module 21 is also configured to determine the coordinates of an end-of-track margin M corresponding to a predetermined distance margin M before the downstream end G of the track T in the direction landing plane F of the aircraft AC on the track T. According to this embodiment, the first transmission module 23 is also configured to transmit a set of signals allowing the display unit 1 to display a representative symbol the predetermined margin M from the coordinates of the margin M end of the track T.
    Without limitation, the predetermined distance margin M has a length of 300 m.
    According to a preferred embodiment, the device 12 further comprises: a third determination module 22 COMP3 configured to repeatedly determine at least one stopping distance, when the piloting assistance unit 10 transmits to the third module of determining a representative slO signal of the second mode of operation, and a second transmission module 24 TRANS2 configured to repetitively transmit a set of signals s24 allowing the display unit 1 to display a representative symbol of at least a stopping distance and displaying at least one symbol representative of the characteristics of the track T.
    Alternatively, the crew has the ability to select a track condition using a track condition select module 15. The track condition select module 15 is configured to send a signal if 5 representative of the track condition selected by the crew. For example, the track condition selection module 15 is a button having at least one position corresponding to a wet track and a position corresponding to a dry track.
    If the third determining module 15 does not receive a signal if representative of the selected track state transmitted by the track condition selecting module 15, the third determining module 22 is able to repeatedly determine a distance. dry runway stop and wet runway stopping distance. The second transmission module 24 is then able to repetitively transmit a set of signals s24 allowing the display unit 1 to display a symbol representative of a dry runway stopping distance and a stopping distance. on wet track.
    If the third determining module 15 receives a signal if representative of the selected track state transmitted by the track condition selecting module 15, the third determining module 22 is configured to repeatedly determine a distance of stopping on a track in the state selected by means of the track condition selection module 15. The second transmission module 24 is then able to repetitively transmit a set of signals s24 allowing the unit 1 d display to display a symbol representative of a stopping distance on the track in the selected state.
    According to a preferred embodiment, the display device 12 also comprises a reconfiguration module RECONF (for "reconfiguration unit") configured to perform at least one of the substeps of: transmitting a control signal s25 to the display unit 1 controlling the erasure of the symbols displayed on the display unit 1, when the control assistance unit 10 changes from a second operating mode to a first operating mode, and transmitting a control signal s25 to the display unit 1 controlling the erasing of the symbols displayed on the display unit 1, when the piloting aid unit 10 goes from a first operating mode to a second mode of operation.
    According to one embodiment, the COMP1, COMP2, COMP3, TRANSI, TRANS2, RECONF modules are integrated in a central unit 13 or a computer. By way of example, the modules may correspond to algorithms implemented in software in the central unit 13.
    In particular, the modules can be stored in at least one memory zone of the central unit 13.
    The display device 12 may be part of a system for assisting the piloting of an aircraft AC in the landing phase on a landing strip T. This system 10 comprises a display device 12 and a flight control unit 10 during the landing phase.
    The device, as described above, implements all of the following steps of a method of displaying a symbology shown in FIG. 2. Said method comprises at least one step El of determining the characteristics of the landing track T, implemented by the first determination module 21, consisting in determining the characteristics of the track T.
    According to one embodiment, the step E of determining the characteristics of the track T consists in determining a length of the track T and the coordinates of a release point L of track T in a reference frame R linked to the track T ( Figure 3).
    When the piloting aid unit 10 operates in the first mode of operation, said unit 10 transmits to the second determination module 20 a signal slO representative of the first mode of operation.
    The method then comprises a first series of sub-steps including: a first substep E2 of distance determination, implemented, repetitively, by the second determination module 20, consisting in determining a rolling distance corresponding to a distance required for the aircraft AC to reach a running speed; a substep E3 of transmission to the display unit 1 of a symbology OG of the first mode of operation, implemented by the first transmission module 23. This transmission substep E3 consists in transmitting to the display unit 1 a set of signals s23 allowing the display unit 1 to display a symbol 7 representative of a rolling distance and to display at least one symbol 3 representative of the characteristics of the track T.
    According to one embodiment, the first distance determination sub-step E2 consists in determining the coordinates of a running point X from which the aircraft AC reaches a running speed in the reference R linked to the track T, from signals from the piloting aid unit 10 (FIG. 3).
    According to one embodiment, the substep E3 for transmitting a first-mode OG symbology comprises a first substep E3.1 for transmitting a T-track symbology, implemented by the first transmission module 23. and a first sub-step E3.2 for transmitting a distance symbology, implemented repetitively by the first transmission module 23.
    The first sub-step E3.1 for transmitting a track symbology T consists in transmitting a set of signals enabling the display unit 1 to display a symbol 3 representative of the landing track T from the length of the track T and a symbol 6 locating the release point L of the track T from the coordinates of the release point of track T in the reference linked to the track T.
    The first sub-step E3.2 for transmitting a distance symbology consists in repetitively transmitting a set of signals enabling the display unit 1 to display a symbol 7 locating the running point X from the coordinates of the driving point. The display of the symbol 7 locating the rolling point X is able to be refreshed by the display unit 1 with each transmission of all the signals s23 by the first transmission module 23.
    According to one embodiment, the determination step E1 further consists in determining, by the first determination module 21, the coordinates of a margin M at the end of the track T in the reference R linked to the track T (FIG. ). The coordinates of the margin M at the end of the track T corresponds to a predetermined distance margin M before the downstream end G of the track T in the landing direction F of the aircraft AC. In this embodiment, the first transmission substep E3.1 further comprises transmitting by the first transmission module 23 a set of signals enabling the display unit 1 to display a symbol 8 representative of the predetermined margin M before the downstream end G of track T from the coordinates of the end-of-track margin T.
    Thus, during the first mode of operation of the flight control unit 10, a synthetic landing strip corresponding to the first mode of operation is displayed on the display unit 1 of the navigation screen ("navigation display "in English) with the characteristics of the landing runway T such that its length, the location of the release point L of track T and the rolling distance X on the same mark R linked to the track T.
    When the flight aid unit 10 operates in the first mode of operation, the aircraft AC being essentially on the ground, the crew intends to stop the aircraft AC. The navigation and monitoring information 2 are therefore usually no longer useful. Thus, the display of the symbols of the OG symbology of the first mode can be centered on the display unit 1.
    In a preferred embodiment, the track T is symbolized by a rectangle 3. The rectangle 3 may further comprise a measurement graduation 9, for example, every 300 m in the coordinate system linked to the track T. The location of the point running X is symbolized by a bar 7 perpendicular to the symbol 3 of the track T and arranged according to its coordinates on the reference R linked to the track T. The location of the release point L of track T is symbolized by a point or a disk 6 placed on the symbol 3 of the track T according to its coordinates on the mark R linked to the track T. The predetermined margin M is symbolized by a dashed line 8 parallel to the symbol 3 of the track T. The display of the symbol 7 of the location of the rolling point X is updated repeatedly so that it corresponds to a rolling distance determined according to the actual parameters of the aircraft AC, such as the deceleration of the aircraft AC.
    This allows the crew to be aware in real time of the stopping margin or its ability to clear the T track at the appropriate pre-selected point.
    In one embodiment, different colors may be used to differentiate the symbols between them or to alert the crew.
    For example, in the case where the rolling distance is smaller than the release distance and the length of the track T as shown in FIG. 7, the track T is symbolized by a gray rectangle 3, the location of the rolling point X by a green bar 7, the location of the release point L by a blue dot or a blue disk 6 and the predetermined margin M by a red dashed line 8.
    In the case where the rolling distance is greater than the length of the track T as represented in FIG. 8, the location of the rolling point X is symbolized by a red bar 7.
    The OG symbology of the first mode can be superimposed on the symbology 2 corresponding to the information necessary for piloting during the landing phase of the aircraft.
    When the piloting aid unit 10 operates in the second mode of operation, said unit 10 transmits to the third determination module a signal slO representative of the second mode of operation.
    The method then comprises a second series of sub-steps including: a second substep E4 for determining distances, implemented repetitively by the third determination module 22, consisting in determining at least one stopping distance on a track ; and a substep E5 of transmission to the display unit 1 of a symbology IA of the second mode of operation, implemented by the second transmission module 24. This transmission substep E5 consists in transmitting to the 1 display unit a set of signals s24 allowing the display unit 1 to display a symbol 4 representative of at least a stopping distance and display at least one symbol representative of the characteristics of the track T.
    According to one embodiment, the second substep E4 for determining distances consists in determining the coordinates of at least one stopping point of the aircraft AC according to the reference R linked to the track T. If the third module of If a signal 22 is not representative of the selected track condition transmitted by the track selection module 15, the third determination module 22 determines the coordinates of a stop point D of the aircraft AC on dry track in the reference R linked to the track T and the coordinates of a breakpoint W of the aircraft AC wet track in the R mark bound to the track. If the third determining module 22 receives a signal if representative of the selected track state transmitted by the track selection module 15, the third determining module 22 determines the coordinates of a stopping point of the aircraft. AC on the track in the state selected in the R mark linked to the T track.
    According to one embodiment, the substep E5 transmitting a symbology IA of the second mode comprises a second substep E5.1 transmission of a T track symbology, implemented by the second transmission module 24 and a second substep E5.2 for transmitting a distance symbology, implemented repetitively by the second transmission module 24.
    The second substep E5.1 transmitting a T track symbology consists in transmitting a set of signals allowing the display unit 1 to display a symbol 3 representative of the track T from the length of the track T and a symbol 6 locating the release point L of track T from the coordinates of the release point L of track T in the reference R linked to the track T.
    The second sub-step E5.2 for transmitting a distance symbology consists in repetitively transmitting a set of signals enabling the display unit 1 to display a symbol 4 representative of the stopping distance or distances. of the AC aircraft.
    If the third determination module 22 has not received a signal s15 representative of the selected track state transmitted by the track selection module 15, the second transmission module 24 repetitively transmits a set of signals allowing the display unit 1 to display a symbol representative of the dry run stop distance from the coordinates of the dry runway stop point D and a symbol 5 of the runway stop distance wet from coordinates W of the wet track stop point in the R mark bound to the track T. If the third determination module 22 has received a signal if representative of the track condition, the second transmission module 24 transmits repetitively a set of signals allowing the display unit 1 to display a symbol representative of the stopping distance on the track in the state selected from the coordinates es of the stop point of the aircraft AC on the track in the state selected in the reference R linked to the track T. The display of the symbols 4 and 5 representative of the stopping distances is able to be refreshed by the display unit 1 with each transmission of these sets of signals s24 by the second transmission module 24.
    Thus, during the second mode of operation of the display unit, a synthetic landing strip corresponding to the second mode of operation is displayed on the display unit 1 identical to the display unit displaying an OG symbology. of the first mode of operation with the characteristics of the track T, such as its length, the location of the release point L of the track T and the stopping distances on the same mark R linked to the track T.
    The symbology IA of the second mode of operation is superimposed on the symbology 2 corresponding to the information necessary for piloting during this landing phase such as navigation and monitoring information.
    Preferably, the display of the symbology symbols IA of the second mode of operation is implemented in such a way that it does not mask the information necessary for control such as navigation and monitoring information. For example, the symbols of the second operating mode are displayed to the right or left of the display unit 1.
    In a preferred embodiment as shown in FIGS. 4 to 6, the track T is symbolized by a rectangle 3. If the third determination module 22 has not received a signal s15 representative of the track condition, the points stops D and W are symbolized by bars 4 and 5 perpendicular to the symbol 2 of the track T and arranged according to their coordinates on the reference R linked to the track T. The location of the release point L of track T is symbolized by a point or a disc 6 placed on the symbol 2 of the track T according to its coordinates on the mark R linked to the track T. The display of the symbols 4 and 5 of the stopping points is updated in a repetitive way. they correspond to stopping distances determined according to the actual parameters of the aircraft AC, such as the current configuration of the aircraft AC or the speed of the aircraft AC, and according to the actual outside conditions. Actual outdoor conditions may correspond to weather conditions such as windy conditions. This allows the crew to be aware of the stop margin of the AC aircraft in real time until landing.
    In one embodiment, different colors can be used. Different colors can differentiate the symbols between them or alert the crew with dedicated colors in case of alert.
    For example, in the case where the stopping distances are smaller than the length of the track T as represented in FIG. 4, the track T is symbolized by a gray rectangle 3, the stopping points D and W by bars. magenta 4, 5 and the location of the release point L by a blue dot or a blue disk 6.
    In the case where the stopping distance W on the wet track is greater than the length of the track T and when the stopping distance D on the dry track is smaller than the length of the track T as represented in FIG. 5, the T track is symbolized by an orange rectangle 3, the dry track D stop point by a magenta bar 4 and the wet track stop point W by an orange bar 5.
    In the case where the stopping distances D and W are greater than the length of the track T as represented in FIG. 6, the track T is symbolized by a red rectangle 3 and the stopping points 4 and 5 are symbolized by red bars.
    The transition from the OG symbology of the first mode to the second mode IA symbology and vice versa corresponds to the decision point whose concept is explained above.
    Thus, according to a preferred embodiment, the method comprises a reconfiguration step E6, implemented by the reconfiguration module 25, consisting of performing at least one of the following substeps: a substep E6.1 consisting of to transmit a control signal s25 to the display unit 1 controlling the erasure of the symbols displayed following the substep E3 for transmitting a symbology IA of the second mode, when the flight control unit 10 transition from the second operating mode to the first operating mode, and a substep E6.2 of transmitting a control signal s25 to the display unit 1 controlling the erasure of the displayed symbols following the transmission step of an OG symbology of the first mode, when the piloting aid unit 10 changes from the first operating mode to the second operating mode. The flight control unit 10 transmits to the reconfiguration module 25 a signal si 01 representative of its operating mode to indicate to the reconfiguration module 25 the change of operating mode of the piloting aid unit 10.
    Thus, when the flight control unit 10 switches from one mode to another, the display of the symbology is reconfigured automatically without the action of the crew.
    Below a predetermined altitude, for example 400 feet (about 122 m), the method is implemented automatically by the display device 12 of a steering assistance symbology.
    According to one embodiment, the scale used for the OG symbology of the first mode of operation is defined so that a distance is always displayed in front of the aircraft AC. This distance is chosen for a stopping distance required in the worst performance conditions. Without limitation, the distance corresponds to a distance of 3000 m. If the crew is able to visualize the performance on the ground on such a distance in front of the AC aircraft, it can then perform corrective actions correct.
    If the crew decides to perform a go-around after the decision point, ie when the OG symbology of the first operating mode is displayed, the OG symbology of the first operating mode is automatically cleared when the throttles are pushed into a take-off / go-around mode (TO / GA for "Take Off / Go Around"). The navigation screen returns to a navigation and monitoring information display.
    权利要求:
    Claims (15)
    [1" id="c-fr-0001]
    1. A method for displaying an aircraft piloting aid (AC) symbology during the landing phase on an airstrip (T), said symbology being displayed on a display unit (1) in association with a landing aid assisting unit (10) capable of operating in at least one first mode of operation when the aircraft (AC) is on the ground, the flight control unit (10) ) being able to emit a signal (slO) representative of its mode of operation, the method being characterized in that it comprises: a step (El) for determining characteristics of the track (T), implemented by a first determination module (21) for determining characteristics of the track (T); a first series of sub-steps (E2, E3) when the driver assistance unit (10) transmits to a second determination module (20) a signal (slO) representative of the first mode of operation, the first series of sub-steps comprising: O a first distance determining sub-step (E2), implemented repetitively by the second determining module (20), of determining a running distance corresponding to a distance required by the aircraft (AC) to reach a rolling speed; O a sub-step (E3) of transmission to the display unit (1) of a symbology (OG) of the first mode of operation, implemented by a first transmission module (23), consisting in transmitting to the display unit (1) a set of signals (s23) enabling the display unit (1) to display a symbol (7) representative of a rolling distance and to display at least one symbol (3) representative of the characteristics of the track (T).
    [2" id="c-fr-0002]
    2. Method according to claim 1, characterized in that it comprises: a second series of sub-steps (E4, E5) when the control assistance unit (10) transmits to a third determination module (22) a signal (slO) representative of a second mode of operation when the aircraft (AC) is in flight, the second series of substeps comprising: O a second substep (E4) of distance determination, implemented repetitively by the third determination module (22), namely determining: either a stopping distance on a dry track and a stopping distance on a wet track, or a stopping distance on a track in a state selected, if the third determination module (22) receives a signal (if 5) representative of the selected track state, said signal (if 5) being adapted to be transmitted to the third determination module (22) by a module of track condition selection (15); O a sub-step (E5) of transmission to the display unit (1) of a symbology (IA) of the second mode of operation, implemented by a second transmission module (24), consisting in transmitting to the display unit (1) a set of signals (s24) enabling the display unit (1) to display at least one symbol (3) representative of the characteristics of the track (T) and to display : a symbol (4) representative of the stopping distance on a dry runway and a symbol (5) representative of the stopping distance on a wet runway and displaying, or a symbol representative of the stopping distance on a track in the selected state.
    [3" id="c-fr-0003]
    3. Method according to claim 1, characterized in that the step (E1) for determining the characteristics of the track (T) consists in determining a length of the track (T) and the coordinates of a release point (L). ) track (T) in a mark (R) linked to the track (T), from signals (s14) from an airport database (14).
    [4" id="c-fr-0004]
    4. Method according to at least one of claims 1 to 3, characterized in that the first sub-step (E2) distance determination consists in determining coordinates of a rolling point from which the aircraft (AC) reaches a running speed in the mark (R) bound to the track (T), from signals (slO) coming from the driving assistance unit (10).
    [5" id="c-fr-0005]
    5. Method according to at least one of claims 1 to 4, characterized in that the substep (E3) for transmitting a symbology (OG) of the first mode comprises: a first substep (E3.1) transmission a track symbology (T), implemented by the first transmission module (23), of transmitting a set of signals (s23) enabling the display unit (1) to display a symbol ( 3) representative of the track (T) from the length of the track (T) and a symbol (6) locating the release point (L) of track (T) from the coordinates of the release point (L) track (T) in the reference (R) linked to the track (T); a first sub-step (E3.2) for transmitting a distance symbology, implemented repetitively by the first transmission module (23), comprising transmitting a set of signals (s23) enabling the unit displaying (1) displaying a symbol (7) locating the rolling point from the coordinates of the rolling point, the display of this symbol (7) being able to be refreshed by the display unit ( 1) with each transmission of all the signals (s23).
    [6" id="c-fr-0006]
    6. Method according to at least one of claims 1 to 5, characterized in that: the step (E1) for determining characteristics of the track (T) further comprises determining coordinates of an end margin (M). track (T) in the mark (R) bound to the track (T) corresponding to a predetermined margin (M) before the downstream end (G) of the track (T) in the landing direction (F) of the aircraft (AC), the first substep (E3.1) for transmitting a track symbology (T) further comprises transmitting, by the first transmission module (23), a set of signals enabling the display unit (1) displaying a symbol (8) representative of the predetermined margin (M) from the coordinates of the end-of-track margin (M) (T).
    [7" id="c-fr-0007]
    Method according to at least one of claims 1 to 6, characterized in that the second distance determination sub-step (E4) consists in determining from signals (s10) originating from the flight control unit ( 10): either coordinates of a dry runway (AC) stop point of the aircraft according to the reference (R) linked to the runway (T) and coordinates of a stop point of the aircraft (AC) on a wet runway in the runway-related reference (R) (T), ie, coordinates of a runway aircraft (AC) breakpoint in the selected state in the (R) -mark linked to the track.
    [8" id="c-fr-0008]
    8. Method according to at least one of claims 1 to 7, characterized in that the substep (E5) for transmitting a symbology (IA) of the second mode comprises: a second substep (E5.1) transmission a track symbology (T), implemented by the second transmission module (24), of transmitting a set of signals (s24) enabling the display unit (1) to display a symbol ( 3) representative of the track (T) from the length of the track (T) and a symbol (6) locating the release point (L) of track (T) from the coordinates of the release point (L) track (T) in the reference (R) linked to the track (T); a second sub-step (E5.2) for transmitting a distance symbology, implemented repetitively by the second transmission module (24), of transmitting a set of signals (s24) enabling the unit display (1) display: O is a symbol (4) representative of the dry runway aircraft (AC) stopping distance from the coordinates of the dry runway stopping point and a symbol ( 5) representative of the wet runway stopping distance from the wet runway stopping point coordinates in the (R) track mark (T), where O is a symbol representative of the stopping distance of the aircraft (AC) on the track in the state selected from the coordinates of the runway stop point in the selected state, the display of these symbols being able to be refreshed by the display unit (1 ) each transmission of sets of these signals (s24).
    [9" id="c-fr-0009]
    9. Method according to at least one of claims 1 to 8, characterized in that the method further comprises a reconfiguration step (E6), implemented by a reconfiguration module (25), of performing at least one sub-steps: a substep (E6.1) of transmitting a control signal (s25) to the display unit (1) controlling the erasing of the displayed symbols following the substep (E3 ) of transmission of a symbology (OG) of the first mode, when the flight control unit (10) changes from a first mode to a second operating mode, a substep (E6.2) consisting of transmitting a control signal (s25) to the display unit (1) controlling the erasing of the displayed symbols following the step of transmitting a symbology (IA) of the second mode, when the assistance unit control (10) changes from a second mode to a first mode of operation.
    [10" id="c-fr-0010]
    10. Apparatus for displaying an aircraft flight aid (AC) assistance symbology during the landing phase on an airstrip (T) in association with a flight aid unit (10) in landing phase, the flight aid unit (10) operating in at least a first mode when the aircraft (AC) is on the ground, the flight aid unit (10) being able to transmit a signal (slO) representative of the operating mode, characterized in that it comprises: a display unit (1) able to display said symbology, a first feature determination module (21) of the track (T) configured to determining the characteristics of the track (T), a second determining module (20) configured to repeatedly determine a rolling distance corresponding to a distance required by the aircraft (AC) to reach a rolling speed, when the flight assistance unit (10) transmits to the the second determining module (20) a signal (slO) representative of the first operating mode, a first transmission module (23) configured to repetitively transmit a set of signals (s23) enabling the display unit (1 ) display a symbol (7) representative of the driving distance and display at least one symbol (3) representative of the characteristics of the track (T).
    [11" id="c-fr-0011]
    11. Device according to claim 10, characterized in that it further comprises: a third determination module (22) configured to determine in a repetitive manner, when the piloting assistance unit (10) transmits to the third module of determining (22) a signal (slO) representative of the second mode of operation: O is a stopping distance on a dry track and a stopping distance on a wet track, O is a stopping distance on a track in a selected state, if the third determination module (22) receives a signal (s15) representative of the selected track state, said signal (s15) being adapted to be transmitted to the third determination module (22) by a selection module runway condition (15); a second transmission module (24) configured to repetitively transmit a set of signals (s24) enabling the display unit (1) to display at least one symbol (3) representative of the characteristics of the track (T ) and to display: O is a symbol (4) representative of the stopping distance on a dry track and a symbol (5) representative of a stopping distance on a wet track and, O is a representative symbol of the stopping distance on a track in the selected state.
    [12" id="c-fr-0012]
    12. Device according to claim 10, characterized in that the first determination module (21) is also configured to determine the coordinates of an end of track margin (T) corresponding to a predetermined margin (M) before the end downstream (G) of the track (T) in the landing direction of the aircraft (AC), the first transmission module (23) being also configured to transmit a set of signals (s23) allowing the unit displaying (1) displaying a symbol (8) representative of the predetermined margin (M) from the coordinates of the end of track margin (T).
    [13" id="c-fr-0013]
    Apparatus according to at least one of claims 9 and 10, characterized in that it further comprises a reconfiguration module (25) configured to perform at least one of the substeps of: transmitting a control signal ( s25) to the display unit (1) controlling the erasure of the symbols displayed on the display unit (1), when the flight control unit (10) changes from a first operating mode to a second mode of operation. transmitting a control signal (s25) to the display unit (1) controlling the erasing of the symbols displayed on the display unit (1), when the flight aid unit (10) is moved from a second mode of operation to a first mode of operation.
    [14" id="c-fr-0014]
    14. Aircraft flight assistance system (AC) during the landing phase on a runway (T), characterized in that it comprises: a display device (12) according to one of any one of claims 10 to 13, the display unit (1) corresponding to a navigation screen, a flight aid unit (10) in landing phase.
    [15" id="c-fr-0015]
    15. Aircraft, characterized in that it comprises a display device (12) such as that specified in any one of claims 10 to 13.
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    引用文献:
    公开号 | 申请日 | 公开日 | 申请人 | 专利标题
    US20040167685A1|2003-02-24|2004-08-26|Ryan Dean E.|Runway overrun monitor and method for monitoring runway overruns|
    EP1847899A1|2006-04-21|2007-10-24|Honeywell International Inc.|Apparatus to display landing performance data|
    FR2906066A1|2006-09-15|2008-03-21|Thales Sa|Wheel touchdown point estimating method for e.g. airbus A340, involves estimating travel distance during rolling of aircraft on landing runaway to attain controlled speed from real touchdown point, by taking account of braking effects|
    US9245450B1|2008-07-03|2016-01-26|Rockwell Collins, Inc.|System, apparatus, and method for generating runway visual aids on an aircraft display unit|US10214300B2|2016-11-10|2019-02-26|Honeywell International Inc.|System and method for displaying runway overrun information|US5353022A|1987-08-06|1994-10-04|The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration|Airplane takeoff and landing performance monitoring system|
    US8825238B2|2008-07-22|2014-09-02|Honeywell International Inc.|Aircraft systems and methods for monitoring energy height|
    FR2936077B1|2008-09-16|2014-12-12|Airbus France|METHOD AND DEVICE FOR AIDING THE CONTROL OF AN AIRCRAFT DURING A LANDING PHASE.|
    US20100161158A1|2008-12-18|2010-06-24|Honeywell International Inc.|Systems and methods for enhancing terrain elevation awareness|
    FR2941554B1|2009-01-29|2011-04-01|Airbus France|METHOD AND DEVICE FOR AIDING THE CONTROL OF AN AIRCRAFT DURING A LANDING PHASE|
    US8958942B2|2012-05-30|2015-02-17|Honeywell International Inc.|Systems and methods for displaying aircraft braking distance during surface operations|
    US9132913B1|2013-09-26|2015-09-15|Rockwell Collins, Inc.|Simplified auto-flight system coupled with a touchscreen flight control panel|
    US9082301B2|2013-10-28|2015-07-14|The Boeing Company|Aircraft stopping performance display and warning|
    FR3043387B1|2015-11-05|2018-06-22|Airbus |METHOD AND SYSTEM FOR BRAKING AN AIRCRAFT|FR3078811B1|2018-03-06|2020-04-03|Dassault Aviation|METHOD FOR DYNAMICALLY DETERMINING THE POSITION OF THE STOP POINT OF AN AIRCRAFT ON A RUNWAY, AND ASSOCIATED SYSTEM|
    US10956016B1|2019-11-14|2021-03-23|Rockwell Collins, Inc.|No look touchscreen panel / CDU|
    EP3945289A1|2020-07-27|2022-02-02|Rockwell Collins, Inc.|Runway overrun awareness alerting system with discrete indicator|
    US20220028281A1|2020-07-27|2022-01-27|Rockwell Collins, Inc.|Runway Overrun Awareness Alerting System with Trending Indicator|
    法律状态:
    2017-03-22| PLFP| Fee payment|Year of fee payment: 2 |
    2017-09-29| PLSC| Publication of the preliminary search report|Effective date: 20170929 |
    2018-03-23| PLFP| Fee payment|Year of fee payment: 3 |
    2019-03-22| PLFP| Fee payment|Year of fee payment: 4 |
    2020-03-19| PLFP| Fee payment|Year of fee payment: 5 |
    2021-03-23| PLFP| Fee payment|Year of fee payment: 6 |
    优先权:
    申请号 | 申请日 | 专利标题
    FR1652559A|FR3049265B1|2016-03-24|2016-03-24|METHOD AND DEVICE FOR DISPLAYING A HELP SYMBOL FOR AIDING AN AIRCRAFT DURING A LANDING PHASE|
    FR1652559|2016-03-24|FR1652559A| FR3049265B1|2016-03-24|2016-03-24|METHOD AND DEVICE FOR DISPLAYING A HELP SYMBOL FOR AIDING AN AIRCRAFT DURING A LANDING PHASE|
    US15/462,499| US10518897B2|2016-03-24|2017-03-17|Method and device for displaying a symbology for assisting the piloting of an aircraft during a landing phase|
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