• 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 at least one position indicator of an aircraft. - The display device (15) comprises at least one information generating unit (16A, 16B) for determining, during a flight of the aircraft, a control value representative of the travel by a first pilot of his control stick (2A, 2B) relative to at least one of the roll and pitch axes of the aircraft, at least one calculation unit (17A, 17B) for calculating a piloting command representative of the determined control value by the information generation unit (16A, 16B), and a display unit (18) for displaying at least one symbol on at least one screen (20A, 20B) for the second pilot and directly visible thereto , said symbol representing the position indicator and being displayed on the screen (20A, 20B) at a position illustrating on said screen said control command.
    公开号:FR3039135A1
    申请号:FR1557048
    申请日:2015-07-24
    公开日:2017-01-27
    发明作者:Franck Crosta；Christophe Cail
    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 at least one position indicator of an aircraft, in particular of a transport aircraft.
    The present invention applies to any type of aircraft configured to be piloted by two pilots.
    It is known that the manual piloting of an aircraft by a pilot around two of his three control (or control) axes, namely the pitch axis and the roll axis, is realized, via a control stick, in particular a mini-stick. Such control handles, in particular of the mini-handle type, thus make it possible, by their primary function, to control the lateral and longitudinal sides of the aircraft.
    STATE OF THE ART Generally, the mini-sleeves are: positioned on the lateral part, outwards relative to the pilots' seats; and - decoupled in their movement. Thus, any action on a control stick does not cause movement of the opposite control stick.
    It emerges from this conception that the movements exercised during the flight, by a first pilot who manages the aircraft, on his control stick, may be, in certain circumstances, hardly, or not at all perceptible, by the second pilot not providing piloting.
    The only way to try to perceive the movement controlled by the first pilot is for the second pilot (not providing steering) to look away or to lean, which induces a loss on the near and outside visual.
    This solution is not completely satisfactory.
    STATEMENT OF THE INVENTION
    The present invention aims to overcome this disadvantage. It relates to a method for displaying at least one position indicator of at least a first control stick of an aircraft, the aircraft being configured to be piloted by two pilots, a first pilot and a second pilot, the first control stick being configured to be actuated by the first pilot to fly the aircraft along two axes of control, namely the roll axis and the pitch axis.
    According to the invention, the display method comprises: an information generating step of determining, at least during a flight of the aircraft, at least one control value representative of the deflection of the first control stick; in relation to at least one of said flight axes of the aircraft; - A calculation step of calculating at least one control command according to at least one control axis, the control command being representative of the control value thus determined; and a display step of displaying at least one so-called second symbol symbol on at least one screen said second screen intended for the second pilot and directly visible to the latter, said second symbol representing the position indicator and being displayed on the second screen at a position illustrating on said second screen said control command.
    In the context of the present invention, it is considered that a "screen is directly visible by a pilot" if this screen is visually accessible by the pilot from his seat without having to move his body and without having to look away. is directed generally towards the front of the aircraft.
    Thus, thanks to the invention, it displays on a screen at least the pilot who does not provide control, a screen that is directly accessible visually and without diversion of view, a position indicator which is easily detectable information and interpretable by this pilot as to the position of the control stick of the other pilot, as specified below.
    It is no longer necessary for a pilot to look away or to look to try to perceive the actions on the control stick of the other driver. This results in no loss on the near or outside visual.
    In a preferred embodiment, the display step also consists of displaying at least one so-called first symbol symbol on at least one so-called first screen screen intended for the first pilot (who actuates his control stick) and directly visible to him. , said first symbol representing the position indicator and being displayed on the first screen at a position illustrating on said first screen said control command.
    Advantageously, during the actuation of the first control stick to control the aircraft simultaneously along said two control axes, each corresponding symbol is displayed on the screen at a position simultaneously illustrating the two control commands along these two axes. piloting.
    In addition, in a particular embodiment, the method includes a step of monitoring the piloting of the aircraft of being able to detect an aircraft flight and a manual piloting phase, and the display step consists in displaying said at least one position indicator only when a flight situation of the aircraft with a manual steering phase is detected and as long as such a situation is detected.
    Preferably, the measurement, calculation and display steps are implemented, simultaneously, for the first control stick configured to be able to be actuated by the first pilot and for a second control stick configured to be able to be actuated by the second pilot to fly the aircraft according to the two control axes.
    Furthermore, advantageously, on the same screen, the symbol representing the position indicator of the first control stick and the symbol representing the position indicator of the second control stick are differentiated visually.
    The present invention also relates to a device for displaying at least one position indicator of at least a first control stick of an aircraft, the aircraft being configured to be piloted by two pilots, a first pilot and a pilot. second pilot, the first control stick being configured to be actuated by the first pilot to fly the aircraft along two axes of control, namely the roll axis and the pitch axis.
    According to the invention, the display device comprises: at least one information generating unit configured to determine, at least during a flight of the aircraft, at least one control value representative of the deflection of the first run; control relative to at least one of said flight axes of the aircraft; at least one calculation unit configured to calculate at least one control command according to at least one control axis, the control command being representative of the control value determined by the information generation unit; and a display unit configured to display at least one so-called second symbol symbol on at least one screen called second screen intended for the second pilot and directly visible to the latter, said second symbol representing the position indicator and being displayed on the second screen at a position illustrating on said second screen said control command.
    In a preferred embodiment, the display unit is configured to also display at least one so-called first symbol symbol on at least one so-called first screen screen intended for the first driver (who actuates his control stick) and directly visible by this last, said first symbol representing the position indicator and being displayed on the first screen at a position illustrating on said first screen said control command.
    In addition, in a particular embodiment, the device comprises an aircraft flight monitoring unit configured to be able to detect an aircraft flight and a manual flight phase, and the display unit is configured to display said at least one position indicator only when a flight situation of the aircraft with a manual pilot phase is detected by the monitoring unit and as such a situation is detected.
    Moreover, advantageously, the measurement, calculation and display units are used, simultaneously, for the first control stick configured to be able to be actuated by the first pilot and for a second control stick configured to be able to be actuated by the second pilot to fly the aircraft according to the two control axes.
    The present invention also relates to an aircraft control system, comprising at least two control handles configured to be operable, each by a pilot to control the aircraft along the roll axis and the pitch axis, said control system comprising a display device as described above.
    The present invention further relates to an aircraft, in particular a transport aircraft, which is provided with a display device and / or a steering system such as those specified above.
    BRIEF DESCRIPTION OF THE FIGURES
    The appended figures will make it clear how the invention can be realized. In these figures, identical references designate similar elements.
    Figure 1 is a block diagram of an aircraft control system.
    Figure 2 shows an aircraft, namely a transport aircraft, on which the three control axes were highlighted.
    Figure 3 is a block diagram of a particular embodiment of a display device.
    Figures 4 to 6 show control handles and display screens, intended on the right half to one of the drivers and on the left half to the other pilot, respectively for different driving situations.
    DETAILED DESCRIPTION
    The present invention applies to an aircraft AC (Figures 1 and 2), for example a transport aircraft, which is configured to be controlled by two pilots.
    The manual piloting of the aircraft AC, by each pilot, around two of the three axes of control (or control), namely the pitch axis and the roll axis, is achieved by means of a control handle 2A, 2B, in particular a mini-stick. These control handles 2A and 2B are part of a control system 1 shown schematically in FIG.
    Although the control system 1 is shown in Figure 1 outside the aircraft AC for reasons of clarity and simplification, this control system 1 is of course mounted in the aircraft AC.
    Each control stick 2A, 2B ("side stick" type, "control column", ...), is configured to be actuated by a pilot, in order to control the aircraft AC with respect to these two axes of control , i.e., with respect to the pitch axis Y and the roll axis X shown in FIG.
    The piloting system 1 also comprises, for each pilot, a rudder bar (not shown) for steering the aircraft with respect to the yaw axis Z. In FIG. 2, the X, Y and Z axes meet at a point G, preferably the center of gravity of the aircraft AC, and the movement of the aircraft AC around the X, Y and Z axes is highlighted, respectively, by double arrows E1, E2 and E3 (respectively showing the variations of roll, pitch and yaw angles).
    The control system 1 is thus able to allow the pilots to control the aircraft AC around its three control (or control) axes, namely the pitch axis, the roll axis and the yaw axis. .
    Furthermore, as shown in Figure 1, a control chain 3A, 3B is associated with each control sleeve 2A, 2B.
    The control system 1 comprises for each control chain 3A, 3B: a set 4A, 4B of measuring elements or sensors ("SENSOR" in English) of the usual type, which are able to measure, as illustrated by an arrow 13A, 13B in phantom, the amplitude of the deflections of the control sleeve 2A, 2B according to its pivot axes F1 and F2, specified below with reference to Figures 5 and 6; and a calculation unit 5A, 5B ("COMPUTATION" in English), for example a guidance computer of the FGC ("Flight Guidance Computer") type of aircraft, for determining control commands representative of the deflections measured by the assembly 4A, 4B and received via a link 6A, 6B.
    The control commands (roll and pitch commands) generated by the calculation units 5A and SB are transmitted, respectively, via links 7A and 7B to a selection set ("SELECTION" in English), for example a voter, who chooses the orders received from one of said calculation means 5 and transmits them to a set 9 of actuators ("ACTUATORS" in English) of the aircraft AC.
    These actuators are able to actuate, in the usual way, as illustrated schematically by dashed lines, including the elevators 10, a drift 11 and the usual control rudders 12 roll of the aircraft.
    The present invention mainly relates to a display device 15 shown in FIG. 3, which is preferably part of the control system 1.
    This display device 15 is intended to display at least one position indicator of at least one control handle 2A, 2B of the aircraft.
    To do this, according to the invention, the display device 15 which is embarked on the aircraft, comprises, as represented in FIG. 3: an information generating unit 16A, 16B configured to determine, at least during of a flight of the aircraft, at least one control value representative of the deflection of the control stick 2A, 2B by a pilot relative to at least one of said X and Y steering axes (FIG. 2) of the aircraft ; a calculation unit 17A, 17B configured to calculate at least one control command according to at least one control axis X, Y, the control command being representative of the control value determined by the information generation unit 16A, 16B; and - a display unit 18 connected via a link 19A, 19B to the calculation unit 17A, 17B and configured to display at least one symbol on at least one screen 20A, 20B ("SCREEN" in FIG. English), a screen intended for the other pilot and directly visible by the latter, said symbol representing the position indicator and being displayed on the screen at a position illustrating on this screen said control command, as specified below in reference to Figures 5 and 6.
    In a preferred embodiment, the display unit 18 is configured to also display at least one symbol on the screen intended for the pilot who carries out the actuation of his control stick. This screen is also directly visible by this pilot. The symbol represents a position indicator and is displayed on the screen at a position illustrating on this screen the corresponding driving order.
    In the context of the present invention, the display of the symbol can be achieved either on the screen of the other driver only, or on the screens of both drivers.
    It is considered that a "screen is directly visible by a pilot" if this screen is visually accessible by the pilot from his seat without having to move his body and without having to divert the gaze which is directed towards the front of the car. 'aircraft.
    The display device 15 may comprise any type of visually accessible screen. In the context of the present invention, the screen or screens 20A and 20B of the display unit 18 may correspond to at least one of the following screens; an ND navigation screen ("Navigation Display"); a central electronic monitoring screen of ECAM type ("Electronic Centralized Aircraft Monitoring" in English); and a screen for displaying primary flight parameters of the PFD type ("Primary Flight Display"), as represented in the examples of FIGS. 4 to 6.
    In the particular embodiment shown in FIG. 1, the display device 15 comprises: - an information generation unit 16A and a calculation unit 17A associated with the control handle 2A; and an information generation unit 16B and a calculation unit 17B associated with the control stick 2B.
    In addition, in this particular embodiment: the information generating unit 16A corresponds to the set 4A of the control system 1 (FIG. 1); the calculation unit 17A corresponds to the calculation unit 5A; the information generating unit 16B corresponds to the set 4B; and the calculation unit 17B corresponds to the calculation unit 5B.
    In an alternative embodiment (not shown), some of the aforementioned elements of Figures 1 and 3 may be different, in particular the calculation unit 17A, 17B may be different from the calculation unit 5A, 5B.
    Of course, when actuating a control stick to control the aircraft simultaneously according to the two steering axes (roll and pitch), each corresponding symbol is displayed on the screen at a position simultaneously illustrating the two orders of steering according to these two axes of control.
    In addition, in a preferred embodiment, the display device 15 comprises a monitoring unit 21. This monitoring unit 21 is configured to be able to detect, in the usual way, that the aircraft is in flight (and not at the ground) and that it is in a phase of manual piloting, that is to say that it is piloted manually by one of the pilots (and not automatically). The display unit 18 is linked via a link 22 to the monitoring unit 21 and is configured to display the position indicator or indicators, only when a flight situation of the aircraft with a manual steering phase is detected by the monitoring unit 21 and as long as such a situation is detected.
    Moreover, in a preferred embodiment, the aforementioned measurement, calculation and display units are used, simultaneously, for the control stick 2A configured to be actuated by a first pilot, preferably the flying pilot (who performs the flight), and for the control stick 2B configured to be actuated by the second pilot, preferably the co-pilot (who does not perform the flight).
    In addition, on the same screen 20A, 20B, the symbol S2A, SI B representing the position indicator of the control column 2A and the symbol SIA, S2B representing the position indicator of the control column 2B are differentiated visually, in particular by different symbologies, colors and / or light intensities, as illustrated by way of example in FIG. 6.
    In the examples of FIGS. 5 and 6, the symbols are represented in the form of a cross. However, in the context of the present invention, the symbols may be represented as any symbology of any shape and color.
    The present invention is hereinafter specified using three examples of piloting situations, represented respectively in FIGS. 4 to 6. In each of these FIGS. 4 to 6, the screen 20A and the control stick 2A of FIG. left part PG are dedicated to one of the pilots, said first pilot hereinafter, in particular the flying pilot, and the screen 20B and the control stick 2B of the right part PD are dedicated to the other pilot, said second pilot, including the co-pilot. In these FIGS. 4 to 6, the screens 20A and 20B are standard displays for displaying PFD-type primary flight parameters, and are not described further.
    In the example of FIG. 4, neither driver actuates his control stick 2A, 2B. Thus, no symbol representing a position indicator is displayed on the screens 20A and 20B.
    In the example of FIG. 5, the first pilot, whose hand 23A is shown, actuates his control stick 2A. In this case, a display is made on the screen 20B of the second pilot, as illustrated by an arrow 24. More precisely, a symbol S1B is displayed on the screen 20B, and this at a position P1B which is representative, on the screen 20B, of the control command generated by the actuation of the control stick 2A, along pivot directions F1 (forward / backward) and / or F2 (right / left) to control the aircraft, respectively, along the pitch axis Y and the roll axis X (Figure 2).
    In this example of FIG. 5, the display unit 18 is configured so that a display is made only on the screen 20B of the second pilot and not on the screen 20A of the first pilot who actuates his control stick 2A. .
    Moreover, in the example of FIG. 6, the first pilot, whose hand 23A is shown, actuates his control stick 2A. In this case, a display is thus made on the screen 20B of the second driver, as illustrated by an arrow 25. More specifically, the symbol B (represented in the form of a solid line cross) is displayed on the screen 20B, at a PIB position which is representative of the control command generated by the actuation of the control stick 2A according to the pivot directions Fl (forward / backward) and / or F2 (right / left).
    Moreover, in this example of FIG. 6, the second pilot, whose hand 23B is shown, also operates his control stick 2B. In this case, a display is made on the screen 20A of the first driver, as illustrated by an arrow 26. More specifically, the symbol SIA (represented as a solid line cross) is displayed on the screen 20A, and this at a position P1A which is representative, on the screen 20A, of the control command generated by the actuation of the control stick 2B according to pivot directions F1 (forward / backward) and / or F2 (right / left).
    In addition, in this example of FIG. 6, the display unit 18 is configured to also display a symbol on the screen intended for the pilot who carries out the actuation of his control stick. More precisely: the symbol S2A (represented in the form of a dashed cross) is displayed on the screen 20A, and this at a position P2A which is representative of the command command generated by the actuation of the control stick 2A according to the pivoting directions F1 and / or F2; and the symbol S2B (represented in the form of a dashed cross) is displayed on the screen 20B, and this at a position P2B which is representative of the control command generated by the actuation of the following control stick 2B the pivoting directions F1 and / or F2.
    The operation of the display device 15, as described above, is as follows.
    When actuating a control stick 2A, 2B by a pilot to steer the aircraft along the pitch and / or roll axes: the information generation unit 16A, 16B determines a value of control representative of the travel of the control stick thus actuated; the calculation unit 17A, 17B calculates at least control commands according to these control axes, the control commands being representative of the control value determined by the information generation unit 16A, 16B; and the display unit 18 displays a symbol on at least one screen intended for the other pilot and directly visible to the latter, this symbol is displayed on the screen at a position illustrating on said screen said control commands.
    The display device 15 may also display a symbol on the pilot screen which actuates its control stick 2A.
    Thus, the display device 15 displays, on a screen, information that is easily detectable and interpretable by a pilot as to the position of the control stick of the other pilot. It is no longer necessary for a pilot to look away or to look to try to perceive the actions on the control stick of the other driver. This results in no loss on the near or outside visual.
    The display device 15 thus makes it possible to display, whatever the flight phase, during a deflection of a control stick, a symbol on a screen, for example on a PFD type primary flight screen ( "Primary Flight Display". Thus, any individual or cumulative action of the pilot or pilots ensuring the flight on their respective control stick is immediately displayed on the screen and is perceived by the entire crew.
    权利要求:
    Claims (11)
    [1" id="c-fr-0001]
    1. Method for displaying at least one position indicator of at least one first control stick (2A) of an aircraft (AC), the aircraft (AC) being configured to be piloted by two pilots, a first pilot and a second pilot, the first control stick (2A) being configured so that it can be actuated by the first pilot to steer the aircraft (AC) along two steering axes, namely the roll axis (X) and the pitch axis (Y), characterized in that it comprises: an information generation step of determining, at least during a flight of the aircraft (AC), at least one value of control representative of the deflection of the first control stick (2A) relative to at least one of said flight axes (X, Y) of the aircraft (AC); ~ a calculation step of calculating at least one control command according to at least one control axis (X, Y), the control command being representative of the control value thus determined; and a display step of displaying at least one symbol said second symbol (S1B) on at least one screen said second screen (20B) intended for the second pilot and directly visible by the latter, said second symbol (S1B) representing position indicator and being displayed on the second screen (20B) at a position (P1B) illustrating on this second screen (20B) said control command.
    [2" id="c-fr-0002]
    2. Method according to claim 1, characterized in that the display step is also to display at least one symbol called first symbol (S2A) on at least one screen said first screen (20A) for the first driver and directly visible by the latter, said first symbol (S2A) representing the position indicator and being displayed on the first screen (20A) at a position (P2A) illustrating on said first screen (20A) said control command.
    [3" id="c-fr-0003]
    3. Method according to one of claims 1 and 2, characterized in that, upon actuation of the first control stick (2A) to control the aircraft (AC) simultaneously along said two control axes, each symbol ( S2A, S1B) is displayed on the screen (20A, 20B) at a position (P2A, P1B) simultaneously illustrating the two control commands along these two control axes (X, Y).
    [4" id="c-fr-0004]
    4. Method according to one of claims 1 to 3, characterized in that it comprises a step of monitoring the control of the aircraft (AC) of being able to detect an aircraft flight (AC) and a phase of manual control, and in that the display step consists in displaying said at least one position indicator (S1A, S1B, S2A, S2B) only when a flight situation of the aircraft (AC) with a phase of Manual control is detected and as long as such a situation is detected.
    [5" id="c-fr-0005]
    5. Method according to any one of the preceding claims, characterized in that the measurement, calculation and display steps are implemented, simultaneously, for the first control handle (2A) configured to be actuated by the first pilot and for a second control stick (2B) configured to be actuated by the second pilot to control the aircraft according to the two control axes (X, Y).
    [6" id="c-fr-0006]
    6. Method according to claims 2 and 5, characterized in that, on the same screen (20A, 20B), the symbol (S2A, S1 B) representing the position indicator of the first control stick (2A) and the symbol (S1A, S2B) representing the position indicator of the second control stick (2B) are differentiated visually.
    [7" id="c-fr-0007]
    7. Device for displaying at least one position indicator of at least one first control stick (2A) of an aircraft (AC), the aircraft (AC) being configured to be piloted by two pilots, a first pilot and a second pilot, the first control stick (2A) being configured so that it can be actuated by the first pilot to steer the aircraft (AC) along two steering axes, namely the roll axis (X) and the pitch axis (Y), characterized in that it comprises: at least one information generating unit (16A) configured to determine, at least during a flight of the aircraft (AC), at least one control value representative of the deflection of the first control stick (2A) relative to at least one of said control axes (X, Y) of the aircraft (AC); at least one calculation unit (17A) configured to calculate at least one control command according to at least one control axis (X, Y), the control command being representative of the control value determined by the control unit; information generation (16A); and a display unit (18) configured to display at least one so-called second symbol (SI B) on at least one second-screen screen (20B) intended for the second pilot and directly visible to the latter, said second symbol ( IF B) representing the position indicator and being displayed on the second screen (20B) at a position (PIB) illustrating on this second screen (20B) said control command.
    [8" id="c-fr-0008]
    8. Device according to claim 7, characterized in that the display unit (18) is configured to also display at least one symbol called first symbol (S2A) on at least one screen called first screen (20A) for the first pilot and directly visible by the latter, said first symbol (S2A) representing the position indicator and being displayed on the first screen (20A) at a position illustrating on said first screen (20A) said control command.
    [9" id="c-fr-0009]
    9. Device according to one of claims 7 and 8, characterized in that it comprises a monitoring unit (21) of the aircraft control (AC) configured to detect a flight of the aircraft (AC) and a manual driving phase, and in that the display unit (18) is configured to display said at least one position indicator (SIA, SI B, S2A, S2B) only when a flight situation of the An aircraft (AC) with a manual piloting phase is detected by the monitoring unit (21) and as long as such a situation is detected.
    [10" id="c-fr-0010]
    10. Device according to one of claims 7 to 9, characterized in that the measuring units, calculation and display are used simultaneously for the first control handle (2A) configured to be actuated by the first pilot and for a second control stick (2B) configured to be actuated by the second pilot to control the aircraft according to the two control axes (X, Y).
    [11" id="c-fr-0011]
    11. Control system of an aircraft, the control system (1) comprising at least two control handles (2A, 2B) configured to be actuable, each by a pilot to fly the aircraft (AC) according to the roll axis (X) and the pitch axis (Y), characterized in that it comprises a display device (15) such as that specified in any one of claims 7 to 10.
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    同族专利:
    公开号 | 公开日
    US20170021939A1|2017-01-26|
    FR3039135B1|2019-05-03|
    US9908636B2|2018-03-06|
    引用文献:
    公开号 | 申请日 | 公开日 | 申请人 | 专利标题
    EP0204598A1|1985-06-07|1986-12-10|AEROSPATIALE Société Nationale Industrielle|Control system provided with two coupled handles|
    EP0835802A1|1996-10-14|1998-04-15|Aerospatiale Societe Nationale Industrielle|Pilloting aid device for fly-by-wire aircraft|
    GB2447967A|2007-03-30|2008-10-01|Smiths Aerospace Ltd|Aircraft cockpit display panel arrangements|
    FR2643502B1|1989-02-20|1996-01-19|Aerospatiale|SWITCHING HANDLE CONTROL DEVICE, PARTICULARLY FOR AIRCRAFT, AND SYSTEM COMPRISING SUCH A DEVICE|
    US5404305A|1993-11-17|1995-04-04|United Technologies Corporation|Control of pilot control station authority for a dual piloted flight control system|
    FR2756392B1|1996-11-22|1999-01-22|Aerospatiale|CONTROL SLEEVE COUPLING SYSTEM|US10890925B2|2014-12-05|2021-01-12|Command Electronics, LLC|Vehicle leveling systems, devices and methods and computer program products for leveling vehicles using smart devices|
    WO2017195133A1|2016-05-11|2017-11-16|Bombardier Inc.|Method of and system for displaying an aircraft control input|
    US10011348B1|2017-05-02|2018-07-03|Kitty Hawk Corporation|Vertical thrust lever|
    FR3090137B1|2018-12-12|2020-11-27|Airbus Operations Sas|System and method for displaying an aircraft|
    法律状态:
    2016-07-21| PLFP| Fee payment|Year of fee payment: 2 |
    2017-01-27| PLSC| Search report ready|Effective date: 20170127 |
    2017-07-24| PLFP| Fee payment|Year of fee payment: 3 |
    2018-07-25| PLFP| Fee payment|Year of fee payment: 4 |
    2019-07-19| PLFP| Fee payment|Year of fee payment: 5 |
    2020-07-21| PLFP| Fee payment|Year of fee payment: 6 |
    2021-07-27| PLFP| Fee payment|Year of fee payment: 7 |
    优先权:
    申请号 | 申请日 | 专利标题
    FR1557048A|FR3039135B1|2015-07-24|2015-07-24|METHOD AND DEVICE FOR DISPLAYING AT LEAST ONE POSITION INDICATOR OF AN AIRCRAFT.|
    FR1557048|2015-07-24|FR1557048A| FR3039135B1|2015-07-24|2015-07-24|METHOD AND DEVICE FOR DISPLAYING AT LEAST ONE POSITION INDICATOR OF AN AIRCRAFT.|
    US15/211,616| US9908636B2|2015-07-24|2016-07-15|Method and device for displaying at least one position indicator for an aircraft|
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