• 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:
    The display system (10) for a cockpit (3) of an aircraft (1) comprises: a display computer (18) configured to control the display, on a display device (20) carried together of the head (50) of a user, according to a first display mode comprising at least a flight control information of the aircraft, and - a masking device (24), associated with a side window (6a , 6b) of the cockpit, controllable between a transparent state and an opaque state. The display system (10) includes an extended display mode, wherein the display computer is configured to: -determine whether a direction (52) corresponding to the orientation of the user's head has an intersection (Pi) with an area of interest (Zi) of the side window; in the absence of intersection, control the display according to the first display mode; and - at an intersection (Pi), controlling the opaque state of the masking device and controlling the display in a second display mode comprising a virtual display screen on a display area (Zd) of the side window.
    公开号:FR3068481A1
    申请号:FR1756020
    申请日:2017-06-29
    公开日:2019-01-04
    发明作者:Cedric DESCHEEMAEKER；Javier Manjon Sanchez
    申请人:Airbus Operations SAS；
    IPC主号:
    专利说明:

    Display system and method for an aircraft.
    The invention relates to the display of information in an aircraft cockpit. Modern aircraft, particularly transport aircraft, generally have a system for displaying pilot assist information in their cockpit. Such a system, for example of the CDS type ("Control and Display System" in English) controls the display of information on screens, known as heads down, of the cockpit. Usually, these screens are provided for displaying primary flight information of the aircraft, navigation information, etc. To allow the user to see an information display without having to lower their head to look at the screens, some aircraft are now equipped with a head-up display device, commonly called HUD for "Head Up Display" in English, and / or a device configured to be worn integral with the head of the user. Such a device is commonly called HMD for "Head Mounted Display" in English. It is sometimes also called HWD for "Head Worn Display" in English. It generally includes a display mounted integral with glasses or a helmet, so that the user can see information displayed on the display when he is wearing these glasses or helmet. In the following description, the term HMD denotes both an HMD device and an HWD device. In addition, aircraft pilots often have an EFB (“Electronic Flight Bag”) device external to the aircraft's avionics systems, allowing them to use software applications not certified by the certification authorities. aeronautics. According to a first alternative, this EFB-type device corresponds to a computer integrated into the aircraft, the display of which is generally carried out on a screen integrated in the cockpit. The integration of said screen into the cockpit is sometimes difficult because the space available in an aircraft cockpit to integrate a display screen is generally very limited. In addition, the mass of the display screen increases the mass of the aircraft. According to a second alternative, this device of the EFB type corresponds to a laptop or a tablet which the pilot can bring with him in the cockpit of the aircraft. According to a first variant, the EFB type device is then connected to a display screen integrated in the cockpit, which poses the same problems as those mentioned with reference to the first alternative. According to a second variant, the pilot directly uses a screen of the device of the EFB type. However, the screen of the EFB-type device is sometimes smaller than that of a cockpit screen, which limits user comfort, in particular for handling navigation charts. In addition, the use of the EFB type device then requires the presence in the cockpit, near the pilot, of a surface or a support making it possible to place or hang this EFB type device. The integration of such a surface or such a support in the cockpit is sometimes difficult because the space available in a cockpit, near the pilot, is generally very limited. There is therefore a need for a solution allowing the integration of an additional display in the cockpit.
    PRESENTATION OF THE INVENTION:
    The object of the present invention is in particular to provide a solution to this need. It relates to a display system of an aircraft cockpit comprising:
    - a display device configured to be worn integral with the head of a user in the cockpit of the aircraft; and
    a display computer configured to control the display on the display device according to a first display mode in which the display comprises at least information for assisting the piloting of the aircraft relating to a current situation of the aircraft.
    The system is remarkable in that it further includes:
    a masking device associated with a side window of the cockpit, the masking device being controllable between on the one hand a first so-called transparent state in which it allows the user to see the external environment of the aircraft through the side window and, on the other hand, a second so-called opaque state in which the masking device masks the vision of the external environment of the aircraft by the user through at least a predetermined masking surface of the side window; and
    a position and orientation sensor of the user's head in the cockpit, and in that the display system comprises a mode of operation known as extended display, in which the display computer is configured for :
    - acquire from the sensor, position information and orientation information for the user's head in the cockpit;
    -determine a direction corresponding to the orientation of the head of the user according to the position information and orientation of the head of the user in the cockpit;
    -determine whether the direction corresponding to the orientation of the user's head has an intersection with an area of interest including a so-called display area included in the predetermined masking surface of the side window;
    - when the direction corresponding to the orientation of the user's head does not present an intersection with the area of interest, order the display on the display device according to the first display mode; and
    - when the direction corresponding to the orientation of the user's head has an intersection with the area of interest, control the opaque state of the masking device and control the display on the display device according to a second mode display in which said display comprises a virtual display screen on the display area.
    Thus, the user such as an aircraft pilot has an additional display location on a side window of the aircraft. This additional display location is only activated when, on the one hand, the user activates the extended display mode and, on the other hand, the user directs his head so as to look towards the side window. This allows the user to maintain visibility of the external environment of the aircraft through the side window, when the extended display mode is not activated. In addition, this additional display location does not increase the weight of the aircraft. In addition, the dimensions of the display area corresponding to the additional display location are essentially limited by the dimensions of the side window. It is therefore possible to choose dimensions larger than those of the screen of an EFB type device, which improves the comfort of use.
    According to particular embodiments which can be taken into account individually or in combination:
    the display system furthermore comprises a device for activating the extended display mode, and the display calculator is configured to activate or deactivate the extended display mode according to actions of the user on the device for activating the extended display mode;
    - the display calculator (18) is configured to:
    acquire, from an avionics computer of the aircraft, current flight phase information of the aircraft; and when the current flight phase information of the aircraft corresponds to a predetermined flight phase, controlling the opaque state of the masking device when the extended display mode is activated;
    - in the second display mode, the display calculator is further configured to:
    determining a distance between a current position of the user's eyes and the display area of the side window; and controlling the display of said virtual display screen on the display device (20) with a collimation distance corresponding substantially to the distance determined between the current position of the user's eyes and the display area of the window lateral.
    - the display system is connected at the input to an EFB type device and, in the second display mode, the display on the virtual display screen corresponds to information coming from the EFB type device.
    The invention also relates to a display method in an aircraft cockpit, the aircraft comprising a display system comprising:
    - a display device configured to be worn integral with the head of a user in the cockpit of the aircraft; and
    a display computer configured to control the display on the display device according to a first display mode in which the display comprises at least information for assisting the piloting of the aircraft relating to a current situation of the aircraft.
    The method is remarkable in that the display system further comprising:
    a masking device associated with a side window of the cockpit, the masking device being controllable between on the one hand a first so-called transparent state in which it allows the user to see the external environment of the aircraft through the side window and, on the other hand, a second so-called opaque state in which the masking device masks the vision of the external environment of the aircraft by the user through at least a predetermined masking surface of the side window; and
    a sensor (16) for the position and orientation of the head of the user in the cockpit, in an operating mode known as extended display of the display system, the method comprises the following steps implemented by the display calculator:
    - acquire from the sensor, position information and orientation information for the user's head in the cockpit;
    -determine a direction corresponding to the orientation of the head of the user according to the position information and orientation of the head of the user in the cockpit;
    -determine whether the direction corresponding to the orientation of the user's head has an intersection with an area of interest including a so-called display area included in the predetermined masking surface of the side window;
    - when the direction corresponding to the orientation of the user's head does not present an intersection with the area of interest, order the display on the display device according to the first display mode; and
    - when the direction corresponding to the orientation of the user's head has an intersection with the area of interest, control the opaque state of the masking device and control the display on the display device according to a second mode display in which said display comprises a virtual display screen on the display area.
    The invention also relates to an aircraft comprising a display system as mentioned above.
    DETAILED DESCRIPTION :
    The invention will be better understood on reading the description which follows and on examining the appended figures.
    Figure 1 illustrates in a simplified manner an aircraft comprising a cockpit.
    FIG. 2 schematically illustrates an embodiment, in accordance with the invention, of a display system for a cockpit of an aircraft.
    FIGS. 3a, 3b and 3c illustrate the orientation of the head of a user of the display system, respectively in top view, in side view and in back view.
    Figure 4 illustrates an example of a typical display on an HMD display device.
    FIG. 5 illustrates, in top view, a cockpit of an aircraft equipped with a display system in accordance with an embodiment of the invention.
    Figures 6 and 7 illustrate a display, on an HMD display device, in accordance with an embodiment of the invention.
    The aircraft 1 shown in FIG. 1 comprises a cockpit 3 in a front part 4 of said aircraft. It has a longitudinal axis 5, corresponding to a roll axis of the aircraft. This longitudinal axis is substantially horizontal when the aircraft is parked on the ground. The aircraft also has a yaw axis (not shown), which is substantially vertical when the aircraft is parked on the ground. By convention, in the following description, the term horizontal designates a line or a substantially horizontal plane when the aircraft is parked on the ground, so that this line or this plane is perpendicular to the yaw axis of the aircraft. Similarly, the term vertical designates a line or a plane that is substantially vertical when the aircraft is parked on the ground, such that this line or this plane is parallel to (or contains) the yaw axis of the aircraft.
    The display system 10 shown in FIG. 2 comprises a display computer 18 comprising a processing unit (labeled PROC in the figure). This processing unit can in particular correspond to a processor or a microprocessor of the display computer. According to different embodiments, the display computer 18 is a common display computer controlling several display devices of the aircraft or even a computer dedicated to the display system 10. In a particular embodiment, this computer corresponds to a modular avionics type IMA (“Integrated Modular avionics” in English) computer which also supports functions other than display. The display system 10 further comprises a display device 20 configured to be worn integral with the head of a user in the cockpit of the aircraft. This display device corresponds to an HMD (or HWD) display device as mentioned above. It is connected to the display computer 18 by a link 19. The display computer 18 is connected to at least one avionics computer 12 of the aircraft. In the particular example shown in FIG. 2, the display computer is connected to several avionics computers 12 by a link 15 of a communication network 14 (labeled “Net” in the figure) to which these avionics computers are also connected. . The avionics computers 12 are for example located in an avionics bay 2 of the aircraft. The display system 10 also includes at least one masking device 24 (labeled “Mask” in the figure) associated with a side window 6a, 6b of the cockpit 3. This masking device is connected to the display computer 18 by a link 25. The masking device 24 can be controlled, by means of the link 25, between a first so-called transparent state in which it allows a user located in the cockpit to see the external environment of the aircraft at through the side window of the cockpit and, at least a second so-called opaque state in which this masking device masks the vision of the external environment of the aircraft by the user through at least a predetermined surface for masking the side window . In a particular embodiment, the masking device 24 corresponds to an electrochromatic or electro-optical film applied to said predetermined masking surface of the side window. It can be controlled between the first transparent state and the second opaque state by applying an electric voltage between two terminals of said electrochromatic or electrooptic film. For example, the absence of application of an electrical voltage (electrical voltage of substantially zero value) corresponds to the transparent state of the masking device on the one hand and an electrical voltage of a non-zero value (for example 10 volts) corresponds to the opaque state on the other hand. According to a first alternative, the voltage is applied to the terminals of the electrochromatic or electro-optical film directly by means of the link 25. According to a second alternative, a local controller is located near the side window. This local controller is configured to control the application of an appropriate voltage across the electrochromatic or electro-optical film as a function of instructions received from the display computer 18 by the link 25. The display system 10 further comprises a sensor 16 for orientation and position of the user's head. This sensor 16 is connected to the display computer 18 by a link 17. In a particular embodiment, the sensor 16 is mounted integral with the display device 20, as symbolized by the arrow 21 in broken lines. It then corresponds, for example, to a set of inertial sensors integrated into the display device 20. In another particular embodiment, the sensor 16 is mounted integral with the cockpit 3 of the aircraft. It then corresponds, for example, to a camera arranged so as to automatically monitor the head of the user of the display device 20. Without departing from the scope of the invention, the sensor 16 can correspond to a group of sensors, by example a user head orientation sensor and a user head position sensor. The display system also includes a device 29 (labeled “Ext” in the figure) for activating an operating mode known as extended display. This device corresponds for example to a button on the aircraft cockpit or to a man-machine interface of the cockpit, comprising a display screen as well as a keyboard and / or a pointing unit of the trackball or mouse type. This extended display mode activation device is configured to transmit information to the display computer 18 according to user actions on said extended display mode activation device. The display computer 18 is configured to activate or deactivate the extended display mode as a function of said information.
    In operation, when the extended display mode is not activated, the display computer 18 controls on the one hand the transparent state of the masking device 24 and on the other hand controls the display on the display device. HMD display 20, in the usual way, according to a first display mode in which the display comprises at least one piece of information for assisting the piloting of the aircraft relating to a current situation of the aircraft. This pilot assistance information comes from the at least one avionics computer 12 or is determined by the display computer 18 as a function of information received from the at least one avionics computer 12. An example of display of a set of information for assistance with piloting on the display device 20, according to this first display mode, is shown in FIG. 4. The display on a display 8 of the display device 20 comprises for example a aircraft reference symbol 38 (or “aircraft referenced” in English), an aircraft speed vector symbol 40 and an aircraft attitude scale 36, displayed in accordance with the environment of the aircraft. The display also includes an altitude scale 32, a speed scale 30 and an aircraft roll scale 34.
    In the example shown in FIG. 5, the cockpit of the aircraft comprises a windshield 4 comprising two front windows 7a and 7b, a left side window 6a and a right side window 6b. The user, for example an aircraft pilot, is seated in the cockpit so that his head 50 is located near the left side window 6a. The masking device 24 is associated with the left side window 6a. When the user wishes to have an additional display location on the left side window 6a, for example for the display of an EFB type device, he commands the activation of the extended display mode by means of the device 29. The display computer 18 receives the command to activate the extended display mode and it then implements the following steps repeatedly:
    - acquire from the sensor 16, position information and orientation information of the user's head in the cockpit;
    - Determine a direction 52, as illustrated in FIG. 5, corresponding to the orientation of the user's head, as a function of the position and orientation information of the user's head in the cockpit;
    -determine if the direction 52 corresponding to the orientation of the user's head has an intersection with an area of interest Zi including a so-called display area Zd included in the predetermined area for masking the side window 6a by the masking device 24;
    - when the direction 52 corresponding to the orientation of the user's head does not have an intersection with the area of interest, control the display on the display device according to the first display mode, such as illustrated by way of example in FIG. 4. Advantageously, although not necessarily, the display computer then also controls the transparent mode of the masking device 24; and
    - when the direction 52 corresponding to the orientation of the user's head has an intersection, at a point Pi, with the area of interest, control the opaque state of the masking device 24 and control the display on the display device 20 according to a second display mode in which said display comprises a virtual display screen on the display area Zd.
    Thus, when the extended display mode is activated and the user looks towards the front of the aircraft for example through the window 7a of the windshield, as illustrated in FIG. 5 by a direction 52a of the head of the user not having an intersection with the area of interest of the side window 6a, the display computer controls the display on the display device 20 according to the first display mode, as illustrated for example on FIG. 4. When the user turns his head 50 to the left, the direction 52 corresponding to the orientation of the user's head comes to intersect with the left side window 6a at a point of intersection Pi of the area of interest Zi represented in FIG. 6. The determination of the point of intersection Pi implements usual geometry calculations which are not detailed further since they are within the reach of those skilled in the art. The area of interest Zi is a predetermined area chosen so as to encompass a display area Zd. According to a first example, the area of interest Zi is defined by taking into account a right lateral margin and a left lateral margin relative to the display area Zd, as well as a high vertical margin and a low vertical margin relative to the display area Zd. The display area Zd corresponds to an area of the side window 6a intended for the display of the virtual display screen. Advantageously, the lateral and vertical margins between the display area Zd and the area of interest Zi are predefined so that the point of intersection Pi is located in the area of interest Zi when the display area Zd is located at least partially in the field of vision of the user visible through the display device 20 (which corresponds to a situation in which the virtual display screen is capable of being displayed at least in part, by the display device 20, on the display zone Zd). According to a second example, the area of interest Zi corresponds to the entire surface of the side window 6a. Thus, the direction 52 corresponding to the orientation of the head of the user has an intersection, at a point Pi, with the zone of interest Zi since said direction 52 corresponding to the orientation of the head of the user intersects the side window 6a.
    Advantageously, the display system 10 includes a memory comprising position information of the side window 6a in a reference of the cockpit. According to a first alternative, this memory is a memory of the display calculator 18. According to a second alternative, this memory corresponds to a memory or to a database 28 external to the display calculator 18 and connected to the display calculator 18 by a link 27, as shown in FIG. 2. In a first embodiment, this memory contains position information of the area of interest Zi and / or of the display area Zd. When the memory contains only position information of the display area Zd, said lateral and vertical margins are predefined in the display computer 18 and the latter calculates the area of interest Zi as a function of the area of display Zd and said margins. In a second embodiment, the memory contains information on the position of the side window 6a. The characteristics (in particular the dimensions) of the display area Zd and of the area of interest Zi are predetermined in the display computer 18. Depending on the position of the side window and said characteristics, the computer display determines the positions of the display area Zd and of the area of interest Zi. In a particular embodiment, the display computer determines these positions by considering the display zone Zd centered on the side window 6a.
    The display computer 18, which has determined the direction 52 corresponding to the orientation of the user's head, as well as the position of the area of interest Zi, can thus determine whether the direction 52 corresponding to the orientation of the user's head presents an intersection with the zone of interest Zi.
    Advantageously, in the second display mode, the display computer is further configured to determine a distance between a current position of the user's eyes and the display area Zd of the side window. According to a first alternative, the display calculator calculates this distance based on the one hand on the position of the user's head in the cockpit and on the other hand on the position of the display area Zd. According to a second alternative, the display system 10 also comprises a distance sensor associated with the display device 20. This distance sensor corresponds for example to a sensor using waves such as ultrasound or electromagnetic waves, in particular infrared type. The display computer 18 acquires a measurement supplied by said sensor and determines the distance between the current position of the user's eyes and the display area Zd as a function of the measurement supplied by the sensor. According to a third alternative, the display calculator uses a predetermined distance value as the value of the distance between the current position of the user's eyes and the display zone Zd of the side window. This distance value is for example predetermined as a function of a theoretical position of the user's head 50 in the cockpit 3 of the aircraft. The display computer 18 controls the display of the virtual display screen on the display device 20 with a collimation distance corresponding substantially to the distance determined between the current position of the user's eyes and the area d display of the side window. This allows the user to see the virtual display screen as if it were a real screen arranged on the side window 6a.
    In the particular case where the virtual display screen is used for the display of an EFB type device, the display system 10 is connected as an input to this EFB type device. For example, the display computer 18 has a video input connected to a video output of the device of the EFB type. In the second display mode, the display computer 18 controls the display on the virtual display screen, so that this display corresponds to information coming from the video output of the device of the EFB type.
    In a particular embodiment, the display computer 18 is further configured to acquire, from an avionics computer of the aircraft, current flight phase information of the aircraft. When the current flight phase information of the aircraft corresponds to a predetermined flight phase, the display computer 18 controls the opaque state of the masking device when the extended display mode is activated. The predetermined flight phase corresponds for example to a cruise flight phase. In such a flight phase, a pilot has less need to see the external environment of the aircraft through the side window 6a than during a taxiing or landing phase. Consequently, when the user activates the extended display mode, it is possible to control the opaque state of the masking device 24 associated with the side window 6a without this being penalizing for the user. This particular embodiment has the advantage of avoiding successive switching between the transparent state and the opaque state of the masking device 24 according to the orientation of the head of the user.
    The various embodiments mentioned above have been described with reference to a masking device 24 associated with the left side window 6a of the cockpit, in particular when the user is a pilot of the aircraft whose head is located near said side window. left 6a. The invention applies similarly to a masking device 24 associated with a right side window 6b of the cockpit, in particular when the user is a co-pilot of the aircraft whose head is located near said right side window 6b .
    In an advantageous embodiment, the orientation information of the user's head corresponds to at least one angle from a set of angles, as illustrated in FIGS. 3a, 3b and 3c. In these figures, the orientation of the user's head 50 is represented by a straight line 52. In an exemplary embodiment, this straight line 52 corresponds to a theoretical direction of gaze of the user when he looks in front of him without turning his eyes neither on the right nor on the left and without raising or lowering the eyes. Other definitions of the orientation of the head of the user are however possible without departing from the scope of the invention. In said advantageous embodiment, the orientation information of the user's head corresponds to at least one angle from a yaw angle ψ, a pitch angle Θ and a roll angle φ illustrated respectively in FIGS. 3a , 3b and 3c. These angles are defined in a coordinate system linked to the aircraft. Thus, the yaw angle ψ is an angle, defined in projection in a horizontal plane, between a straight line 5 'parallel to the longitudinal axis 5 of the aircraft and the straight line 52 representing the orientation of the head of the user. The pitch angle Θ is an angle, defined in projection in a vertical plane parallel to the longitudinal axis 5 of the aircraft, between a straight line 5 parallel to the longitudinal axis 5 of the aircraft and the straight line 52 representing l orientation of the user's head. The roll angle φ is an angle defined in projection in a vertical plane perpendicular to the longitudinal axis 5 of the aircraft, between a vertical straight line 566 and a yaw axis 54 of the user's head . The orientation information of the head of the user acquired by the display computer 18 corresponds to at least one of the angles ψ, Θ and φ.
    Also advantageously, the position information of the user's head corresponds to Cartesian coordinates, in an orthonormal reference frame 10, of a point located in the center of a segment connecting the two eyes of the user. In particular, a first axis of the orthonormal coordinate system is parallel to the longitudinal axis 5, a second axis of the orthonormal coordinate system is vertical and a third axis of the orthonormal coordinate system is horizontal and perpendicular to the first two axes.
    权利要求:
    Claims (7)
    [1" id="c-fr-0001]
    1- Display system (10) for a cockpit (3) of an aircraft (1), said display system comprising:
    - a display device (20) configured to be worn integral with the head (50) of a user in the cockpit of the aircraft; and
    - a display computer (18) configured to control the display on the display device (20) according to a first display mode in which the display comprises at least information for assistance in piloting the aircraft relating to a current situation of the aircraft, characterized in that it further comprises:
    - a masking device (24) associated with a side window (6a, 6b) of the cockpit, the masking device being controllable between on the one hand a first so-called transparent state in which it allows the user to see the environment exterior of the aircraft through the side window and, on the other hand, a second so-called opaque state in which the masking device masks the vision of the exterior environment of the aircraft by the user through at least one surface predetermined masking of the side window; and
    - a sensor (16) for the position and orientation of the user's head in the cockpit, and in that the display system (10) comprises an operating mode known as extended display, in which the computer display (18) is configured to:
    acquiring from the sensor (16) position information and orientation information for the head of the user in the cockpit;
    -determine a direction (52) corresponding to the orientation of the head of the user according to the position information and orientation of the head of the user in the cockpit;
    -determine if the direction (52) corresponding to the orientation of the user's head has an intersection (Pi) with an area of interest (Zi) including a so-called display area (Zd) included in the predetermined area masking the side window;
    - When the direction (52) corresponding to the orientation of the head of the user does not present an intersection with the area of interest, order the display on the display device according to the first display mode; and
    - when the direction (52) corresponding to the orientation of the user's head has an intersection (Pi) with the area of interest, control the opaque state of the masking device and control the display on the device d display (20) according to a second display mode in which said display comprises a virtual display screen on the display area (Zd).
    [2" id="c-fr-0002]
    2- System according to claim 1, characterized in that it further comprises a device (29) for activating the extended display mode, and the display computer is configured to activate or deactivate the extended display mode according to user actions on the activation device of the extended display mode.
    [3" id="c-fr-0003]
    3- System according to any one of the preceding claims, characterized in that the display computer (18) is configured for:
    - acquire, from an avionics computer of the aircraft, current flight phase information of the aircraft; and
    - when the current flight phase information of the aircraft corresponds to a predetermined flight phase, control the opaque state of the masking device when the extended display mode is activated.
    [4" id="c-fr-0004]
    4- System according to any one of the preceding claims, characterized in that, in the second display mode, the display computer is further configured for:
    -determine a distance between a current position of the user's eyes and the display area (Zd) of the side window; and
    - controlling the display of said virtual display screen on the display device (20) with a collimation distance corresponding substantially to the distance determined between the current position of the user's eyes and the display area of the window lateral.
    [5" id="c-fr-0005]
    5- System according to any one of the preceding claims, characterized in that it is connected at input to a device of the EFB type and, in the second display mode, the display on the virtual display screen corresponds to information from the EFB type device.
    [6" id="c-fr-0006]
    6- Display method for a cockpit (3) of an aircraft (1), the aircraft comprising a display system (10) comprising:
    - a display device (20) configured to be worn integral with the head (50) of a user in the cockpit of the aircraft; and
    - a display computer (18) configured to control the display on the display device (20) according to a first display mode in which the display comprises at least information for assistance in piloting the aircraft relating to a current situation of the aircraft, characterized in that, the display system (10) further comprising:
    - a masking device (24) associated with a side window (6a, 6b) of the cockpit, the masking device being controllable between on the one hand a first so-called transparent state in which it allows the user to see the environment exterior of the aircraft through the side window and, on the other hand, a second so-called opaque state in which the masking device masks the vision of the exterior environment of the aircraft by the user through at least one surface predetermined masking of the side window; and
    - a sensor (16) for position and orientation of the head of the user in the cockpit, in an operating mode known as extended display of the display system (10), the method comprises the following steps work by the display calculator (18):
    acquiring from the sensor (16) position information and orientation information for the head of the user in the cockpit;
    -determine a direction (52) corresponding to the orientation of the head of the user according to the position information and orientation of the head of the user in the cockpit;
    -determine if the direction (52) corresponding to the orientation of the user's head has an intersection (Pi) with an area of interest (Zi) including a so-called display area (Zd) included in the predetermined area masking the side window;
    5 - when the direction (52) corresponding to the orientation of the head of the user does not present an intersection with the area of interest, order the display on the display device according to the first display mode; and
    - when the direction (52) corresponding to the orientation of the head of
    10 the user presents an intersection (Pi) with the zone of interest (Zi), control the opaque state of the masking device and control the display on the display device (20) according to a second display mode wherein said display includes a virtual display screen on the display area (Zd).
    [7" id="c-fr-0007]
    7- aircraft (1) characterized in that it comprises a display system (10) according to any one of claims 1 to 5.
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    同族专利:
    公开号 | 公开日
    US20190004318A1|2019-01-03|
    FR3068481B1|2019-07-26|
    US10627630B2|2020-04-21|
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    法律状态:
    2019-01-04| PLSC| Search report ready|Effective date: 20190104 |
    2020-06-19| PLFP| Fee payment|Year of fee payment: 4 |
    2021-06-22| PLFP| Fee payment|Year of fee payment: 5 |
    优先权:
    申请号 | 申请日 | 专利标题
    FR1756020A|FR3068481B1|2017-06-29|2017-06-29|DISPLAY SYSTEM AND METHOD FOR AN AIRCRAFT|
    FR1756020|2017-06-29|FR1756020A| FR3068481B1|2017-06-29|2017-06-29|DISPLAY SYSTEM AND METHOD FOR AN AIRCRAFT|
    US16/016,918| US10627630B2|2017-06-29|2018-06-25|Display system and method for an aircraft|
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