• 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 system (10) includes a viewing surface (42) at least partially transparent to allow visualization, through the viewing surface (42), of an environment external to the aircraft, and a display management assembly. (44) on the display surface (42), comprising a generation and display module (60), on the viewing surface (42), information representative of flight parameters of the aircraft on a first region (46) at least partially transparent of the viewing surface (42). The display management assembly (44) comprises a display module (62), in a given operational state of the aircraft, of at least one pop-up window (48) on a second region (50) of the viewing surface (42), the pop-up window (48) being more opaque than the first region (46), the display management assembly (44) comprising a generation module (66) of additional information specific to the determined operational state, intended to be displayed on the popup window (48).
    公开号:FR3016448A1
    申请号:FR1400083
    申请日:2014-01-15
    公开日:2015-07-17
    发明作者:Paul Kou
    申请人:Dassault Aviation SA；
    IPC主号:
    专利说明:

    [0001] The present invention relates to an aircraft information display system, comprising: a display surface that is at least partially transparent to enable visualization, through the surface; visualization, an environment outside the aircraft; a set of display management on the viewing surface, comprising a module for generating and displaying, on the viewing surface, information representative of flight parameters of the aircraft on a first region that is at least partially transparent; of the viewing surface. Such a system is intended to be installed in particular in the cockpit of an aircraft, to facilitate the piloting of the aircraft by the crew. In modern aircraft, it is known to project on an at least partially transparent viewing surface information relating to the control of the aircraft, such as information on speed, altitude, heading, and attitude. The above information is projected for example on a head-up display formed by a transparent screen disposed opposite the head of a pilot of the aircraft, at the windshield. Alternatively, the information is projected directly on the windshield, on a helmet visor, or on a porthole or on a side window.
    [0002] The pilot of the aircraft visualizes both the environment outside the aircraft in front of him by transparency across the screen, and the relevant information relating to the piloting, without having to move his field of vision to the head-down displays of the cockpit. The driver thus retains the "real world" view in the background of the information displayed on the viewing surface. Such a system is therefore particularly useful in operations that require the pilot to focus on the external environment, for example during the take-off, approach and landing phases and more generally, during short-time tasks. . Such systems are effective when visibility is good. However, in certain circumstances of flying in high light, especially when the sun is in front, or when the sky and / or the ground floor are bright or lack of contrast, for example in urban, forest or snow, visualization of information on the transparent surface is difficult. To overcome this problem, compromises are made to avoid placing too many constraints on the display of information. These compromises result in a choice of limited colors, for example green, in a simple symbology, without too many segments, or different thicknesses, and in a limited textual content, made of acronyms and acronyms.
    [0003] The more complex and elaborate information is presented on the head-down display screens. This forces the crew to go back and forth visually with head-down displays to fetch a small amount of information punctually. These round trips are tedious, especially in certain critical phases of the piloting of the aircraft. To partially overcome the aforementioned problems, WO 2008/109231 describes a display system of the aforementioned type, able to generate distinct areas of transparency on the viewing surface. Such a system does not give complete satisfaction. Indeed, the overall decrease in the transparency of the viewing surface, to improve the contrast and therefore the visibility of the symbology removes one of the essential advantages of the head-up visualization concept, namely to have the outside world in the visual background of the symbology. In addition, the solution proposed in the aforementioned document is technically difficult to implement and economically unfavorable compared to removable sun visors, especially when the display surface increases significantly, for example in the case of a display on a full windshield. An object of the invention is therefore to provide a head-up display system, which allows the crew to have easily and quickly all the information necessary for the piloting in each operational state of the aircraft whatever the brightness and / or the type of external environment. For this purpose, the subject of the invention is a system of the aforementioned type, characterized in that the display management assembly comprises a display module, in a given operational state of the aircraft, of at least one window on a second region of the viewing surface, the popup window being more opaque than the first region, the display management assembly comprising a module for generating additional information specific to the determined operational state, intended for be displayed on the pop-up window. The system according to the invention may comprise one or more of the following characteristics, taken in isolation or in any technically possible combination: the display management assembly is able to activate the display module of the window context in the determined operational state of the aircraft and to maintain the second region of the viewing surface at least partially transparent out of the determined operational state; the display management assembly comprises an operational state detection module determined on the basis of information received from functional systems of the aircraft, the detection module being able to automatically control the activation and / or deactivation of the display module of the pop-up window according to the operational state of the detected aircraft; it comprises a set of manual control of the display module of the popup window adapted to control the activation and / or deactivation of the display module of the pop-up window on the basis of a manual control of a user of the display system; the determined operational state is chosen from an evolution phase of the aircraft, in particular a taxiing phase, a climbing phase, a cruising phase, a phase preceding the approach, an approach phase, or among a phase of malfunction of the aircraft, including an abnormality or a failure of a functional system of the aircraft; the additional information generated by the module for generating additional information is chosen from an alphanumeric text, in particular a text message, a cartography, an indication of guiding the trajectory of the aircraft, an operating status symbol of an aircraft system, in particular a deployment symbol of a wing surface and / or landing gear or a symbol representative of an engine speed; the display module is capable of displaying a totally opaque pop-up window, totally preventing visualization through the viewing surface of an environment outside the aircraft located opposite the second region of the viewing surface; the area of the or each second display region of a pop-up window is less than 50%, especially less than 10% of the area of the viewing surface; the or each second display region of a pop-up window is located at the periphery of the viewing surface; the display management assembly comprises a set of adjustment of the opacity of the popup window; it comprises an element defining the viewing surface, the element being chosen from a transparent head-up screen, a helmet visor, a windshield pane, a side window, a window; - The transmission through the popup window more opaque than the first region is less than 50%, especially less than 20%, preferably less than 5%. The invention also relates to a method for displaying information in an aircraft, comprising the following steps: providing a system as described above; displaying information representative of parameters of the aircraft on a first at least partially transparent region of the viewing surface by the display management assembly; in a given operational state of the aircraft, activating the generating module of a pop-up window to display at least one pop-up window on a second region of the viewing surface, the pop-up window being more opaque than the first region; activating the module for generating additional information specific to the determined operational state, and displaying additional specific information on the popup window. The method according to the invention may comprise one or more of the following characteristics, taken separately or in any technically possible combination: it comprises a step of automatically controlling the activation and / or deactivation of the module; display of the pop-up window according to the operational state of the detected aircraft; it comprises a step of manual control, by the user of the display system, of the display module of the popup window to control the activation and / or deactivation of the display module of the popup window. The invention will be better understood on reading the description which will follow, given solely by way of example, and with reference to the appended drawings, in which: FIG. 1 is a schematic view of the cockpit of an aircraft comprising a first display system according to the invention; FIG. 2 is a schematic view of the first display system according to the invention; FIG. 3 is a view of a viewing surface of the first display system according to the invention, in a first operational state of the aircraft; FIG. 4 is a view similar to FIG. 3, in a second operational state of the aircraft; FIG. 5 is a view similar to FIG. 3, in a third operational state of the aircraft; - Figure 6 is a view similar to Figure 3, in a fourth operational state of the aircraft.
    [0004] A first display system 10 according to the invention is illustrated in FIG. 1. This system 10 is intended to be placed in the cockpit 12 of an aircraft, in order to allow the crew of the aircraft to fly the aircraft. aircraft, manage its navigation, monitor and control the various functional systems present in the aircraft. The aircraft is provided with an avionics central control unit 14. The unit 14 is connected to measurement sensor systems 16 on the aircraft, to external communication systems 18, and to systems 20 actuation of the controls of the aircraft. The measurement systems 16 comprise, for example, sensors for measuring parameters outside the aircraft such as temperature, pressure or speed, sensors for measuring parameters internal to the aircraft and its various functional systems, and positioning sensors, such as GPS sensors, inertial units, and / or an altimeter. The positioning sensors are capable of providing information on the geographical position of the aircraft, on its speed, heading and attitude (longitudinal attitude, roll angle). Outdoor communication systems 18 include, for example, VOR / LOC radio systems, ADS, DME, ILS, NLS, and / or radar systems. The control systems 20 include, on the one hand, various actuators capable of actuating aircraft controls, such as flaps, control surfaces, pumps, or else mechanical, electrical and / or hydraulic circuits, and on the other hand various software actuators suitable for configuring the avionic states of the aircraft. The different systems 16, 18 and 20 are connected to the central control unit 14, for example digitally, by at least one data bus traveling on a network internal to the aircraft.
    [0005] The cockpit 12 includes a dashboard 22 provided with a plurality of base screens 24A to 24D forming head-down displays. In a known manner, the basic screens 24A and 24C are, for example, primary display screens intended for displaying flight parameters of the aircraft. The basic screens 24B and 24D are, for example, multifunctional navigation and / or monitoring and control screens for avionics systems.
    [0006] The dashboard 22 is provided with a display management assembly (not shown) able to display the different windows present on these screens 24A to 24D. The central unit 14 comprises at least one computer 30 and a memory 32 able to receive the information from the various systems 16, 18, 20 and to process them, and possibly to control the systems 20 to execute flight commands. As illustrated in FIG. 1, the display system 10 comprises a head-up display 40 defining a viewing surface 42 that is at least partially transparent. With reference to FIG. 2, the display system 10 further comprises a display management assembly 44 on the viewing surface 42, able to display information representative of flight parameters of the aircraft on a first region 46. at least partially transparent of the viewing surface 42. According to the invention, the display management unit 44 is also clean, in at least one operational state of the aircraft, to display a pop-up window 48 on at least one second region 50 of the viewing surface 42, the pop-up window 48 being more opaque than the first region 46, and having complementary information associated with the determined operational state. Advantageously, the display system 10 further comprises a set 52 for manually controlling the display of each pop-up window 50, suitable for being controlled by a user of the system 10, in particular a member of the crew of the aircraft, and optionally a set 54 for adjusting the opacity of each pop-up window 48. In this example, the head-up display 40 is formed by an at least partially transparent screen, arranged facing the front windshield of the aircraft, above the dashboard 22. The screen is formed for example by a plate of semi-transparent material. The head-up display 40 is intended to be placed opposite the eyes of a user of the display system 10 sitting in front of the dashboard 22. By "at least partially transparent", it is understood that a lens human is able to visualize through the screen and the viewing surface 42, an environment outside the aircraft, located opposite the viewing surface 42 relative to the eye. The transparency of a surface is generally characterized by a dimensionless quantity called "transmission", which is advantageously defined by the ratio between the light energy at the output of a medium considered and the light energy at the input of this same medium.
    [0007] In all that follows, the spectral range considered is that of visible light, generally between 350 nm and 800 nm. In the context of the invention, a zone is described as "at least partially transparent" if its transmission is greater than 50%, in particular is greater than 90%. Alternatively, the head-up display 40 is formed directly by a windshield pane, a helmet visor, a side window, or a window of the aircraft. The display surface 42 of the display is able to be controlled in transparency, to pass at least one region of the surface between an at least partially transparent state and a more opaque state than the at least partially transparent state and advantageously totally opaque. In the "more opaque" state, the transmission is less than 50%, generally 20%, advantageously less than 5%. Advantageously, the viewing surface 42 comprises at least one active layer of material with controlled electrochromic properties and, associated with this active layer, one or more network electrode layers. The geographical distribution of the electrodes on the viewing surface allows the local control of the absorption and / or reflectivity of the electrochromic materials of the active layer to obtain the level of spectral transmission, and thus the level of transparency or transparency. desired opacity. The display management assembly 44 comprises a module 60 for generating and displaying information representative of flight parameters of the aircraft on the first region 46 of the viewing surface 42, and a display module 62 in at least one determined operational state of the aircraft, a pop-up window 48 on at least a second region 50 of the viewing surface 42. The display management assembly 44 further comprises a generation module 64 additional information specific to the determined operational state, suitable for being displayed on the popup window 48. The display management unit 44 advantageously comprises a module 66 for detecting the determined operational state, on the basis of information received from functional systems 16, 18, 20 of the aircraft, the detection module 66 being adapted to automatically control the activation and / or deactivation of the display module 62 of the window be context 48 based on the detected operational state. The display management assembly 44 preferably comprises a computer and a memory containing in software form each of the modules 60 to 66. It furthermore comprises a display device, for example a device for direct projection or rear projection on the viewing surface 42, connected to the computer, for causing the display of the information representative of the flight parameters and additional information, respectively on the first region 46 and on each pop-up window 48.
    [0008] The display management assembly 44 is connected to each of the systems 16, 18, 20 to collect in real time information from these systems 16, 18, 20. The generation and display module 60 is able to generate symbols representative of flight parameters, based notably on the information received from each of the systems 16, 18, 20, and to display them on the first region 46.
    [0009] The generation and display module 60 is for example suitable for displaying alphanumeric information, or analog information such as scales. These symbols are for example representative of at least one of the following parameters: altitude indicator, horizontal situation indicator, air speed, altitude, vertical speed, corrected air speed, engine information, aircraft lift conformation, etc. In the example shown in FIG. 3, the generation and display module 60 is able to generate and display on the first region 46 of the viewing surface 42, a speed scale 70, an altitude scale 72 , a symbol 74 or mock representative of the position of the aircraft and its longitudinal attitude, a longitudinal attitude scale 76, a zero longitudinal attitude indicator 78, and a heading indicator 80. The display module 62 each pop-up window 48 is adapted to be controlled between a deactivated state of rest, in which the second region 50 associated with the pop-up window 48 is at least partially transparent, with a transparency identical to that of the first region 46, and a state activated display of the pop-up window 48, wherein the second region 50 associated with the pop-up window 48 is more opaque than the first region 46. The display module 62 is pro pre pilot the local opacity of the second region 50 associated with each pop-up window 48 to go from the disabled state to the activated state. In particular, in the case where the viewing surface 42 is formed by at least one layer of material with controlled electrochromic properties, and by at least one network electrode layer, the display module 62 is able to control the electrodes of the electrode layer for adjusting the absorption and / or the reflectivity of the electrochromic material in each second region 50 between an at least partially transparent state and a more opaque state than the at least partially transparent state, advantageously totally opaque . Advantageously, in the activated state, the pop-up window 48 is completely opaque. By "totally opaque" is meant in particular that a human eye is unfit to visualize through the screen and the viewing surface 42, an environment outside the aircraft, located opposite the second region 50 relative to at the eye. In the example shown in FIGS. 3 to 6, the area of each second display region 50 of each pop-up window 48 is less than 50%, especially less than 10% of the total area of the viewing surface 42 .
    [0010] In addition, the or each second display region 50 of a pop-up window 48 is located at the periphery of the viewing surface 42, preferably at a minimum distance from the center of the viewing surface 42 representing more than 30% of the viewing area. maximum distance between the center of the viewing surface 42 and the contour of the viewing surface 42.
    [0011] The transition between the deactivated state and the activated state of the display module 62 is able to be controlled automatically on detecting the passage in the operational state determined by the detection module 66, or manually by a user's action on the manual control assembly 52. The module 64 for generating additional information specific to the determined operational state is able to generate the information to be displayed in each pop-up window 48 of each second region 50 in the determined operational state. . This information is specific to the given operational state. The additional information is for example chosen from an alphanumeric text (see FIG. 3), a map (see FIG. 4), an operating state symbol of a system of the aircraft (see FIG. 5 or FIG. 6). An example of alphanumeric text that can be displayed as complementary information is a text message, in particular based on CPDLC technology. This message is for example representative of a flight level and / or a descent rate to be reached by the aircraft, as authorized by the air traffic control. He can understand the definition of a constraint in time, in speed, etc. The cartography is for example representative of the topography of an aerodrome on which the aircraft rolls. It comprises for example topographical indications on the position of the taxiways, and runways of takeoff and / or landing of the aircraft. The representation is for example a broader overview of the exocentric type to better situate the aircraft on the aerodrome and for example anticipate or locate with respect to intersections that are not yet in the visible field. Thus, the displayed cartography is able to offer a wider field than that perceived by the human eye through the viewing surface 42.
    [0012] Examples of operating system status symbols of the aircraft are for example visualization symbols of the position or state of a system of the aircraft, such as the position of the beaks and flaps, or landing gear. In a variant, the symbols are representative of a driving state, for example are formed by a motor speed scale, for example a "N1" type scale.
    [0013] The additional information generated by the generation module 64 is displayed by the display device of the display management unit 44, or alternatively by a display device specific to the generation module 64. The detection module 66 is connected to the functional systems 16, 18, 20 of the aircraft 12. It is able to detect the occurrence of a determined operational state of the aircraft 12, on the basis of information received from each functional system 16, 18, 20 and activate the display module 62 and the generation module 64, when the determined operational state is detected. The determined operational state is for example a specific flight phase, in particular an ascent phase, a cruise phase, a phase preceding an approach, an approach phase, and a taxiing phase. As a variant, the determined operational state is, for example, a phase involving an evolution of a functional system of the aircraft, such as a movement of a mobile element of the aircraft, in particular a nose or a nose. shutter, or landing gear. In another variant, the determined operational state is an anomaly or a fault generating a system event, such as an anomaly or a failure on an engine of the aircraft. The control assembly 52 comprises for example a tangible physical control in the cockpit 12 of the aircraft, such as a button, a lever, a touch surface. As a variant, the control unit 52 comprises a graphic software command, notably driven by a cursor, or a remote control, for example a voice command, a command by detecting the position of the gaze of an occupant of the aircraft, a command by detection of a gesture. A first example of information display method according to the invention, implemented using the system 10, will now be described, with reference to FIG.
    [0014] Initially, during a cruise phase of the aircraft 12, the generation and display module 60 continuously generates and displays information representative of flight parameters of the aircraft on a first region 46 of the viewing surface. 42. In the example shown in FIG. 3, as specified above, this information comprises a speed scale 70, an altitude scale 72, a symbol 74 or model representative of the position of the aircraft and its attitude. longitudinal, a longitudinal attitude scale 76, a zero longitudinal attitude indicator 78, and a heading indicator 80. This information is displayed continuously, even when the display module 62 of the pop-up windows is deactivated.
    [0015] The display module 62 of the pop-up windows 48 occupies its deactivated state. The second regions 50 are then at least as transparent as the first region 46. The user is able to observe through the viewing surface 42 the environment outside the aircraft, located opposite the viewing surface 42 , and in superposition, the information representative of the flight parameters. When the detection module 66 detects a flight phase preceding the approach and the landing, on the basis of the information received in particular from the measurement systems 16, or on manual control of the crew via the set of command 52, the detection module 46 automatically activates the display module 62 of a pop-up window 48 to make it go into the activated state. The display module 62 opacifies at least partially, and advantageously completely, a second region 50 of the viewing surface 42, located in this example in the right corner at the top of the viewing surface 42. The generation module 64 is also activated. by the detection module 66.
    [0016] When the measurement systems 16 receive a text message from the air traffic control, in particular to indicate a planned flight level, a time constraint and / or a speed of descent constraint, the generation module 64 generates an alphanumeric text translating the message. text. This alphanumeric text is for example of the type "descend to flight level N1 to N2 feet per minute minimum." When the crew wishes, or on a system event, for example near the expiration of a time constraint, the display management unit 44 displays the relevant text message in the popup window 48. The crew therefore has the relevant additional information associated with the operational state of the aircraft without having to display this information on a head-down display. The information is directly accessible on the viewing surface 42, which allows the pilot to maintain a relatively short-term horizon for the implementation of the tasks associated with his descent plan. No visual round-trip with 24A to 24D head-down displays is required to collect or recall this information.
    [0017] When the operational state is no longer detected by the module 66, or on command of the crew, the display module 62 is deactivated. This causes the disappearance of the pop-up window 48 and the at least partial transparency of the second region 50. Thus, the transparency of the viewing surface 42 is not obscured more than is necessary.
    [0018] As a variant, such a popup window 48 displaying alphanumeric text is displayed during other flight phases, in operational states such as ascent, cruising, approach, or taxiing. The presence of a popup window 48 more opaque than the first region 46 or totally opaque allows to display enriched textual content, possibly in color with a satisfactory contrast for the user regardless of the brightness and / or the type of environment outside. A second example of a display method according to the invention will now be described, with reference to FIG. 4. This display method is implemented during a taxiing phase on an aerodrome. When the detection module 66 detects the operational state constituted by a taxi on the aerodrome, it activates the display module 62 to display on a second region 50 of the viewing surface, a popup window 48, which in this example is located substantially down and to the right of the viewing surface 42.
    [0019] The generation module 64 is also activated to generate a map 100 representative of the topography of the aerodrome including a representation of the taxiways of the aircraft and the landing and / or take-off runways, and possibly guidance indications. 102 of the flight path of the aircraft, such as arrows, representative of the required ground route from the controller.
    [0020] The guidance indication 102 is for example in the form of a symbology providing the crew with information relating to a need to bend the aircraft trajectory in its direction or in its speed. Preferably, the cartography presents a larger overview, of exocentric type, to better situate the aircraft on the aerodrome and to anticipate how to place with respect to the intersections that are not yet in the visible field through the aerodrome. viewing surface 42.
    [0021] The display management unit 44 then displays the map on the popup window 48, in particular on the basis of a system event, such as the proximity of an intersection. The cartography displayed in the popup window 48 provides a wider field than that perceived by the crew view. This provides enriched elements to feed the perception of the situation by the crew in this phase of taxiing, especially in the vicinity of intersections, without having to look for information on a head-down screen. As before, when the operational state is no longer detected by the module 66, or on command of the crew, the display module 62 is deactivated, which causes the disappearance of the pop-up window 48 and the re-transparency at least partial of the second region 50. In addition, the guidance indication 102, when present, allows the crew to anticipate a change of trajectory to come, without having to go back and forth visually . A third example of a display method according to the invention is illustrated in FIG. 5. When the detection module 66 detects an operational state constituted by a final approach phase, it activates the display module 62 to display, on the viewing surface 42, a first contextual window 48 representative of the position of the spouts and flaps (bottom left in FIG. 5) and a second contextual window 48 representative of the position of the landing gear (lower right on Figure 5). The generation module 64 then generates a graphical representation 110 of the state of the spouts and flaps, in particular illustrating the exit of the spout, and the inclination of the shutters for its display on the first popup window 48. It generates a graphical representation 112 of the state of exit of each landing gear, shown, for each landing gear by a downwardly directed arrow 114, of green color when the associated train is well out. The display management unit 44 then displays the graphical representations mentioned above respectively on the first window 48 and on the second window 48. The crew is then able to monitor the smooth running and the smooth operation of the deployment of the moving elements, without have to refer to a head-down display 24A to 24D. This differs from the usual head-up visualizations, which have a stripped symbiosis, thanks to enriched complementary information available to the crew in a colorful and graphically rich manner, thanks to the at least partial opacity of the popup window 48. verification of the deployment carried out, the detection module 66 or the crew is able to hide the windows 48, which can be displayed again in case of subsequent anomalies. A fourth example of a display method according to the invention is illustrated in FIG. 6. When the detection module 66 detects an operational state constituted by an anomaly on the aircraft system, such as a motor, or when a particular procedure relating to the system, the detection module 66 here displays two adjacent contextual windows 48 each presenting additional information representative of the state of a particular engine of the aircraft. The generation module 94 then generates a symbol 130 representative of this engine state, for example a pointer, a marker, a dial, a circular arc, an encrypted value, a colored value which illustrates the engine speed. For example, the representative information is a so-called "N1" scale, associated with an exact value of this parameter. The pilot is then able to visualize this value, for each engine, which allows it not to exceed or not to fall below a chosen setpoint, without having to refer frequently to a head-down display 24A to 24D. As before, when the operational state is no longer detected by the module 66, or on command of the crew, the display module 62 is deactivated, which causes the disappearance of the pop-up window 48 and the re-transparency at least partial of the second region 50.
    [0022] Thus, the crew of the aircraft punctually has a better awareness of the operational situation, having access to graphically complex symbols or presenting rich texts, without having to look down at head-down displays. The presence of a pop-up window 48, in which the contrast constraint is relaxed, offers the advantage of having a black background guaranteeing legibility on any type of background, the possibility of introducing colored symbols, complex with a rich cognitive content, or to introduce textual information in complete and readable form without acronyms or abbreviations likely to cause errors of interpretation or to solicit an important memory effort on the part of the user.
    [0023] Since the pop-up window 48 is temporarily displayed, and on a small area, the transparency and conformance qualities to the outside world of the viewing surface 42 are preserved, which is essential for efficiently performing the short-term tasks. The crew remains available "head-up" by minimizing the use of low head visualizations, while having access to additional information that is sought in the current operational state of the aircraft. Furthermore, the viewing surfaces 42 are relatively simple to manufacture and are economical, since the surface to be opacified to display each window 48 is small. In a variant, the additional information generated by the generation module 64 and displayed on the window 48 contains one or more video sources. In another variant, each window 48 is advantageously divided functionally and / or in its surface. In another variant, the specific additional information is able to be displayed without projection on the viewing surface 42 by modifying the opacity and the local color of this surface 42. In particular, in the case where the opacity of the viewing surface 42 is controlled, it is possible to divide at least a portion of the viewing surface 42 to form the regions 50 in pixels, then to control the level of spectral transmission of each pixel, as well as the color of each pixel .
    [0024] This makes it possible to create a contrast in each second region 50, when the second region 50 is opaque to display the pop-up window 48, between the pixels intended to form the bottom of the window 48 and the pixels intended to display the complementary information generated by the 64.25 generation module
    权利要求:
    Claims (15)
    [0001]
    Aircraft information display system (10), comprising: - a viewing surface (42) at least partially transparent to allow viewing, through the viewing surface (42), an environment outside the aircraft; a display management assembly (44) on the display surface (42), comprising a generation and display module (60), on the viewing surface (42), information representative of flight parameters; the aircraft on a first (46) at least partially transparent region of the viewing surface (42); characterized in that the display management assembly (44) comprises a display module (62), in a given operational state of the aircraft, of at least one popup window (48) on a second region ( 50) of the viewing surface (42), the pop-up window (48) being more opaque than the first region (46), the display management assembly (44) having a data generation module (66) additional specific to the determined operational state, to be displayed on the popup window (48).
    [0002]
    2. - System (10) according to claim 1, characterized in that the display management assembly (44) is adapted to activate the display module (62) of the popup window (48) in the state determined operational condition of the aircraft and to maintain the second region (50) of the viewing surface (42) at least partially transparent out of the determined operational state.
    [0003]
    3. - System (10) according to any one of claims 1 or 2, characterized in that the display management assembly (44) comprises a detection module (66) of the operational state determined on the basis information received from functional systems (16; 18; 20) of the aircraft, the detection module (66) being adapted to automatically control the activation and / or deactivation of the display module (62) of the window contextual (48) depending on the operational state of the detected aircraft.
    [0004]
    4. - System (10) according to any one of claims 1 to 3, characterized in that it comprises a set (52) of manual control of the display module (62) of the pop-up window (48) specific to controlling the activation and / or deactivation of the display module (62) of the pop-up window (48) on the basis of manual control of a user of the display system (10).
    [0005]
    5. - System (10) according to any one of the preceding claims, characterized in that the determined operational state is chosen from a phase of evolution of the aircraft, in particular a taxiing phase, a climbing phase , a cruise phase, a phase preceding the approach, an approach phase, or among a phase of malfunction of the aircraft, including an anomaly or a failure of a functional system of the aircraft.
    [0006]
    6. - System (10) according to any one of the preceding claims, characterized in that the additional information generated by the generation module (66) of additional information is chosen from an alphanumeric text, including a text message, a map , an indication of guidance of the trajectory of the aircraft, a symbol of the operating state of a system of the aircraft, in particular a symbol for deploying a wing surface and / or a landing gear or a representative symbol of a engine speed.
    [0007]
    7. - System (10) according to any one of the preceding claims, characterized in that the display module (62) is adapted to display a totally opaque pop-up window (48), totally preventing the visualization through the surface of viewing (42) an environment outside the aircraft located opposite the second region (50) of the viewing surface (42).
    [0008]
    8. - System (10) according to any one of the preceding claims, characterized in that the area of the or each second region (50) for displaying a pop-up window (48) is less than 50%, in particular less than 10% of the area of the viewing surface (42).
    [0009]
    9. - System (10) according to any one of the preceding claims, characterized in that the or each second region (50) for displaying a pop-up window (48) is located at the periphery of the viewing surface ( 42).
    [0010]
    10. - System (10) according to any one of the preceding claims, characterized in that the display management assembly (44) comprises a set (54) for adjusting the opacity of the popup window (48). .
    [0011]
    11. - System (10) according to any one of the preceding claims, characterized in that it comprises a member (40) defining the viewing surface (42), the element being selected from a transparent head-up screen, a helmet visor, windshield pane, side window, porthole.
    [0012]
    12. - System (10) according to any one of the preceding claims, characterized in that the transmission through the contextual window (48) more opaque than the first region (46) is less than 50%, especially less than 20% preferably less than 5%.
    [0013]
    13. - Method of displaying information in an aircraft, comprising the following steps: providing a system (10) according to any one of the preceding claims; displaying information representative of parameters of the aircraft on a first region (46) at least partially transparent of the viewing surface (42) by the display management assembly (44); in a determined operational state of the aircraft, activating the generating module of a pop-up window (48) to display at least one pop-up window (48) on a second region (50) of the viewing surface (42), the pop-up window (48) being more opaque than the first region (46), - activating the generating module (66) with additional information specific to the determined operational state, and displaying additional specific information on the popup window (48). ).
    [0014]
    14. - Method according to claim 13, characterized in that it comprises a step of automatically controlling the activation and / or deactivation of the display module of the popup window (48) according to the operational state of the detected aircraft.
    [0015]
    15. - Method according to one of claims 13 or 14, characterized in that it comprises a step of manual control, by the user of the display system, the display module (62) of the popup window ( 48) for controlling the activation and / or deactivation of the display module (62) of the pop-up window (48).
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    同族专利:
    公开号 | 公开日
    FR3016448B1|2017-05-26|
    引用文献:
    公开号 | 申请日 | 公开日 | 申请人 | 专利标题
    US20020044152A1|2000-10-16|2002-04-18|Abbott Kenneth H.|Dynamic integration of computer generated and real world images|
    WO2008109231A2|2007-03-05|2008-09-12|The Boeing Company|Electrically dimmable combiner optics for head-up display|
    FR2922323A1|2007-10-12|2009-04-17|Airbus France Sas|CROSS-MONITORING DEVICE FOR HIGH HEAD DISPLAYS|
    US20100113149A1|2008-10-31|2010-05-06|Honeywell International Inc.|Methods and systems for displaying sensor-based images of an external environment|WO2018193447A1|2017-04-20|2018-10-25|Elbit Systems Ltd.|Helicopter head-mounted see-through displays|
    FR3066619A1|2017-05-17|2018-11-23|Airbus Operations |AIRCRAFT DISPLAY SYSTEM|
    FR3098932A1|2019-07-15|2021-01-22|Airbus Helicopters|Method and system for assisting the piloting of an aircraft by adaptive display on a screen|
    FR3098900A1|2019-07-15|2021-01-22|Airbus Helicopters|Method and system for assisting the piloting of an aircraft by adaptive display on a screen|
    法律状态:
    2015-12-15| PLFP| Fee payment|Year of fee payment: 3 |
    2016-12-19| PLFP| Fee payment|Year of fee payment: 4 |
    2017-12-22| PLFP| Fee payment|Year of fee payment: 5 |
    2019-12-12| PLFP| Fee payment|Year of fee payment: 7 |
    2020-12-30| PLFP| Fee payment|Year of fee payment: 8 |
    2021-12-10| PLFP| Fee payment|Year of fee payment: 9 |
    优先权:
    申请号 | 申请日 | 专利标题
    FR1400083A|FR3016448B1|2014-01-15|2014-01-15|AIRCRAFT INFORMATION DISPLAY SYSTEM AND ASSOCIATED METHOD|FR1400083A| FR3016448B1|2014-01-15|2014-01-15|AIRCRAFT INFORMATION DISPLAY SYSTEM AND ASSOCIATED METHOD|
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