Electronic information display system for piloting an aircraft, with peripheral light strip(s), associated aircraft

Abstract

Electronic aircraft piloting information display system, with peripheral light strip(s), associated aircraft This electronic aircraft piloting information display system (10) comprises an assembly (24) of electronic screen(s) (26) forming an information display surface (S); a peripheral light strip (28) arranged around at least a portion of a periphery of the display surface (S), the light strip (28) comprising a plurality of light sources; and a control device (30) configured to control at least one group of light source(s) of said strip (28).The control device (30) comprises a plurality of distinct control logics (52A, 52B, 52C, 52D) for at least one group corresponding to a plurality of distinct control aids, each control logic (52A, 52B, 52C, 52D) corresponding to a respective control aid, and the control device (30) is configured to control at least one group of light source(s) according to at least one of the plurality of control logics (52A, 52B, 52C, 52D). See Figure 2 for abbreviations.

Description

Title of the invention: Electronic information display system for piloting an aircraft, with peripheral light strip(s), associated aircraft

[0001] The present invention relates to an electronic information display system for piloting an aircraft.

[0002] The invention also relates to an aircraft comprising such an electronic display system.

[0003] The invention relates to the field of assistance in piloting an aircraft, such as an airplane, a helicopter, or even a drone.

[0004] The on-board systems of aircraft, piloted or remotely piloted, interact with humans through increasingly complex human-machine interfaces, also called HMIs.

[0005] The major challenge for humans, in particular the aircraft pilot, remains the understanding of the operational situation (awareness) provided by these HMIs and the ability to control and command the systems safely, without error, via these same HMIs.

[0006] Many developments have led to an increasingly high-level definition for the definition of HMIs, with humans acting more and more as a global supervisor, and controlling less and less directly the low-level parameters of each system.

[0007] The introduction of the open world (non-critical but optimized on-board systems), often based on artificial intelligence, in the same cockpit environment as critical on-board systems brings to light new sources of errors and data reliability issues, which must be properly understood by crews.

[0008] Document FR 3 083 524 A1 discloses an immersive attitude display system comprising a set of light sources distributed at predefined positions in a cockpit of an aircraft. Real-time values ​​of pitch and roll angles represent the attitude of the aircraft and define a virtual attitude plane in the cockpit relative to a reference point in the cockpit. A control system orders the illumination of each light source with a respective color, any light source located above the virtual attitude plane being controlled to be illuminated with a first color and any light source located below the virtual attitude plane being controlled to be illuminated with a second color distinct from the first color. The pilot of the aircraft is immersed in the display of the attitude of the aircraft, which makes it possible to avoid loss of bearings. spatial.

[0009] However, the assistance provided to the pilot by such a display system only concerns the attitude of the aircraft.

[0010] The aim of the invention is then to propose an electronic information display system making it possible to provide greater assistance for piloting the aircraft, and thus to increase the safety of the flight of the aircraft by reducing the risk of an incident.

[0011] To this end, the invention relates to an electronic information display system for piloting an aircraft, comprising:

[0012] - a set of electronic screen(s) forming a display surface of information;

[0013] - a peripheral light strip arranged around at least part of a around the display surface, the light strip comprising a plurality of light sources; and

[0014] - a control device configured to control at least one group of light source(s) of the light strip,

[0015] the control device comprising a plurality of distinct logics for controlling the at least one group corresponding to a plurality of distinct piloting aids, each control logic corresponding to a respective piloting aid, and the control device is configured to control the at least one group of light source(s) according to at least one of the plurality of control logics.

[0016] According to other advantageous aspects of the invention, the electronic display system comprises one or more of the following characteristics, taken individually or in all technically possible combinations:

[0017] - the control device is configured to control several groups distinct light source(s) corresponding to several distinct portions of the light strip, each group being controlled according to a respective logic among the plurality of control logics.

[0018] the control device preferably being configured to simultaneously control said distinct groups of light source(s).

[0019] - the control device is configured to control the at least one group of light source(s) with a respective illumination mode for each control logic, the illumination modes associated with the control logics being distinct from each other and varying from one control logic to another;

[0020] - each illumination modality is distinct from the other modalities by a color respective ignition of the group of light source(s) and / or by a mode respective ignition of the group of light source(s);

[0021] - each ignition color is associated with a criticality level;

[0022] each lighting color being preferably chosen from the group consisting of: a first level color, called nominal; a second level color, called informative; a third level color, called caution color; and a fourth level color, called alert color;

[0023] - each ignition mode is chosen from the group consisting of: a fixed mode, a flashing mode, a slow pulse mode, and a chase mode;

[0024] - the aircraft comprises a communication installation compartmentalized in a avionics domain and an open domain external to the avionics domain; and the plurality of distinct control logics comprises first, second, third and fourth control logics;

[0025] the first control logic being the control of light source(s) of a portion of the light strip corresponding to the appearance of an aeronautical event, the light source(s) of said portion being switched on when the event is detected, then switched off when said event disappears;

[0026] the second control logic being the control of light source(s) of a portion of the light strip arranged around an area of ​​the display surface associated with a transfer of data between the open domain and the avionics domain, preferably from the open domain to the avionics domain, the light source(s) of said portion being temporarily lit during said data transfer;

[0027] the third control logic being the control of light source(s) of a portion of the light strip arranged around an area of ​​the display surface on which a new request is displayed for a user of the aircraft, the light source(s) of said portion being temporarily lit during the display of the new request;

[0028] the fourth control logic being the control of light source(s) of a portion of the light strip arranged around an area of ​​the display surface on which a set of information(s) is displayed according to a first illumination mode if the set of information(s) belongs to the avionics domain and according to a second illumination mode if the set of information(s) belongs to the open domain, the second illumination mode being distinct from the first illumination mode;

[0029] - according to the first control logic, if the aeronautical event is a external event to the aircraft, then the controlled portion of the light strip is a portion oriented in the direction of said external event; and

[0030] if the aeronautical event is an internal anomaly in the aircraft, displayed on a respective area of ​​the display surface, then the controlled portion of the light strip is a portion arranged around said area on which the anomaly is displayed;

[0031] - each of the light sources of the light strip is arranged at less than 10 cm, and preferably less than 5 cm, from the perimeter of the display surface.

[0032] The invention also relates to an aircraft comprising an electronic information display system for piloting the aircraft and a communication installation compartmentalized into an avionics domain and an open domain external to the avionics domain, the communication installation comprising several avionics systems belonging to the avionics domain, one or more electronic devices belonging to the open domain, the display system being as defined above.

[0033] According to other advantageous aspects of the invention, the aircraft comprises one or more of the following characteristics, taken individually or in all technically possible combinations:

[0034] - the avionics domain is a domain corresponding to a level of security as high as raised on board the aircraft;

[0035] the avionics domain preferably being the ACD domain according to the ARINC 811 standard of December 20, 2005; and

[0036] - the aircraft further comprises a pedestal equipped with at least one member of flight control, and the electronic display system further comprises an additional light strip disposed around at least a portion of an edge of the pedestal, the additional light strip comprising a plurality of additional light sources, and the control device being configured to further control at least one group of additional light source(s) of the additional light strip.

[0037] These characteristics and advantages of the invention will appear more clearly on reading the description which follows, given solely by way of non-limiting example, and made with reference to the appended drawings, in which:

[0038] [Fig-1] [Fig.l] is a schematic representation of an aircraft according to the invention comprising an electronic information display system for piloting the aircraft and a communication installation compartmentalized into an avionics domain and an open domain external to the avionics domain;

[0039] [Fig.2] [Fig.2] is a three-dimensional schematic view of the display system of [Fig.l], as well as a central pedestal equipped with a first flight control member and side pedestals each equipped with a second flight control member, these pedestals being included in the aircraft of [Fig.l], the display system comprising a set of electronic screens forming a display surface and a light strip arranged around the display surface and comprising a plurality of light sources; and

[0040] [Fig.3] [Fig.3] is a schematic representation of different views of the system display according to different logics for controlling light sources of the light strip.

[0041] The expressions “substantially equal to” and “of the order of” define a relationship of equality to plus or minus 20%, preferably to plus or minus 10%, and more preferably to plus or minus 5%.

[0042] In [Fig.l], an aircraft 5 comprises an electronic system 10 for displaying information for piloting the aircraft 5.

[0043] In addition, the aircraft 5 comprises a communication installation 12 compartmentalized into an avionics domain 14 and an open domain 16, external to the avionics domain 14.

[0044] In addition, the aircraft 5 further comprises at least one pedestal 18 equipped with at least one flight control member 20. In the example of [Fig. 2], the aircraft 5 comprises three pedestals 18, each being equipped with a respective flight control member 20, namely a central pedestal 18A equipped with a first flight control member 20A, such as a throttle lever used to control the thrust of engines, not shown; and two lateral pedestals 18B each being equipped with a second flight control member 20B, such as an aileron and rudder control lever, not shown, used to control the attitude of the aircraft 5. The throttle lever forming the first flight control member 20A typically comprises two lateral branches 22, each lateral branch 22 being intended to be manipulated respectively by the pilot or by the co-pilot.Each control lever forming a second respective flight control member 20B is typically in the form of a joystick, and is intended to be manipulated respectively by the pilot or by the co-pilot.

[0045] The aircraft 5 is typically an airplane, such as a commercial airliner. Alternatively, the aircraft 5 is a helicopter.

[0046] As a further variant, the aircraft 5 is a drone, i.e. an unmanned aerial vehicle (UAV). According to this variant, the aircraft 5 is then remotely piloted by an operator, and the display system 10 is then configured to display information intended for said operator.

[0047] The electronic display system 10, hereinafter called display system 10, is connected to the communication installation 12, and is configured to display information relating to the piloting of the aircraft 5, intended for at least one member of the crew of the aircraft, in particular the pilot and / or the co-pilot.

[0048] The display system 10 comprises a set 24 of electronic screen(s) 26 forming an information display surface S; a peripheral light strip 28 arranged around at least a portion of a periphery of the display surface S, the light strip 28 comprising a plurality of light sources, not shown; and a control device 30 configured to control at least one group of light source(s) of the light strip 28.

[0049] In addition, the display system 10 comprises a console 31 ensuring the mechanical maintenance of the assembly 24 of electronic screen(s) 26 and the peripheral light strip 28, the control device 30 then being advantageously arranged inside the console 31.

[0050] When the aircraft 5 additionally comprises at least one pedestal 18, the display system 10 advantageously comprises at least one additional light strip 32 arranged around at least a portion of an edge of a respective pedestal 18, each additional light strip 32 comprising a plurality of additional light sources. The control device 30 is then configured to further control at least one group of additional light source(s) of the additional light strip 32.

[0051] In the example of [Fig.2], the display system 10 comprises an additional light strip 32 arranged around at least a portion of an upper edge of the central pedestal 18A. Alternatively or additionally, not shown, the display system 10 comprises an additional light strip 32 arranged around at least a portion of an upper edge of each lateral pedestal 18B.

[0052] The communication installation 12 comprises several avionics systems 36 belonging to the avionics domain 14; as well as one or more electronic devices 38, external to the avionics domain 14 and belonging to the open domain 16; and an electronic communication gateway 40 connected between the electronic device(s) 38 and the avionics systems 36. In the example of [Fig.l], the communication installation 12 comprises several electronic devices 38, each belonging to the open domain 16.

[0053] In addition, the communication installation 12 further comprises a communication server 42 communicating via a communication link 44 with at least one electronic equipment 46, external to the aircraft 5.

[0054] The display system 10 is then, for example, connected to each of the elements of the communication installation 12, i.e. to the avionics systems 36 of the avionics domain 14, to the gateway 40 and to the electronic devices 38 of the open domain 16. As a variant, the display system 10 is connected to the avionics systems 36 of the avionics domain 14 and to the electronic devices 38 of the open domain 16, but not to the gateway 40. As a further variant, the display system 10 is connected to the avionics systems 36 of the avionics domain 14 and indirectly to the electronic devices 38 of the open domain 16 via the gateway 40, which performs filtering of the information from the open world.

[0055] The avionics domain 14 is a domain corresponding to a highest level of security on board the aircraft 5, in particular the highest required level of security of the communication installation 12 of the aircraft 5. The avionics domain 14 is also called the certified domain, the elements belonging to the avionics domain 14 having to be subject to certification.

[0056] The avionics domain 14 is then a domain for limiting a risk of disruption - by at least one communication with an electronic device or apparatus external to the avionics domain 14 - of function(s) implemented by the at least one avionics system 38 of the avionics domain 14. The avionics domain 14 includes the avionics system(s) 38.

[0057] Avionics domain 14 is typically the ACD domain according to the ARINC 811 standard of December 20, 2005.

[0058] The open domain 16 is a domain to which corresponds a lower security level than the security level of the avionics domain 14. The open domain 16 includes the electronic device(s) 38. The open domain 16 is also called the non-certified domain, the elements belonging to the open domain 16 not requiring certification.

[0059] The assembly 24 generally comprises several separate electronic screens 26 to form the display surface S. The electronic display screens 26 are further typically disjointed and separated from one another, and the display surface S is then a discontinuous display surface. Alternatively, the electronic display screens 26 are placed next to one another, and the display surface S is then a continuous display surface.

[0060] In the example of [Fig.2], the assembly 24 comprises three main screens 26A arranged in the lower part and four secondary screens 26B arranged in the upper part. Each main screen 26A is for example a 15-inch screen, and each secondary screen 26B is for example a 6-inch screen. Each main screen 26A is preferably a touch screen, and each secondary screen 26B is preferably a non-touch screen. In addition, each secondary screen 26B is equipped with at least one member 48 for interfacing with the displayed elements, and advantageously with two interface members 48, each interface member 48 being for example in the form of a rotator.

[0061] The light strip 28 is advantageously arranged around the entire perimeter of the display surface S, that is to say all around the display surface S.

[0062] Each of the light sources of the light strip 28 is arranged less than 10 cm, and preferably less than 5 cm, from the periphery of the display surface S.

[0063] Each light source of the light strip 28 is for example a light-emitting diode or LED (from the English Light-Emitting Diode), and preferably a multi-colored LED capable of being controlled according to several distinct lighting colors at distinct time instants, with a respective color at each instant.

[0064] The distinct lighting colors are for example chosen from the group consisting of: a blue color, a pink color, an amber color and a red color.

[0065] In addition, the light strip 28 comprises a protective ring 50 encompassing the light sources, in order to protect said light sources against impacts. Advantageously, the protective ring 50 is made of a diffusing translucent material, in order to transmit the light from the light sources in a less directive manner, the light diffused by the light strip 28 then being informative for a user, while not disturbing his vision.

[0066] The control device 30 comprises several distinct logics 52 for controlling the at least one group of light source(s) of the light strip 28, 32, the plurality of control logics 52 corresponding to a plurality of distinct piloting aids, each control logic 52 corresponding to a respective piloting aid, and the control device 30 is configured to control the at least one group of light source(s) according to at least one of the plurality of control logics 52.

[0067] In the example of [Fig.2], the control device 30 comprises four separate control logics 52, namely a first control logic 52A, a second control logic 52B, a third control logic 52C and a fourth control logic 52D.

[0068] The first control logic 52A is the control of light sources of a portion of the light strip 28 corresponding to the appearance of an aeronautical event El, E2. According to the first control logic 52A, the light source(s) of said portion are switched on upon detection of the event El, E2, then switched off upon disappearance of said event El, E2.

[0069] This first control logic 52A is illustrated through first C1 and second C2 use cases in the example of [Fig.3].

[0070] The first use case C1 corresponds to the case of a first aeronautical event E1 which is an anomaly internal to the aircraft 5, displayed on a respective zone of the display surface S, and the controlled portion of the light strip 28 is then a portion arranged around said zone on which the anomaly forming the first aeronautical event E1 is displayed. In the example of [Fig. 3], the anomaly forming the first event E1 is displayed on a central zone of the display surface S, and the controlled portion of the light strip 28 is then, for example the entirety of the light strip 28, that is to say the portion corresponding to the entire periphery of the display surface S. As a variant, not shown, the controlled portion of the light strip 28 is a central portion of the light strip 28 when the first event El is displayed on said central zone. As a variant, not shown, if the first event El is displayed on an area corresponding to a right third of the display surface S, the controlled portion of the light strip 28 is for example a right portion of said strip. Similarly, if the first event El is displayed on an area corresponding to a left third of the display surface S, the controlled portion of the light strip 28 is for example a left portion of said strip.

[0071] The second use case C2 corresponds to the case of a second aeronautical event E2 which is an event external to the aircraft 5, and the controlled portion of the light strip 28 is then a portion oriented in the direction of said external event forming the second event E2. The external event is for example another aircraft heading towards the aircraft 5. In the example of [Fig. 3], the external event forming the second event E2 is an event arriving towards the aircraft 5 from the front and the left thereof, and the controlled portion of the light strip 28 is for example a first portion PI corresponding to a top quarter (or slightly in front, the display surface S being typically inclined towards the front) and left of the light strip 28.In this example, the first portion PI of the light strip 28 is then controlled according to the first control logic 52A, while a second portion P2 of the light strip 28, corresponding for example to the remaining portion of the light strip 28, is not controlled, or is controlled according to another control logic 52 distinct from the first control logic 52A.

[0072] The second control logic 52B is the control of light sources of a portion of the light strip 28 arranged around an area of ​​the display surface S associated with a transfer of data between the open domain 16 and the avionics domain 14, preferably from the open domain 16 to the avionics domain 14. According to the second control logic 52B, the light source(s) of said portion are temporarily lit during said data transfer. This second control logic 52B is illustrated through a third use case C3 in the example of [Fig. 3]. The third use case C3 corresponds for example to the case where data is sent from the open domain 16, that is to say from the non-certified domain, to the certified avionics domain 14. In the example of [Fig.3], and for this third use case C3, the controlled portion of the light strip 28 is for example the entirety of said strip, this portion being controlled with an ignition mode corresponding to a mode. chaser, where the light sources of the controlled portion are lit successively in batches of sources in order to give the impression of a movement of the illumination in a first direction, symbolized by a first arrow Fl in [Fig.3], or in a second direction, opposite to the first direction, the second direction being symbolized by a second arrow F2; or alternatively in the first direction, then in the second direction, the chaser mode then corresponding to a back-and-forth movement.

[0073] The third control logic 52C is the control of light sources of a portion of the light strip 28 arranged around an area of ​​the display surface S on which a new request is displayed to the user, such as the pilot or co-pilot of the aircraft 5. According to the third control logic 52C, the light source(s) of said portion are temporarily lit when the new request is displayed. This third control logic 52C is illustrated through a fourth use case C4 in the example of [Fig. 3]. The fourth use case C4 corresponds for example to the case where an assistance system in a software application of the open domain 16 has a suggestion to propose to the user. In the example of [Fig.3], and for this fourth use case C4, the controlled portion of the light strip 28 is for example the entirety of said strip, this portion being controlled with an ignition mode corresponding to a slow pulsation mode, such as an ignition mode where a lighting intensity of the controlled portion, also called illumination intensity, first begins to increase, as symbolized by a third arrow F3 in [Fig. 3], then subsequently decreases, as symbolized by a fourth arrow F4 in [Fig. 3]; before increasing again, then decreasing again; and so on.

[0074] Those skilled in the art will observe that in the example of [Fig. 3], the different types of filling (such as hatching with one orientation, hatching with another orientation and point cloud) inside the band representing the light strip 28 symbolize different lighting colors.

[0075] The fourth control logic 52D is the control of light sources of a portion of the light strip 28 arranged around an area of ​​the display surface S on which a set of information is displayed according to a first illumination mode if the set of information belongs to the avionics domain 14 and according to a second illumination mode if the set of information belongs to the open domain 16, the second illumination mode being distinct from the first illumination mode. The first and second illumination modes are typically distinct from each other by distinct lighting colors, the first illumination mode then corresponding to a first lighting color, characteristic of the avionics domain 14, such as the color blue, and the second illumination mode then corresponding to a second lighting color, characteristic of the open domain 16, such as the color pink, the second lighting color being distinct from the first lighting color. The first and second illumination modes typically each correspond to an lighting mode equal to a fixed mode, described below.

[0076] Those skilled in the art will then understand that when the display surface S comprises both a first zone displaying information from the avionics domain 14, the first zone being surrounded by a first portion of the light strip 28, and a second zone displaying information from the open domain 16, the second zone being distinct from the first zone and surrounded by a second portion of the light strip 28, the second portion being distinct from the first portion, then - according to the fourth control logic 52D - the first portion of the light strip 28 is controlled with the first illumination mode, while the second portion of said strip is controlled with the second illumination mode, distinct from the first mode.This fourth control logic 52D then allows the user to more easily distinguish the information belonging to the certified avionics domain 14 from that belonging to the non-certified open domain 16, and also to see more easily when information passes from one domain to the other, for example after filtering in the case of a transfer from the open domain 16 to the avionics domain 14, this change of domain of said information then being accompanied by a change in the illumination mode of the portion of the light strip 28 surrounding the area of ​​the display surface S displaying said information.

[0077] In addition, a person skilled in the art will also observe that according to a combined implementation of the third and fourth control logics 52C, 52D, when information passes from one domain, called the departure domain, to the other domain, called the arrival domain, by moving from one zone, called the departure zone, to another zone, called the arrival zone, of the display surface S, then a portion of the light strip 28 surrounding the departure zone is first controlled according to the chase mode and according to the color among the first and second lighting colors which is associated with the type (among certified avionics domain 14 and non-certified open domain 16) of the departure domain. Then, the chaser moves towards another portion of the light strip 28 surrounding the arrival zone, at the same time as it changes lighting color to pass from one lighting color to the other among the first and second lighting colors.In other words, the other portion of the light strip 28 surrounding the arrival zone is then controlled according to the chase mode and according to the color among the first and second lighting colors which. is associated with the type of the destination domain.

[0078] As an example of this combined implementation of the third and fourth control logics 52C, 52D, if information passes from the open domain 16 to the certified avionics domain 14, the chaser starts from the portion of the light strip 28 surrounding the area of ​​the open domain 16, corresponding for example to one of the main screens 26A, with the color of the open domain 16 (pink for example); then becomes the color of the certified avionics domain 14 (blue for example) as it approaches the other portion of the light strip 28 surrounding the area of ​​the certified avionics domain 14, corresponding for example to another of the main screens 26A. According to this example, the starting domain is then the open domain 16 with the second associated lighting color, and the arrival domain is the certified avionics domain 14 with the first associated lighting color.

[0079] Advantageously, the control device 30 is configured to control several distinct groups of light sources corresponding to several distinct portions of the light strip 28, such as the first and second portions P1, P2, each group then being controlled according to a respective logic among the plurality of control logics 52, 52A, 52B, 52C, 52D.

[0080] According to this advantageous aspect, the control device 30 is preferably configured to simultaneously control said distinct groups of light sources. This then makes it possible to simultaneously provide several distinct piloting aids intended for one or more users, such as the pilot and the co-pilot of the aircraft 5.

[0081] Advantageously again, the control device 30 is configured to control the at least one group of light sources with a respective illumination mode for each control logic 52, 52A, 52B, 52C, 52D, the illumination modes associated with the control logics 52, 52A, 52B, 52C, 52D being distinct from one another and varying from one control logic to another. This then allows the user to distinguish even more easily each of the different control logics 52, 52A, 52B, 52C, 52D, and then to allow him to understand more quickly which one or which of the plurality of distinct piloting aids are highlighted via the control of the light strip 28.

[0082] According to this advantageous aspect, each illumination mode is distinct from the other modes by a respective lighting color of the group of light sources and / or by a respective lighting mode of the group of light sources.

[0083] Each ignition color is typically associated with a criticality level. Each ignition color is then preferentially chosen from the group consisting of: a first-level color, called nominal; a second-level color, called informative; a third-level color, called caution; and a fourth-level color, called alert. The first-level color corresponds, for example, to blue, the second-level color to pink, the third-level color to amber, or orange, and finally the fourth-level color to red.

[0084] Each lighting mode is typically selected from the group consisting of: fixed mode, flashing mode, slow pulse mode, and chase mode. The fixed mode is a lighting mode in which the light source(s) of the controlled portion are kept lit in a fixed manner and without variation in light intensity. The flashing mode is a lighting mode in which the light source(s) of the controlled portion are alternately lit and extinguished according to a control frequency corresponding to the flashing frequency. The slow pulse mode has been described above for the fourth use case C4. The chase mode has also been described above for the third use case C3.

[0085] For the control of the at least one group of light source(s) according to at least one of the plurality of control logics 52, the control device 30 comprises for example a module 54 for detecting a triggering condition from among a plurality of triggering conditions, each triggering condition being associated with a respective control logic 52, and a module 56 for activating the control logic 52 corresponding to the detected triggering condition.

[0086] The controlled portion of the light strip 28 corresponds for example to an angular sector of said light strip 28, and the angular sector of said light strip 28 corresponds to the same angular sector of the display surface S, the angular sector of the display surface S then defining a display zone with which the detected triggering condition is associated.

[0087] For the first control logic 52A, the triggering condition is then the aeronautical event, for example the first event E1 or the second event E2. For the second control logic 52B, the triggering condition is the transfer of data between the open domain 16 and the avionics domain 14, for example from the non-certified open domain 16 to the certified avionics domain 14. For the third control logic 52C, the triggering condition is the new request to the user, such as the pilot or co-pilot of the aircraft 5.

[0088] More generally, each control logic 52 among the plurality of distinct control logics 52 is associated with a respective trigger condition, the trigger conditions being distinct from one another, and varying from one control logic to another. The detection module 54 is then configured to detect one of the plurality of predefined trigger conditions. The activation module 56 is then configured to activate the control logic 52 which is associated with the trigger condition detected by the detection module 54.

[0089] The control device 30 comprises for example an information processing unit 60 typically formed of a memory 62 and a processor 64 associated with the memory 62. The memory 62 is typically capable of storing each of the distinct control logics 52, in particular the first 52A, second 52B, third 52C and fourth 54C control logics.

[0090] According to this example, the detection module 54 and the activation module 56 are each produced in the form of software, or a software brick, executable by the processor 64. The memory 62 of the control device 30 is then able to store software for detecting a trigger condition from among the plurality of trigger conditions and software for activating the control logic corresponding to the detected trigger condition. The memory 62 of the control device 30 also comprises the plurality of control logics 52, such as the first 52A, second 52B, third 52C and fourth 54C control logics. The processor 64 of the control device 30 is then able to execute each of the software from among the detection software and the activation software.

[0091] In a variant not shown, the detection module 54 and the activation module 56 are each produced in the form of a programmable logic component, such as an FPGA (Field Programmable Gate Array) or an integrated circuit, such as an ASIC (Application Specific Integrated Circuit).

[0092] When the control device 30 is produced in the form of one or more software programs, that is to say in the form of a computer program, also called a computer program product, it is furthermore capable of being recorded on a medium, not shown, that is readable by a computer. The computer-readable medium is, for example, a medium capable of storing electronic instructions and of being coupled to a bus of a computer system. By way of example, the readable medium is an optical disk, a magneto-optical disk, a ROM memory, a RAM memory, any type of non-volatile memory (for example EPROM, EEPROM, FLASH, NVRAM), a magnetic card or an optical card. A computer program comprising software instructions is then stored on the readable medium.

[0093] Each additional strip 32 is advantageously arranged all around the edge of the respective pedestal 18, that is to say around the entire circumference of said edge of the corresponding pedestal 18.

[0094] Each of the additional light sources of the additional strip 32 is arranged less than 10 cm, and preferably less than 5 cm, from the periphery of the corresponding edge of the respective pedestal 18.

[0095] Each additional light source of the additional strip 32 is for example a light-emitting diode or LED, and preferably a multi-colored LED capable of being controlled according to several distinct lighting colors at distinct time instants, with a respective color at each instant.

[0096] In addition, each additional strip 32 comprises an additional protective ring 70 encompassing the additional light sources, in order to protect said additional light sources against impacts. Advantageously, the additional protective ring 70 is made of a diffusing translucent material, in order to transmit the light from the additional light sources in a less directive manner, the light diffused by each additional strip 32 then being informative for the users, while not disturbing their vision.

[0097] Each avionics system 36 is on board the aircraft 5 and belongs to the avionics domain 14. Each avionics system 36 is known per se, also called an avionics computer, and is configured to implement one or more respective avionics functions.

[0098] Each avionics system 36 is for example chosen from the group consisting of: a flight management system, also called FMS (Flight Management System); a guidance system, or FG (Flight Guidance); a flight control system, or FCS (Flight Control System); a GNSS (Global Navigation Satellite System) satellite positioning system, such as a GPS (Global Positioning System); an inertial reference system, also called 1RS (Inertial Reference System); an ILS (Instrument Landing System) landing aid system or an MLS (Microwave Landing System) landing aid system; an active runway excursion prevention system, also called ROPS (Runway Overrun Prevention System); and a radio altimeter, also noted RA (RadioAltimeter).

[0099] Each electronic device 38 belonging to the open domain 16 does not implement a respective avionics function, and therefore generally does not require specific certification.

[0100] The electronic communication gateway 40, hereinafter called the communication gateway 40 or gateway 40, is an interface between the open domain 16 and the avionics domain 14. A data message transmitted between the open domain 16 and the avionics domain 14, i.e. from the open domain 16 to the avionics domain 14, or conversely from the avionics domain 14 to the open domain 16, then typically passes through the communication gateway 40.

[0101] The communication gateway 40 is also called a security gateway, and is configured to perform at least one filtering of a data message intended for a respective avionics system 36.

[0102] The communication server 42 is configured to communicate via the communication link 44 with the at least one external electronic device 46, said at least one external electronic device 46 being for example a ground station, or even cloud computing equipment. The communication server 42 is preferably connected to the communication gateway 40. The communication server 42 typically belongs to the open domain 18.

[0103] The communication server 42 is known per se, and notably comprises a transceiver, not shown, compatible with the communication link 44. The communication link 44 is typically a radio link, that is to say a radio wave link, such as a satellite link. The transceiver is then a radio transceiver.

[0104] The external electronic equipment 46 is typically connected to a computer infrastructure of an operational control center, also called OCC (from the English Operational Control Center). The external electronic equipment 46 is then advantageously configured to transmit data, such as for example a flight plan of the aircraft 5 and information relating to the aircraft 5, such as its mass, its configuration, its balancing, or even its identifier.

[0105] When the electronic screen(s) 26 forming the display surface S are switched off, the strip 28, and in addition the additional strip 32 around the pedestal 18, are lit in white, that is to say with a white color, making it possible to provide additional lighting inside the cockpit of the aircraft 5, and also to provide the user with an indication that the display surface S is switched off even when the user is far from it.

[0106] When the electronic screen(s) 26 forming the display surface S are initially lit, the strip 28, and in addition the additional strip 32, are lit with a blue color, representative of a nominal default mode.

[0107] Then, during a mission of the aircraft 5, and in particular during the flight thereof, the strip 28, and in addition the additional strip 32, are intended to be lit successively and in portions according to several distinct control logics among the plurality of control logics 52A, 52B, 52C, 52D.

[0108] Thus, in the event of the occurrence of a particular aeronautical event, such as the first event E1 corresponding to an anomaly internal to the aircraft 5 or the second event E2 corresponding to an event external to the aircraft 5, the strip 28, and in addition the additional strip 32, are in whole or in part controlled according to the first control logic 52A, aimed at alerting the user more effectively as to the occurrence of this event. The first control logic 52A then corresponds for example to an illumination mode with an illumination color equal to the third level color, such as amber, or the fourth level color, such as red, the illumination color being selected according to the criticality of the event that has occurred, and with an illumination mode equal to the fixed mode, or alternatively to the flashing mode.

[0109] In the event of data transfer between the non-certified open domain 16 and the certified avionics domain 14, the strip 28, and in addition the additional strip 32, are in whole or in part controlled according to the second control logic 52B, aimed at informing the user of this data transfer in progress, which may represent a cyber-security risk. The second control logic 52B then corresponds for example to an illumination mode with an illumination color equal to the second level color, such as the color pink, and with an illumination mode equal to the chase mode.

[0110] In the event of a new request to the user, the strip 28, and in addition the additional strip 32, are in whole or in part controlled according to the third control logic 52C, aimed at informing the user of this request requiring an intervention on his part. The third control logic 52C then corresponds for example to an illumination mode with an illumination color equal to the second level color, such as the color pink, and with an illumination mode equal to the slow pulsation mode.

[0111] At the end of the implementation of a respective control logic 52, the strip 28, and in addition the additional strip 32, are again lit with the color representative of the default mode, such as the color blue.

[0112] Thus, the display system 10 according to the invention makes it possible to provide the user, such as the pilot or co-pilot of the aircraft 5, with greater assistance for piloting the aircraft 5, for example by alerting him more effectively to the occurrence of an event, by informing him of a data transfer in progress likely to represent a cyber risk and / or by drawing his attention to the presence of a new request requiring intervention on his part.

[0113] Generally speaking, the display system 10 according to the invention then makes it possible to provide the user with additional information in relation to the information displayed on the display surface S, this via the control of the strip 28, and in addition to the additional strip 32, according to a particular control logic among the plurality of control logics 52A, 52B, 52C, 52D corresponding to several distinct piloting aids.

[0114] Furthermore, the different control logics 52A, 52B, 52C, 52D correspond to different illumination modalities, each being associated with a respective control logic 52 and varying from one control logic 52 to another. Also, the user can then recognize even more easily the control logic(s) implemented at a given time instant for the strip 28, and in addition the additional strip 32, and therefore know more quickly which piloting aid(s) are then highlighted at this instant by the strip 28, and in addition the additional strip 32.

[0115] The display system 10 according to the invention then makes it possible to reduce the risk of an incident by providing greater assistance in piloting the aircraft 5, and in doing so to increase the safety of the flight of the aircraft 5.

Claims

Claims

1. Electronic system (10) for displaying information for piloting an aircraft (5), comprising: - a set (24) of electronic screen(s) (26) forming an information display surface (S); - a peripheral light strip (28) arranged around at least part of a periphery of the display surface (S), the light strip (28) comprising a plurality of light sources;and - a control device (30) configured to control at least one group of light source(s) of the light strip (28), characterized in that the control device (30) comprises a plurality of separate logics (52, 52A, 52B, 52C, 52D) for controlling the at least one group corresponding to a plurality of separate piloting aids, each control logic (52, 52A, 52B, 52C, 52D) corresponding to a respective piloting aid, and the control device (30) is configured to control the at least one group of light source(s) according to at least one of the plurality of control logics (52, 52A, 52B, 52C, 52D).;

2. System (10) according to claim 1, wherein the control device (30) is configured to control several distinct groups of light source(s) corresponding to several distinct portions (PI, P2) of the light strip (28), each group being controlled according to a respective logic among the plurality of control logics (52, 52A, 52B, 52C, 52D). the control device (30) preferably being configured to simultaneously control said distinct groups of light source(s).

3. System (10) according to claim 1 or 2, wherein the control device (30) is configured to control the at least one group of light source(s) with a respective illumination modality for each control logic (52, 52A, 52B, 52C, 52D), the illumination modalities associated with the control logics (52, 52A, 52B, 52C, 52D) being distinct from each other and varying from one control logic to another.

4. System (10) according to claim 3, each illumination mode is distinct from the other modes by a respective lighting color of the group of light source(s) and / or by a mode respective ignition of the group of light source(s).

5. System (10) according to claim 4, each lighting color is associated with a criticality level; each lighting color preferably being chosen from the group consisting of: a first level color, called nominal; a second level color, called informative; a third level color, called caution; and a fourth level color, called alert.

6. The system (10) of claim 4 or 5, each ignition mode is selected from the group consisting of: a steady mode, a flashing mode, a slow pulse mode, and a chase mode.

7. System (10) according to any one of the preceding claims, in which the aircraft (5) comprises a communication installation (12) compartmentalized into an avionics domain (14) and an open domain (16) external to the avionics domain (14); and the plurality of separate control logics (52, 52A, 52B, 52C, 52D) comprises first (52A), second (52B), third (52C) ​​and fourth (52D) control logics; the first control logic (52A) being the control of light source(s) of a portion (PI) of the light strip (28) corresponding to the appearance of an aeronautical event (El, E2), the light source(s) of said portion (PI) being lit upon detection of the event, then extinguished upon disappearance of said event;the second control logic (52B) being the control of light source(s) of a portion of the light strip (28) arranged around an area of ​​the display surface (S) associated with a transfer of data between the open domain (16) and the avionics domain (14), preferably from the open domain (16) to the avionics domain (14), the light source(s) of said portion being temporarily lit during said data transfer; the third control logic (52C) ​​being the control of light source(s) of a portion of the light strip (28) arranged around an area of ​​the display surface (S) on which a new request is displayed for a user of the aircraft (5), the light source(s) of said portion being temporarily lit during the display of the new request; the fourth control logic (52D) being the control of; light source(s) of a portion of the light strip (28) arranged around an area of ​​the display surface (S) on which a set of information(s) is displayed according to a first illumination mode if the set of information(s) belongs to the avionics domain (14) and according to a second illumination mode if the set of information(s) belongs to the open domain (16), the second illumination mode being distinct from the first illumination mode.

8. System (10) according to claim 7, wherein according to the first control logic (52A), if the aeronautical event is an event (E2) external to the aircraft (5), then the controlled portion of the light strip (28) is a portion oriented towards said external event (E2); and if the aeronautical event is an anomaly (El) internal to the aircraft (5), displayed on a respective area of ​​the display surface (S), then the controlled portion of the light strip (28) is a portion arranged around said area on which the anomaly (El) is displayed.

9. System (10) according to any one of the preceding claims, in which each of the light sources of the light strip (28) is arranged less than 10 cm, and preferably less than 5 cm, from the periphery of the display surface (S).

10. Aircraft (5) comprising an electronic system (10) for displaying information for piloting the aircraft (5) and a communication installation (12) compartmentalized into an avionics domain (14) and an open domain (16) external to the avionics domain (14), the communication installation (12) comprising several avionics systems (36) belonging to the avionics domain (14), one or more electronic devices (38) belonging to the open domain (16), characterized in that the electronic display system (10) is according to any one of the preceding claims.

11. Aircraft (5) according to claim 10, in which the avionics domain (14) is a domain corresponding to a highest level of safety on board the aircraft (5).

12. An aircraft (5) according to claim 10 or 11, wherein the aircraft (5) further comprises a pedestal (18) equipped with at least one flight control member (20), and the electronic display system (10) further comprises an additional light strip (32) arranged around at least a portion of an edge of the pedestal (18), the light strip additional (32) comprising a plurality of additional light sources, and the control device (30) being configured to further control at least one group of additional light source(s) of the additional light strip (32).

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