Avionics system and aviation aircraft

Abstract

The utility model discloses an avionics system and an aviation aircraft, and relates to the technical field of avionics, the avionics system comprises two avionics computing devices and two display devices, the two avionics computing devices are in communication connection, and each display device is connected with each avionics computing device through a digital video line and a signal transmission line; wherein the two pieces of avionics computing equipment form a dual-redundancy avionics computing subsystem for providing avionics computing backup; the two pieces of avionics computing equipment and the two pieces of display equipment form a cross redundancy display control subsystem, when any one piece of avionics computing equipment and / or any one piece of display equipment fails, display reconstruction is carried out through other pieces of avionics computing equipment and display equipment except the failed equipment, and display control backup is provided. According to the invention, decoupling of display control and avionics calculation is realized, and the configuration display flexibility of the avionics system is improved.

Description

TECHNICAL FIELD

[0001] The present application relates to the technical field of avionics, in particular to an avionics system and an aircraft. BACKGROUND

[0002] The core of an avionics system generally includes a display control system and an avionics computing system. The display control system is mainly used to provide human-computer interaction, and the avionics computing system is mainly used to provide a common computing platform. There are generally two kinds of current avionics system architectures: one is a separated architecture, and the other is an integrated architecture. Both of the two system architectures have the problem that the physical hardware DHA (Display Head Assembly) and the IDU (Integrated Display Unit) computer are integrated, so that the display size of the DHA is fixed with the volume of the IDU, and the size cannot be flexibly adjusted. CONTENT OF THE UTILITY MODEL

[0003] The main purpose of the present application is to provide an avionics system and an aircraft, which aims to solve the technical problem that the hardware display size of the avionics system is limited and cannot be flexibly adjusted in the related art.

[0004] To achieve the above-mentioned purpose, the present application provides an avionics system, which includes two avionics computing devices and two display devices, the two avionics computing devices are communicatively connected, and each display device is connected with each avionics computing device through a digital video line and a signal transmission line.

[0005] Among them, the two avionics computing devices constitute a dual-redundancy avionics computing subsystem, and provide avionics computing backup.

[0006] The two avionics computing devices and the two display devices constitute a cross-redundancy display control subsystem, and when any avionics computing device and / or any display device fails, the display is reconfigured through the other avionics computing device and display device except the failed device, and display control backup is provided.

[0007] In an embodiment, each display device includes:

[0008] A display unit is connected with the two avionics computing devices through the digital video line respectively, and the display unit is used for displaying according to the received video signal.

[0009] In an embodiment, each display device further includes:

[0010] A communication unit is connected with the two avionics computing devices through the signal transmission line respectively, and the communication unit is used for outputting user operation instructions according to user operation information.

[0011] The self-checking unit is connected with the two avionics computing devices through signal transmission lines, and is used for detecting device faults and outputting self-checking information.

[0012] In an embodiment, each display device further comprises:

[0013] The freeze detection unit is connected with the two avionics computing devices through digital video lines, and is also connected with the display unit, and is used for freeze detection according to the received video signals and outputting the video signals passing the detection to the display unit.

[0014] In an embodiment, each avionics computing device comprises:

[0015] The avionics computing module is used for avionics computing according to the received external information and outputting a graphic processing signal;

[0016] The graphic processing module is connected with the avionics computing module, and is connected with the two display devices through digital video lines, and is used for graphic generation and image rendering according to the graphic processing signal, and outputs two video signals which are transmitted to the two display devices through the digital video lines respectively.

[0017] The avionics computing module is connected with the two display devices through signal transmission lines, and is also used for receiving the user operation instructions and the self-checking information outputted by the display devices through the signal transmission lines.

[0018] In an embodiment, each avionics computing device further comprises:

[0019] The display management module is connected with the avionics computing module and the graphic processing module, and is also connected with the two display devices through digital video lines and signal transmission lines, and the display management modules in the two avionics computing devices are communicatively connected, and the display management module is used for monitoring the fault conditions of the display devices and the avionics computing devices, so as to provide avionics computing backup and display control backup.

[0020] In an embodiment, the avionics computing module adopts a multi-core operation processor, and the graphic processing module adopts an independent graphics card.

[0021] In an embodiment, the digital video line is a digital video interface (DVI) cable or an optical fiber.

[0022] In an embodiment, the digital video line is an optical fiber, each avionics computing device comprises an electric-optical conversion module, each display device comprises an optical-electric conversion module, and the electric-optical conversion module and the optical-electric conversion module are connected through the optical fiber.

[0023] In addition, in order to achieve the above-mentioned purpose, the application further provides an aircraft comprising the avionics system as described above.

[0024] The one or more technical solutions provided in the application have at least the following technical effects:

[0025] An avionics system is provided, comprising two avionics computing devices and two display devices, the two avionics computing devices being communicatively connected, each display device being connected to each avionics computing device through a digital video line and a signal transmission line, the two avionics computing devices forming a dual-redundancy avionics computing subsystem, and the two avionics computing devices and the two display devices forming a cross-redundancy display control subsystem, forming a distributed architecture avionics system, the dual-redundancy avionics computing subsystem being capable of providing avionics computing backup by another avionics computing device when any one of the avionics computing devices fails, to ensure normal operation of the avionics system, and the cross-redundancy display control subsystem being capable of providing display reconstruction and display control backup by the remaining other devices when the avionics computing devices and / or any one of the display devices fail, to ensure normal configuration display of the avionics system and avoid affecting user operation; the avionics system realizes decoupling of display control and avionics computing, can be applied to display devices of any size, is flexible in device installation and wiring, and can meet more personalized display requirements, thereby improving flexibility of configuration display of the avionics system. BRIEF DESCRIPTION OF DRAWINGS

[0026] The accompanying drawings, which are incorporated into and form a part of the specification, illustrate an embodiment consistent with the present application and, together with the description, serve to explain the principles of the application.

[0027] In order to more clearly illustrate the technical solutions in the embodiments of the present application or the related art, the accompanying drawings needed to be used in the embodiments or the related art description will be briefly introduced. Obviously, the accompanying drawings in the following description are only some embodiments of the present application, and for those skilled in the art, other drawings can also be obtained from the structures shown in the drawings without creative labor.

[0028] Figure 1 The system architecture schematic diagram of an embodiment of the avionics system of the present application;

[0029] Figure 2 The structure schematic diagram of a display device in another embodiment of the avionics system of the present application;

[0030] Figure 3 The system architecture schematic diagram of another embodiment of the avionics system of the present application;

[0031] Figure 4 The structure schematic diagram of an avionics computing device in another embodiment of the avionics system of the present application.

[0032] The implementation, functional features and advantages of the present application will be further described with reference to the embodiments and the accompanying drawings. DETAILED DESCRIPTION

[0033] The technical solutions in the embodiments of the present application will be described clearly and completely in combination with the drawings in the embodiments of the present application. Obviously, the described embodiments are only some of the embodiments of the present application, rather than all the embodiments. Based on the embodiments in the present application, all other embodiments obtained by a person of ordinary skill in the art without creative work fall within the protection scope of the present application.

[0034] It should be noted that if the embodiments of the present application involve directional indications (such as up, down, left, right, front, back, etc.), the directional indications are only used to explain the relative position relationship, movement condition, etc. between components in a certain posture, and if the certain posture changes, the directional indications also change accordingly. In addition, if the embodiments of the present application involve descriptions such as “first”, “second”, etc., the descriptions of “first”, “second”, etc. are only for description purposes, and cannot be understood as indicating or implying the relative importance or implicitly indicating the number of the indicated technical features. Therefore, the features limited by “first”, “second” can explicitly or implicitly include at least one of the features. In addition, “and / or” or “and / or” appearing throughout the text means that the three parallel schemes are included, for example, “A and / or B” includes A scheme, or B scheme, or A and B are satisfied at the same time. In addition, the technical solutions of each embodiment can be combined with each other, but it must be based on the realization of a person of ordinary skill in the art, and when the combination of technical solutions appears contradictory or unachievable, it should be considered that the combination of technical solutions does not exist, and is not within the protection scope claimed by the present application.

[0035] With the progress of eVTOL (Electric Vertical Takeoff and Landing) technology and the increasing demand for air traffic, eVTOL aircraft continue to develop. Based on the advantages of low carbon environmental protection, low noise, high automation level, low operating cost, high safety, etc., eVTOL can be used for urban transportation, emergency rescue tasks, rapid cargo transportation and end delivery, etc. Various scenarios.

[0036] The avionics system (hereinafter referred to as the avionics system) is the brain of the eVTOL, among which the display control system and the avionics computing system are the core of the avionics system. The display control system is mainly used to provide human-computer interaction, and the avionics computing system is mainly used to provide a public computing platform. The architecture of the current display control system and avionics computing system usually has two kinds:

[0037] One is a split architecture, including an IDU (Integrated Display Unit) and an IMA (Integrated Modular Avionics) computer / computing platform two devices, the software of the display control system resides in the IDU and the IMA two devices respectively, and the physical hardware DHA (Display Head Assembly) is integrated with the IDU. This split architecture is usually applied to large aircraft, has the advantages of high system integration, strong computing ability and scalability, high safety redundancy, and the disadvantages of many system devices, large SWaP (Size Weight and Power), high cost, and the display size of the DHA is fixed with the volume of the IDU, and cannot be flexibly adjusted in size.

[0038] The other is an integrated architecture, which is a smart integrated display unit (Smart IDU) computer that simultaneously has computing, graphics processing and display capabilities, only a single device, and the software of the display control system resides in the device, and the physical hardware DHA is integrated with the Smart IDU. This integrated architecture is usually applied to general aviation aircraft, has the advantage of high integration, and the disadvantages of high device complexity, high maintenance difficulty, limited upgrade, large weight and space constraints, single point failure of DHA and IDU (i.e. if the IDU fails, even if the DHA is normal, the DHA will be discarded), and the display size of the DHA is fixed with the volume of the IDU, and cannot be flexibly adjusted in size.

[0039] In addition, in the above two architectures, the avionics computing system part mostly adopts a single-core design, and due to the low computing power of the single-core processor, the system computing power is limited, and usually only the number of modules can be added to meet the computing power requirements of the resident application, resulting in an increase in device weight and cost.

[0040] To solve the above problems, the present application provides an avionics system and an aircraft. The present application and the following embodiments will be described below with reference to the accompanying drawings.

[0041] The present application provides an avionics system.

[0042] In an embodiment of the present application, with reference to Figure 1 , Figure 1 is a schematic diagram of the system architecture of the avionics system, which can include two avionics computing devices and two display devices, the two avionics computing devices are communicatively connected, and each display device is connected to each avionics computing device through a digital video line and a signal transmission line.

[0043] The two avionics computing devices constitute a dual-redundancy avionics computing subsystem to provide avionics computing backup; and the two avionics computing devices and the two display devices constitute a cross-redundancy display control subsystem to provide display control backup by using the other avionics computing device and display device to reconfigure the display when any of the avionics computing device and / or any of the display device fails.

[0044] It should be noted that in the dual-redundancy avionics computing subsystem, the two avionics computing devices can back up each other, or one of them can be designated as a master computing device and the other as a slave computing device to implement master-slave backup. In actual application, the master computing device can be used to perform related operations and control operations of the avionics system, and the master computing device can output two video signals at the same time, and the slave computing device only serves as a hot backup. When the master computing device fails, the slave computing device is enabled to replace the work of the master computing device to ensure normal display control of the display device. Therefore, the dual-redundancy avionics computing subsystem can provide avionics computing backup by using the other avionics computing device when any of the avionics computing devices fails to ensure normal operation of the avionics system.

[0045] It can be understood that the dual-redundancy avionics computing subsystem can maintain normal display of the two display devices even when a single avionics computing device fails, and can ensure normal display function of the system even when the two display devices display different contents.

[0046] It should be further noted that in the cross-redundancy display control subsystem, the two avionics computing devices can back up each other, and the two display devices can also back up each other to implement cross-redundancy backup of the video source end and the display end. In actual application, the backup control can be implemented by the avionics computing device or an external control device in communication with the avionics computing device, for example, when working normally, the two display devices display different contents, when any of the display devices fails, the other display device displays all contents, when any of the avionics computing devices fails, the other avionics computing device controls the two display devices to display different contents, and when any of the avionics computing devices and any of the display devices fails, the other avionics computing device controls the other display device to display all contents. Therefore, the cross-redundancy display control subsystem can be used to reconfigure the display by using the other avionics computing device and display device to provide display control backup when any of the avionics computing device and / or any of the display device fails.

[0047] It can be understood that the cross-redundancy display control subsystem can use a conventional display reconstruction method to switch between the set multiple display modes directly to convert the display of the primary flight information, navigation information, and crew warning information, etc., to ensure the continuity and coherence of the primary flight information and engine main information display for the pilot to use; or the display reconstruction can be performed on the display device of different sizes or quantities by changing the display content, display layout, display direction, and other related display configuration parameters; the built-in display reconstruction logic can also be used to implement different display reconstruction controls. In actual application, the selection can be made according to the needs, which is not limited here.

[0048] In this embodiment, the avionics computing device can be an ACU (Avionics Computing Unit) avionics computer / computing platform, and the display device can be a DHA (Display Head Assembly) display screen / display, which only provides display function and has smaller volume and is easier to install. The two display devices can display the same content, for example, both display the running data of the avionics system and are provided to different users; or the two display devices can display different content, for example, one display device is a PFD (Primary Flight Display) and the other display device is a MFD (Multi-Function Display) to realize PFD+MFD display. The selection can be made according to the actual needs, which is not limited here.

[0049] The digital video line can be a DVI (Digital Visual Interface) cable or an optical fiber.

[0050] For example, the DHA display screen is provided with a DVI (Digital Visual Interface), which can be connected with the ACU avionics computer through the DVI and a video signal line such as a DVI cable to receive the video signal.

[0051] It should be noted that in the avionics system, the DHA display screen is no longer integrated with the IDU computer, but a separate DHA display screen and ACU avionics computer are used, which are connected through a DVI cable or an optical fiber to realize the decoupling of display control and avionics computing.

[0052] It can be understood that the avionics system physically realizes decoupling of the DHA display screen and the ACU avionics computer, and functionally realizes decoupling of the terminal display function and the graphic generation function. When different sizes and shapes of the DHA display screen need to be adapted, only the display software part of the ACU avionics computer needs to be configured and upgraded to match the replaced DHA display screen, and the entire ACU avionics computer does not need to be replaced, so that more personalized display requirements can be met, including flexible adjustment of display size, display shape, display content and display direction, and the like, and the system display flexibility is improved. Moreover, the avionics system does not have the single point failure defect of the related art avionics system.

[0053] In an available embodiment, the digital video line is a DVI cable, and an equalizer chip is integrated on each of the avionics computing devices and the display devices.

[0054] In another available embodiment, the digital video line is an optical fiber, each of the avionics computing devices can include an electro-optical conversion module, each of the display devices can include an optical-electric conversion module, and the electro-optical conversion module and the optical-electric conversion module are connected through the optical fiber.

[0055] It should be noted that the transmission distance of the conventional DVI on the aircraft is generally 7 m, but in the avionics system, the connection distance between the DHA display screen and the ACU avionics computer is about 10 m, so some conventional DVI connection methods cannot be directly applied to the avionics system, otherwise signal attenuation will occur. Therefore, an electro-optical conversion module can be designed in the avionics computing device as a sending end, and an optical-electric conversion module can be designed in the display device as a receiving end. In actual application, the electro-optical conversion module can be arranged in the ACU avionics computer, and the optical-electric conversion module can be arranged in the DHA display screen.

[0056] For example, the signal transmission line can adopt a communication line of various interface standards, such as an RS232, RS422, RS485, or the like. A digital signal interface is further arranged on the DHA display screen, and the DHA display screen can be connected with the ACU avionics computer through the digital signal interface and the signal transmission line, such as the RS422 communication line, to send user operation instructions and self-checking information. Here, the RS422 communication line is preferred, which has a longer transmission distance and a higher transmission rate, and supports point-to-multiple bidirectional communication.

[0057] It can be understood that the connection between the ACU avionics computer and the DHA display screen through the optical fiber can realize long-distance wiring and anti-EMI (Electromagnetic Interference) interference. At the same time, the installation and wiring of the cable are simple and convenient.

[0058] For example, the avionics system can be installed using a simple quick-release method, such as a self-locking bracket nut / screw, without the need for a special chassis or equipment rack, thus offering flexible installation options.

[0059] The avionics system provided in this embodiment includes two avionics computing devices and two display devices. The two avionics computing devices are communicatively connected, and each display device is connected to each avionics computing device via digital video cables and signal transmission lines. The two avionics computing devices constitute a dual-redundant avionics computing subsystem, and the two avionics computing devices and two display devices constitute a cross-redundant display control subsystem, forming a new distributed avionics system architecture of avionics computing subsystem + display control subsystem. In this distributed architecture, the dual-redundant avionics computing subsystem can provide avionics computing backup through the other avionics computing device when either avionics computing device fails, ensuring the normal operation of the avionics system. The cross-redundant display control subsystem can reconstruct the display through the remaining devices when either avionics computing device or any display device fails, providing display control backup to ensure the normal configuration and display of the avionics system and avoid affecting user operation. This avionics system achieves decoupling of display control and avionics computing, can be used with display devices of any size, offers flexible device installation and wiring, can meet more personalized display needs, and improves the flexibility of avionics system configuration and display.

[0060] In another embodiment of this application, reference is made to Figure 2 , Figure 2 This is a schematic diagram of the structure of display devices in an avionics system. Each display device may include a display unit.

[0061] The display unit is connected to two avionics computing devices via digital video cables, and is used to display the received video signals.

[0062] It should be noted that the display unit can be a hardware display component, such as a 1080P (1920×1080 pixels) display, a 1440P (1920×1440 pixels) display, or other displays of different sizes; displays with different aspect ratios such as 16:9 and 4:3; displays of different shapes such as rectangular screens and oval screens, etc., without specific limitations here.

[0063] In one feasible implementation, such as Figure 2 As shown, each display device may also include a communication unit and a self-test unit.

[0064] The communication unit is connected to two avionics computing devices via signal transmission lines. The communication unit is used to output user operation commands based on the user's operation information. The self-test unit is connected to the two avionics computing devices via signal transmission lines. The self-test unit is used to detect equipment faults and output self-test information.

[0065] It should be noted that the communication unit can directly use the touch display screen of the display unit to realize touch input, and / or use physical keys, buttons, etc. to realize mixed input. The self-checking unit can realize the BIT (Built-In Test) function, automatically detects the hardware and software functions and performance of the display device, and generates self-checking information, which is fed back to the avionics computing device, so that the avionics computing device can respond to faults or give an alarm when a fault is found.

[0066] For example, user operation instructions such as touch screen instructions, key instructions, etc., self-checking information such as device fault information of the DHA, etc. are not specifically limited here. The self-checking unit can realize self-detection and fault reporting through PBIT (Power-On Self-Test), CIBT (Cycle-Interval Built-In Test) and IBIT (In-Service Built-In Test).

[0067] In a feasible implementation, as shown in Figure 2 Each display device can further include a frozen screen detection unit.

[0068] The frozen screen detection unit is connected to the two avionics computing devices through digital video lines respectively, and is also connected to the display unit. The frozen screen detection unit is used to perform frozen screen detection according to the received video signals, and output the video signals that pass the detection to the display unit.

[0069] It can be understood that the frozen screen detection unit can perform frozen screen detection according to the received video signals, for example, similarity judgment can be performed on the display screen analyzed based on the video signals, if the similarity is less than a preset value, it is determined that the detection passes, otherwise the detection fails; and then the video signals that pass the detection are output to the display unit for real-time display, which can effectively prevent the error display screen of the video card of the avionics computing device from being sent to the card stall, frozen screen, thereby avoiding affecting the user operation.

[0070] In the avionics system provided in the embodiment, a single display device can have two independent video source access functions, and can realize high-reliability display; can also realize self-detection function and self-checking feedback, to ensure normal user operation and fault monitoring of multiple devices; and can also detect display image integrity to ensure complete display content.

[0071] In another embodiment of the present application, referring to Figure 3 and Figure 4 , Figure 3 FIG. 1 is a schematic diagram of the system architecture of the avionics system, Figure 4 FIG. 2 is a schematic diagram of the structure of the avionics computing device in the avionics system, and each avionics computing device can include an avionics computing module and a graphics processing module.

[0072] The avionics computing module is configured to perform avionics computation based on the received external information and output a graphic processing signal; the graphic processing module is connected with the avionics computing module and connected with the two display devices through digital video lines, and the graphic processing module is configured to perform graphic generation and image rendering based on the graphic processing signal and output two video signals to the two display devices through the digital video lines; the avionics computing module is connected with the two display devices through signal transmission lines, and the avionics computing module is further configured to receive user operation instructions and self-checking information output by the display devices through the signal transmission lines.

[0073] Optionally, the avionics computing module can further output other control signals, such as start / stop control signals, as needed, and transmit the control signals to the two display devices through the signal transmission lines, to realize more control functions of the display devices.

[0074] An example is shown in FIG. 1, in which two avionics computing devices are used, and two display devices are used. Figure 3 As shown in FIG. 1, the two avionics computing devices are ACU avionics computers, denoted as left avionics computer ACU_L and right avionics computer ACU_R, and the two display devices are DHA display screens, denoted as left display screen DHA_L and right display screen DHA_R. The ACU_L is connected with the DHA_L and the DHA_R through RS422 communication lines and DVI cables, the ACU_R is also connected with the DHA_L and the DHA_R through RS422 communication lines and DVI cables, and the ACU_L and the ACU_R are connected through a communication bus. The ACU_L and the ACU_R are respectively provided with avionics computing modules and graphic processing modules to perform avionics computation and display control.

[0075] It can be understood that the avionics computing device of the embodiment integrates the avionics computation function and the graphic generation function, and compared with the way of integrating and designing the IDU computing unit and the avionics computing unit in the related art, the embodiment can effectively reduce the weight of the device, the weight of the cable and the hardware cost.

[0076] Another example is shown in FIG. 2, in which two avionics computing devices are used, and two display devices are used. Figure 4 As shown in FIG. 2, the two avionics computing devices can be set as a master computing device and a slave computing device, and are connected with each other through a communication bus, and other crosslinking devices can be connected between the two avionics computing devices, or the two avionics computing devices can be connected with an external crosslinking system through an external bus, so that the avionics computing modules in the avionics computing devices can receive external information sent by the external crosslinking devices / crosslinking system, to perform avionics computation.

[0077] It should be noted that the master computing device and the slave computing device can all reside all applications, receive external input and complete data processing, cross-checking. The difference is that in the normal working state, the master computing device sends instructions and data to the outside, including sending video signals to the display device for picture display, receiving user operation instructions and self-checking information sent by the display device, etc. The slave computing device acts as a hot backup and does not actively send information to the outside.

[0078] In practical application, there can be a certain time difference in the power-on of the two avionics computing devices. After both avionics computing devices complete power-on self-checking, they can perform handshaking and health degree comparison through the communication bus. If the health degrees are consistent, the master-slave relationship recorded during the previous power-on can be switched for this time power-on, for example, if ACU_L was the master computing device during the previous power-on, ACU_R is selected as the master computing device after this time power-on. If it is the first power-on or the records on both sides are inconsistent, the master-slave relationship can be determined according to the date of the day, or the master-slave relationship can be set according to actual needs, which is not limited here.

[0079] Among them, the avionics computing module adopts a multi-core operation processor, and the graphics processing module adopts a separate graphics card.

[0080] It can be understood that a single avionics computing device adopts a multi-core operation processor, and compared with the GPM used in the related art, the multi-core operation has higher computing power, which can improve the computing capability of the avionics computing device and realize more avionics computing functions. A single avionics computing device adopts a separate graphics card, which can independently output two video sources, realizing cross-redundancy backup of the video source end and the display end, that is, cross-redundancy display control backup of the two avionics computing devices and the two display devices.

[0081] In a feasible implementation manner, as shown in Figure 3 and Figure 4 The avionics computing device can further include a display management module.

[0082] Among them, the display management module is connected with the avionics computing module and the graphics processing module respectively, and is further connected with the two display devices through digital video lines and signal transmission lines respectively. The display management modules in the two avionics computing devices are in communication connection, and the display management module is used to monitor the fault conditions of the display devices and the avionics computing devices to provide avionics computing backup and display control backup.

[0083] It should be noted that the display management (DM: Display Manager) module can also be used to determine that the avionics computing device where the module is located is the master computing device, so that the avionics computing module in the master computing device can output two video signals to the two display devices. At this time, the other avionics computing device is automatically determined as the slave computing device and acts as a hot backup without actively outputting video signals.

[0084] In the implementation, the DM module can monitor the health of the four devices, i.e., two avionics computing devices and two display devices, in real time, perform corresponding display management control, and monitor the failure of the display software on the avionics computing device. For example, in the case of failure of the main computing device, the slave computing device can be automatically switched to, the backup ACU avionics computer is used to continue to maintain two independent and effective video signal outputs, and the two DHA display screens are provided with the video signal outputs, so that the normal mode display of the dual-screen content can be continued, i.e., the backup function of the avionics computing subsystem is used to ensure the normal display of the two DHA display screens. For another example, the failure monitoring information of the two avionics computing devices and the two display devices can be acquired, the failure device and other devices are determined according to the failure monitoring information, and the display reconstruction is performed by using the other devices according to the failure of the failure device and the preset display reconstruction logic, so that the dual-screen display, single-screen display, or failure alarm can be continued, i.e., the backup function of the cross-redundancy display control subsystem is used. The failure device can be any avionics computing device and / or any display device, the other devices are the other avionics computing devices and display devices except the failure device among the two avionics computing devices and the two display devices, and the failure includes the failure of a line replaceable unit (LRU) and / or the failure of a hosted application (HA).

[0085] For example, the DM module can also be configured to, when the failure of the failure device is the failure of a single LRU, perform dual-screen display reconstruction or single-screen display reconstruction by using the other devices according to a single-LRU failure display reconstruction mechanism, wherein the failure of a single LRU refers to the failure of an LRU of any avionics computing device or any display device; when the failure of the failure device is the failure of double LRUs, perform single-screen display reconstruction or display failure alarm by using the other devices according to a double-LRU display reconstruction mechanism, wherein the failure of double LRUs refers to the failure of an LRU of any avionics computing device and any display device, or the failure of an LRU of the two display devices; when the failure of the failure device is the failure of a single HA, perform dual-screen display reconstruction by using the other devices according to a single-HA failure display reconstruction mechanism, wherein the failure of a single HA refers to the failure of an HA of any avionics computing device; and when the failure of the failure device is the failure of double HAs, perform single-screen display reconstruction by using the other devices according to a double-HA failure display reconstruction mechanism, wherein the failure of double HAs refers to the failure of an HA of the two avionics computing devices.

[0086] Optionally, the DM module can be further configured to: if the master computing device has LRU failure, switch to dual-screen display reconstruction of the two display devices by the slave computing device; if the slave computing device has LRU failure, maintain normal display control of the two display devices by the master computing device; if any display device has LRU failure, perform single-screen display reconstruction of the other display device by the master computing device, and the slave computing device remains in an active but output invalid state.

[0087] Optionally, the DM module can be further configured to: if the master computing device and any display device has LRU failure, switch to single-screen display reconstruction of the other display device by the slave computing device; if the slave computing device and any display device has LRU failure, perform single-screen display reconstruction of the other display device by the master computing device, and the slave computing device remains in an active but output invalid state; if the master computing device and the slave computing device both have LRU failure, restart the master computing device and the slave computing device; if both display devices have LRU failure, perform display failure alarm by the master computing device.

[0088] Optionally, the graphic processing module can include a primary flight display (PFD) unit and a multi-function display (MFD) unit, and the PFD unit and the MFD unit are connected to the two display devices through digital video lines and signal transmission lines respectively; the DM module can be further configured to: if the PFD unit or the MFD unit in the master computing device has HA failure, switch to dual-screen display reconstruction of the two display devices by the PFD unit and the MFD unit in the slave computing device; if the PFD unit or the MFD unit in the slave computing device has HA failure, maintain normal display control of the two display devices by the PFD unit and the MFD unit in the master computing device.

[0089] Optionally, the DM module can be further configured to: if the PFD unit in the master computing device and the MFD unit in the slave computing device have HA failure, send the MSG structure of the PFD unit in the slave computing device to the master computing device to form a new PFD unit in the master computing device, so that the new PFD unit and the MFD unit in the master computing device perform dual-screen display reconstruction on the two display devices; if the MFD unit in the master computing device and the PFD unit in the slave computing device have HA failure, send the structure of the MFD unit in the slave computing device to the master computing device to form a new MFD unit in the master computing device, so that the PFD unit and the new MFD unit in the master computing device perform dual-screen display reconstruction on the two display devices; if the PFD units in the master computing device and the slave computing device have HA failure, keep the MFD unit in the master computing device to perform MFD display control and PFD display fault alarm on the two display devices; and if the MFD units in the master computing device and the slave computing device have HA failure, keep the PFD unit in the master computing device to perform PFD display control and MFD display fault alarm on the two display devices.

[0090] As shown in the example, Figure 4 The avionics computing device can further include interface modules, power supply modules, and the like, basic modules, underlying software, and real-time operating systems (RTOS: Real-Time Operating System), etc., which are not limited here. The interface module can provide video signal interfaces, digital signal interfaces, bus communication interfaces, etc., and the power supply module can ensure the power supply requirements of each module in the avionics computing device to enable the normal use of the corresponding functions. Among them, the interface module can be connected with the avionics computing module and the graphics processing module respectively, and connected with the two display devices through digital video lines, connected with the two display devices through signal transmission lines, and connected with another avionics computing device through a communication bus; the interface module can be used to forward the video signal provided by the graphics processing module to the display device through the digital video line, and can also be used to receive the user operation instructions and self-checking information output by the display device through the signal transmission line, and then forward them to the avionics computing module, and can also be used to send various interactive information to another avionics computing device through the communication bus, so that the interface module of another avionics computing device receives the information correspondingly.

[0091] It can be understood that the ACU avionics computer and the DHA display screen are separated, the avionics computer has multiple types of interfaces, can be arranged in a region concentrated with interconnection systems, receives information input by external systems, then performs avionics computing, graphics generation, and image rendering to generate video signals, and then transmits the video signals to the DHA display screen through optical fibers for display. Compared with the architecture of the integrated IDU, the installation and wiring of the avionics system of the embodiment are more flexible, and the weight of the airborne cable is greatly reduced.

[0092] In the avionics system provided by the embodiment, the avionics computing device can not only realize high computing power of the avionics computing device and display control function, but also reduce the number of modules, installation and wiring are more flexible, and the SWaP (size, weight and power) of the device is reduced, thereby reducing the weight of the entire system, providing an avionics system with a distributed architecture of high reliability, high availability, high performance and low weight, increasing the flexibility and integration of the system compared with the existing avionics system architecture, and reducing the connection cost of the hardware devices in the system.

[0093] The application further provides an aircraft.

[0094] In an embodiment of the application, the aircraft comprises the avionics system as described above.

[0095] It should be noted that the specific architecture of the avionics system refers to the above embodiments. Since the aircraft adopts all the technical solutions of the above embodiments, it at least has all the beneficial effects brought by the technical solutions of the above embodiments, which will not be repeated here.

[0096] The above is only some embodiments of the application, and does not limit the patent scope of the application. Any equivalent structural transformation, direct / indirect application in other related technical fields based on the technical concept of the application, and the contents of the specification and drawings are included in the patent protection scope of the application.

Claims

1. An avionics system, characterized in that, It includes two avionics computing devices and two display devices. The two avionics computing devices are communicatively connected, and each of the display devices is connected to each of the avionics computing devices via a digital video cable and a signal transmission line. Among them, the two avionics computing devices constitute a dual-redundant avionics computing subsystem, providing avionics computing backup; The two avionics computing devices and the two display devices constitute a cross-redundant display control subsystem. When any of the avionics computing devices and / or any of the display devices fails, the display is reconstructed through the other avionics computing devices and display devices besides the failed device, providing a display control backup.

2. The avionics system as described in claim 1, characterized in that, Each of the aforementioned display devices includes: The display unit is connected to the two avionics computing devices respectively via the digital video cable, and the display unit is used to display the received video signal.

3. The avionics system as described in claim 2, characterized in that, Each of the aforementioned display devices further includes: The communication unit is connected to the two avionics computing devices respectively via the signal transmission line. The communication unit is used to output user operation commands based on the user's operation information. The self-test unit is connected to the two avionics computing devices respectively through the signal transmission line. The self-test unit is used to detect equipment faults and output self-test information.

4. The avionics system as described in claim 2 or 3, characterized in that, Each of the aforementioned display devices further includes: The screen freeze detection unit is connected to the two avionics computing devices via the digital video cable and also to the display unit. The screen freeze detection unit is used to perform screen freeze detection based on the received video signal and output the video signal that has passed the detection to the display unit.

5. The avionics system as described in claim 1, characterized in that, Each of the aforementioned avionics computing devices includes: The avionics calculation module is used to perform avionics calculations based on received external information and output graphics processing signals. A graphics processing module is connected to the avionics computing module and is connected to the two display devices respectively via the digital video cable. The graphics processing module is used to generate graphics and render images according to the graphics processing signal, and output two video signals, which are respectively transmitted to the two display devices via the digital video cable. The avionics calculation module is connected to the two display devices respectively through the signal transmission line. The avionics calculation module is also used to receive user operation commands and self-test information output by the display devices through the signal transmission line.

6. The avionics system as described in claim 5, characterized in that, Each of the aforementioned avionics computing devices also includes: The display management module is connected to the avionics computing module and the graphics processing module, respectively, and is also connected to the two display devices through the digital video cable and the signal transmission line, respectively. The display management modules in the two avionics computing devices are connected to each other. The display management module is used to monitor the fault status of each display device and each avionics computing device to provide avionics computing backup and display control backup.

7. The avionics system as described in claim 5 or 6, characterized in that, The avionics computing module uses a multi-core processor, and the graphics processing module uses a dedicated graphics card.

8. The avionics system as described in claim 1, characterized in that, The digital video cable is either a digital video interface (DVI) cable or an optical fiber.

9. The avionics system as described in claim 8, characterized in that, The digital video line is the optical fiber, each of the avionics computing devices includes an electro-optical conversion module, each of the display devices includes an optical-electrical conversion module, and the electro-optical conversion module and the optical-electrical conversion module are connected through the optical fiber.

10. An aircraft, characterized in that, Includes the avionics system as described in any one of claims 1 to 9.

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