Aviation bus interface card and data transmission method

Abstract

The invention provides an aviation bus interface card and a data transmission method, the aviation bus interface card is configured in an all-moving flight simulator, the aviation bus interface card comprises a signal transceiver module and a high-speed data exchange module, the signal transceiver module is connected with a signal transceiver of an aviation bus, and the high-speed data exchange module is connected with the signal transceiver of the aviation bus. The signal receiving and transmitting module is connected with the signal receiving and transmitting module and used for processing received bus signals of an aviation bus type, and the high-speed data exchange module is connected with the signal receiving and transmitting module and used for transmitting the bus signals sent by the signal receiving and transmitting module to an upper computer or transmitting the bus signals sent by the upper computer to the signal receiving and transmitting module according to a transmission queue of a plurality of bus signals. According to the invention, receiving and sending of a single-card multi-protocol aviation bus signal are realized, the integration level of a full-moving flight simulator system is improved, the space occupation of an electronic cabin of the full-moving flight simulator is reduced, the dynamic hardware configurable capability is realized, and the reliability of the system is improved. And the requirements of all-moving flight simulators of different models on aviation bus signals can be met by changing software configuration.

Description

Background Art

[0002] The full-motion flight simulator realizes the subject training and examination of pilots by simulating the aircraft cockpit environment on the ground. Its cockpit consists of a large number of real components, which are externally connected through various signals, mainly including analog signals, discrete signals, and various avionics bus signals (such as ARINC429, ARINC708, AFDX, etc.).

[0003] The prior art docks and aggregates the above signals through a simulator interface system. Users control the transceiver of the system through a general interface such as Ethernet. The simulator interface system generally consists of various general single-protocol avionics bus interface cards, and each interface card is connected to the system main control to achieve data communication and signal transceiver. The existing avionics bus interface cards are not designed specifically for full-motion flight simulators, resulting in a high overall system delay, difficulty in synchronizing and timing different types of signals, a single signal type, and a lack of flexibility.

[0004] Among them, the patent document with the patent number CN202410638535.5 discloses a gigabit Ethernet AFDX end system board based on the miniVPX architecture, which uses miniVPX to implement the AFDX (Avionics Full-Duplex Switched Ethernet) avionics bus. The invention content focuses on the standard features and protocol implementation of AFDX and only supports one type of avionics bus signal, AFDX.

[0005] Furthermore, the patent document with the patent number CN202410346045.8 discloses a comprehensive avionics bus test system that collaboratively controls the avionics bus test function based on the FPGA (Field Programmable Gate Array) and ARM heterogeneous architecture for the automated test of avionics equipment bus communication. The invention content supports multiple avionics bus types, but it is mainly designed for the avionics equipment test scenario and simplifies the test process through methods such as relay switching and automation scripts, without considering the key requirements of full-motion flight simulators such as delay and signal synchronization.

[0006] In addition, the patent document with the patent number CN202311649567.7 discloses an avionics bus multi-protocol conversion chip architecture that realizes a multi-protocol avionics bus at the chip architecture level, improves the overall integration degree by integrating parts such as a computing unit and a transceiver unit, reduces peripheral devices, and increases the radiation tolerance. However, this invention is an innovation at the chip architecture level and has not been specifically optimized for the key requirements of full-motion flight simulators.

[0007] Therefore, there is currently no multi-protocol avionics bus interface card optimized for the key index requirements of full-motion flight simulators, which cannot meet the communication requirements of full-motion flight simulators. Summary of the Invention

[0008] In view of the above technical problems, the technical solution adopted by the present invention is as follows: According to one aspect of the present application, there is provided an avionics bus interface card configured in a full-motion flight simulator. The avionics bus interface card includes: A signal transceiver module connected to signal transceivers of a plurality of avionics buses, for processing bus signals of a plurality of avionics bus types received; A high-speed data exchange module connected to the signal transceiver module, for transmitting the bus signals sent by the signal transceiver module to the host computer or transmitting the bus signals sent by the host computer to the signal transceiver module according to the transmission queues of the plurality of bus signals.

[0009] In an exemplary embodiment of the present application, the signal transceiver module includes: A signal modulation and demodulation module for demodulating the bus signals of the avionics buses received or modulating the bus signals sent by the high-speed data exchange module; A signal timing synchronization module for determining the transmission timings of the plurality of bus signals according to the priorities of the bus types of the plurality of bus signals; A dynamic hardware configuration module for determining the avionics buses and coupling modes corresponding to each signal channel according to the channel configuration preset by the host computer, so as to establish a signal transmission relationship between each signal channel and the avionics bus corresponding to the signal channel.

[0010] In an exemplary embodiment of the present application, the high-speed data exchange module includes: A priority control module for determining the transmission queues of the plurality of bus signals according to the bus types corresponding to the plurality of bus signals and the preset user configuration; A high-speed data transceiver module for building a signal transmission channel between the host computer and the signal transceiver module to transmit the bus signals sent by the signal transceiver module to the host computer and transmit the bus signals sent by the host computer to the signal transceiver module.

[0011] In an exemplary embodiment of the present application, a large-capacity buffer is provided between the high-speed data exchange module and the host computer. The large-capacity buffer is used for storing the bus signals sent by the host computer to the high-speed data exchange module and storing the bus signals sent by the high-speed data exchange module to the host computer.

[0012] In an exemplary embodiment of the present application, the high-speed data exchange module further includes: A large-capacity buffer control module for transmitting the bus signals sent by the signal transceiver module to the large-capacity buffer and transmitting the bus signals stored in the large-capacity buffer to the signal transceiver module; A direct memory access control module is used to configure each signal channel of the signal transceiver module and a large-capacity buffer, so as to transmit the bus signals sent by each signal channel to the large-capacity buffer.

[0013] In an exemplary embodiment of the present application, both between the signal transceiver module and the high-speed data exchange module, and between the high-speed data exchange module and the large-capacity buffer are connected through the AXI bus.

[0014] In an exemplary embodiment of the present application, between the high-speed data exchange module and the host computer are connected through the PCIE high-speed differential bus.

[0015] In an exemplary embodiment of the present application, the protocol types of the avionics buses connected by the signal transceiver module include ARINC429 bus protocol, ARINC708 bus protocol, ARINC453 bus protocol, MIL-STD-1553B bus protocol, AFDX bus protocol; The general signals connected by the signal transceiver module include standard Ethernet signals, analog signals, and discrete signals.

[0016] According to one aspect of the present application, there is also provided a data transmission method for an avionics bus interface card, which is applied to the above-mentioned avionics bus interface card. The data transmission method of the avionics bus interface card includes the following steps: Step S100, establish a connection relationship between the host computer and the high-speed data exchange module and a connection relationship between the signal transceiver module and several avionics buses; each avionics bus transmits bus signals of a unique avionics bus type; Step S200, determine the avionics bus type of the bus signals received and transmitted by each signal channel of the signal transceiver module according to the channel configuration preset by the host computer; Step S300, when the signal transceiver module receives the bus signals sent by any avionics bus, the signal transceiver module demodulates the bus signals to obtain demodulated signals; Step S400, obtain the general signals connected by the signal transceiver module; Step S500, store the demodulated signals and the general signals into the large-capacity buffer; Step S600, the high-speed data exchange module transmits the demodulated signals and the general signals stored in the large-capacity buffer to the host computer.

[0017] In an exemplary embodiment of the present application, after step S200, the data transmission method of the avionics bus interface card further includes: Step S210, when the host computer sends data to be sent, store the data to be sent into the large-capacity buffer; Step S220: The high-speed data exchange module determines the transmission queue of the data to be sent according to the bus type corresponding to the data to be sent and the preset user configuration. Step S230: The high-speed data exchange module sends the data to be sent stored in the large-capacity buffer to the signal transceiver module according to the transmission queue of the data to be sent. Step S240: After receiving the data to be sent, the signal transceiver module performs modulation processing on the data to be sent to obtain a modulated signal. Step S250: The signal transceiver module sends the modulated signal to the corresponding avionics bus according to the signal type of the modulated signal.

[0018] The present invention has at least the following beneficial effects: The avionics bus interface card of the present invention is configured in a full-motion flight simulator. The avionics bus interface card includes a signal transceiver module and a high-speed data exchange module. The signal transceiver module is connected to the signal transceivers of several avionics buses and is used to process the bus signals of several avionics bus types received. The high-speed data exchange module is connected to the signal transceiver module and is used to transmit the bus signals sent by the signal transceiver module to the host computer according to the transmission queue of several bus signals, or transmit the bus signals sent by the host computer to the signal transceiver module, so as to realize the reception and transmission of single-card multi-protocol avionics bus signals, improve the integration degree of the full-motion flight simulator system, reduce the space occupancy of the full-motion flight simulator's electronics bay, and have the ability of dynamic hardware configuration. By changing the software configuration, the requirements of different models of full-motion flight simulators for avionics bus signals can be met, reducing the system's reuse cost. It also has a signal synchronization mechanism, which can ensure the synchronization and timing of different types of signals, reducing the configuration difficulty of the full-motion flight simulator's timing. Moreover, the avionics bus interface card of the present invention has low-latency data transmission with the host computer (user computer), greatly reducing the overall delay introduced by signal conversion and improving the data refresh efficiency of the full-motion flight simulator. Description of the Drawings

[0019] In order to more clearly illustrate the technical solutions in the embodiments of the present invention, the following will briefly introduce the drawings required for the description of the embodiments. Obviously, the following drawings are only some embodiments of the present invention. For those of ordinary skill in the art, other drawings can be obtained based on these drawings without creative efforts. [[ID=Y18]]

[0020] Figure 1 It is a composition framework diagram of the avionics bus interface card provided by the embodiment of the present invention; Figure 2 It is an operation flow chart of the avionics bus interface card provided by the embodiment of the present invention; Figure 3 Schematic diagram of low-latency transmission operation of the avionics bus interface card provided by the embodiments of the present invention. Detailed implementation manners

[0021] Next, the technical solutions in the embodiments of the present invention will be clearly and completely described in conjunction with the accompanying drawings in the embodiments of the present invention. Obviously, the described embodiments are only a part of the embodiments of the present invention, rather than all the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without creative efforts shall fall within the protection scope of the present invention.

[0022] This application proposes an avionics bus interface card, which is configured in a full-motion flight simulator. As Figure 1 shown, the avionics bus interface card is connected to the host computer (i.e., the user computer) of the full-motion flight simulator. A supporting driver program and software interface are run in the host computer. The user performs read and write operations on the avionics bus interface card through the software interface to achieve the configuration and control of the avionics bus interface card.

[0023] The avionics bus interface card is also connected to several signal transceivers, including transceivers for ARINC429 bus, ARINC708 bus, ARINC453 bus, MIL-STD-1553B bus, AFDX bus, transceivers for standard Ethernet signals, converters for analog signals, converters for discrete signals, etc. The several signal transceivers are connected to the front panel connector of the full-motion flight simulator. The front panel connector of the full-motion flight simulator is the connector of the operation panel of the full-motion flight simulator.

[0024] Among them, the avionics bus interface card is implemented by FPGA (Field Programmable Gate Array). The avionics bus interface card includes a signal transceiver module and a high-speed data exchange module.

[0025] The signal transceiver module is connected to the signal transceivers of several avionics buses, and is used for modulating and / or demodulating the received bus signals of several avionics bus types (multi-protocol avionics buses, multi-type general signals).

[0026] The high-speed data exchange module is connected to the signal transceiver module through the AXI bus, and is used for transmitting the bus signals sent by the signal transceiver module to the host computer according to the transmission queue of several bus signals, or transmitting the bus signals sent by the host computer to the signal transceiver module.

[0027] Among them, the protocol types of the multi-protocol avionics bus connected to the signal transceiver module include ARINC429 bus protocol, MIL-STD-1553B bus protocol, ARINC708 bus protocol, ARINC453 bus protocol, and AFDX bus protocol; the multi-type general signals connected to the signal transceiver module include standard Ethernet signals, analog signals, and discrete signals.

[0028] The ARINC429 bus is a differential twisted pair wire, which is a unidirectional broadcast transmission bus. Only one transmitter is allowed on one bus, but multiple receivers (up to 20) are allowed. The rates are divided into two types: 100 kb / s and 12.5 kb / s. It is the most common type of airborne bus in existing civil aviation aircraft. Most important signals on the aircraft are transmitted through this protocol, including aircraft position, altitude, speed, heading, engine status, various warning messages, fuel information, etc. Almost every device on the aircraft, from an aviation clock to engine control, includes ARINC429 communication capabilities.

[0029] The Chinese name of the MIL-STD-1553B bus is the digital time-division command / response type multiplex data bus. It is an airborne bus standard for military aircraft. It uses Manchester coding technology and is transmitted through twisted pair wires. The rate is 1 Mbps. Multiple devices are allowed to be mounted on one bus, and each device can have different roles. It is widely used in various airborne devices on military aircraft.

[0030] The ARINC708 bus is simplified from MIL-STD-1553B. It is a bus dedicated to airborne weather radars on civil aviation aircraft. The size of each frame is fixed at 1600 bit, including echo information and target tracking information of the airborne weather radar. Multiple data frames can be combined to form a complete weather radar image.

[0031] The ARINC453 bus is a bus similar to ARINC708 that emerged due to the too low transmission rate of ARINC429. Different from ARINC708 which can only transmit weather radar data and has a fixed frame size, ARINC453 can transmit various general data at a higher rate.

[0032] The AFDX bus, also known as ARINC664, is a new generation of avionics bus technology. It is based on Ethernet at the hardware level and can achieve a transmission rate of up to 1000 Mbps. It is used to replace the ARINC429 bus with a lower rate and is the main communication method for the airborne equipment of new generation aircraft. New generation aircraft such as the Airbus A380 and the Commercial Aircraft Corporation of China C919 have adopted this type of bus.

[0033] The Ethernet signal is the wired network signal. Non-critical devices on the aircraft use this technology to reduce costs.

[0034] Analog signals are mainly used to collect information from various sensors. Discrete signals are input for signal acquisition of airborne equipment, and discrete signals are output for driving airborne equipment. General airborne equipment (such as standby instruments) will include several communication buses (such as ARINC429), and also require some discrete signal inputs (such as the status of indicator lights), and will itself give some discrete and analog signal outputs (such as the status of switches and buttons on the instrument).

[0035] A large-capacity buffer is set between the high-speed data exchange module and the host computer. The large-capacity buffer is implemented based on Double Data Rate (DDR) synchronous dynamic random access memory. The high-speed data exchange module and the large-capacity buffer are connected through the AXI bus, and the high-speed data exchange module and the host computer are connected through the PCIE high-speed differential bus. The large-capacity buffer is used to store the bus signals sent by the host computer to the high-speed data exchange module, and to store the bus signals sent by the high-speed data exchange module to the host computer.

[0036] As Figure 3 shown, based on the operating characteristics of the full-motion flight simulator, a low-latency data channel is constructed between the high-speed data exchange module and the host computer through the PCIE high-speed differential bus and the Direct Memory Access (DMA) technology.

[0037] Furthermore, the signal transceiver module includes a signal modulation and demodulation module, a signal timing synchronization module, and a dynamic hardware configuration module.

[0038] The signal modulation and demodulation module is used to demodulate the bus signals of the aviation bus received, or to modulate the bus signals sent by the high-speed data exchange module.

[0039] The signal timing synchronization module is used to determine the transmission timing of several bus signals according to the priority of the bus types of several bus signals, so as to have a signal synchronization and timing mechanism. Based on a high-precision clock source (such as Figure 1 the high-precision clock source in), a nanosecond-level timestamp is embedded for data transmission, and priority scheduling and time slot allocation are performed on different protocol data to ensure that the transmissions of different types of aviation buses meet the overall timing requirements.

[0040] The dynamic hardware configuration module is used to determine the avionics bus and coupling method corresponding to each signal channel according to the channel configuration preset by the host computer, so as to establish the signal transmission relationship between each signal channel and the avionics bus corresponding to this signal channel, so as to have the ability of dynamic hardware configurability. The same signal channel can be configured as different types of avionics buses and coupling methods through software, including: configuring the transceiver switch of the ARINC429 bus to receive or transmit through software; configuring the avionics bus type as one of ARINC708 / ARINC453 / MIL-STD-1553B through software, and configuring the coupling mode switch as one of direct coupling and transformer coupling through software; configuring the avionics bus type as one of AFDX / standard Ethernet through software, and configuring or adapting to the 10 / 100 / 1000 Mbps rate mode through software; configuring the input / output switching of analog and discrete signals through software.

[0041] Furthermore, the high-speed data exchange module includes a priority control module, a high-speed data transceiver module, a large-capacity buffer control module, and a direct memory access control module.

[0042] The priority control module is used to determine the transmission queue of several bus signals according to the bus types corresponding to the several bus signals and the preset user configuration, so as to meet the scenario of mixed reception and transmission of multi-priority data.

[0043] When determining the transmission queue of several bus signals, the priority control module first judges the priority of the bus signals according to the data types of the bus signals. Each data type has its own inherent priority. Three types of data belonging to different priorities are listed: alarm information (such as emergency information, fault information), control signals (such as throttle position), and information with low non-critical or real-time requirements (such as cabin lights, avionics clock). Based on this, a preliminary transmission queue will be formed. On this basis, the user can queue additional data into this queue as needed, or modify the priorities of some data to meet the overall timing. For example, the data of the airborne weather radar must be sent strictly in accordance with the radar screen scanning order and interval during transmission, otherwise there will be abnormal display or misalignment. Another example is the avionics clock. The time signals it displays are distributed in multiple data packets, and these data packets must also arrive in strict order to be parsed normally. Therefore, the transmission queue of the bus signals can be determined according to the data type (i.e., the bus type), or the transmission queue of the bus signals can be adjusted according to the actual needs of the user.

[0044] The high-speed data transceiver module is used to build a signal transmission channel between the host computer and the signal transceiver module, so as to transmit the bus signals sent by the signal transceiver module to the host computer, and transmit the bus signals sent by the host computer to the signal transceiver module.

[0045] The large-capacity buffer control module is used to transmit the bus signals sent by the signal transceiver module to the large-capacity buffer, and to transmit the bus signals stored in the large-capacity buffer to the signal transceiver module.

[0046] The direct memory access control module combines the internal bus of the full-motion flight simulator and direct memory access, and is used to configure each signal channel of the signal transceiver module and the large-capacity buffer, so as to transmit the bus signals sent by each signal channel to the large-capacity buffer, allocate the large-capacity buffer to each signal channel of the signal transceiver module according to the configuration, and users can send and receive data through direct reading and writing of specific address areas, thereby building a low-latency data channel between the high-speed data exchange module and the host computer.

[0047] After the host computer is connected to the avionics bus interface card and issues channel configurations, subsequent avionics bus data transmission and reception are both carried out through DMA and the large-capacity buffer. The entire address range of the DDR memory is divided and allocated to each receive and transmit channel (the signal channels of the signal transceiver module) according to the configuration, without overlapping or sharing with each other, to avoid possible data errors. The host computer can access any address in the DDR buffer on the avionics bus interface card with extremely low latency during data transmission and reception through DMA and the memory read / write controller, and indicates the operation of data transmission and reception of the high-speed data exchange module through specific control fields in the data packet.

[0048] On the other hand, the present application also proposes a data transmission method for an avionics bus interface card, which is applied to the above-mentioned avionics bus interface card. As Figure 2 shown, the data transmission method of the avionics bus interface card includes the following steps: Step S100: Establish a connection relationship between the host computer and the high-speed data exchange module and a connection relationship between the signal transceiver module and several avionics buses; each avionics bus transmits bus signals of a unique avionics bus type. Step S200: Determine the avionics bus type or coupling method of the bus signals received and transmitted by each signal channel of the signal transceiver module according to the channel configuration preset by the host computer. Step S300: When the signal transceiver module receives the bus signals sent by any avionics bus (during the signal reception process), the signal transceiver module demodulates the bus signals to obtain demodulated signals. Step S400: Obtain the general signals connected to the signal transceiver module. Step S500: Store the demodulated signals and the general signals into the large-capacity buffer. Step S600: The high-speed data exchange module transmits the demodulated signals and the general signals stored in the large-capacity buffer to the host computer.

[0049] In addition, the data transmission method of the aviation bus interface card further includes a signal sending process, that is, after step S200, the data transmission method of the aviation bus interface card further includes steps S210 - S250: Step S210, when the host computer sends data to be sent, store the data to be sent in the large-capacity buffer; Step S220, the high-speed data exchange module determines the transmission queue of the data to be sent according to the bus type corresponding to the data to be sent and the preset user configuration; Step S230, the high-speed data exchange module sends the data to be sent stored in the large-capacity buffer to the signal transceiver module according to the transmission queue of the data to be sent; Step S240, after receiving the data to be sent, the signal transceiver module performs modulation processing on the data to be sent to obtain a modulated signal; Step S250, the signal transceiver module sends the modulated signal to the aviation bus corresponding to the signal type of the modulated signal according to the signal type of the modulated signal.

[0050] When the transceiver of any signal channel of the signal transceiver module ends, close the signal channel according to the channel disable instruction sent by the host computer.

[0051] The aviation bus interface card of the present invention is configured in a full-motion flight simulator. The aviation bus interface card includes a signal transceiver module and a high-speed data exchange module. The signal transceiver module is connected to the signal transceivers of several aviation buses and is used to process the bus signals of several aviation bus types received. The high-speed data exchange module is connected to the signal transceiver module and is used to transmit the bus signals sent by the signal transceiver module to the host computer or transmit the bus signals sent by the host computer to the signal transceiver module according to the transmission queues of several bus signals, so as to realize the reception and transmission of single-card multi-protocol aviation bus signals, improve the integration degree of the full-motion flight simulator system, reduce the space occupation of the electronic compartment of the full-motion flight simulator, and have the ability of dynamic hardware configuration. By changing the software configuration, the requirements of different types of full-motion flight simulators for aviation bus signals can be met, the reuse cost of the system is reduced, and it also has a signal synchronization mechanism, which can ensure the synchronization and timing of different types of signals, reduce the configuration difficulty of the timing of the full-motion flight simulator, and the aviation bus interface card of the present invention has low-latency data transmission with the host computer (user computer), greatly reducing the overall delay introduced by signal conversion and improving the data refresh efficiency of the full-motion flight simulator.

[0052] The embodiment of the present invention also provides a computer program product, which includes program codes. When the program product runs on an electronic device, the program codes are used to cause the electronic device to execute the steps in the methods according to various exemplary embodiments of the present invention described above in this specification.

[0053] In addition, although the steps of the methods in the present disclosure are described in a specific order in the drawings, this does not require or imply that these steps must be performed in that specific order, or that all of the steps shown must be performed to achieve the desired result. Additionally or alternatively, certain steps may be omitted, multiple steps may be combined into one step for execution, and / or one step may be decomposed into multiple steps for execution, etc.

[0054] From the description of the above embodiments, those skilled in the art can easily understand that the exemplary embodiments described herein can be implemented by software, or by a combination of software and necessary hardware. Therefore, the technical solutions according to the embodiments of the present disclosure can be embodied in the form of a software product, which can be stored in a non-volatile storage medium (which can be a CD-ROM, a USB flash drive, a portable hard drive, etc.) or on a network, including several instructions to enable a computing device (which can be a personal computer, a server, a mobile terminal, or a network device, etc.) to execute the methods according to the embodiments of the present disclosure.

[0055] In an exemplary embodiment of the present disclosure, there is also provided an electronic device capable of implementing the above method.

[0056] Those skilled in the art can understand that various aspects of the present invention can be implemented as a system, a method, or a program product. Therefore, various aspects of the present invention can be specifically implemented in the following forms, namely: a complete hardware implementation, a complete software implementation (including firmware, microcode, etc.), or an implementation combining hardware and software aspects, which can be collectively referred to herein as "circuitry", "module", or "system".

[0057] An electronic device according to this embodiment of the present invention. The electronic device is merely an example and should not impose any limitation on the functions and usage scope of the embodiments of the present invention.

[0058] The electronic device is presented in the form of a general-purpose computing device. The components of the electronic device may include, but are not limited to: at least one of the above-mentioned processors, at least one of the above-mentioned memories, and a bus connecting different system components (including the memory and the processor).

[0059] Wherein, the memory stores program code, and the program code can be executed by the processor, so that the processor executes the steps according to various exemplary embodiments of the present invention described in the above "Exemplary Method" section of this specification.

[0060] The memory may include a readable medium in the form of a volatile memory, such as a random access memory (RAM) and / or a cache memory, and may further include a read-only memory (ROM).

[0061] The memory may also include a program / utility having a set (at least one) of program modules, such program modules including but not limited to: an operating system, one or more application programs, other program modules, and program data, and implementation of a network environment may be included in each or some combination of these examples.

[0062] The bus may represent one or more of several types of bus structures, including a memory bus or memory controller, a peripheral bus, a graphics acceleration port, a processor, or a local bus using any of a variety of bus structures.

[0063] The electronic device may also communicate with one or more external devices (such as a keyboard, a pointing device, a Bluetooth device, etc.), may also communicate with one or more devices that enable a user to interact with the electronic device, and / or may communicate with any device that enables the electronic device to communicate with one or more other computing devices (such as a router, a modem, etc.). Such communication may be through an input / output (I / O) interface. Further, the electronic device may also communicate with one or more networks (such as a local area network (LAN), a wide area network (WAN), and / or a public network, such as the Internet) through a network adapter.

[0064] In an exemplary embodiment of the present disclosure, there is also provided a computer-readable storage medium having stored thereon a program product capable of implementing the above-described method of this specification. In some possible implementation manners, various aspects of the present invention may also be implemented in the form of a program product, which includes program code that, when the program product runs on a terminal device, is used to cause the terminal device to execute the steps according to various exemplary embodiments of the present invention described in the above "Exemplary Method" section of this specification.

[0065] The program product may employ any combination of one or more readable media. The readable media may be a readable signal medium or a readable storage medium. The readable storage medium may, for example, but not be limited to, an electrical, magnetic, optical, electromagnetic, infrared, or semiconductor system, apparatus, or device, or any combination of the above. More specific examples (a non-exhaustive list) of the readable storage medium include: an electrical connection having one or more wires, a portable disk, a hard disk, a random access memory (RAM), a read-only memory (ROM), an erasable programmable read-only memory (EPROM or flash memory), an optical fiber, a portable compact disc read-only memory (CD-ROM), an optical storage device, a magnetic storage device, or any suitable combination of the above.

[0066] A computer-readable signal medium may include a data signal propagated in a baseband or as part of a carrier wave, in which readable program code is carried. Such a propagated data signal may take many forms, including but not limited to electromagnetic signals, optical signals, or any suitable combination of the foregoing. The readable signal medium may also be any readable medium other than a readable storage medium, which can send, propagate, or transmit a program for use by or in conjunction with an instruction execution system, apparatus, or device.

[0067] The program code contained on the readable medium may be transmitted with any appropriate medium, including but not limited to wireless, wired, optical fiber cable, RF, etc., or any suitable combination of the foregoing.

[0068] The program code for performing the operations of the present invention may be written in any combination of one or more programming languages, including object-oriented programming languages such as Java, C++, etc., and also including conventional procedural programming languages such as the "C" language or similar programming languages. The program code may be executed entirely on the user computing device, partially on the user device, executed as a stand-alone software package, partially on the user computing device and partially on a remote computing device, or entirely on a remote computing device or server. In the case of a remote computing device, the remote computing device may be connected to the user computing device through any kind of network, including a local area network (LAN) or a wide area network (WAN), or may be connected to an external computing device (e.g., by using an Internet service provider to connect through the Internet).

[0069] In addition, the above drawings are only schematic illustrations of the processes included in the method according to the exemplary embodiments of the present invention, and are not for limiting purposes. It is easy to understand that the processes shown in the above drawings do not indicate or limit the time sequence of these processes. Additionally, it is also easy to understand that these processes may be executed synchronously or asynchronously, for example, in multiple modules.

[0070] It should be noted that although several modules or units of devices for action execution are mentioned in the above detailed description, such a division is not mandatory. In fact, according to the embodiments of the present disclosure, the features and functions of two or more of the above-mentioned modules or units may be embodied in one module or unit. Conversely, the features and functions of one module or unit described above may be further divided and embodied by multiple modules or units.

[0071] As described above, it is only the specific implementation manner of the present invention, but the protection scope of the present invention is not limited thereto. Any changes or substitutions that can be easily thought of by those skilled in the art within the technical scope disclosed by the present invention should be covered within the protection scope of the present invention. Therefore, the protection scope of the present invention shall be subject to the protection scope of the claims.

Claims

1. An aviation bus interface card, characterized in that, Configured in a full-motion flight simulator, the avionics bus interface card includes: A signal transceiver module connected to signal transceivers of several avionics buses, for processing bus signals of several avionics bus types received; A high-speed data exchange module connected to the signal transceiver module, for transmitting the bus signals sent by the signal transceiver module to the host computer according to the transmission queues of several bus signals, or transmitting the bus signals sent by the host computer to the signal transceiver module; Among them, the signal transceiver module includes: A signal modulation and demodulation module for demodulating the bus signals of the avionics bus received, or modulating the bus signals sent by the high-speed data exchange module; A signal timing synchronization module for determining the transmission timings of several bus signals according to the priorities of the bus types of several bus signals; A dynamic hardware configuration module for determining the avionics bus and coupling mode corresponding to each signal channel according to the channel configuration preset by the host computer, so as to establish a signal transmission relationship between each signal channel and the avionics bus corresponding to this signal channel; Among them, the high-speed data exchange module includes: A priority control module for determining the transmission queues of several bus signals according to the bus types corresponding to several bus signals and the preset user configuration; A high-speed data transceiver module for building a signal transmission channel between the host computer and the signal transceiver module, so as to transmit the bus signals sent by the signal transceiver module to the host computer, and transmit the bus signals sent by the host computer to the signal transceiver module.

2. The aviation bus interface card according to claim 1, characterized in that, A large-capacity buffer is arranged between the high-speed data exchange module and the host computer, and the large-capacity buffer is used for storing the bus signals sent by the host computer to the high-speed data exchange module, and storing the bus signals sent by the high-speed data exchange module to the host computer.

3. The aviation bus interface card according to claim 2, characterized in that The high-speed data exchange module further includes: A large-capacity buffer control module for transmitting the bus signals sent by the signal transceiver module to the large-capacity buffer, and transmitting the bus signals stored in the large-capacity buffer to the signal transceiver module; A direct memory access control module for configuring each signal channel of the signal transceiver module and the large-capacity buffer, so as to transmit the bus signals sent by each signal channel to the large-capacity buffer.

4. The aviation bus interface card according to claim 3, characterized in that, Both between the signal transceiver module and the high-speed data exchange module, and between the high-speed data exchange module and the large-capacity buffer are connected through the AXI bus.

5. The aviation bus interface card according to claim 4, characterized in that, Between the high-speed data exchange module and the host computer is connected through the PCIE high-speed differential bus.

6. The aviation bus interface card according to claim 5, characterized in that, The protocol types of the avionics buses connected by the signal transceiver module include ARINC429 bus protocol, ARINC708 bus protocol, ARINC453 bus protocol, MIL-STD-1553B bus protocol, AFDX bus protocol; The general signals connected by the signal transceiver module include standard Ethernet signals, analog signals, and discrete signals.

7. A data transmission method for an avionics bus interface card, characterized in that Applied to the avionics bus interface card as described in any one of claims 2-6, the data transmission method of the avionics bus interface card comprises the following steps: Step S100, establish a connection relationship between the host computer and the high-speed data exchange module and a connection relationship between the signal transceiver module and several avionics buses; each of the avionics buses transmits bus signals of a unique avionics bus type; Step S200, determine the avionics bus type of the bus signals received and transmitted by each signal channel of the signal transceiver module according to the channel configuration preset by the host computer; Step S300, when the signal transceiver module receives the bus signals sent by any one of the avionics buses, the signal transceiver module demodulates the bus signals to obtain demodulated signals; Step S400, obtain the general signals connected to the signal transceiver module; Step S500, store the demodulated signals and the general signals into the large-capacity buffer; Step S600, the high-speed data exchange module transmits the demodulated signals and the general signals stored in the large-capacity buffer to the host computer.

8. The data transmission method of the avionics bus interface card according to claim 7, characterized in that, After the step S200, the method further comprises: Step S210, when the host computer sends data to be sent, store the data to be sent into the large-capacity buffer; Step S220, the high-speed data exchange module determines the transmission queue of the data to be sent according to the bus type corresponding to the data to be sent and the preset user configuration; Step S230, the high-speed data exchange module sends the data to be sent stored in the large-capacity buffer to the signal transceiver module according to the transmission queue of the data to be sent; Step S240, after receiving the data to be sent, the signal transceiver module modulates the data to be sent to obtain modulated signals; Step S250, the signal transceiver module sends the modulated signals to the avionics bus corresponding to the signal type of the modulated signals according to the signal type of the modulated signals.

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