CN208188636U - A kind of more member's aircraft avionics systems - Google Patents

Abstract

The utility model discloses a kind of more member's aircraft avionics systems comprising: mode control panel MCP, primary flight display PFD, multifunction display MFD, automatic Pilot/flight director AP/FD, flight management system FMS, tuning control panel TCP, audio-frequency control panel ACP, data interface unit DIU, air data system ADS, inertial navigation/GPS combined navigation system INS/GPS, VHF radio VHF, ILS/VOR and multitask audio frequency controller unit AMU.The double redundancy transmission and processing of airborne equipment data are carried out by the first data interface unit and the second data interface unit, and pass through with the realizing high-reliability flight management of unified flight management system, the problem of overcoming the larger more member's flight management system volume and weights of tradition and higher cost, can be applied to the integrated avionic system upgrading of the more member's aircrafts of various tradition.

Description

A kind of more member's aircraft avionics systems

Technical field

The utility model relates to avionic device technical field more particularly to a kind of more member's aircraft avionics systems.

Background technique

The information of avionic devices various on aircraft is carried out at unified usually using unified processor on modern aircraft Reason combines the same or similar equipment of function in a component, over the display the relevant parameter of synthesis display, and each It is transmitted between avionic device by airborne databus for information about, so that all aviation electronics on entire aircraft be made to set Standby performance reaches higher level, and such system is known as integrated avionic system.

However, due to the more member's aircrafts of tradition there are flight management system and data processing Redundancy Designs excessively and avionics System is excessively dispersed, and leads to system bulk and weight is larger and higher cost.Moreover, original system can not with it is existing each Kind airborne equipment docking leads to system entirety it is thus impossible to take into account Data Centralized Processing and system margin backup design well Reliability is lower, and is inconvenient to carry out follow-up system extension or upgrading.

Utility model content

One of the purpose of this utility model at least that, for how to overcome the above-mentioned problems of the prior art, provide A kind of more member's aircraft avionics systems can be improved the system integration suitable for the various general-purpose aircrafts with multiple flight members Degree, while reducing total weight, guarantees the safety and reliability of aircraft.

To achieve the goals above, the technical solution adopted in the utility model includes following aspects.

A kind of more member's aircraft avionics systems comprising: it is mode control panel MCP, primary flight display PFD, multi-functional Display MFD, automatic Pilot/flight director AP/FD, flight management system FMS, tuning control panel TCP, audio frequency control face Plate ACP, data interface unit DIU, air data system ADS, inertial navigation/GPS combined navigation system INS/GPS, very High frequency radio set VHF, instrument-landing-system/VHF Omnidirection range multimode rake receiver ILS/VOR and multitask audio frequency controller list First AMU；

Wherein, the MCP, for be arranged the flight control mode of aircraft, navigation channel, course, flying height, ramp rate and Flying speed with a variety of man-machine interactive interfaces to receive the setting instruction of pilot's input, and passes through multiple communication interfaces It is respectively connected to the first PFD, the first MFD, the 2nd PFD, the 2nd MFD and AP/FD；

First PFD and the 2nd PFD is respectively for display posture instruction interface, flying speed and height instruction interface, vertical Speed indicates interface and bearing indication interface, and receives setting instruction from human-computer interaction interface, setting instruction based on the received Change the corresponding contents shown in interface；

First MFD and the 2nd MFD are disposed as the integral structure with processor and display, respectively for flying Information integration shows, engine monitoring, flight parameter configuration and air pressure and environmental Kuznets Curves；AP/FD is used for according to instruction certainly Dynamic control aircraft trace, adjusts aspect；

FMS has full liquid crystal display and infrared touch panel and processor, for inputting and/or showing aircraft programs, speed Degree control and navigation control data, and connect with AP/FD to send automatic Pilot control instruction, with each data interface unit DIU connection is to receive airborne device data and send control instruction, also with each tuning control panel TCP connection to send tuning It instructs and receives tuning data；

First DIU and the 2nd DIU is respectively used to carry out data acquisition, data processing and data distribution, and wherein data acquire It include the data that will be acquired including obtaining data that each airborne equipment is sent and its status data, data processing by communication interface Packet is set for unpacking and organized according to target device；

First TCP and the first ACP passes through spare communication interface and is directly connected to the first VHF and the first ILS/VOR, and second TCP and the 2nd ACP passes through spare communication interface and is directly connected to the 2nd VHF and the 2nd ILS/VOR, in data interface unit Tuning and the audio frequency control of emergency communication are carried out when the channel of offer is unavailable；

AMU is connect with the first DIU and the 2nd DIU, and is respectively connected to the first ACP and the 2nd ACP；AMU is equal at work It first passes through the first DIU or the 2nd DIU and receives the audio frequency control instruction from audio-frequency control panel, and carry out audio data processing； And it directly receives the audio frequency control from audio-frequency control panel when data interface unit breaks down to instruct and carry out audio Data processing.

Preferably, the first PFD and the 2nd PFD is used to be instructed according to setting, and one in the two is set as navigating Display, to show next destination, current wind speed and direction current line navigation information.

Preferably, the first MFD and the 2nd MFD is used for when showing dimensional topography view, is changed according to setting instruction State of weather shows specified landform synthesis visual pattern and corresponding flight and weather data under a variety of weather conditions, schemes Table, aircraft system information and range planning information.

Preferably, the AP/FD includes multiple sensing elements for sensing aspect variable signal, for according to appearance State variable signal calculates the processor of amendment rudder deviator, and for rudder face to be adjusted to multiple servo mechanisms to required position.

Preferably, the first DIU and the 2nd DIU with answering machine/Automatic dependent surveillance broadcast system XPDR/ADS- B, weather radar WXR, range finder DME, radio altimeter RA and Automatic Direction Finder ADF are connected and are received data and transmission Control instruction；And the first DIU and the 2nd DIU are provided with mutually redundant direct-connected communication interface, are connect with a data wherein Mouth unit carries out the transmission and processing of airborne equipment data by another data interface unit when breaking down.

Preferably, the first DIU and the first TCP, the first ACP, the first ADS, the first INS/GPS, the first VHF and First ILS/VOR connection to receive data and send the data to the first PFD, the first MFD and FMS, the 2nd DIU and the 2nd TCP, 2nd ACP, the 2nd ADS, the 2nd INS/GPS, the 2nd VHF and the 2nd ILS/VOR connection are to receive data and send data To the 2nd PFD, the 2nd MFD and FMS.

Preferably, the first DIU or the 2nd DIU further with high frequency radio set HF, satellite communication system SATCOM, aerial Anti-collision system TCAS connection, to send and receive corresponding data.

Preferably, the indicator screen of the PFD and MFD is disposed as with infrared touch structure, to support multiple spot to touch It touches, and control switching, selection is realized by key on display frame and knob, adjusted and tuning.

Preferably, each of described data interface unit includes the FPGA and CPU connected by SRIO interface； Wherein, FPGA includes multiple serial input interfaces, the data sent for receiving multiple airborne equipment data channel；It is multiple with The reception cache module of serial input interface connection, for carrying out temporal cache to the data from each channel；With each reception First group of packet module of cache module connection, for packaging according to preset coding mode the data of caching to obtain the One heartbeat data packets, and the first heartbeat data packets are passed through by the SRIO interface between FPGA and CPU according to scheduled heart beat cycle It is sent to CPU；CPU includes unpacking module, for reading according to preset coding mode from the first heartbeat data packets from FPGA Take the data in each channel；Data processing module is handled for the data to each channel, is generated for each airborne equipment Control data；Second group of packet module packages for that will control data according to preset coding mode, to obtain the second heartbeat Data packet, and FPGA is sent to according to scheduled second heart beat cycle；FPGA further comprises: connecting with each transmission cache module The decoding module connect for reading the control data for being directed to each airborne equipment in the second heartbeat data packets, and is sent to corresponding Transmission cache module；Multiple transmission cache modules are respectively connected to multiple serial output interfaces and at least one Ethernet Interface, and control data are sent to each airborne equipment at a predetermined rate according to communication protocol corresponding with interface.

Preferably, the communication interface includes one or more of serial communication interface and Ethernet interface.

In conclusion by adopting the above-described technical solution, the utility model at least has the advantages that

Pass through the first data interface unit and the second number according to more member's aircraft avionics systems of the utility model embodiment The double redundancy transmission and processing of airborne equipment data are carried out according to interface unit, and height is realized by unified flight management system The flight management of reliability ground overcomes the more member's flight management systems of tradition and data processing Redundancy Design excessively and boat Electric system is excessively dispersed, and is led to system bulk and the problem of weight is larger and higher cost, can improved integrated avionic system Integrated level and reliability while, keep open access structure, convenient for various airborne equipments access, it is ensured that system configuration spirit Living, extension is convenient, can be applied to the integrated avionic system upgrading of the more member's aircrafts of various tradition.

Detailed description of the invention

Fig. 1 is the structural schematic diagram according to more member's aircraft avionics systems of the utility model embodiment.

Specific embodiment

With reference to the accompanying drawings and embodiments, the present invention will be further described in detail, so that the utility model Objects, technical solutions and advantages are more clearly understood.It should be appreciated that specific embodiment described herein is only to explain this reality With novel, it is not used to limit the utility model.

Fig. 1 shows the structure of more member's aircraft avionics systems according to the utility model embodiment, the side of specifically including that Formula control panel MCP, primary flight display PFD, multifunction display MFD, automatic Pilot/flight director AP/FD, tof tube Reason system FMS, tuning control panel TCP, audio-frequency control panel ACP, data interface unit DIU, air data system ADS, it is used to Property navigation/GPS combined navigation system INS/GPS, VHF radio VHF, instrument-landing-system/VHF Omnidirection range Multimode rake receiver ILS/VOR, answering machine/Automatic dependent surveillance broadcast system XPDR/ADS-B, weather radar WXR, range finder DME, radio altimeter RA, Automatic Direction Finder ADF, multitask audio frequency controller unit AMU.

Wherein, mode control panel MCP, for flight control mode, navigation channel, course, flying height, the liter of aircraft to be arranged Reduction of speed rate and flying speed etc. are flown with a variety of man-machine interactive interfaces (such as key, knob, touching display screen etc.) with receiving The setting instruction of office staff's input, and the first primary flight display PFD1, more than first function are respectively connected to by multiple communication interfaces It can display MFD1, the second primary flight display PFD2, the second multifunction display MFD2 and automatic Pilot/flight director Instrument AP/FD.

First primary flight display PFD1 and the second primary flight display PFD2 indicates interface respectively for display posture, flies Scanning frequency degree and height instruction interface, vertical speed instruction interface and bearing indication interface, and set from human-computer interaction interface reception Instruction is set, setting instruction changes corresponding contents (such as the amplification display speed or heading device shown in interface based on the received Breath).And it is possible to be instructed according to setting, by one in the first primary flight display PFD1 and the second primary flight display PFD2 It is a to be set as navigation indicator, to show the current lines navigation informations such as next destination, current wind speed and direction.

First multifunction display MFD1 and the second multifunction display MFD2 are disposed as with processor and display Integral structure, respectively for carrying out flight information integrative display, engine monitoring, flight parameter configuration and air pressure and ring Border control.For example, being instructed according to setting when showing dimensional topography view and changing state of weather, check pilot Specified landform synthesis visual pattern and corresponding flight and weather data, chart, aircraft system letter under various weather conditions Breath and range planning information.

Automatic Pilot/flight director AP/FD, for adjusting aspect according to instruction autoplane track, Including multiple sensing elements for sensing aspect variable signal, for calculating amendment rudder deviator according to attitudes vibration signal Processor, and for by rudder face adjust to required position multiple servo mechanisms.

Flight management system FMS has full liquid crystal display and infrared touch panel and processor, for inputting and/or showing Show flight plan, speed control and navigation control data, and connect with automatic Pilot/flight director AP/FD to send automatically Driving control instruction, connect with each data interface unit DIU to receive airborne device data and send control instruction, also and often A tuning control panel TCP connection is to send tuning instruction and receive tuning data.

First data interface unit DIU1 and the second data interface unit DIU2 is respectively used to carry out data acquisition, at data Reason and data distribution, wherein data acquisition includes that the data and its status number that each airborne equipment is sent are obtained by communication interface According to data processing includes being set for unpacking and organizing packet according to target device for the data of acquisition.Specifically, the first data connect Mouthful cells D IU1 and the second data interface unit DIU2 with answering machine/Automatic dependent surveillance broadcast system XPDR/ADS-B, Weather radar WXR, range finder DME, radio altimeter RA and Automatic Direction Finder ADF connect and receive data and send control System instruction；Also, the first data interface unit DIU1 and first tuning control panel TCP1, the first audio-frequency control panel ACP1, First air data system ADS1, the first inertial navigation/GPS combined navigation system INS/GPS1, the first VHF radio VHF1 and first instrument landing system/VHF Omnidirection range multimode rake receiver ILS/VOR1 connection are to receive data and incite somebody to action Data are sent to the first primary flight display PFD1, the first multifunction display MFD1 and flight management system FMS, the second data Interface unit DIU2 and second tuning control panel TCP2, the second audio-frequency control panel ACP2, the second air data system ADS2, Second inertial navigation/GPS combined navigation system INS/GPS2, the second VHF radio VHF2 and second instrument land System/VHF Omnidirection range multimode rake receiver ILS/VOR2 connection is aobvious to receive data and send the data to the second main flight Show device PFD2, the second multifunction display MFD2 and flight management system FMS.First data interface unit DIU1 and the second data It is further provided with mutually redundant direct-connected communication interface between interface unit DIU2, is gone out with a data interface unit wherein The transmission and processing of airborne equipment data are carried out when existing failure by another data interface unit.Pass through the first data-interface list Member and the second data interface unit are transmitted and are handled to carry out the double redundancy of airborne equipment data, and pass through unified flight management System with realizing high-reliability flight management, overcomes the more member's flight management systems of tradition and data processing Redundancy Design Excessively and avionics system excessively disperses, and leads to system bulk and the problem of weight is larger and higher cost.

Also, the first tuning control panel TCP1 and the first audio-frequency control panel ACP1 passes through spare communication interface and the One VHF radio VHF1 and first instrument landing system/VHF Omnidirection range multimode rake receiver ILS/VOR1 are directly connected to, Second tuning control panel TCP2 and the second audio-frequency control panel ACP2 passes through spare communication interface and the second VHF radio VHF2 and second instrument landing system/VHF Omnidirection range multimode rake receiver ILS/VOR2 are directly connected to, in data-interface Tuning and the audio frequency control that emergency communication is carried out when the channel that unit provides is unavailable, to improve the reliability of system.

Audio frequency controller in more member's aircraft avionics systems is realized by multitask audio frequency controller unit AMU, wherein more Business audio frequency controller unit AMU is connect with the first data interface unit DIU1 and the second data interface unit DIU2, and is separately connected To the first audio-frequency control panel ACP1, the second audio-frequency control panel ACP2 and for the audio-frequency control panel of other multiple users ACPs；Multitask audio frequency controller unit AMU is preferentially connect by the first data interface unit DIU1 or the second data at work Mouth cells D IU2 receives the audio frequency control instruction from audio-frequency control panel, and carries out audio data processing (for example, voice-grade channel Switch, carry out volume adjustment, the switching of different voice-grade channel, audio fusion etc.)；And it breaks down in data interface unit When directly receive the audio frequency control from audio-frequency control panel instruct and carry out audio data processing.

Further, the first data interface unit DIU1 or the second data interface unit DIU2 can with high frequency radio set HF, Satellite communication system SATCOM, aerial anti-collision system TCAS and other systems O-SYS (such as engine, take-off and landing device, the flap Wing etc.) connection, to receive and send richer airborne equipment data.

The communication interface of above-described embodiment includes serial communication interface (such as RS-422, RS-429 bus etc.) and Ethernet One of interface (Fast Ethernet, 10G Ethernet of standard ethernet, 100Mbit/s including 10Mbit/s etc.) is more Person.

Air data system ADS includes the pitot and total temperature probe with dual output channel, and has dual input With the air data computer of output channel；Each output channel of air data computer by RS-422 bus respectively and often A data interface unit DIU connection, to export the aircraft parameters being calculated according to atmosphere data (for example, pressure altitude, school Quasi- air speed, true air speed, Mach number, lifting speed, total temperature, static temperature, the angle of attack, yaw angle etc.)；Each of air data computer is defeated Enter channel to connect with the first data interface unit and the second data interface unit respectively by RS-422 bus, to receive pilot The air pressure of input is set right value information.

Inertial navigation/GPS combined navigation system INS/GPS is used to measure posture, position, the speed ginseng of aircraft Number comprising optical fiber aviation attitude system FINS, MEMS aviation attitude system AHRS and global positioning system, by RS-422 bus from data Interface unit receives the atmosphere data from air data system ADS, to resolve wind speed and direction information；It is total by RS-422 Line is connect with the first data interface unit and the second data interface unit respectively, with export the posture of aircraft, position, course, The parameters such as ground velocity, wind speed and direction.

The indicator screen of primary flight display PFD and multifunction display MFD are disposed as with infrared touch structure, To support multiple point touching, and can realize every control switching, selection by key uniformly distributed on display frame, adjust etc., It can also be tuned by being located at the double-deck knob of the left and right inferior horn of screen.In a preferred embodiment, multifunction display MFD and the first data interface unit or the second data interface unit by pulse signal come interaction data, it is multi-functional aobvious to reduce Show the processing load of processor in device MFD.For example, only when there is data to need to send just by Ethernet send, and by with The csma/cd mechanism netted very much occupies industry ethernet, realizes the high efficiency of transmission of data.

Each of data interface unit of the various embodiments described above may each comprise the FPGA connected by SRIO interface With CPU；Wherein, FPGA includes multiple serial input interfaces, the data sent for receiving multiple airborne equipment data channel； Multiple reception cache modules being connect with serial input interface, for carrying out temporal cache to the data from each channel；With it is every It is a receive cache module connection first group of packet module, for by the data of caching according to preset coding mode package with The first heartbeat data packets are obtained, and are passed through the first heartbeat data packets between FPGA and CPU according to scheduled heart beat cycle SRIO interface is sent to CPU；CPU includes unpacking module, for according to preset coding mode from the first heartbeat from FPGA Data packet reads the data in each channel；Data processing module is handled for the data to each channel, is generated and is directed to each machine Carry the control data of equipment；Second group of packet module packages for that will control data according to preset coding mode, to obtain Second heartbeat data packets, and FPGA is sent to according to scheduled second heart beat cycle；FPGA further comprises: delaying with each send The decoding module of storing module connection, for reading the control data for being directed to each airborne equipment in the second heartbeat data packets, concurrently Give corresponding transmission cache module；Multiple transmission cache modules are respectively connected to multiple serial output interfaces and at least one A Ethernet interface, and control data are sent to each airborne equipment at a predetermined rate according to communication protocol corresponding with interface.

In a preferred embodiment, above-mentioned first heart beat cycle is 5ms or 2ms, and the second heart beat cycle is less than or equal to First heart beat cycle.It receives cache module and transmission cache module is all made of block random access memory BRAM and does temporal cache. Specifically, the CPU uses P2020NXN2MHC chip, serial input, output interface use ISO3080DWR communication module, FPGA uses XC7A100T-2FGG484I chip.

Each of data interface unit can further include: system detection unit, for during powering on The working condition of internal each component is detected, and whether in place to the connection status of equipment and board in the process of work It is detected, and can be also used for real-time monitoring system temperature (including temperature of processor, power source temperature and environment temperature etc.)； Storage unit, for the data and processing result of acquisition are selectively stored according to preset instruction or rule (for example, In order to carry out test analysis and malfunction elimination)；Clock unit, for providing reference clock signal for data interface unit；Debugging Module, for carrying out digital simulation input and exporting the processing result of DSP, to carry out combined debugging with ground checkout equipment.

Moreover, in a preferred embodiment, data interface unit can further include EEPROM to carry out power down number According to protection.The outer dimension of data interface unit is set as 120mm (length) × 170mm (height) × 300mm (width), and weight is set as It no more than 4.5Kg, is powered using the airborne DC power supply of the 28V of 40W, and using the sheet radiator structure with shell integral structure.

Moreover, data interface unit and air data system ADS and inertial navigation/GPS combined navigation system INS/ GPS by periodic signal come interaction data, to improve the reliability for passing through each sensors for data.For example, whether having Data need to transmit, and establish transmission channel by RS-422 bus, to ensure the reliable transmission of data, while simplifying data and connecing Signal processing logic inside mouth unit.

The above, the only detailed description of specific embodiment of the present invention, rather than limitations of the present invention. Those skilled in the technology concerned in the case where not departing from the principle and range of the utility model, the various replacements made, Modification and improvement should be included within the scope of protection of this utility model.

Claims (10)

1. a kind of more member's aircraft avionics systems characterized by comprising mode control panel MCP, primary flight display PFD, Multifunction display MFD, automatic Pilot/flight director AP/FD, flight management system FMS, tuning control panel TCP, audio Control panel ACP, data interface unit DIU, air data system ADS, inertial navigation/GPS combined navigation system INS/ GPS, VHF radio VHF, instrument-landing-system/VHF Omnidirection range multimode rake receiver ILS/VOR and multitask audio Administrative unit AMU；

Wherein, the MCP, for flight control mode, navigation channel, course, flying height, ramp rate and the flight of aircraft to be arranged Speed with a variety of man-machine interactive interfaces to receive the setting instruction of pilot's input, and is distinguished by multiple communication interfaces It is connected to the first PFD, the first MFD, the 2nd PFD, the 2nd MFD and AP/FD；

First PFD and the 2nd PFD is respectively for display posture instruction interface, flying speed and height instruction interface, vertical speed It indicates interface and bearing indication interface, and receives setting instruction from human-computer interaction interface, setting instruction based on the received changes The corresponding contents shown in interface；

First MFD and the 2nd MFD are disposed as the integral structure with processor and display, respectively for progress flight information Integrative display, engine monitoring, flight parameter configuration and air pressure and environmental Kuznets Curves；AP/FD, for according to the automatic control of instruction Aircraft trace processed adjusts aspect；

FMS has full liquid crystal display and infrared touch panel and processor, for inputting and/or showing aircraft programs, speed control System and navigation control data, and connect with AP/FD to send automatic Pilot control instruction, connect with each data interface unit DIU It connects to receive airborne device data and send control instruction, also with each tuning control panel TCP connection to send tuning instruction And receive tuning data；

First DIU and the 2nd DIU is respectively used to carry out data acquisition, data processing and data distribution, and wherein data acquisition includes Obtain the data and its status data that each airborne equipment is sent by communication interface, data processing include the data that will acquire according to Target device is set for unpacking and organize packet；

First TCP and the first ACP passes through spare communication interface and is directly connected to the first VHF and the first ILS/VOR, the 2nd TCP Pass through spare communication interface with the 2nd ACP to be directly connected to the 2nd VHF and the 2nd ILS/VOR, to mention in data interface unit Tuning and the audio frequency control of emergency communication are carried out when the channel of confession is unavailable；

AMU is connect with the first DIU and the 2nd DIU, and is respectively connected to the first ACP and the 2nd ACP；AMU first leads at work It crosses the first DIU or the 2nd DIU and receives the audio frequency control instruction from audio-frequency control panel, and carry out audio data processing；And The audio frequency control from audio-frequency control panel is directly received when data interface unit breaks down to instruct and carry out audio data Processing.

2. more member's aircraft avionics systems according to claim 1, which is characterized in that the first PFD and the 2nd PFD is used It is instructed according to setting, navigation indicator is set by one in the two, to show next destination, current wind speed and direction Current line navigation information.

3. more member's aircraft avionics systems according to claim 1, which is characterized in that the first MFD and the 2nd MFD is used In when showing dimensional topography view, is instructed according to setting and change state of weather, show the specified landform under a variety of weather conditions Synthesize visual pattern and corresponding flight and weather data, chart, aircraft system information and range planning information.

4. more member's aircraft avionics systems according to claim 1, which is characterized in that the AP/FD includes for sensing Multiple sensing elements of aspect variable signal, for calculating the processor of amendment rudder deviator according to attitudes vibration signal, with And for rudder face to be adjusted to multiple servo mechanisms to required position.

5. more member's aircraft avionics systems according to claim 1, which is characterized in that the first DIU and the 2nd DIU is equal With answering machine/Automatic dependent surveillance broadcast system XPDR/ADS-B, weather radar WXR, range finder DME, radio altimeter RA and Automatic Direction Finder ADF connects and receives data and sends control instruction；And the first DIU and the 2nd DIU are provided with mutually For the direct-connected communication interface of backup, to pass through another data interface unit when a data interface unit breaks down wherein Carry out the transmission and processing of airborne equipment data.

6. more member's aircraft avionics systems according to claim 5, which is characterized in that the first DIU and the first TCP, First ACP, the first ADS, the first INS/GPS, the first VHF and the first ILS/VOR connection are to receive data and send data To the first PFD, the first MFD and FMS, the 2nd DIU and the 2nd TCP, the 2nd ACP, the 2nd ADS, the 2nd INS/GPS, the 2nd VHF, And the 2nd ILS/VOR connection to receive data and send the data to the 2nd PFD, the 2nd MFD and FMS.

7. more member's aircraft avionics systems according to claim 1, which is characterized in that the first DIU or the 2nd DIU into One step is connect with high frequency radio set HF, satellite communication system SATCOM, aerial anti-collision system TCAS, to send and receive corresponding number According to.

8. more member's aircraft avionics systems according to claim 1, which is characterized in that the display screen of the PFD and MFD Curtain is disposed as with infrared touch structure, to support multiple point touching, and passes through the key on display frame and knob realization Control switching, is adjusted and is tuned selection.

9. more member's aircraft avionics systems according to claim 1, which is characterized in that every in the data interface unit One, include the FPGA and CPU connected by SRIO interface；Wherein, FPGA includes multiple serial input interfaces, for connecing Receive the data that multiple airborne equipment data channel are sent；Multiple reception cache modules being connect with serial input interface, for pair Data from each channel carry out temporal cache；First group of packet module being connect with each reception cache module, for that will cache Data packaged according to preset coding mode to obtain the first heartbeat data packets, and according to scheduled heart beat cycle by One heartbeat data packets are sent to CPU by the SRIO interface between FPGA and CPU；CPU includes unpacking module, for according to pre- If coding mode the data in each channel are read from the first heartbeat data packets from FPGA；Data processing module, for pair The data in each channel are handled, and the control data for being directed to each airborne equipment are generated；Second group of packet module, for data will to be controlled It packages according to preset coding mode, to obtain the second heartbeat data packets, and is sent according to scheduled second heart beat cycle To FPGA；FPGA further comprises: the decoding module connecting with each transmission cache module, for reading the second heartbeat data packets In be directed to the control data of each airborne equipment, and be sent to and corresponding send cache module；Multiple transmission cache modules, respectively It is connected to multiple serial output interfaces and at least one Ethernet interface, and according to communication protocol corresponding with interface with predetermined Rate to each airborne equipment send control data.

10. more member's aircraft avionics systems according to any one of claim 1 to 9, which is characterized in that the communication connects Mouth includes one or more of serial communication interface and Ethernet interface.