CN108545202A - A kind of integrated avionic system - Google Patents
A kind of integrated avionic system Download PDFInfo
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- CN108545202A CN108545202A CN201810332216.6A CN201810332216A CN108545202A CN 108545202 A CN108545202 A CN 108545202A CN 201810332216 A CN201810332216 A CN 201810332216A CN 108545202 A CN108545202 A CN 108545202A
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D43/00—Arrangements or adaptations of instruments
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01C—MEASURING DISTANCES, LEVELS OR BEARINGS; SURVEYING; NAVIGATION; GYROSCOPIC INSTRUMENTS; PHOTOGRAMMETRY OR VIDEOGRAMMETRY
- G01C23/00—Combined instruments indicating more than one navigational value, e.g. for aircraft; Combined measuring devices for measuring two or more variables of movement, e.g. distance, speed or acceleration
- G01C23/005—Flight directors
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- H—ELECTRICITY
- H04—ELECTRIC COMMUNICATION TECHNIQUE
- H04L—TRANSMISSION OF DIGITAL INFORMATION, e.g. TELEGRAPHIC COMMUNICATION
- H04L12/00—Data switching networks
- H04L12/28—Data switching networks characterised by path configuration, e.g. LAN [Local Area Networks] or WAN [Wide Area Networks]
- H04L12/40—Bus networks
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- H—ELECTRICITY
- H04—ELECTRIC COMMUNICATION TECHNIQUE
- H04L—TRANSMISSION OF DIGITAL INFORMATION, e.g. TELEGRAPHIC COMMUNICATION
- H04L67/00—Network arrangements or protocols for supporting network services or applications
- H04L67/01—Protocols
- H04L67/12—Protocols specially adapted for proprietary or special-purpose networking environments, e.g. medical networks, sensor networks, networks in vehicles or remote metering networks
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- H—ELECTRICITY
- H04—ELECTRIC COMMUNICATION TECHNIQUE
- H04L—TRANSMISSION OF DIGITAL INFORMATION, e.g. TELEGRAPHIC COMMUNICATION
- H04L12/00—Data switching networks
- H04L12/28—Data switching networks characterised by path configuration, e.g. LAN [Local Area Networks] or WAN [Wide Area Networks]
- H04L12/40—Bus networks
- H04L2012/40267—Bus for use in transportation systems
- H04L2012/4028—Bus for use in transportation systems the transportation system being an aircraft
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- Computer Networks & Wireless Communication (AREA)
- Signal Processing (AREA)
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- Radar, Positioning & Navigation (AREA)
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Abstract
The invention discloses a kind of integrated avionic systems, can improve level of integrated system, while reducing total weight, ensure the safety and reliability of aircraft.The system includes the first synthetical display control unit and the second synthetical display control unit, the first data interface unit and the second data interface unit, double remaining air data systems, INS/GNSS integrated navigation systems, comprehensive wireless electric system, head-up display unit and cockpit monitoring system；Synthetical display control unit is set as the integral structure with processor and display, for showing state of flight and navigation information and by the control operational order of touch screen and physical button reception pilot；Data interface unit carries out data acquisition, data processing and data distribution for independent, wherein data acquisition includes obtaining the data and its status data that each airborne equipment generates by 422 buses of RS and industry ethernet, and data processing includes being set for unpacking and organizing packet according to target device by the data of acquisition.
Description
Technical field
The present invention relates to avionic device technical field more particularly to a kind of integrated avionic systems.
Background technology
The information of various avionic devices 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 for information about by airborne databus between avionic device, to make all aviation electronics on entire aircraft set
Standby performance reaches higher level, and such system is known as integrated avionic system.
It is a kind of for light-small aircraft that application publication number is that the Chinese invention patent application of CN106789499A discloses
Integrated avionic system comprising navigation subsystem, communication subsystem and instruction/recording subsystem；Its programmable integrated process includes the
One programmable integrated process and the second programmable integrated process；The input terminal of the aeroengine parameter collector connects the defeated of engine sensor
Outlet, and the output signal of the aeroengine parameter collector divides two-way, be separately input into all the way the first programmable integrated process and
Second programmable integrated process, another way are separately input into primary flight display and multifunction display；The fuselage state acquisition device
Output signal divide two-way, be separately input into the first programmable integrated process and the second programmable integrated process all the way, another way difference is defeated
Enter to primary flight display and multifunction display.
However, the system is relatively low there are part integrated level and part it is integrated it is unreasonable (such as：1, it is aobvious to use main flight for it
Show that the independent small-size displays of device PFD and multifunction display MFD two carry out human-computer interaction, and does not use an entire big ruler
Very little double remainings are shown, touch control device carries out human-computer interaction；2, GPS receiver is integrated in radionavigation control system, and
It is not integrated in Strapdown Attitude Heading Reference System, GPS information can not introduce Strapdown Attitude Heading Reference System and be modified；3, air data computer and
Strapdown Attitude Heading Reference System does not interact, can not carry out the resolving of the information such as wind speed, wind direction；4, answering machine, telecompass ADF,
VOR/LOC/GS receivers, marker beacon machine and rangefinder these wireless devices are not integrated into an integral device, cause to set
Standby quantity is excessive, and wiring is complicated on machine), and the air data system and Strapdown Attitude Heading Reference System closely related with flight safety is not
It is designed using redundance, leads to problems such as security of system and reliability relatively low.
Invention content
An object of the present invention at least that, for how to overcome the above-mentioned problems of the prior art, provide one kind
Integrated avionic system is suitable for, with the general-purpose aircraft of front and back distributed cockpit, to improve level of integrated system, reducing gross weight
While amount, ensure the safety and reliability of aircraft.
To achieve the goals above, the technical solution adopted by the present invention includes following aspects.
A kind of integrated avionic system comprising：First synthetical display control unit and the second synthetical display control unit, the
One data interface unit and the second data interface unit, double remaining air data systems, INS/GNSS integrated navigation systems are comprehensive
Radio system, head-up display unit and cockpit monitoring system；
Wherein, the first synthetical display control unit and the second synthetical display control unit are separately positioned on the first cockpit and
The front end of two cockpits is connect each by industry ethernet with the first data interface unit and the second data interface unit, and point
It is not directly connected to by RS-422 buses and double remaining air data systems and INS/GNSS integrated navigation systems；First synthesis is aobvious
Show that control unit and the second synthetical display control unit are disposed as the integral structure with processor and display, for showing
State of flight and navigation information and the control operational order that pilot is received by touch screen and physical button；
Double remaining air data systems include the pitot and total temperature probe for having dual output channel, and have lose-lose
Enter the air data computer with output channel；Each input channel of air data computer by RS-422 buses respectively with
First data interface unit is connected with the second data interface unit, and the air pressure to receive pilot's input is set right value information；Air
Each output channel of data computer is aobvious with the first synthetical display control unit and the second synthesis respectively by RS-422 buses
Show control unit, the first data interface unit and the second data interface unit and the connection of INS/GNSS integrated navigation systems, with
Output calculates the aircraft parameters obtained according to atmosphere data；
INS/GNSS integrated navigation systems are used to measure the posture of aircraft, position, speed parameter, total by RS-422
Line receives the atmosphere data from double remaining air data systems, to resolve wind speed and direction information；Pass through RS-422 buses
It is counted respectively with the first synthetical display control unit and the second synthetical display control unit and the first data interface unit and second
It is connected according to interface unit, to export posture, position, course, ground velocity, the wind speed and direction parameter of aircraft；Comprehensive radio system
System is connect by RS-422 buses with the first data interface unit and the second data interface unit, to receive control instruction and carry out
Tuning, audio adjusts and radio communication, and tuning state and frequency data are sent to the first data interface unit and the
Audio data is sent to airborne flight parameter recorder by two data interface units；Comprehensive wireless electric system has 2 very high
Frequency radio station VHF, 1 multimode rake receiver VOR/ILS and 1 radio altimeter RA, respectively by RS-422 buses directly with
One synthetical display control unit and the connection of the second synthetical display control unit, to realize backup communication function；
First data interface unit and the second data interface unit be respectively used to it is independent carry out data acquisition, data processing and
The acquisition of data distribution, wherein data include by RS-422 buses and industry ethernet obtain data that each airborne equipment generates and
Its status data, data processing include being set for unpacking and organizing packet according to target device by the data of acquisition；
Head-up display unit is connected by industry ethernet and the first data interface unit and the second data interface unit respectively
It connects, to obtain flying quality, navigation data and alarm data from different data sources, and it is preferential according to from the first data
Main flight image information, navigation screen information and alarm prompt image information are drawn and shown to the data of interface unit；It is flat
Aircraft exterior scenery picture is further acquired by its external television camera in real time depending on display unit, and by the aircraft of acquisition
External scenery picture is sent to cockpit monitoring system after being superimposed with glyph image；
Cockpit monitoring system accesses and shows simultaneously the monitor video of the vision signal and the first cockpit of head-up display unit
Signal, and will be stored after video data compression in cache registration card inside it；Cockpit monitoring system is received from the first number
According to the aircraft flight data of interface unit and the second data interface unit, and record in cache registration card inside it.
Preferably, the power supply of each in the first synthetical display control unit and the second synthetical display control unit
There is module two-way independently to export, and respectively first processor and second processor provide 28V DC power supplies；
Each synthetical display control unit is combined by RS-422 buses with double remaining air data systems and INS/GNSS
Navigation system is directly connected to, first processor and second processor respectively by industry ethernet and the first data interface unit and
Second data interface unit connects；First processor and second processor, which are carried out at the same time display data and handle and receive control, to be referred to
It enables；And by duplexing Ethernet that transmission rate all the way is 100Mb/s into line number between first processor and second processor
According to communication, double remaining backups are realized；Acquiescence only shows the handling result of first processor, only when first processor cannot normal work
When making, the handling result of display second processor is automatically switched to.
Preferably, the first processor acquiescence uses the data from the first data interface unit, second processor equal
Acquiescence uses the data from the second data interface unit, when can not be from the first data interface unit and the second data interface unit
When obtaining data or acquired data beyond preset range, directly using from double remaining air data systems and INS/
The data of GNSS integrated navigation systems.
Preferably, each in the first synthetical display control unit and the second synthetical display control unit with
One data interface unit or the second data interface unit by pulse signal come interaction data, only just when there is data to need to send
It is sent by Ethernet, and it is total by the csma/cd mechanism of Ethernet to occupy Ethernet
Line, to reduce the processing load of processor in synthetical display control unit.
Preferably, the head-up display unit is rigidly connected by mounting bracket and airframe, and it is adjustable to be set as height
Section structure is so that its height is located at the front of pilot's eyes；Mounting bracket is not in direct contact with airframe, junction pad
There are conductive rubber or equivalent conductive material.
Preferably, the cockpit monitoring system includes being separately positioned on the video camera of the first cockpit and being arranged in the second cockpit
Display, wherein video camera for shooting the operation and control process of pilot in the first cockpit and corresponding display interface, and
By the first digital visual interface DVI by video signal transmission to display；Display also accesses head-up display by the 2nd DVI
The vision signal of unit；Cockpit monitoring system is carried out while being recorded to the two-path video signal of input display, and upon compression
It is stored in the cache registration card of itself.
Preferably, each in first data interface unit and the second data interface unit includes DSP unit
And FPGA unit；Wherein, FPGA unit includes that at least 22 RS-422 interfaces and at least nine Ethernet being connect with FPGA connect
Mouthful, to realize sending and receiving for data；FPGA is connect by universal parallel interface with DSP unit.
Preferably, the DSP unit include the system detectio unit being connect with DSP, storage unit, clock unit and
Debugging module；Wherein, DSP is for parsing the data of acquisition and being combined into the data packet for meeting target device agreement；System
System detection unit is used to be detected the working condition of internal each component during powering on, and right in the process of work
Whether the linking status and board of equipment are detected in place, and can be also used for real-time monitoring system temperature；Storage unit
For selectively being stored to the data and handling result of acquisition according to preset instruction or rule；Clock unit is for being
Data interface unit provides reference clock signal；Debugging module is used to carry out digital simulation input and export the handling result of DSP,
To carry out combined debugging with ground checkout equipment.
Preferably, each in first data interface unit and the second data interface unit and the big destiny of double remainings
Whether there are data to need to transmit, come interaction data by periodic signal according to system and INS/GNSS integrated navigation systems
Transmission channel is established by RS-422 buses, to ensure the transmitting of data.
Preferably, data that each in first data interface unit and the second data interface unit is handled include from
VHF radio VHF in double remaining air data systems, INS/GNSS integrated navigation systems and comprehensive wireless electric system,
Multimode rake receiver VOR/ILS, radio altimeter RA, Automatic Direction Finder ADF, range finder DME, aviation management answering machine XPDR, in machine
The data that telephony unit ACU and data processor CNI are acquired.
In conclusion by adopting the above-described technical solution, the present invention at least has the advantages that：
Integrated avionic system according to the ... of the embodiment of the present invention can provide communication, navigation, monitoring, main flight instrument for aircraft
Various functions, the system architectures such as table, engine instruction, pattern notice use open integrated framework, centric data networks
Using Ethernet, mass data interaction is realized by data interface unit, it, can by the way that the remaining of each component part is rationally arranged
While improving the integrated level and reliability of integrated avionic system, open access structure is kept, is accessed convenient for airborne equipment,
Ensure that system configuration is flexible, extension is convenient, and is convenient for system upgrade and maintenance.
Description of the drawings
Fig. 1 is the structural schematic diagram of integrated avionic system according to the ... of the embodiment of the present invention.
Fig. 2 is the structural schematic diagram of synthetical display control unit according to the ... of the embodiment of the present invention.
Fig. 3 is the structural schematic diagram of data interface unit according to the ... of the embodiment of the present invention.
Specific implementation mode
With reference to the accompanying drawings and embodiments, the present invention will be described in further detail, so that the purpose of the present invention, technology
Scheme and advantage are more clearly understood.It should be appreciated that described herein, specific examples are only used to explain the present invention, and does not have to
It is of the invention in limiting.
Fig. 1 shows the structure of integrated avionic system 100 according to the ... of the embodiment of the present invention, includes mainly：
First synthetical display control unit 101 and the second synthetical display control unit 102, the first data interface unit 103
With the second data interface unit 104, double remaining air data systems 105, INS/GNSS integrated navigation systems 106, comprehensive wireless
Electric system 107, head-up display unit 108 and cockpit monitoring system 109.
Wherein, the first synthetical display control unit 101 and the second synthetical display control unit 102 are separately positioned on First
The front end in cabin and the second cockpit (such as front deck and rear deck), each by industry ethernet (in figure with solid line connection indicate, including
The standard ethernet of 10Mbit/s, the Fast Ethernet of 100Mbit/s, 10G Ethernets etc.) and the first data interface unit 103
It is connected with the second data interface unit 104, and big with double remainings by RS-422 buses (being indicated with dotted line connection in figure) respectively
Gas data system 105 and INS/GNSS integrated navigation systems 106 are directly connected to；First synthetical display control unit 101 and second
Synthetical display control unit 102 is disposed as the integral structure with processor and display, for showing state of flight and leading
Information of navigating and the control operational order that pilot is received by touch screen and physical button.For example, can show pitching, tilt and
Flying height, speed, Mach number, lifting speed, course etc. allow driver that the actual flight state of aircraft is understood more intuitively,
Accurate manipulation is made to aircraft.
Double remaining air data systems 105 include the pitot and total temperature probe for having dual output channel, and are had
The air data computer of dual input and output channel；Each output channel of air data computer passes through RS-422 buses point
Not with the first synthetical display control unit 101 and the second synthetical display control unit 102, the first data interface unit 103 and
Two data interface units 104 and INS/GNSS integrated navigation systems 106 connect, and are calculated and are obtained according to atmosphere data with output
Aircraft parameters (for example, pressure altitude, calibrated air speed, true air speed, Mach number, lifting speed, total temperature, static temperature, the angle of attack, side
Sliding angle etc.)；Each input channel of air data computer by RS-422 buses respectively with the first data interface unit 103 and
Second data interface unit 104 connects, and the air pressure to receive pilot's input is set right value information.
INS/GNSS integrated navigation systems 106 are used to measure the posture of aircraft, position, speed parameter comprising optical fiber
Aviation attitude system FINS, MEMS (MEMS) aviation attitude system AHRS and global navigation satellite system GNSS, it is total by RS-422
Line receives the atmosphere data from double remaining air data systems 105, to resolve wind speed and direction information；It is total by RS-422
Line respectively with the first synthetical display control unit 101 and the second synthetical display control unit 102 and the first data interface unit
103 and second data interface unit 104 connect, with ginsengs such as the posture, position, course, ground velocity, the wind speed and directions that export aircraft
Number.
Comprehensive wireless electric system 107 includes mainly two VHF radio VHF, multimode rake receiver VOR/ILS, radio height
Spend table RA, Automatic Direction Finder ADF, range finder DME, aviation management answering machine XPDR, flight interphone unit ACU and data processor
CNI.Wherein, data processor CNI passes through RS-422 buses and the first data interface unit 103 and the second data interface unit
104 connections to receive wireless electric tuning control instruction, audio regulating control command, alarm signal code, and are led to after dissection process
It crosses 107 internal bus of comprehensive wireless electric system and is distributed to the equipment such as VHF, VOR/ILS, ADF, these equipment refer to according to tuning control
Be tuned after order, audio is adjusted, outputting alarm signal, and the data such as tuning state and frequency are concentrated by data processor
It is sent to the first data interface unit 103 and the second data interface unit 104, audio data is sent to airborne flight parameter
Recorder 120.Two VHF radio VHF, multimode rake receiver VOR/ILS, radio altitude in comprehensive wireless electric system 107
Table RA respectively by RS-422 buses directly with the first synthetical display control unit 101 and the second synthetical display control unit 102
Connection, to realize backup communication function.
First data interface unit 103 and the second data interface unit 104 are respectively used to independent progress data acquisition, data
The acquisition of processing and data distribution, wherein data includes obtaining various airborne equipments (packet by RS-422 buses and industry ethernet
Acquisition module containing engine parameter 130) data that generate and its status data, data processing include the data that will acquire according to mesh
Marking device is set for unpacking and organize packet.
Head-up display unit 108 passes through industry ethernet and the first data interface unit 103 and the second data-interface respectively
Unit 104 connects, to obtain flying quality, navigation data and alarm data from different data sources, and it is preferential according to next
Draw and show that main flight image information, navigation screen information and alarm are carried from the data of the first data interface unit 103
Show image information.Head-up display unit 108 can acquire aircraft exterior scenery picture in real time by its external television camera,
And cockpit monitoring system 109 is sent to after being superimposed aircraft exterior scenery picture with glyph image.Head-up display unit 108 passes through
Mounting bracket is rigidly connected with airframe, is set as height-adjustable structure so that its height is located just at pilot's eyes
Front.Mounting bracket is not in direct contact with airframe, connection (such as screw or bayonet connection) at be lined with conductive rubber or
Equivalent conductive material, causes to corrode to avoid organism material to equipment.
Cockpit monitoring system 109 includes being separately positioned on the video camera of the first cockpit and the display in the second cockpit being arranged
Device, wherein video camera pass through number for shooting the operation and control process of pilot in the first cockpit and corresponding display interface
Word video interface DVI is by video signal transmission to display；Display also accesses the video of head-up display unit 108 by DVI
Signal；Cockpit monitoring system 109 is carried out while being recorded to the two-path video signal of input display, and is stored in it upon compression
In internal cache registration card, to realize the real-time record of operating process and corresponding result；Cockpit monitoring system 109 can pass through
RS422 buses receive the aircraft flight data from the first data interface unit 103 and the second data interface unit 104, and remember
In the cache registration card of record inside it.After pilot terminates flight, can quickly choose the registration card, with ground device analysis its
In video and flying quality.
Fig. 2 shows the structural schematic diagrams of synthetical display control unit 200 according to the ... of the embodiment of the present invention, correspond to Fig. 1
The first synthetical display control unit 101 and the second synthetical display control unit 102 in each, be all made of double remainings processing
Device designs.As shown in Fig. 2, synthetical display control unit 200 is powered by airborne 28V DC power supplies, synthetical display control unit
There is power module 203 in 200 two-way independently to export, and respectively first processor 201 and second processor 202 provides electricity
Source.
Synthetical display control unit 200 passes through RS-422 buses and double remaining air data systems 105 and INS/GNSS groups
It closes navigation system 106 to be directly connected to, first processor 201 and second processor 202 are counted by industry ethernet and first respectively
It is connected according to interface unit 103 and the second data interface unit 104；First processor 201 and second processor 202 are carried out at the same time aobvious
Show data processing and receives control instruction；And pass through transmission rate all the way between first processor 201 and second processor 202
For 100Mb/s duplexing Ethernet (operation udp protocol) into row data communication, realize remaining backup；Acquiescence is only at display first
The handling result of device 201 is managed, only when 201 cisco unity malfunction of first processor (for example, defeated more than preset time period no data
Go out, data output is beyond preset range etc.), automatically switch to the handling result of display second processor 202.
Further, first processor 201 and second processor 202 are given tacit consent to using from the first data interface unit
103 or second data interface unit 104 data, when can not be from the first data interface unit 103 and the second data interface unit
When 104 acquisition data or acquired data exceed preset range, directly using from double 105 Hes of remaining air data system
The data of INS/GNSS integrated navigation systems 106.
The indicator screen of synthetical display control unit 200 is set as with infrared touch structure, to support multiple point touching,
And can realize every control switching, selection by button uniformly distributed on display frame, adjust etc., it can also be by being located at screen
The double-deck knob of the left and right inferior horn of curtain is tuned.In a preferred embodiment, synthetical display control unit 200 and first counts
According to interface unit 103 or the second data interface unit 104 by pulse signal come interaction data, to reduce synthetical display control list
The processing load of processor in member 200.For example, only just being sent by Ethernet when there are data to need to send, and pass through ether
The csma/cd mechanism of net occupies industry ethernet, realizes the high efficiency of transmission of data.
Fig. 3 shows the structural schematic diagram of data interface unit 300 according to the ... of the embodiment of the present invention, corresponding to the of Fig. 1
Each in one data interface unit 103 and the second data interface unit 104 includes DSP unit 301 and FPGA unit
302.Wherein, FPGA unit 302 includes at least 22 RS-422 interfaces 304 and at least nine Ethernet interface being connect with FPGA
305, to realize sending and receiving for data；FPGA is connect by universal parallel interface uPP 303 with DSP unit 301；
DSP unit 301 include the system detectio unit 306 being connect with DSP, storage unit 307, clock unit 308 and
Debugging module 309；Wherein, DSP be used for from HUD, DU, ADS, AHRS, GNSS, XPDR, ADS-B, ILS, VOR, DME, ADF,
The data of the acquisitions such as RA, VHF are parsed and are combined into the data packet for meeting target device agreement (for example, being combined into Ethernet
Protocol data packet is simultaneously sent to synthetical display control unit, or otherwise)；System detectio unit 306 is used in the process powered on
In the working condition of internal each component is detected, and in the process of work to the linking status of equipment and board whether
Position is detected, and can be also used for real-time monitoring system temperature (including temperature of processor, power source temperature and environment temperature
Deng)；Storage unit 307 is used to selectively store the data and handling result of acquisition according to preset instruction or rule
(for example, in order to carry out test analysis and malfunction elimination)；When clock unit 308 is used to provide benchmark for data interface unit 300
Clock signal；Debugging module 309 is used to carry out digital simulation input and exports the handling result of DSP, so as to ground checkout equipment
Carry out combined debugging.
Moreover, in a preferred embodiment, data interface unit 300 can further include EEPROM to carry out power down
Data protection.And by the appearance and size of data interface unit 300 be limited in 120mm (length) × 170mm (height) × 300mm (width) it
Interior, weight is set as being not more than 4.5Kg, is powered using the airborne DC power supplies of the 28V of 40W, and use and shell integral structure
Sheet radiator structure.
Moreover, data interface unit 300 and double remaining air data systems 105 and INS/GNSS integrated navigation systems 106
By periodic signal come interaction data, to improve the reliability by each sensors for data.For example, whether there is data
It needs to transmit, transmission channel is established by RS-422 buses, to ensure the transmitting of data, while simplifying data-interface list
Signal processing logic inside member 300.
The above, the only detailed description of the specific embodiment of the invention rather than limitation of the present invention.The relevant technologies
The technical staff in field is not in the case where departing from the principle and range of the present invention, various replacements, modification and the improvement made
It should all be included in the protection scope of the present invention.
Claims (10)
1. a kind of integrated avionic system, which is characterized in that the integrated avionic system includes：First synthetical display control unit and
Second synthetical display control unit, the first data interface unit and the second data interface unit, double remaining air data systems,
INS/GNSS integrated navigation systems, comprehensive wireless electric system, head-up display unit and cockpit monitoring system；
Wherein, the first synthetical display control unit and the second synthetical display control unit are separately positioned on the first cockpit and second
The front end in cabin connect with the first data interface unit and the second data interface unit each by industry ethernet, and leads to respectively
RS-422 buses are crossed to be directly connected to double remaining air data systems and INS/GNSS integrated navigation systems；First synthesis display control
Unit processed and the second synthetical display control unit are disposed as the integral structure with processor and display, for showing flight
State and navigation information and the control operational order that pilot is received by touch screen and physical button；
Double remaining air data systems include the pitot and total temperature probe for having dual output channel, and with dual input and
The air data computer of output channel；Each input channel of air data computer is by RS-422 buses respectively with first
Data interface unit is connected with the second data interface unit, and the air pressure to receive pilot's input is set right value information；Atmosphere data
Each output channel of computer by RS-422 buses respectively with the first synthetical display control unit and the second synthesis display control
Unit processed, the first data interface unit and the second data interface unit and the connection of INS/GNSS integrated navigation systems, with output
The aircraft parameters obtained are calculated according to atmosphere data；
INS/GNSS integrated navigation systems are used to measure the posture of aircraft, position, speed parameter, are connect by RS-422 buses
The atmosphere data from double remaining air data systems is received, to resolve wind speed and direction information；Distinguished by RS-422 buses
It is connect with the first synthetical display control unit and the second synthetical display control unit and the first data interface unit and the second data
Mouth unit connection, to export posture, position, course, ground velocity, the wind speed and direction parameter of aircraft；Comprehensive wireless electric system is logical
It crosses RS-422 buses to connect with the first data interface unit and the second data interface unit, to receive control instruction and be adjusted
Humorous, audio adjusts and radio communication, and tuning state and frequency data are sent to the first data interface unit and second
Audio data is sent to airborne flight parameter recorder by data interface unit；Comprehensive wireless electric system has 2 very high frequency(VHF)s
Radio station VHF, 1 multimode rake receiver VOR/ILS and 1 radio altimeter RA, respectively by RS-422 buses directly with first
Synthetical display control unit and the connection of the second synthetical display control unit, to realize backup communication function；
First data interface unit and the second data interface unit are respectively used to independent progress data acquisition, data processing and data
Distribution, wherein data acquisition include obtaining the data and its shape that each airborne equipment generates by RS-422 buses and industry ethernet
State data, data processing include being set for unpacking and organizing packet according to target device by the data of acquisition；
Head-up display unit is connect by industry ethernet with the first data interface unit and the second data interface unit respectively, with
Flying quality, navigation data and alarm data from different data sources are obtained, and preferential according to from the first data-interface
Main flight image information, navigation screen information and alarm prompt image information are drawn and shown to the data of unit；Head-up is aobvious
Show that unit further acquires aircraft exterior scenery picture in real time by its external television camera, and by the aircraft exterior of acquisition
Scenery picture is sent to cockpit monitoring system after being superimposed with glyph image；
Cockpit monitoring system accesses and shows the vision signal of head-up display unit and the monitor video signal of the first cockpit simultaneously,
And it will be stored after video data compression in cache registration card inside it；Cockpit monitoring system, which receives, comes from the first data-interface
The aircraft flight data of unit and the second data interface unit, and record in cache registration card inside it.
2. integrated avionic system according to claim 1, which is characterized in that the first synthetical display control unit and
There is the power module of each in two synthetical display control units two-way independently to export, respectively first processor and second
Processor provides 28V DC power supplies；
Each synthetical display control unit passes through RS-422 buses and double remaining air data systems and INS/GNSS integrated navigations
System is directly connected to, and first processor and second processor pass through industry ethernet and the first data interface unit and second respectively
Data interface unit connects；First processor and second processor are carried out at the same time display data and handle and receive control instruction；And
And data are carried out by the duplexing Ethernet that transmission rate all the way is 100Mb/s between first processor and second processor and are led to
Letter realizes double remaining backups；Acquiescence only shows the handling result of first processor, only when first processor cisco unity malfunction
When, automatically switch to the handling result of display second processor.
3. integrated avionic system according to claim 2, which is characterized in that first processor acquiescence is used from the
The data of one data interface unit, second processor are given tacit consent to using the data from the second data interface unit, when can not be from
When first data interface unit and the second data interface unit obtain data or acquired data beyond preset range, directly
Use the data from double remaining air data systems and INS/GNSS integrated navigation systems.
4. integrated avionic system according to claim 3, which is characterized in that the first synthetical display control unit and
Each in two synthetical display control units is believed by pulse with the first data interface unit or the second data interface unit
Number carry out interaction data, only just sent by Ethernet when there are data to need to send, and by Ethernet with collision detection
Csma mechanism occupies industry ethernet, negative with the processing for reducing processor in synthetical display control unit
Lotus.
5. integrated avionic system according to claim 1, which is characterized in that the head-up display unit passes through mounting bracket
It is rigidly connected with airframe, is set as height-adjustable structure so that its height is located at the front of pilot's eyes；Installation
Holder is not in direct contact with airframe, and junction is lined with conductive rubber or equivalent conductive material.
6. integrated avionic system according to claim 1, which is characterized in that the cockpit monitoring system includes being respectively set
The first cockpit video camera and the display in the second cockpit is set, wherein video camera is for shooting pilot in the first cockpit
Operation and control process and corresponding display interface, and by the first digital visual interface DVI by video signal transmission to display
Device；Display also accesses the vision signal of head-up display unit by the 2nd DVI；Cockpit monitoring system to input display two
Road vision signal is carried out while being recorded, and is stored in upon compression in the cache registration card of itself.
7. integrated avionic system according to claim 1, which is characterized in that first data interface unit and the second number
Include DSP unit and FPGA unit according to each in interface unit；Wherein, FPGA unit include connect with FPGA to
Few 22 RS-422 interfaces and at least nine Ethernet interface, to realize sending and receiving for data；FPGA is connect by universal parallel
Mouth is connect with DSP unit.
8. integrated avionic system according to claim 7, which is characterized in that the DSP unit include connect with DSP be
System detection unit, storage unit, clock unit and debugging module；Wherein, DSP is for parsing simultaneously the data of acquisition
It is combined into the data packet for meeting target device agreement；System detectio unit is used for during powering on to the work of internal each component
It is detected as state, and whether the linking status of equipment and board is detected in place in the process of work, but also
For real-time monitoring system temperature；Storage unit be used for according to preset instruction or rule to the data of acquisition and handling result into
Row selectively stores；Clock unit is used to provide reference clock signal for data interface unit；Debugging module is used for into line number
According to simulation input and the handling result of DSP is exported, to carry out combined debugging with ground checkout equipment.
9. integrated avionic system according to claim 8, which is characterized in that first data interface unit and the second number
According to each in interface unit with double remaining air data systems and INS/GNSS integrated navigation systems by periodic signal come
Interaction data whether has data to need to transmit, and establishes transmission channel by RS-422 buses, to ensure the reliable of data
Transmission.
10. integrated avionic system according to claim 9, which is characterized in that first data interface unit and second
In data interface unit each handle data include from double remaining air data systems, INS/GNSS integrated navigation systems,
And VHF radio VHF, multimode rake receiver VOR/ILS, radio altimeter RA, automatic orientation in comprehensive wireless electric system
The data that machine ADF, range finder DME, aviation management answering machine XPDR, flight interphone unit ACU and data processor CNI are acquired.
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| CN112197792A (en) * | 2020-10-10 | 2021-01-08 | 江西洪都航空工业集团有限责任公司 | Course precision improving method for trainer attitude and heading system |
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| CN114189315A (en) * | 2021-12-06 | 2022-03-15 | 中电科航空电子有限公司 | Point-to-point Ethernet-based civil aircraft airborne digital audio transmission system and method |
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Denomination of invention: An integrated avionics system Effective date of registration: 20230111 Granted publication date: 20210126 Pledgee: Zheshang Bank Co.,Ltd. Chengdu Branch Pledgor: CHENGDU HERMES TECHNOLOGY CO.,LTD.|CHENGDU ZIRUI QINGYUN AERONAUTICAL AND ASTRONAUTICAL TECHNOLOGY CO.,LTD. Registration number: Y2023510000018 |