CN112040143A - Dual-redundancy graphic display device of airborne display - Google Patents
Dual-redundancy graphic display device of airborne display Download PDFInfo
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- CN112040143A CN112040143A CN202010729503.8A CN202010729503A CN112040143A CN 112040143 A CN112040143 A CN 112040143A CN 202010729503 A CN202010729503 A CN 202010729503A CN 112040143 A CN112040143 A CN 112040143A
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- module
- dual
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- redundancy
- power supply
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- H—ELECTRICITY
- H04—ELECTRIC COMMUNICATION TECHNIQUE
- H04N—PICTORIAL COMMUNICATION, e.g. TELEVISION
- H04N5/00—Details of television systems
- H04N5/222—Studio circuitry; Studio devices; Studio equipment
- H04N5/262—Studio circuits, e.g. for mixing, switching-over, change of character of image, other special effects ; Cameras specially adapted for the electronic generation of special effects
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D43/00—Arrangements or adaptations of instruments
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- H—ELECTRICITY
- H04—ELECTRIC COMMUNICATION TECHNIQUE
- H04N—PICTORIAL COMMUNICATION, e.g. TELEVISION
- H04N7/00—Television systems
- H04N7/22—Adaptations for optical transmission
Abstract
The invention discloses a dual-redundancy graph display device of an airborne display, wherein the MFD mainly comprises a graph display control module, an interface bus module, a power supply module, an AFDX terminal module, a video fiber module, a liquid crystal display module, a light guide plate and other 7 functional modules, wherein the graph display control module, the power supply module and the AFDX terminal module adopt dual-redundancy design, 2 pieces of the graph display control module, the power supply module and the AFDX terminal module are respectively designed, and the two pieces of hardware, software and functional performance are completely consistent and mutually perform hot backup. The interface bus module is designed into 1 board card, but is composed of two parts of circuits with the same function, and the task is backed up; the reliability is strong, the power consumption is low, the anti-interference capability is strong, and the structural design is stable and reliable; the components are selected from 100% of localization; and (5) optimizing the human-computer efficiency.
Description
Technical Field
The invention relates to the field of aviation, in particular to a dual-redundancy graph display device of an airborne display.
Background
Early aircraft cabin instrument is mostly mechanical instrument and shows, and one of them information is only shown to every kind of instrument, and LCD's successful application, avionics system begin to use LCD to 8 cun, 10.4 cun are common display, and just as singly showing more, through 20 years's development, the large-size screen multifunctional display of now universal adoption.
Three multifunctional displays are arranged in a cabin of the F-22 bird warrior, which is an important technical transition from a traditional mechanical instrument to an advanced touch type multifunctional display on the F-35 fighter today, the multifunctional display is arranged in the middle of the cabin in the cabin layout, and the MFD sizes on two sides of the cabin are about 16.5cm x 16.5 cm.
The F-35 cockpit layout uses a large color digital touch LCD of approximately 20cm by 50.8 cm. The pilot can not only switch the air refueling mode and the flight system test module of the airplane by touching the display, but also control various airborne radio systems, task system computers, friend or foe identification systems and navigation systems on the touch display. Different display window sizes and arrangements may be customized as desired by the pilot. The 'human-computer interface design' is very good. By touching the display screen, the pilot can divide the display screen into two display windows of 20cm × 25cm, or 4 display windows of 8cm × 12.5cm, so as to simultaneously display navigation information, warning threats, target indication, oil quantity, weapons and other information. The pilot can divide the size and arrangement mode of the display window at will to meet the operation habits of different pilots. The F-35 display for the warplane cabin is formed by splicing two 20cm multiplied by 25cm displays, the two displays do not influence each other in work and are backup to each other, and if one display fails, all information is automatically transferred to the other 20cm multiplied by 25cm display for displaying.
1.2 domestic Presence analysis
At present, the domestic large-screen multifunctional display has two models: the display is 9 multiplied by 24 inches, the display is 8 multiplied by 20 inches, and the F-20 adopts a large-size infrared touch screen 9 multiplied by 24 inches multifunctional liquid crystal display. the-16D display adopts an 8-inch × 20-inch liquid crystal display, can realize functions of division display, video superposition and the like of different areas, can display information such as battlefield situation, friend or foe identification, oil quantity, weapons and the like on the multifunctional display in real time, is mature in relative technology, is in a test flight verification stage at present and is not shaped.
The structure of the domestic multifunctional display comprises a liquid crystal display module and an image processing module at present.
2. Description of the Prior Art
2.1 Overall design:
the main hardware components of the multifunctional display comprise 4 functional modules, such as an interface bus module (IOM), a Power Supply Module (PSM), a liquid crystal display module (LCM), a light guide plate and the like, and all the modules are crosslinked through the interface bus module. The multifunctional display is composed of a block diagram as shown in fig. 1, an interface bus module (IOM) has a photoelectric conversion function, receives and analyzes an ARINC818 video protocol, decodes an ARINC818 video electrical signal into an odd-even dual-channel LVDS video signal and transmits the odd-even dual-channel LVDS video signal to an LCM; and encodes and outputs the parity LVDS video signal into an ARINC818 video optical signal. The key detection function is provided; video switching is carried out according to the key demand, and the video contrast and brightness are adjusted. And the RS422 is communicated with the host computer to transmit key information and touch information.
A liquid crystal display module (LCM) receives and displays the LVDS video signals sent by the IOM; collecting a key of the light guide plate and an ambient light brightness signal, receiving coordinate information of the infrared touch screen, converting the coordinate information into protocol data, and transmitting the protocol data; sending key values, brightness data, screen temperature data, backlight temperature data and BIT detection information to the IOM through an RS232 interface, and receiving an IOM instruction to adjust brightness and switch day and night; giving the touch screen coordinate value to the IOM through an RS422 interface; low-temperature heating and control are realized.
The light guide plate provides peripheral keys for pilot operation, including brightness, contrast adjustment, switches and other keys. An ambient light brightness sensor is arranged to sense ambient brightness and provide illumination for all keys and characters on the panel.
The Power Supply Module (PSM) provides working power supply required by each module of the display, and carries out lightning protection, filtering, isolation secondary conversion and other treatments on the input power supply on the display.
Disclosure of Invention
The technical problem to be solved by the embodiments of the present invention is to provide a dual redundant graphic display device with a better effect for an onboard display.
The utility model provides an airborne display dual-redundancy figure display device, MFD main hardware constitution include figure display control module, interface bus module, power module, AFDX terminal module, video fiber module, liquid crystal display module and 7 kinds of functional module constitutions such as light guide plate, wherein, figure display control module, power module and AFDX terminal module adopt dual-redundancy design, each designs 2, and two hardware, software and functional performance are identical, each other is the hot backup. The interface bus module is designed into 1 board card, but consists of two parts of circuits with completely the same functions, and the tasks are backed up.
The control circuit and the physical interface of the liquid crystal display module, the circuit and the physical interface of the interface bus module are designed in a dual-redundancy mode, the graphic display control module, the AFDX terminal module and the power supply module are designed in a dual-redundancy mode, the whole machine is divided into a main part and a standby part 2, and the dual-redundancy design of a product is realized between the main part and the standby part through corresponding software instructions.
The embodiment of the invention has the following beneficial effects:
the invention relates to a dual-redundancy graph display device of an airborne display, which comprises (1) a simplified circuit design and complete functions; the reliability is strong, the power consumption is low, the anti-interference capability is strong, and the structural design is stable and reliable; the components are selected from 100% of localization; and (5) optimizing the human-computer efficiency.
Drawings
FIG. 1 is a prior art multi-function display composition block diagram;
FIG. 2 is a block diagram of the MFD external cross-link according to the embodiment of the present invention;
FIG. 3 is a block diagram of the MFD internal cross-linking of the embodiment of the present invention.
Detailed Description
In order to make the objects, technical solutions and advantages of the present invention more apparent, the present invention will be described in further detail with reference to the accompanying drawings.
According to the dual-redundancy graph display device of the airborne display, disclosed by the embodiment of the invention, the MFD main hardware comprises 7 functional modules, namely a graph display control module, an interface bus module, a power supply module, an AFDX terminal module, a video optical fiber module, a liquid crystal display module, a light guide plate and the like, wherein the graph display control module, the power supply module and the AFDX terminal module adopt dual-redundancy design, 2 modules are designed, and the two hardware, software and functional performances are completely consistent and mutually perform hot backup. The interface bus module is designed into 1 board card, but consists of two parts of circuits with completely the same functions, and the tasks are backed up.
The control circuit and the physical interface of the liquid crystal display module, the circuit and the physical interface of the interface bus module are designed in a dual-redundancy mode, the graphic display control module, the AFDX terminal module and the power supply module are designed in a dual-redundancy mode, the whole machine is divided into a main part and a standby part 2, and the dual-redundancy design of a product is realized between the main part and the standby part through corresponding software instructions. Under the normal working state, the MFD receives an instruction through the AFDX bus, and processes and displays the working picture and the character of the airborne system; receiving two paths of video signals through an ARINC818 bus, and windowing/overlapping display in a display picture; and providing the video signal output of the current display picture for video recording.
In a backup state, flight parameters are acquired through ARINC429 and RS422 buses, and a designated picture is generated according to requirements and displayed and output.
The graphic display control module is a main control module of the MFD, resides in system software and is responsible for system task progress and scheduling management; and receiving and analyzing data from the AFDX, generating a drawing instruction and transmitting the drawing instruction. And the interaction of AFDX, RS422 and ARINC429 data and the reception of discrete quantity states are realized by crosslinking with other SRUs through a PCI-E bus.
The interface bus module expands the high-speed bus into discrete quantity, RS422 and ARINC429 buses, and performs data communication with each module in the MFD and the onboard equipment; generating a graphic picture, realizing the functions of video superposition, windowing and the like, and simultaneously outputting the superposed video picture; the photoelectric conversion of ARINC818 video signals is realized.
The video optical fiber module is used for analyzing an ARINC818 video protocol, decoding ARINC818 video electric signals into DVI video signals and transmitting the DVI video signals to the interface bus module; DVI video output by the receiving interface bus module is encoded into ARINC818 video electric signals and output.
The AFDX terminal module is an AFDX protocol network node of the MFD, realizes the mutual conversion and forwarding of AFDX protocol data and PCI-E bus protocol data, and realizes the data communication, online upgrade and other works of the MFD and the onboard processor.
The liquid crystal display module receives and displays DVI video signals sent by the interface bus module; collecting a key of the light guide plate and an ambient light brightness signal, receiving coordinate information of the infrared touch screen, converting the coordinate information into protocol data, and transmitting the protocol data; the 1 st RS422 interface sends the key value, the brightness data, the screen temperature data, the backlight temperature data and the BIT detection information to the interface bus module, and receives the instruction of the interface bus module to carry out brightness adjustment and day and night switching; sending the coordinate value of the touch screen to an interface bus module through a 2 nd RS422 interface; low-temperature heating and control are realized.
The light guide panel provides emergency keys for pilot operation, including brightness adjustment, switches, and home keys. An ambient light brightness sensor is arranged to sense ambient brightness and provide illumination for all keys and characters on the panel.
The power supply module provides working power supply required by each MFD module, and carries out lightning protection, filtering, isolation secondary conversion and other treatment on the input power supply on the machine.
3. Main tactical technical index and use requirement
3.1 functional requirements
a) Acquiring required data from the AFDX bus, and processing and displaying working pictures and characters of the airborne system;
b) the device has the functions of collecting and displaying external video signals;
c) the video signal is input into 2-path ARINC818, and 1-path ARINC818 is output for the recording and replaying of the data acquisition and recording subsystem;
d) the backup state obtains the flight parameter display from HB6096-86 and RS-422 buses.
3.2 Performance requirements
3.2.1 Properties of the product
a) Has the functions of generating and displaying graphs;
b) the touch control function is provided:
touch-sensitive mode: infrared ray type
A touch sensitive medium: opaque medium
Multi-point touch: can realize 2-point touch control
Minimum touch size: not more than 6mm x 6mm
Response time: not more than 16ms
Linearity error: not more than 3mm
The abrasion resistance of the touch screen is in accordance with American military standard MIL-PRF-13830B section C4.5.10 and C4.5.11 of general standards for monitoring production, assembly and detection of optical elements for military fire control equipment, and other performance indexes are not influenced.
c) Has the function of day/night mode conversion;
d) the automatic/manual brightness adjusting function is realized;
e) the external video processing and displaying function is provided;
f) the key software and hardware modules have dual-redundancy backup function;
g) the power-on self-checking function, the periodic self-checking function and the starting self-checking function are provided;
h) the digital map display function is provided;
i) support for windowing display capabilities;
j) the radiance of the MFD should meet the requirements for "electronic and electro-optic (color)" for type i class B illumination in GJB 1394-1992:
k) the MFD's day/night switching lighting controller controls the lighting controller in a unified way, and the lighting controller outputs a suspension/28V ground signal to control day/night switching, wherein the suspension signal is in a day state, and the 28V ground signal is in a night state.
l) power supply and power consumption:
rated operating voltage: 28VDC +/-10% normal temperature power consumption: less than or equal to 135W (Single piece)
Maximum power consumption at low temperature heating: less than or equal to 335W (Single piece)
The power supply system has the advantages that the power supply system must normally work during 18V-32V power supply and 50ms power failure, and the other power supply requirements meet the power utilization requirements of GJB181B-2012 equipment;
m) the same type of display should be interchangeable.
3.2.2 display Properties
a) Effective display area: 508.8mm +/-1 mm multiplied by 203.5mm +/-1 mm;
b) display medium: an active matrix liquid crystal display screen with each color of RGB not less than 8 bits;
c) resolution ratio: 2560 pixels × 1024 pixels;
d) contrast ratio under all daylight environmental conditions: the contrast ratio of white figures and alpha-digital images within 75% of the whole observation angle is not less than 5;
e) uniformity of luminance: less than 25% in daytime mode (white field maximum brightness);
f) color gamut range: not less than 68%;
g) day mode brightness: the maximum brightness is not less than 1000cd/m2, and the minimum brightness is 5-10 cd/m2;
h) night mode luminance: the maximum brightness is not less than 25-30 cd/m2, and the minimum brightness is not more than 0.17cd/m2;
i) gray scale: not less than 256;
j) reflectance ratio: specular reflection + diffuse reflection is less than 1.3%;
k) visual angle envelope: horizontal 60 °, vertical +40 °/-20 °.
l) preheating time: the picture can be displayed when the temperature is less than 15s at 20 ℃ and is not more than 5min at-45 ℃;
m) the picture refresh rate is not less than 20 frames/s.
3.2.3 interface requirements
The front and back cabin multifunctional displays are all cross-linked with the core processor, the video processor and the data loading recorder, receive and process system instructions, video and other data, complete corresponding display and control functions, and output video optical signals for recording. The specific cross-linking interfaces are as follows:
a) peripheral keys; an emergency key is provided;
b) discrete quantity: not less than 4 paths;
c) aviation Ethernet interface: 2-path;
d) the video signal is input into 2 paths and output into 1 path. The video input/output interface is ARINC818, the input resolution is 1280 multiplied by 1024@60Hz, and the output resolution is 2560 multiplied by 1024@30 Hz;
e) HB6096-86 bus interface: 4 paths of reaction:
f) testing interface requirements:
an independent interface is provided to support PDF file loading;
the off-line and on-line software loading capacity is realized;
g) by adopting an RS422 interface, an external signal can be input to excite the display;
the software loading and upgrading should conform to the AIRINC615A standard.
The invention relates to a dual-redundancy graph display device of an airborne display, which comprises (1) a simplified circuit design and complete functions; the reliability is strong, the power consumption is low, the anti-interference capability is strong, and the structural design is stable and reliable; the components are selected from 100% of localization; and (5) optimizing the human-computer efficiency.
While the invention has been described in connection with what is presently considered to be the most practical and preferred embodiment, it is to be understood that the invention is not to be limited to the disclosed embodiment, but on the contrary, is intended to cover various modifications and equivalent arrangements included within the spirit and scope of the appended claims.
Claims (2)
1. The utility model provides an airborne display dual redundant figure display device which characterized in that: the MFD main hardware comprises a graphic display control module, an interface bus module, a power supply module, an AFDX terminal module, a video fiber module, a liquid crystal display module, a light guide plate and other 7 functional modules, wherein the graphic display control module, the power supply module and the AFDX terminal module adopt a dual redundancy design, 2 pieces of hardware, software and functional performance are completely consistent, and the two pieces of hardware, software and functional performance are mutually hot backed up; the interface bus module is designed into 1 board card, but consists of two parts of circuits with completely the same functions, and the tasks are backed up.
2. The dual-redundancy graphic display device of claim 1, wherein the control circuit and the physical interface of the liquid crystal display module, the circuit and the physical interface of the interface bus module are designed with dual redundancy, the graphic display control module, the AFDX terminal module and the power supply module are designed with dual redundancy, the whole device is divided into a main part and a standby part 2, and the dual-redundancy design of the product is realized between the main part and the standby part through corresponding software instructions.
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| Application Number | Priority Date | Filing Date | Title |
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| CN202010729503.8A CN112040143A (en) | 2020-07-27 | 2020-07-27 | Dual-redundancy graphic display device of airborne display |
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| Application Number | Priority Date | Filing Date | Title |
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| CN202010729503.8A CN112040143A (en) | 2020-07-27 | 2020-07-27 | Dual-redundancy graphic display device of airborne display |
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| CN112040143A true CN112040143A (en) | 2020-12-04 |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN106846661A (en) * | 2017-03-21 | 2017-06-13 | 广州市华标科技发展有限公司 | One kind entry and exit self-help certificate handling devices and methods therefor |
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| CN203143009U (en) * | 2012-12-25 | 2013-08-21 | 中航(苏州)雷达与电子技术有限公司 | Novel airborne display |
| CN105539867A (en) * | 2015-12-10 | 2016-05-04 | 中国航空工业集团公司西安航空计算技术研究所 | Utility aircraft airborne electronic system based on unified processing platform |
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| US20080291686A1 (en) * | 2005-01-14 | 2008-11-27 | Cull Brian D | Extended avionics lcd backlight |
| US20070046670A1 (en) * | 2005-08-24 | 2007-03-01 | Hedrick Geoffrey S | Aircraft flat panel display system with graphical image integrity |
| CN203143009U (en) * | 2012-12-25 | 2013-08-21 | 中航(苏州)雷达与电子技术有限公司 | Novel airborne display |
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