CN205619938U - Spare flight display and spare instrument of integration - Google Patents
Spare flight display and spare instrument of integration Download PDFInfo
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- CN205619938U CN205619938U CN201620226719.1U CN201620226719U CN205619938U CN 205619938 U CN205619938 U CN 205619938U CN 201620226719 U CN201620226719 U CN 201620226719U CN 205619938 U CN205619938 U CN 205619938U
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Abstract
The utility model discloses a spare flight display, including central processing module, atmosphere measured module, boat appearance measured module and display module, still disclose the spare instrument of integration, including magnetic sensor with spare flight display, magnetic sensor's output passes through aircraft parameter input interface and is connected with central processing module's input. The utility model discloses in one kind backup the flight display and have an abundant function, integrated central processing module, atmosphere measured module and boat appearance measured module, the integrated level is high, the practicality is strong, the utility model discloses in the spare instrument of integration contain spare flight display, have the characteristics of integrated level height, small and low power dissipation, still alleviateed the quality of spare instrument. The utility model relates to a but spare flight display and spare instrument of integration wide application in spare instrument field of aviation.
Description
Technical field
This utility model relates to aviation backup instrument field, especially a kind of backup flight displays and integration backup instrument.
Background technology
MEMS i.e. MEMS (Microelectro Mechanical Systems), MEMS sensor is the novel sensor using microelectronics and micromachining technology to manufacture.Compared with traditional sensor, it has, and volume is little, lightweight, low cost, low in energy consumption, reliability is high, be suitable to mass production, is easily integrated and realizes intelligentized feature.
ARINC429 bus structures are simple, stable performance, strong interference immunity.Maximum advantage is that reliability is high, this be due to decentralized control, transmission is reliable, mistake isolation is good.
The full name of RS-232C standard (agreement) is EIA-RS-232C standard (being called for short 232, RS232), wherein EIA (Electronic Industry
Association) EIA is represented, RS(recommended
Standard) representing proposed standard, 232 is identification number, and C represents the up-to-date once amendment (1969) of RS232, before this, has RS232B, RS232A.Its regulation connects cable and machinery, electrical characteristic, semiotic function and the process of transmission.Conventional physical criterion also has EIARS-422A, EIA RS-423A, EIARS-485.
RS-422 standard full name is " electrical characteristic of balanced voltage digital interface circuit ", it defines the characteristic of interface circuit.Actually also have a signal ground, totally 5 lines.Owing to receptor uses high input impedance and sends the driving force that driver is more higher than RS232, therefore allow to connect multiple receiving node on the same transmission line, at most can connect 256 nodes.I.e. one main equipment (Master), remaining is from equipment (Slave), can not communicate between equipment, so RS-422 supports point-to-points two-way communication.
Synthetic backup instrument refers to use the new techniques such as MEMS solid state sensor, electronics and information, pressure altimeter, airspeed-indicator, horizon sensor, magnetic compass etc. are separated the information of instrument and carries out COMPREHENSIVE CALCULATING and integrated, integrated display aspect, highly, the integrated emergency equipment of speed, replace tradition separate mechanical type altimeter, airspeed-indicator, on a crash basis level and magnetic compass.Applying widely on the backup the most various aircraft of instrument at present, it in emergency circumstances can provide emergency navigation information in master instrument inefficacy etc., is the visual plant ensureing the safest landing of carrier aircraft.
Synthetic backup instrument is typically by three LRUs: display unit, air navigation attitude measurement in a closed series unit and Strapdown Magnetometer Sensor form, and integrated level is relatively low, and volume is relatively big, heavier-weight, power consumption are higher.
Utility model content
In order to solve above-mentioned technical problem, the purpose of this utility model is to provide a kind of backup flight displays and integration backup instrument, and described backup flight displays has abundant function, and integrated level is high, practical；Described integration backup instrument has high integration, and volume is little, and quality is little, feature low in energy consumption.
This utility model be the technical scheme is that a kind of backup flight displays, including central processing module, aeromerric moasurenont module, navigation attitude measurement module and display module, wherein:
The described outfan of aeromerric moasurenont module is connected with the input of central processing module；
The described outfan of navigation attitude measurement module is connected with the input of central processing module；
The outfan of described central processing module is connected with the input of display module.
Further, described backup flight displays also includes that aircraft is to connection module, described aircraft includes that to connection module power interface, aircraft parameter output interface, aircraft parameter input interface and multichannel spare interface, described power interface, aircraft parameter output interface, aircraft parameter input interface and multichannel spare interface are all connected with central processing module.
Further, described backup flight displays also includes that filtration module, described power interface, aircraft parameter output interface, aircraft parameter input interface and multichannel spare interface are all connected with central processing module by filtration module.
Further, described backup flight displays also includes sensing module, the outfan of described sensing module is connected with the input of central processing module, described sensing module includes that luminance sensor and temperature sensor, the outfan of described luminance sensor and temperature sensor are all connected with the input of central processing module.
Further, described backup flight displays also includes that the key-press module with light guide plate, the outfan of the described key-press module with light guide plate are connected with the input of central processing module.
Further, described aeromerric moasurenont module includes dynamic pressure transducer and static pressure transducer, the outfan of described dynamic pressure transducer and static pressure transducer is all connected with the input of central processing module, and described dynamic pressure transducer and static pressure transducer are silicon resonance type pressure transducer.
Further, described navigation attitude measurement module is MEMS sensor.
Further, described display module is wide temperature LCDs.
What this utility model was used another solution is that a kind of integration backup instrument, and including Magnetic Sensor and described backup flight displays, the outfan of described Magnetic Sensor is connected with the input of central processing module by aircraft parameter input interface.
Further, described aircraft parameter input interface includes RS422 interface and ARINC429 interface.
The beneficial effects of the utility model are: in this utility model, a kind of flight displays that backs up has abundant function, integrating central processing module, aeromerric moasurenont module and navigation attitude measurement module, and integrated level is high, practical；In this utility model, a kind of integration backup instrument comprises backup flight displays, has the advantages that integrated level is high, volume is little and low in energy consumption, also reduces the quality of backup instrument.
It addition, the aeromerric moasurenont module of backup flight displays uses the silicon resonance type pressure transducer that precision height volume is little, drift when reducing atmosphere data, temperature drift error and weight；Navigation attitude measurement module uses miniaturization MEMS solid state sensor, is integrated in backup flight displays, with satisfied use requirement；Also increase filtration module, be filtered processing to outside and backup flight displays crosslinking all signals, improve the anti-electromagnetic interference capability of backup flight displays.
Accompanying drawing explanation
Below in conjunction with the accompanying drawings detailed description of the invention of the present utility model is described further:
Fig. 1 is a kind of structured flowchart backing up flight displays in this utility model；
Fig. 2 is the structured flowchart of a kind of integration backup instrument in this utility model；
Fig. 3 is a kind of specific embodiment structured flowchart backing up flight displays in this utility model.
Detailed description of the invention
It should be noted that in the case of not conflicting, the embodiment in the application and the feature in embodiment can be mutually combined.
A kind of backup flight displays, with reference to Fig. 1, including central processing module, aeromerric moasurenont module, navigation attitude measurement module and display module, wherein:
The described outfan of aeromerric moasurenont module is connected with the input of central processing module；
The described outfan of navigation attitude measurement module is connected with the input of central processing module；
The outfan of described central processing module is connected with the input of display module.
As further preferred embodiment, described aeromerric moasurenont module includes dynamic pressure transducer and static pressure transducer, the outfan of described dynamic pressure transducer and static pressure transducer is all connected with the input of central processing module, and described dynamic pressure transducer and static pressure transducer are silicon resonance type pressure transducer.Use the silicon resonance type pressure transducer that precision is high and volume is little, drift when reducing atmosphere data, temperature drift error and the weight of integration backup instrument.
As further preferred embodiment, described navigation attitude measurement module is MEMS sensor, meets the demand of user.
As further preferred embodiment, described display module is wide temperature LCDs, makes display picture become apparent from.
Described central processing module is high-performance treatments chip, uses high-performance treatments chip to improve picture refreshing rate, makes display picture seem more smooth, and when aircraft does high maneuver, the followability of picture is more preferable.Use high-performance treatments chip to replace original computing chip and display processes chip, reach to reduce volume, alleviate weight, the purpose of reduction power consumption.
Aeromerric moasurenont module, navigation attitude measurement module, display module are integrated in parts with central processing module, Highgrade integration, adapt to Aviation Industry demand.
As further preferred embodiment, described backup flight displays also includes that aircraft is to connection module, described aircraft includes that to connection module power interface, aircraft parameter output interface, aircraft parameter input interface and multichannel spare interface, described power interface, aircraft parameter output interface, aircraft parameter input interface and multichannel spare interface are all connected with central processing module.
As further preferred embodiment, described backup flight displays also includes that filtration module, described power interface, aircraft parameter output interface, aircraft parameter input interface and multichannel spare interface are all connected with central processing module by filtration module.Outside and backup flight displays crosslinking all signals are all filtered processing by filtration module, improve the anti-electromagnetic interference capability of integration backup instrument.
As further preferred embodiment, described backup flight displays also includes sensing module, the outfan of described sensing module is connected with the input of central processing module, described sensing module includes that luminance sensor and temperature sensor, the outfan of described luminance sensor and temperature sensor are all connected with the input of central processing module.
As further preferred embodiment, described backup flight displays also includes that the key-press module with light guide plate, the outfan of the described key-press module with light guide plate are connected with the input of central processing module.Owing to key-press module is configured with light guide plate, can make key light emitting under dark condition, user can normally use button.
A kind of integration backup instrument, with reference to Fig. 2, including Magnetic Sensor and described backup flight displays, the outfan of described Magnetic Sensor is connected with the input of central processing module by aircraft parameter input interface.
As further preferred embodiment, described aircraft parameter input interface includes RS422 interface and ARINC429 interface.
It is a kind of specific embodiment structured flowchart backing up flight displays in this utility model with reference to Fig. 3, Fig. 3.As it is shown on figure 3, the afterbody at backup flight displays is provided with the air pressure pressure inlet being connected with pitot total head, described dynamic pressure transducer is by experiencing the air pressure Pt of this air pressure pressure inlet to measure stream pressure, thus judges flight speed；It is also provided with the air pressure pressure inlet being connected with pitot static pressure, described static pressure transducer is by experiencing the air pressure Ps of this air pressure pressure inlet to measure static air pressure, thus judging flying height, the outfan of two pressure inlets is connected with the dynamic pressure transducer of aeromerric moasurenont module and the input of static pressure transducer respectively.
Front portion at backup flight displays, connection module is connected with other equipment of aircraft by backup flight displays by aircraft, described aircraft includes power interface, aircraft parameter output interface, aircraft parameter input interface and multichannel spare interface to connection module, power interface is divided into aircraft power supply interface and stand-by power supply interface, aircraft parameter output interface is ARINC429 interface, and aircraft parameter input interface includes ARINC429 interface and RS422 interface.Particularly as follows: backup flight displays is connected with direct current 28V power supply by aircraft power supply interface, backup flight displays sends local signal to flying to join record system by 1 road ARINC429 interface, backup flight displays receives the signal of radio altimeter and telecompass respectively by 2 road ARINC429 interfaces, backup flight displays is connected with magnetic compass by 1 tunnel full duplex RS422 interface, backup flight displays is connected by 1 road emergency power supply interface and emergency power supply, aircraft is provided with 3 road expansion interfaces and 2 road RS422 EBIs as spare interface to connection module, in the present embodiment, RS422 bus uses full duplex RS422A bus.With reference to Fig. 3, described filtration module is filter connector, after the data that the airborne equipment that connection module is connected by aircraft is inputted are filtered processing by described filter connector, transfers data to central processing module.
When integration backup instrument is in running order, aeromerric moasurenont module gathers the total head of aircraft, static pressure data and sends data to central processing module and carry out atmosphere data resolving.
Linear acceleration that navigation attitude measurement module perception aircraft three is axial and angular velocity signal, through processing and resolving obtains course, attitude data, sent to central processing module by RS232 interface.
Magnetic Sensor gathers the magnetic heading data message of aircraft, and is used for revising course data by the transmission of RS422 interface to central processing module, improves the certainty of measurement of heading measure data.
Central processing module receives the data that connection module is gathered by aeromerric moasurenont module, navigation attitude measurement module, Magnetic Sensor, key-press module and aircraft, through data analysis and process, generate R, G, B digital video signal by picture requirement to send to display module and show, the content of display include course angle, roll angle, the angle of pitch, pressure altitude, indicator air speed, rising or falling speed, field press-fit order value, airborne equipment has related parameter and fault message.
It is above preferable enforcement of the present utility model is illustrated, but the invention is not limited to described embodiment, those of ordinary skill in the art it may also be made that all equivalent variations or replacement on the premise of this utility model spirit, and deformation or the replacement of these equivalents are all contained in the application claim limited range.
Claims (10)
1. a backup flight displays, it is characterised in that include central processing module, aeromerric moasurenont module, navigation attitude measurement module and display module, wherein:
The described outfan of aeromerric moasurenont module is connected with the input of central processing module；
The described outfan of navigation attitude measurement module is connected with the input of central processing module；
The outfan of described central processing module is connected with the input of display module.
Backup flight displays the most according to claim 1, it is characterized in that, described backup flight displays also includes that aircraft is to connection module, described aircraft includes that to connection module power interface, aircraft parameter output interface, aircraft parameter input interface and multichannel spare interface, described power interface, aircraft parameter output interface, aircraft parameter input interface and multichannel spare interface are all connected with central processing module.
Backup flight displays the most according to claim 2, it is characterized in that, described backup flight displays also includes that filtration module, described power interface, aircraft parameter output interface, aircraft parameter input interface and multichannel spare interface are all connected with central processing module by filtration module.
4. according to the backup flight displays described in Claims 2 or 3, it is characterized in that, described backup flight displays also includes sensing module, the outfan of described sensing module is connected with the input of central processing module, described sensing module includes that luminance sensor and temperature sensor, the outfan of described luminance sensor and temperature sensor are all connected with the input of central processing module.
5. according to the backup flight displays described in Claims 2 or 3, it is characterised in that described backup flight displays also includes that the key-press module with light guide plate, the outfan of the described key-press module with light guide plate are connected with the input of central processing module.
Backup flight displays the most according to claim 2, it is characterized in that, described aeromerric moasurenont module includes dynamic pressure transducer and static pressure transducer, the outfan of described dynamic pressure transducer and static pressure transducer is all connected with the input of central processing module, and described dynamic pressure transducer and static pressure transducer are silicon resonance type pressure transducer.
Backup flight displays the most according to claim 6, it is characterised in that described navigation attitude measurement module is MEMS sensor.
8. according to the backup flight displays described in claim 2,3,6 or 7, it is characterised in that described display module is wide temperature LCDs.
9. an integration backup instrument, it is characterised in that including the backup flight displays described in Magnetic Sensor and any one of claim 2 to 8, the outfan of described Magnetic Sensor is connected with the input of central processing module by aircraft parameter input interface.
Integration backup instrument the most according to claim 9, it is characterised in that described aircraft parameter input interface includes RS422 interface and ARINC429 interface.
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| Application Number | Priority Date | Filing Date | Title |
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| CN201620226719.1U CN205619938U (en) | 2016-03-23 | 2016-03-23 | Spare flight display and spare instrument of integration |
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| CN201620226719.1U CN205619938U (en) | 2016-03-23 | 2016-03-23 | Spare flight display and spare instrument of integration |
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Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108163216A (en) * | 2017-11-03 | 2018-06-15 | 中航通飞研究院有限公司 | A kind of low cost avionics system |
| CN109115241A (en) * | 2018-08-07 | 2019-01-01 | 中国航空无线电电子研究所 | Vector data source integrity monitoring method |
| CN111189470A (en) * | 2019-11-15 | 2020-05-22 | 陕西飞机工业（集团）有限公司 | Backup instrument for canceling full static pressure pipeline |
| CN113127269A (en) * | 2019-12-31 | 2021-07-16 | 上海紫港信息科技有限公司 | Method for maintaining reconstruction of flight display |
| CN113280834A (en) * | 2021-05-24 | 2021-08-20 | 北京安达维尔民用航空技术有限公司 | Airplane comprehensive backup electronic instrument system |
-
2016
- 2016-03-23 CN CN201620226719.1U patent/CN205619938U/en active Active
Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108163216A (en) * | 2017-11-03 | 2018-06-15 | 中航通飞研究院有限公司 | A kind of low cost avionics system |
| CN108163216B (en) * | 2017-11-03 | 2022-06-28 | 中航通飞研究院有限公司 | Low-cost avionics system |
| CN109115241A (en) * | 2018-08-07 | 2019-01-01 | 中国航空无线电电子研究所 | Vector data source integrity monitoring method |
| CN111189470A (en) * | 2019-11-15 | 2020-05-22 | 陕西飞机工业（集团）有限公司 | Backup instrument for canceling full static pressure pipeline |
| CN113127269A (en) * | 2019-12-31 | 2021-07-16 | 上海紫港信息科技有限公司 | Method for maintaining reconstruction of flight display |
| CN113280834A (en) * | 2021-05-24 | 2021-08-20 | 北京安达维尔民用航空技术有限公司 | Airplane comprehensive backup electronic instrument system |
| CN113280834B (en) * | 2021-05-24 | 2022-11-11 | 北京安达维尔民用航空技术有限公司 | Airplane comprehensive backup electronic instrument system |
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