CN204883226U - Twin bus avionics system configuration - Google Patents
Twin bus avionics system configuration Download PDFInfo
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- CN204883226U CN204883226U CN201520554002.5U CN201520554002U CN204883226U CN 204883226 U CN204883226 U CN 204883226U CN 201520554002 U CN201520554002 U CN 201520554002U CN 204883226 U CN204883226 U CN 204883226U
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Abstract
The utility model discloses a twin bus avionics system configuration, relate to aircraft design technical field, it the bus design theory based on MIL -STD -1553B, can effectively improve the reliability of system, this configuration includes the avionics system, display device, collection equipment, controlgear, a controller, the sensor, this twin bus avionics system configuration is the twin bus avionics system configuration based on MIL -STD -1553B, this configuration is with each equipment of avionics system through showing accuse bus and task bus, and be aided with the RS422A bus, the HB6096 bus inserts the avionics system, the bus load of avionics system has been reduced, attenuates the shock of a rotor and enhances the reliability of a system, the messenger system possesses stronger extended capability, the market competition of aircraft has been improved.
Description
Technical field
The utility model relates to airplane design technical field, particularly a kind of dual bus avionics system configuration.
Background technology
Along with the increase that present generation aircraft task ability requires, increasing to the information quantity requirement of present generation aircraft, corresponding avionics system develops into the system integration, namely with the association type bussing technique of MIL-STD-1553B bussing technique for application by initial autonomous device is not crosslinked mutually.
At present, MIL-STD-1553B bussing technique has been widely used in three generations's fighter plane, but different from functional requirement and have the application of different modes according to the various feature of concrete aircraft, particularly for the aircraft that volume is less than normal, general employing Single Wire Bus Technology, system stability is poor, and extended capability is not enough.
Summary of the invention
Technical problem to be solved in the utility model is to provide a kind of dual bus avionics system configuration, and the bussing technique of the two remaining of dual bus of employing, to solve the above-mentioned multinomial defect caused in prior art.
For achieving the above object, the utility model provides following technical scheme: a kind of dual bus avionics system configuration, comprise avionics system, display device, collecting device, opertaing device, controller, sensor, it is characterized in that: described dual bus avionics system configuration comprises controller, sensor, and be all interconnected by MIL-STD-1553B bus and collecting device, and MIL-STD-1553B bus is also by some display devices and opertaing device, controller, sensor couples together, some display devices are also connected by video line with controller, collecting device is by backup signal line and sensor, avionics system and some display devices connect, controller is connected with opertaing device by RS422A bus, opertaing device is connected with controller by RS422A bus, controller is by HB6096 bus access avionics system.
Preferably, described avionics system comprises communication apparatus and navigator.
Preferably, described RS422A bus is asynchronous serial communication STD bus, and is furnished with RS422A interface.
Preferably, described display device is light-emitting diode display.
The beneficial effect of above technical scheme is adopted to be: this dual bus avionics system configuration is a kind of dual bus avionics system configuration based on MIL-STD-1553B, each equipment of avionics system is controlled bus and mission bus by aobvious by this configuration, and be aided with RS422A bus, HB6096 bus access avionics system, reduce the bus load of avionics system, improve the reliability of system, make system possess stronger extended capability, improve the market competitiveness of aircraft.This configuration has taken into full account the remaining problem of system, the mode of the two remaining of the dual bus adopted can possess stronger extended capability under the prerequisite ensureing system margin, when two buses all break down, by backup signal line, the signal of Major Systems can be delivered to display and carry out backup display, make a return voyage for pilot, improve the reliability of system and the security of aircraft.
Accompanying drawing explanation
Fig. 1 is the organigram of a kind of dual bus avionics system of the utility model configuration.
Embodiment
The preferred implementation of a kind of dual bus avionics system of the utility model configuration is described in detail below in conjunction with accompanying drawing.
Fig. 1 shows the embodiment of a kind of dual bus of the utility model avionics system configuration: a kind of dual bus avionics system configuration, comprise avionics system, display device, collecting device, opertaing device, controller, sensor, it is characterized in that: described dual bus avionics system configuration comprises controller, sensor, and be all interconnected by MIL-STD-1553B bus and collecting device, and MIL-STD-1553B bus is also by some display devices and opertaing device, controller, sensor couples together, some display devices are also connected by video line with controller, collecting device is by backup signal line and sensor, avionics system and some display devices connect, controller is connected with opertaing device by RS422A bus, opertaing device is connected with controller by RS422A bus, controller is by HB6096 bus access avionics system.This utility model greatly reduces the bus load of avionics system, improves the reliability of system, makes system possess stronger extended capability, improves the market competitiveness of aircraft.
Avionics system comprises communication apparatus and navigator, RS422A bus is asynchronous serial communication STD bus, and be furnished with RS422A interface, display device is light-emitting diode display, and sensor is pitot or angle of attack sensor, has taken into full account the remaining problem of system, when two buses all break down, by backup signal line, the signal of Major Systems can be delivered to display and carry out backup display, make a return voyage for pilot, improve the reliability of system and the security of aircraft.
Above is only preferred implementation of the present utility model; it should be pointed out that for the person of ordinary skill of the art, under the prerequisite not departing from the utility model creation design; can also make some distortion and improvement, these all belong to protection domain of the present utility model.
Claims (4)
1. a dual bus avionics system configuration, comprise avionics system, display device, collecting device, opertaing device, controller, sensor, it is characterized in that: described dual bus avionics system configuration comprises controller, sensor, and be all interconnected by MIL-STD-1553B bus and collecting device, and MIL-STD-1553B bus is also by some display devices and opertaing device, controller, sensor couples together, some display devices are also connected by video line with controller, collecting device is by backup signal line and sensor, avionics system and some display devices connect, controller is connected with opertaing device by RS422A bus, opertaing device is connected with controller by RS422A bus, controller is by HB6096 bus access avionics system.
2. dual bus avionics system configuration according to claim 1, is characterized in that: described avionics system comprises communication apparatus and navigator.
3. dual bus avionics system configuration according to claim 1, is characterized in that: described RS422A bus is asynchronous serial communication STD bus, and is furnished with RS422A interface.
4. dual bus avionics system configuration according to claim 1, is characterized in that: described display device is light-emitting diode display.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201520554002.5U CN204883226U (en) | 2015-07-29 | 2015-07-29 | Twin bus avionics system configuration |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201520554002.5U CN204883226U (en) | 2015-07-29 | 2015-07-29 | Twin bus avionics system configuration |
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| CN204883226U true CN204883226U (en) | 2015-12-16 |
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| CN201520554002.5U Active CN204883226U (en) | 2015-07-29 | 2015-07-29 | Twin bus avionics system configuration |
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Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107171919A (en) * | 2017-05-02 | 2017-09-15 | 江西洪都航空工业集团有限责任公司 | A kind of trainer aircraft integrated avionic system based on multibus |
| CN108594635A (en) * | 2018-04-13 | 2018-09-28 | 成都赫尔墨斯科技股份有限公司 | A kind of device and method for aggregation of data display control in avionics system |
| CN109799839A (en) * | 2018-12-24 | 2019-05-24 | 北京青云航空仪表有限公司 | A kind of automatic flight control assemblies |
| CN110196552A (en) * | 2019-06-21 | 2019-09-03 | 江西洪都航空工业集团有限责任公司 | A kind of avionics system bus Standby control method |
| CN112233386A (en) * | 2020-09-25 | 2021-01-15 | 中国直升机设计研究所 | Helicopter voice alarm device and method |
-
2015
- 2015-07-29 CN CN201520554002.5U patent/CN204883226U/en active Active
Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107171919A (en) * | 2017-05-02 | 2017-09-15 | 江西洪都航空工业集团有限责任公司 | A kind of trainer aircraft integrated avionic system based on multibus |
| CN108594635A (en) * | 2018-04-13 | 2018-09-28 | 成都赫尔墨斯科技股份有限公司 | A kind of device and method for aggregation of data display control in avionics system |
| CN108594635B (en) * | 2018-04-13 | 2021-06-29 | 成都赫尔墨斯科技股份有限公司 | Device and method for data comprehensive display control in avionics system |
| CN109799839A (en) * | 2018-12-24 | 2019-05-24 | 北京青云航空仪表有限公司 | A kind of automatic flight control assemblies |
| CN110196552A (en) * | 2019-06-21 | 2019-09-03 | 江西洪都航空工业集团有限责任公司 | A kind of avionics system bus Standby control method |
| CN110196552B (en) * | 2019-06-21 | 2022-03-29 | 江西洪都航空工业集团有限责任公司 | Avionics system bus backup control method |
| CN112233386A (en) * | 2020-09-25 | 2021-01-15 | 中国直升机设计研究所 | Helicopter voice alarm device and method |
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