CN204856097U - A miniaturized integrated avionics system for helicopter - Google Patents
A miniaturized integrated avionics system for helicopter Download PDFInfo
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- CN204856097U CN204856097U CN201520639238.9U CN201520639238U CN204856097U CN 204856097 U CN204856097 U CN 204856097U CN 201520639238 U CN201520639238 U CN 201520639238U CN 204856097 U CN204856097 U CN 204856097U
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Abstract
The utility model discloses a miniaturized integrated avionics system for helicopter, synthesize indicative control unit, external system, control stick including the first indicative control unit of synthesis, second, first indicative control unit of synthesis and second are synthesized indicative control unit and are passed through the RS422 data bus connection, first synthesize indicative control unit and second synthesize indicative control unit adopt parallel and external system, control stick are connected, comprehensively the indicative control unit structure is the same for first comprehensively indicative control unit, second, includes respectively: display, bulk storage memory dish, IO connecting device, built -in circuit, built -in circuit includes input and output modules, power module and the comprehensive processing module that shows. The utility model discloses a small -size totalization avionics system configures compactly, and the security is high, is fit for promoting.
Description
Technical field
The utility model relates to aviation electronics field, particularly a kind of miniaturization integrated avionics system for helicopter.
Background technology
Traditional discrete formula avionics system is made up of the analogue instrument and radio communication navigator etc. of discrete installation, discrete avionics system instrument is many, system architecture is comparatively complicated, take up room large, weight is heavy, equipment operating is complicated, system reliability is lower, the avionics system of discrete limits aircraft Function Extension and technology upgrading potentiality, in addition, traditional aviation display & control system, display is what to separate with data processing and controller, synthesization and integrated degree low, cannot provide efficient for driver, succinct driving cabin interactive mode, simultaneously, for small-sized helicopter on market, the navigation such as small-sized fixed wing aircraft class aircraft is little to passenger cabin synthetical display control system bulk, lightweight, the demand that functional integration is high is also more and more higher.
Summary of the invention
The purpose of this utility model is exactly in order to overcome the deficiencies in the prior art, provide a kind of miniaturization integrated avionics system for helicopter, this small comprehensive avionics system integrates information displaying, data processing, maneuvering and control, integrated dispatch, for pilot provides safety, man-machine interface efficiently, possess the typical feature such as functional integration is high, framework open, lightweight, volume is little, in weight, spatial volume and functional performance, all meet the demands of aircraft in avionics system such as small-sized helicopter, small-sized fixed wing aircraft.
The utility model is achieved through the following technical solutions:
A kind of miniaturization integrated avionics system for helicopter, comprise the first synthetical display control unit, the second synthetical display control unit, external system, jociey stick, described first synthetical display control unit is connected by RS422 data bus with the second synthetical display control unit, and described first synthetical display control unit and the second synthetical display control unit adopt parallel way to be connected with described external system, jociey stick;
Described first synthetical display control unit, the second synthetical display control cellular construction are identical, comprise respectively:
Display, massive store dish, I/O coupling arrangement, built-in circuit;
Described built-in circuit comprises input/output module, power module and synthesis display processing module, described power module powers to described input/output module and described synthesis display processing module, described synthesis display processing module for the treatment of the external system of input/output module collection information and control display display frame.
First synthetical display control unit and described second synthetical display control unit can show external system data respectively and backup each other, when wherein a synthetical display control unit breaks down, all external system data can be shown separately by another synthetical display control unit.
Preferably, described display both sides are provided with 16 peripheral keys.
Preferably, described peripheral key is provided with light guide ring, operates under being adapted at dark condition.
Preferably, described display both sides are provided with for selecting the first function knob of all kinds of parameters in display frame and the second function knob for arranging all kinds of parameters in display frame.
Preferably, slip indicator is provided with below described display screen.
Preferably, the built-in night vision material of described slip indicator.Be suitable for night time operation.
Preferably, described I/O coupling arrangement comprises ARINC429 bus interface, RS422 bus interface, video interface, analog quantity interface, discrete magnitude interface, Ethernet interface and power interface.
Preferably, described video interface comprises XGA differential video interface and PAL analog differential video interface, and described jociey stick is connected with described synthetical display control unit by analog quantity interface.
Preferably, described external system comprises engine parameter acquisition system, radio altimeter, integrated navigation system, air data system, Flight Data Record System for Aircraft and communication navigation system, described communication navigation system comprises Audio Controller, automatic direction finder, short-wave radio set, S mode answering machine and instrument landing system (ILS), and wherein said instrument landing system (ILS) and short-wave radio set are for selecting assembling system.
Preferably, described display is also provided with light sensor, brightness regulating button and contrast adjustment button.The external environment condition illumination intensity that display is obtained by described light sensor, the bright dark degree of automatic adjusting screen, described brightness regulating button and described contrast adjustment button control the brightness and contrast of described liquid crystal display respectively.
The beneficial effects of the utility model are: the utility model has supplied to provide a kind of miniaturization integrated avionics system for helicopter, this small comprehensive avionics system collection information displaying, data processing, maneuvering and control, integrated dispatch is in one, for pilot provides safety, efficient man-machine interface, possesses functional integration high, framework is open, lightweight, the typical feature such as volume is little, in weight, spatial volume and functional performance aspect all meet light Medium Helicopter, the demand in avionics system such as small-sized fixed wing aircraft, small comprehensive avionics system compact in architecture of the present utility model, security is high, be applicable to promoting.
Accompanying drawing explanation
Accompanying drawing described herein is used to provide further understanding of the present utility model, forms a part of the present utility model, and schematic description and description of the present utility model, for explaining the utility model, is not formed improper restriction of the present utility model.In the accompanying drawings:
Fig. 1 is one-piece construction schematic diagram of the present utility model;
Fig. 2 is display surface structural representation in the utility model;
In Fig. 2,111 for display, 112 for peripheral key, 113 be the first function knob, 114 for slip indicator, 115 for brightness regulating button, 116 for contrast adjustment button, 117 for light sensor, 118 be the second function knob.
Embodiment
In order to make technical problem to be solved in the utility model, technical scheme and beneficial effect clearly, understand, below in conjunction with drawings and Examples, the utility model is further elaborated.Should be appreciated that specific embodiment described herein only in order to explain the utility model, and be not used in restriction the utility model.
Ginseng Fig. 1, the utility model provides a kind of miniaturization integrated avionics system for helicopter, comprise the first synthetical display control unit, second synthetical display control unit, the external system be connected with two synthetical display control unit, jociey stick and bus system, described first synthetical display control unit is connected by RS422 data bus with the second synthetical display control unit, described first synthetical display control unit and the second synthetical display control unit adopt parallel way to be connected with described external system, synchronization two synthetical display control unit are simultaneously in running order, the first described synthetical display control unit and described second synthetical display control unit independently can show all external system data, two described synthetical display control unit are by ARINC429 data bus, RS422 data bus, PAL video bus, XGA video bus, analog signal bus, industry ethernet and described external system carry out data cube computation,
First synthetical display control unit, the second synthetical display control cellular construction are identical, comprise respectively:
Long 8 inches a, display 111 of wide 6 inches, described display 111 is for showing the data of outside interconnected system.
Massive store dish, described massive store dish is used for memory word map datum, has numerical map systematic function;
I/O coupling arrangement, comprises ARINC429 bus interface, RS422 bus interface, video interface, analog quantity connects, discrete magnitude interface, Ethernet interface and power interface;
Built-in circuit, comprise input/output module, power module and synthesis display processing module, described power module powers to described input/output module and described synthesis display processing module, described synthesis display processing module for the treatment of the external system of input/output module collection information and control display display frame.
As preferred technical scheme, the display information of described first synthetical display control unit and described second synthetical display control unit display comprises: attitude, course, highly, the basic flight parameter display such as speed and alarm prompt; Navigational parameter, flight planning, numerical map and the system failure/maintenance information; Video information; External system status information; Man-machine interface picture.
As preferred technical scheme, described first synthetical display control unit and described second synthetical display control unit display structure are completely the same with composition, backup each other, in specific implementation process, described second synthetical display control unit shows main flight picture, mainly comprise the machine attitude, local state (speed, height etc.), radio navigation guides (position, orientation etc.) information, described first indicative control unit display Multi-function display picture, mainly comprise and comprise engine parameter, flight planning, way point information, engine parameter information can be superposed in the main flight picture of described second synthetical display control unit by button.
As preferred technical scheme, the video interface of described synthetical display control unit I/O coupling arrangement comprises XGA differential video interface and PAL analog differential video interface, and described jociey stick is connected with described synthetical display control unit by analog signal bus.
As preferred technical scheme, described external system comprises engine parameter acquisition system, radio altimeter, integrated navigation system, air data system, Flight Data Record System for Aircraft and communication navigation system, described communication navigation system comprises Audio Controller, automatic direction finder, short-wave radio set, ultrashort wave radio set, S mode answering machine and instrument landing system (ILS), in specific implementation, described instrument landing system (ILS) and short-wave radio set are choosing dress.
In concrete enforcement, described XGA differential video interface can be used for the data transmission between weather radar, and the data that described PAL analog differential video interface can be used between FLIR (Forward-Looking Infrared) video camera are transmitted.
In addition, in concrete enforcement of the present utility model, described power interface comprises mains lighting supply interface and working power interface, described mains lighting supply interface connects 28 volts of direct supplys, described working power interface can connect the direct supply between 12 volts to 32 volts, described ARINC429 bus interface has 11 road input interfaces, connect air data system respectively, radio altimeter, integrated navigation system, automatic direction finder, S mode answering machine, ultrashort wave radio set, Flight Data Record System for Aircraft, the data receiver of instrument landing system (ILS) (choosing dress) and short-wave radio set (choosing dress), described RS422 bus interface is used for described first synthetical display control unit and described second synthetical display control unit and Audio Controller, the data interaction of engine parameter acquisition system, and first interactive communication between synthetical display control unit and described second synthetical display control unit, described discrete magnitude interface is for receiving the id signal of described first synthetical display control unit and described second synthetical display control unit, wheel load signal, left display mode input, backup display input and vernier locking signal, described Ethernet interface is used for Data import.
As shown in Figure 2, display 111 both sides are provided with 16 peripheral keys 112, and every side distributes 8.Described peripheral key 112 is as the input interface of pilot to described synthetical display control unit information, and peripheral key 112 is provided with light guide ring, operates under being adapted at dark condition;
Display 111 both sides are also provided with the first function and revolve 113 and second function knob 118, and described first function knob 113 is for selecting all kinds of parameters in display frame, and described second function knob 118 is for arranging all kinds of parameters in display frame.
Be provided with slip indicator 114 below display 111, the built-in night vision material of described slip indicator 114, has night vision function.
Display 111 is also provided with light sensor 117, brightness regulating button 115 and contrast adjustment button 116, the external environment condition illumination intensity that described display 111 is obtained by described light sensor 117, the bright dark degree of automatic adjusting screen, described brightness regulating button 115 and described contrast adjustment button 116 control the brightness and contrast of described display respectively.
The above, be only embodiment of the present utility model, but protection domain of the present utility model is not limited thereto, and any change of expecting without creative work or replacement, all should be encompassed within protection domain of the present utility model.Therefore, the protection domain that protection domain of the present utility model should limit with claims is as the criterion.
Claims (10)
1. the miniaturization integrated avionics system for helicopter, it is characterized in that: comprise the first synthetical display control unit, the second synthetical display control unit, external system, jociey stick, described first synthetical display control unit is connected by RS422 data bus with the second synthetical display control unit, and described first synthetical display control unit and the second synthetical display control unit adopt parallel way to be connected with described external system, jociey stick;
Described first synthetical display control unit, the second synthetical display control cellular construction are identical, comprise respectively:
Display, massive store dish, I/O coupling arrangement, built-in circuit;
Described built-in circuit comprises input/output module, power module and synthesis display processing module, described power module powers to described input/output module and described synthesis display processing module, described synthesis display processing module for the treatment of the external system of input/output module collection information and control display display frame.
2. a kind of miniaturization integrated avionics system for helicopter according to claim 1, is characterized in that: described display both sides are provided with 16 peripheral keys.
3. a kind of miniaturization integrated avionics system for helicopter according to claim 2, is characterized in that: described peripheral key is provided with light guide ring.
4. a kind of miniaturization integrated avionics system for helicopter according to claim 1, is characterized in that: described display both sides are provided with for selecting the first function knob of all kinds of parameters in display frame and the second function knob for arranging all kinds of parameters in display frame.
5. a kind of miniaturization integrated avionics system for helicopter according to claim 1, is characterized in that: be provided with slip indicator below described display screen.
6. a kind of miniaturization integrated avionics system for helicopter according to claim 5, is characterized in that: the built-in night vision material of described slip indicator.
7. a kind of miniaturization integrated avionics system for helicopter according to claim 1, is characterized in that: described I/O coupling arrangement comprises ARINC429 bus interface, RS422 bus interface, video interface, analog quantity interface, discrete magnitude interface, Ethernet interface and power interface.
8. a kind of miniaturization integrated avionics system for helicopter according to claim 7, it is characterized in that: described video interface comprises XGA differential video interface and PAL analog differential video interface, described jociey stick is connected with described synthetical display control unit by analog quantity interface.
9. a kind of miniaturization integrated avionics system for helicopter according to claim 1, it is characterized in that: described external system comprises engine parameter acquisition system, radio altimeter, integrated navigation system, air data system, Flight Data Record System for Aircraft and communication navigation system, described communication navigation system comprises Audio Controller, automatic direction finder, short-wave radio set, S mode answering machine and instrument landing system (ILS), and wherein said instrument landing system (ILS) and short-wave radio set are for selecting assembling system.
10. a kind of miniaturization integrated avionics system for helicopter according to claim 1, is characterized in that: described display is also provided with light sensor, brightness regulating button and contrast adjustment button.
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| Application Number | Priority Date | Filing Date | Title |
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| CN201520639238.9U CN204856097U (en) | 2015-08-24 | 2015-08-24 | A miniaturized integrated avionics system for helicopter |
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| CN201520639238.9U CN204856097U (en) | 2015-08-24 | 2015-08-24 | A miniaturized integrated avionics system for helicopter |
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Cited By (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| 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 |
| CN106789499A (en) * | 2016-12-12 | 2017-05-31 | 石家庄飞机工业有限责任公司 | A kind of integrated avionic system for light-small aircraft |
| 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 |
| CN108445822A (en) * | 2018-06-05 | 2018-08-24 | 成都赫尔墨斯科技股份有限公司 | A kind of more member's aircraft avionics systems |
| CN108545202A (en) * | 2018-04-13 | 2018-09-18 | 成都赫尔墨斯科技股份有限公司 | A kind of integrated avionic system |
| CN111232232A (en) * | 2019-12-30 | 2020-06-05 | 成都赫尔墨斯科技股份有限公司 | Device and method for comprehensive display control of avionics equipment |
| CN112416827A (en) * | 2020-11-03 | 2021-02-26 | 中国直升机设计研究所 | Universal comprehensive avionics system for helicopter |
| CN113086220A (en) * | 2021-03-09 | 2021-07-09 | 深圳市南航电子工业有限公司 | Flight display method and system of flight display, electronic device and storage medium |
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2015
- 2015-08-24 CN CN201520639238.9U patent/CN204856097U/en active Active
Cited By (14)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| 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 |
| CN106789499A (en) * | 2016-12-12 | 2017-05-31 | 石家庄飞机工业有限责任公司 | A kind of integrated avionic system for light-small aircraft |
| 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 |
| CN108545202B (en) * | 2018-04-13 | 2021-01-26 | 成都赫尔墨斯科技股份有限公司 | Comprehensive avionics system |
| CN108545202A (en) * | 2018-04-13 | 2018-09-18 | 成都赫尔墨斯科技股份有限公司 | A kind of integrated avionic system |
| CN108445822A (en) * | 2018-06-05 | 2018-08-24 | 成都赫尔墨斯科技股份有限公司 | A kind of more member's aircraft avionics systems |
| CN108445822B (en) * | 2018-06-05 | 2024-04-02 | 成都赫尔墨斯科技股份有限公司 | Multi-member aircraft avionics system |
| CN111232232A (en) * | 2019-12-30 | 2020-06-05 | 成都赫尔墨斯科技股份有限公司 | Device and method for comprehensive display control of avionics equipment |
| CN111232232B (en) * | 2019-12-30 | 2023-08-29 | 成都赫尔墨斯科技股份有限公司 | Device and method for comprehensive display control of avionics equipment |
| CN112416827A (en) * | 2020-11-03 | 2021-02-26 | 中国直升机设计研究所 | Universal comprehensive avionics system for helicopter |
| CN112416827B (en) * | 2020-11-03 | 2023-04-11 | 中国直升机设计研究所 | Universal comprehensive avionics system for helicopter |
| CN113086220A (en) * | 2021-03-09 | 2021-07-09 | 深圳市南航电子工业有限公司 | Flight display method and system of flight display, electronic device and storage medium |
| CN113086220B (en) * | 2021-03-09 | 2024-04-30 | 深圳市南航电子工业有限公司 | Flight display method and system of flight display, electronic equipment and storage medium |
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Effective date of registration: 20220601 Address after: 200241 Building 5, No. 432, ziyue Road, Minhang District, Shanghai Patentee after: Shanghai avionics Co.,Ltd. Address before: 432 Guiping Road, Xuhui District, Shanghai, 2003 Patentee before: CHINA AERONAUTICAL RADIO ELECTRONICS Research Institute |