CN105138014A - Light and small type airplane avionics system configuration - Google Patents
Light and small type airplane avionics system configuration Download PDFInfo
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- CN105138014A CN105138014A CN201510613823.6A CN201510613823A CN105138014A CN 105138014 A CN105138014 A CN 105138014A CN 201510613823 A CN201510613823 A CN 201510613823A CN 105138014 A CN105138014 A CN 105138014A
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- control computer
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Abstract
The invention discloses a light and small type airplane avionics system configuration. The configuration comprises a main display control computer, a back-up display control computer, displays, a pitot-static system, a fuel oil computer, a GPS antenna, a radio navigation device and all kinds of sensors. The main display control computer transmits data with the back-up display control computer and is connected with the back-up display control computer via data buses and the displays in a front cabin and a back cabin. The main display control computer and the back-up display control computer are connected with the pitot-static system via an air pressure signal pipeline, with the GPS antenna, a magnetic course sensor, the fuel oil computer and the radio navigation device via data buses and with an engine sensor and a total temperature sensor. According to the invention, complexity degree of the configuration is reduced; weight of the system is reduced; reliability of the system is improved; cost of the avionics system is reduced; and market competitiveness of airplanes is increased.
Description
Technical field
The present invention relates to a kind of Aircraft electric system, particularly relate to a kind of light-small aircraft avionics system configuration.
Background technology
Along with the progress of avionics, middle and high level schoolaeroplane airborne electronic equipment system develops to synthetic aviation electronic, primary trainer is connected with middle and high level schoolaeroplane avionics system and occurs jump, be accustomed to the pilot of simple instrument in the face of middle and high level schoolaeroplane integrated avionics and display frame, be difficult to adapt to as early as possible, extend pilot's incubation time and cost, increase pilot's mortality, therefore need a applicable screening of design, elementary training, aerobatic light-small aircraft.Design as adopted traditional avionics system configuration, configure the independent Aerial Electronic Equipment such as aobvious control computer, mission computer, aviation attitude system, air data computer, aircraft low cost, lightweight demand can not be met, and due to light-small aircraft installing space effective, also these equipment cannot be installed.
Therefore, need to provide a kind of new technical scheme to solve the problems referred to above.
Summary of the invention
The technical issues that need to address of the present invention are to provide a kind of light-small aircraft avionics system configuration.
For solving technical matters of the present invention, the technical solution used in the present invention is:
A kind of light-small aircraft avionics system configuration, it comprises main aobvious control computer, the aobvious control computer of backup, display, pitot-static pressure system, fuel oil computing machine, gps antenna, radio navigation aids and various kinds of sensors, described master shows control computer and the aobvious control computer mutual data transmission of backup, described master shows control computer and backup shows control computer respectively by data bus and front deck, display in rear deck connects, described master shows control computer and is connected with pitot-static pressure system respectively by air pressure signal pipeline with the aobvious control computer of backup, described master shows control computer and backup shows control computer respectively by data bus and gps antenna, magnetic course transmitter, fuel oil computing machine, radio navigation aids connects, described master show control computer and the aobvious control computer of backup also respectively with engine sensor, total temperature probe connects.
Further, described master shows on control computer and is provided with Data import card.
Beneficial effect of the present invention: this configuration by avionics system presentation control function, the impression of boat appearance and resolve function, atmosphere data impression and resolve function, non-avionics system parameter acquisition function, data record comprehensively realize in an aobvious control computer, greatly reduce the complexity of avionics system configuration, reduce system weight, improve the reliability of system, reduce avionics system cost, improve the market competitiveness of aircraft.
Accompanying drawing explanation
Fig. 1 is theory diagram of the present invention.
1, main aobvious control computer, 2, the aobvious control computer of backup, 3, display, 4, pitot-static pressure system, 5, fuel oil computing machine, 6, gps antenna, 7, radio navigation aids, 8, Data import card, 9, magnetic course transmitter, 10, engine sensor, 11, total temperature probe.
Embodiment
Below in conjunction with the drawings and specific embodiments, the invention will be further described.Following examples, only for illustration of the present invention, are not used for limiting the scope of the invention.
As shown in Figure 1, a kind of light-small aircraft avionics system configuration of the present invention, it comprises main aobvious control computer 1, the aobvious control computer 2 of backup, display 3, pitot-static pressure system 4, fuel oil computing machine 5, gps antenna 6, radio navigation aids 7 and various kinds of sensors, main aobvious control computer 1 and aobvious control computer 2 mutual data transmission of backup, main aobvious control computer 1 is provided with Data import card 8, main aobvious control computer 1 and the aobvious control computer 2 of backup are respectively by data bus and front deck, display 3 in rear deck connects, main aobvious control computer 1 is connected with pitot-static pressure system 4 respectively by air pressure signal pipeline with the aobvious control computer 2 of backup, main aobvious control computer 1 and the aobvious control computer 2 of backup are respectively by data bus and gps antenna 6, magnetic course transmitter 9, fuel oil computing machine 5, radio navigation aids 7 connects, main aobvious control computer 1 and the aobvious control computer 2 of backup also respectively with engine sensor 10, total temperature probe 11 connects.
This configuration by the presentation control function of avionics system, the impression of boat appearance and resolve function, atmosphere data impression and resolve function, non-avionics system parameter acquisition function, data recording function comprehensively arrive main aobvious control computer 1, backup shows in the identical aobvious control computer of control computer 2 two and realizes, and effectively can reduce development cost and the weight of avionics system.
In Fig. 1, analog quantity and thermopair are all a kind of signal types, and analog quantity refers to voltage signal, frequency signal, resistance signal etc.; Thermopair is the aspect of a kind of temperature transmission, be exactly two kinds of different metal-clads together, when temperature variation, therebetween electric potential difference can be produced, this electric potential difference is supplied to aobvious control computer, aobvious control computer according to the national standard of associated temperature and electric potential difference, can be converted into corresponding temperature data electric potential difference.
The present invention has taken into full account the remaining problem of system, is configured with two identical processors and 4 identical displays in systems in which, the two remainings achieving system display and control.
Claims (2)
1. a light-small aircraft avionics system configuration, it is characterized in that: it comprises main aobvious control computer, the aobvious control computer of backup, display, pitot-static pressure system, fuel oil computing machine, gps antenna, radio navigation aids and various kinds of sensors, described master shows control computer and the aobvious control computer mutual data transmission of backup, described master shows control computer and backup shows control computer respectively by data bus and front deck, display in rear deck connects, described master shows control computer and is connected with pitot-static pressure system respectively by air pressure signal pipeline with the aobvious control computer of backup, described master shows control computer and backup shows control computer respectively by data bus and gps antenna, magnetic course transmitter, fuel oil computing machine, radio navigation aids connects, described master show control computer and the aobvious control computer of backup also respectively with engine sensor, total temperature probe connects.
2. a kind of light-small aircraft avionics system configuration according to claim 1, is characterized in that: described master shows on control computer and is provided with Data import card.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510613823.6A CN105138014A (en) | 2015-09-24 | 2015-09-24 | Light and small type airplane avionics system configuration |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510613823.6A CN105138014A (en) | 2015-09-24 | 2015-09-24 | Light and small type airplane avionics system configuration |
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| Publication Number | Publication Date |
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| CN105138014A true CN105138014A (en) | 2015-12-09 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN201510613823.6A Pending CN105138014A (en) | 2015-09-24 | 2015-09-24 | Light and small type airplane avionics system configuration |
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| CN (1) | CN105138014A (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| 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 |
| 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 |
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| US5731507A (en) * | 1993-09-17 | 1998-03-24 | Rosemount Aerospace, Inc. | Integral airfoil total temperature sensor |
| CN101672729A (en) * | 2009-10-14 | 2010-03-17 | 清华大学 | High-altitude and low-pressure characteristic simulation test station of air compressor in internal-combustion engine |
| CN103606302A (en) * | 2013-08-13 | 2014-02-26 | 重庆享邑航空科技有限公司 | Aircraft border-crossing management and control method and system |
| CN103713531A (en) * | 2013-12-06 | 2014-04-09 | 长安大学 | Control system of throat area of aeroengine tail nozzle |
| CN103818560A (en) * | 2012-11-16 | 2014-05-28 | 哈尔滨飞机工业集团有限责任公司 | Helicopter integrated information display system |
| CN204496286U (en) * | 2015-04-13 | 2015-07-22 | 中国航空无线电电子研究所 | A kind of Small General Aircraft integration avionics system |
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2015
- 2015-09-24 CN CN201510613823.6A patent/CN105138014A/en active Pending
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5731507A (en) * | 1993-09-17 | 1998-03-24 | Rosemount Aerospace, Inc. | Integral airfoil total temperature sensor |
| CN101672729A (en) * | 2009-10-14 | 2010-03-17 | 清华大学 | High-altitude and low-pressure characteristic simulation test station of air compressor in internal-combustion engine |
| CN103818560A (en) * | 2012-11-16 | 2014-05-28 | 哈尔滨飞机工业集团有限责任公司 | Helicopter integrated information display system |
| CN103606302A (en) * | 2013-08-13 | 2014-02-26 | 重庆享邑航空科技有限公司 | Aircraft border-crossing management and control method and system |
| CN103713531A (en) * | 2013-12-06 | 2014-04-09 | 长安大学 | Control system of throat area of aeroengine tail nozzle |
| CN204496286U (en) * | 2015-04-13 | 2015-07-22 | 中国航空无线电电子研究所 | A kind of Small General Aircraft integration avionics system |
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| 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 |
| 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 |
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Application publication date: 20151209 |
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| RJ01 | Rejection of invention patent application after publication |