CN104743123A - Civil aircraft cockpit without windshields - Google Patents
Civil aircraft cockpit without windshields Download PDFInfo
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- CN104743123A CN104743123A CN201510167661.8A CN201510167661A CN104743123A CN 104743123 A CN104743123 A CN 104743123A CN 201510167661 A CN201510167661 A CN 201510167661A CN 104743123 A CN104743123 A CN 104743123A
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Abstract
The invention relates to a civil aircraft cockpit without windshields, wherein the cockpit is an aluminum alloy sheet sealing structure and isn't equipped with transparent glass windshields; a plurality of panoramic cameras are uniformly arranged on a nose, a plurality of interconnected curved surface display screens are arranged in a cabin, at least two data processing equipment are arranged in the aircraft, the panoramic cameras are connected with the data processing equipment, and the processed data can be displayed on the curved surface display screens by the data processing equipment; said data processing equipment are mutually complementary, one data processing equipment operates while other processing equipment are in the standby state, multiple data processing equipment have the information sharing function, so that other data processing equipment still can operate normally when some data processing equipment is invalid. In the scheme, the view requirements of pilots can meet air worthiness regulations through advanced display technologies, in comparison with a traditional transparent glass windshield cockpit, the civil aircraft cockpit has the many advantages, and the costs are further reduced from design, manufacturing, installation and weight aspects.
Description
Technical field
The present invention relates to a kind of without windscreen civil aircraft control cabin, belong to civil aircraft field.
Background technology
At present at large, civil aircraft control cabin needs at aviator front design large scale opening and installs transparent windshield, on the one hand have valve action, transparent windshield needs to prevent that high velocity air or bird from hitting and waits directly to injure chaufeur and aircraft structural integrity on the other hand.Transparent windscreen is generally made up of organism glass and metal framework, and should meet aviator has enough visuals field in take-off and landing process, has the intensity that enough anti-birds are hit again.
Compared with aluminum alloy outer cover, the curved surface being shaped to fairing of transparent windshield is very difficult, and therefore normally, transparent windscreen is that multiple pieces of glass is spliced, and the aerodynamic configuration fairness of head is poor, and aerodynamic drag is larger thus.
Transparent windscreen needs to install except rain/row's rain system for aviator provides all meteorological conditionss to descend necessary diaphaneity and visibility.Transparent windscreen needs to possess anti icing system, for aviator icing meteorology condition is provided under necessary diaphaneity and visibility.Transparent windscreen needs to possess antifog system, prevents or eliminates droplet that windscreen clear area inside face condenses, for aviator provides necessary visual field condition.Due to the layout of above system, cause that airplane design difficulty increases, system is more, therefore system layout with coordinate that difficulty increases, aircraft weight increases.There is big uncork due to needs in transparent windscreen, around openings structure needs corresponding reinforcement, inevitablely cause aero-structure weight to increase further.
Summary of the invention
The technical problem to be solved in the present invention is to provide a kind of without windscreen civil aircraft control cabin, the program meets the requirement to the aviator visual field in air worthiness regulation by advanced technique of display, and more traditional clear glass windscreen driving compartment has numerous advantage: owing to not having large scale opening, cabin structure design difficulty reduces; Without windscreen head, there is better aerodynamic configuration, reduce air resistance; Clear glass windscreen can be avoided to be hit by bird the danger brought and to decrease windscreen except systems such as rain/row's rain, deicing, demists, all make cost reduce further from aspects such as design, manufacture, installation, weight.
For overcoming the above problems, concrete technical scheme of the present invention is as follows: a kind of without windscreen civil aircraft control cabin, driving compartment is aluminum alloy outer cover closed structure, does not arrange clear glass windscreen, and head is evenly distributed with several full-view cameras; Be provided with the some pieces of camber display screens be connected at engine room inside, arrange data processing equipment at interior of aircraft at least two cover, full-view camera is connected with data processing equipment, data processing equipment again by the data handled well in curved-surface display screen display; Wherein data processing equipment remaining each other, a set of in running order, all the other are in Status of Backups, and many sets of data treatment facility has information sharing function, ensure wherein any a set of inefficacy, do not affect the normal work of remainder data treatment facility.
Described full-view camera quantity is no less than 4, and is positioned at the front of aircraft; Wherein each full-view camera works independently to cover and meets the viewing angle requirements of head front full-view image.
Described camber display screen is at least divided into 4 pieces, and with slitless connection form display head front full-view image, the camber display screen after combination is looped around the dead ahead of chaufeur.
Described arbitrary one piece of camber display screen, under the control of data processing equipment, can show separately head front full-view image.
This adopts aluminum alloy outer cover closed structure without windscreen civil aircraft control cabin, and its structure design is more prone to, and structural strength easily ensures, aircraft weight reduces further, and head aerodynamic drag also reduces further.Adopt full-view camera, camber display screen and data processing equipment simultaneously, the full-view image that full-view camera shows is processed in the data processing apparatus, shows in camber display screen after having processed.
At least 4 full-view cameras are set, ensure at least 4 remainings, ensure any one full-view camera inefficacy can not shadow to the normal work of all the other cameras, and can to work alone, to meet the outer image information of high machine and catch reliability requirement.
Adopt at least 4 pieces of camber display screens, what the impact taked outside was implemented shows, and every monolithic camber display screen can work independently simultaneously, ensure that higher display reliability.
Accompanying drawing explanation
Fig. 1 is without windscreen civil aircraft control cabin inner structure schematic diagram.
Fig. 2 is the outer full-view camera distribution schematic diagram of fuselage.
Fig. 3 is systematic schematic diagram.
Detailed description of the invention
A kind of without windscreen civil aircraft control cabin, driving compartment is aluminum alloy outer cover closed structure, does not arrange clear glass windscreen, and head is evenly distributed with several full-view cameras 3; Be provided with the some pieces of camber display screens be connected 1 at engine room inside, arrange data processing equipment 2 at interior of aircraft at least two cover, full-view camera 3 is connected with data processing equipment 2, data processing equipment 2 again by the data handled well in curved-surface display screen display; Wherein data processing equipment 2 remaining each other, a set of in running order, all the other are in Status of Backups, and many sets of data treatment facility has information sharing function, ensure wherein any a set of inefficacy, do not affect the normal work of remainder data treatment facility.
Described full-view camera 3 quantity is no less than 4, and is positioned at the front of aircraft; Wherein each full-view camera works independently to cover and meets the viewing angle requirements of head front full-view image.
Described camber display screen 1 is at least divided into 4 pieces, and with slitless connection form display head front full-view image, the camber display screen after combination is looped around the dead ahead of chaufeur.
Described arbitrary one piece of camber display screen 1, under the control of data processing equipment, can show separately head front full-view image.
As shown in Figure 1, camber display screen 1 is arranged in driving compartment dead ahead and front side, adopt monolithic large scale camber display screen or polylith Curved screen to be spliced, replace the clear glass windscreen in aircraft cockpit dead ahead and the clear glass windscreen of driving compartment left front or right front.As shown in Figure 2, be arranged in the full-view camera 3 of the multiple position of head, quantity is not limited to 4.Certain physical isolation should be had between each full-view camera, ensure that the inefficacy of any one full-view camera can not affect the normal work of all the other cameras, and each full-view camera works independently and can meet the viewing angle requirements of aviator to head front full-view image, meet the outer image information of high machine and catch reliability requirement.Camber display screen 1 and full-view camera 3 all adopt modular design concept, and conveniently fast disassembling is changed.The image data that full-view camera obtains, through data processing equipment process, is presented on read-out 1 with the visual angle of high fidelity.Read-out 1 can show full-view image separately when certain read-out goes wrong, and minimally reduces aviator's angle effects.
As shown in Figure 3, in equipment compartment, data processing equipment 2 is not limited to two covers, remaining each other, under normal circumstances, a set of in running order, be a set ofly in addition in Status of Backups, two sets of data treatment facilities have information sharing function, ensure wherein any a set of inefficacy, do not affect the normal work of other a set of data processing equipment, meet high data processing reliability requirement.
Design by system margin requirement for the wire harness of signal transmission between camera, data processing equipment, read-out, the wire harness of any one remaining lost efficacy, and did not affect the normal work of other remaining wire harness, met high Signal transmissions reliability requirement.
Claims (4)
1. bright windshield apron, head is evenly distributed with several full-view cameras (3); The some pieces of camber display screens be connected (1) are provided with at engine room inside, at interior of aircraft at least two cover, data processing equipment (2) is set, full-view camera (3) is connected with data processing equipment (2), data processing equipment (2) again by the data handled well in curved-surface display screen display; Wherein data processing equipment (2) remaining each other, a set of in running order, all the other are in Status of Backups, and many sets of data treatment facility has information sharing function, ensure wherein any a set of inefficacy, do not affect the normal work of remainder data treatment facility.
2. as claimed in claim 1 without windscreen civil aircraft control cabin, it is characterized in that: described full-view camera (3) quantity is no less than 4, and is positioned at the front of aircraft; Wherein each full-view camera works independently to cover and meets the viewing angle requirements of head front full-view image.
3. as claimed in claim 1 without windscreen civil aircraft control cabin, it is characterized in that: described camber display screen (1) is at least divided into 4 pieces, and with slitless connection form display head front full-view image, the camber display screen after combination is looped around the dead ahead of chaufeur.
4. as claimed in claim 3 without windscreen civil aircraft control cabin, it is characterized in that: described arbitrary one piece of camber display screen (1), under the control of data processing equipment, can show separately head front full-view image.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510167661.8A CN104743123A (en) | 2015-04-10 | 2015-04-10 | Civil aircraft cockpit without windshields |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510167661.8A CN104743123A (en) | 2015-04-10 | 2015-04-10 | Civil aircraft cockpit without windshields |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN104743123A true CN104743123A (en) | 2015-07-01 |
Family
ID=53583539
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201510167661.8A Pending CN104743123A (en) | 2015-04-10 | 2015-04-10 | Civil aircraft cockpit without windshields |
Country Status (1)
| Country | Link |
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| CN (1) | CN104743123A (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110719425A (en) * | 2018-07-11 | 2020-01-21 | 视联动力信息技术股份有限公司 | Video data playing method and device |
| CN114475526A (en) * | 2021-12-30 | 2022-05-13 | 中国航空工业集团公司西安飞机设计研究所 | Air blowing rain removal system based on supersonic flow injection effect |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP0913325A1 (en) * | 1997-10-30 | 1999-05-06 | Ioannis Vassilios Constantopoulos | Passenger aircraft |
| CN101697036A (en) * | 2009-11-13 | 2010-04-21 | 深圳市博视创电子有限公司 | Information display system of automobile glass and imaging method thereof |
| US20120325962A1 (en) * | 2011-06-27 | 2012-12-27 | Barron Wesley I | Window-less transport aircraft |
| CN103879544A (en) * | 2012-12-21 | 2014-06-25 | 空中客车公司 | Aircraft including a flight deck featuring a viewing surface for at least partial virtual control |
| CN103879543A (en) * | 2012-12-21 | 2014-06-25 | 空中客车公司 | Aircraft comprising a cockpit delocalized outside an upper part of the nose |
-
2015
- 2015-04-10 CN CN201510167661.8A patent/CN104743123A/en active Pending
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP0913325A1 (en) * | 1997-10-30 | 1999-05-06 | Ioannis Vassilios Constantopoulos | Passenger aircraft |
| CN101697036A (en) * | 2009-11-13 | 2010-04-21 | 深圳市博视创电子有限公司 | Information display system of automobile glass and imaging method thereof |
| US20120325962A1 (en) * | 2011-06-27 | 2012-12-27 | Barron Wesley I | Window-less transport aircraft |
| CN103879544A (en) * | 2012-12-21 | 2014-06-25 | 空中客车公司 | Aircraft including a flight deck featuring a viewing surface for at least partial virtual control |
| CN103879543A (en) * | 2012-12-21 | 2014-06-25 | 空中客车公司 | Aircraft comprising a cockpit delocalized outside an upper part of the nose |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110719425A (en) * | 2018-07-11 | 2020-01-21 | 视联动力信息技术股份有限公司 | Video data playing method and device |
| CN114475526A (en) * | 2021-12-30 | 2022-05-13 | 中国航空工业集团公司西安飞机设计研究所 | Air blowing rain removal system based on supersonic flow injection effect |
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| RJ01 | Rejection of invention patent application after publication |
Application publication date: 20150701 |
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| RJ01 | Rejection of invention patent application after publication |