CN111856803A - Airborne display unit of airplane - Google Patents
Airborne display unit of airplane Download PDFInfo
- Publication number
- CN111856803A CN111856803A CN202010503645.2A CN202010503645A CN111856803A CN 111856803 A CN111856803 A CN 111856803A CN 202010503645 A CN202010503645 A CN 202010503645A CN 111856803 A CN111856803 A CN 111856803A
- Authority
- CN
- China
- Prior art keywords
- display unit
- mounting structure
- aircraft
- liquid crystal
- screen
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Pending
Links
- 239000004973 liquid crystal related substance Substances 0.000 claims abstract description 27
- 230000002093 peripheral effect Effects 0.000 claims abstract description 10
- 238000000034 method Methods 0.000 claims abstract description 5
- 239000000853 adhesive Substances 0.000 claims abstract description 4
- 230000001070 adhesive effect Effects 0.000 claims abstract description 4
- 239000006260 foam Substances 0.000 claims abstract description 3
- 230000017525 heat dissipation Effects 0.000 claims description 13
- VYPSYNLAJGMNEJ-UHFFFAOYSA-N Silicium dioxide Chemical compound O=[Si]=O VYPSYNLAJGMNEJ-UHFFFAOYSA-N 0.000 claims description 4
- 239000000741 silica gel Substances 0.000 claims description 4
- 229910002027 silica gel Inorganic materials 0.000 claims description 4
- 239000003795 chemical substances by application Substances 0.000 claims description 3
- 238000004891 communication Methods 0.000 claims description 3
- 230000003287 optical effect Effects 0.000 claims description 3
- 238000002788 crimping Methods 0.000 claims description 2
- 230000003014 reinforcing effect Effects 0.000 claims 4
- 229910001095 light aluminium alloy Inorganic materials 0.000 claims 1
- 230000000694 effects Effects 0.000 abstract description 6
- 229910052751 metal Inorganic materials 0.000 description 4
- 239000002184 metal Substances 0.000 description 4
- 230000003139 buffering effect Effects 0.000 description 3
- 238000004519 manufacturing process Methods 0.000 description 3
- 239000013585 weight reducing agent Substances 0.000 description 3
- 229910052782 aluminium Inorganic materials 0.000 description 2
- XAGFODPZIPBFFR-UHFFFAOYSA-N aluminium Chemical compound [Al] XAGFODPZIPBFFR-UHFFFAOYSA-N 0.000 description 2
- 238000009434 installation Methods 0.000 description 2
- 238000003860 storage Methods 0.000 description 2
- 229920000742 Cotton Polymers 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 239000004568 cement Substances 0.000 description 1
- 230000006835 compression Effects 0.000 description 1
- 238000007906 compression Methods 0.000 description 1
- 239000003292 glue Substances 0.000 description 1
Images
Classifications
-
- G—PHYSICS
- G02—OPTICS
- G02F—OPTICAL DEVICES OR ARRANGEMENTS FOR THE CONTROL OF LIGHT BY MODIFICATION OF THE OPTICAL PROPERTIES OF THE MEDIA OF THE ELEMENTS INVOLVED THEREIN; NON-LINEAR OPTICS; FREQUENCY-CHANGING OF LIGHT; OPTICAL LOGIC ELEMENTS; OPTICAL ANALOGUE/DIGITAL CONVERTERS
- G02F1/00—Devices or arrangements for the control of the intensity, colour, phase, polarisation or direction of light arriving from an independent light source, e.g. switching, gating or modulating; Non-linear optics
- G02F1/01—Devices or arrangements for the control of the intensity, colour, phase, polarisation or direction of light arriving from an independent light source, e.g. switching, gating or modulating; Non-linear optics for the control of the intensity, phase, polarisation or colour
- G02F1/13—Devices or arrangements for the control of the intensity, colour, phase, polarisation or direction of light arriving from an independent light source, e.g. switching, gating or modulating; Non-linear optics for the control of the intensity, phase, polarisation or colour based on liquid crystals, e.g. single liquid crystal display cells
- G02F1/133—Constructional arrangements; Operation of liquid crystal cells; Circuit arrangements
- G02F1/1333—Constructional arrangements; Manufacturing methods
- G02F1/13338—Input devices, e.g. touch panels
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D43/00—Arrangements or adaptations of instruments
-
- G—PHYSICS
- G02—OPTICS
- G02F—OPTICAL DEVICES OR ARRANGEMENTS FOR THE CONTROL OF LIGHT BY MODIFICATION OF THE OPTICAL PROPERTIES OF THE MEDIA OF THE ELEMENTS INVOLVED THEREIN; NON-LINEAR OPTICS; FREQUENCY-CHANGING OF LIGHT; OPTICAL LOGIC ELEMENTS; OPTICAL ANALOGUE/DIGITAL CONVERTERS
- G02F1/00—Devices or arrangements for the control of the intensity, colour, phase, polarisation or direction of light arriving from an independent light source, e.g. switching, gating or modulating; Non-linear optics
- G02F1/01—Devices or arrangements for the control of the intensity, colour, phase, polarisation or direction of light arriving from an independent light source, e.g. switching, gating or modulating; Non-linear optics for the control of the intensity, phase, polarisation or colour
- G02F1/13—Devices or arrangements for the control of the intensity, colour, phase, polarisation or direction of light arriving from an independent light source, e.g. switching, gating or modulating; Non-linear optics for the control of the intensity, phase, polarisation or colour based on liquid crystals, e.g. single liquid crystal display cells
- G02F1/133—Constructional arrangements; Operation of liquid crystal cells; Circuit arrangements
- G02F1/1333—Constructional arrangements; Manufacturing methods
- G02F1/133382—Heating or cooling of liquid crystal cells other than for activation, e.g. circuits or arrangements for temperature control, stabilisation or uniform distribution over the cell
-
- G—PHYSICS
- G06—COMPUTING; CALCULATING OR COUNTING
- G06F—ELECTRIC DIGITAL DATA PROCESSING
- G06F3/00—Input arrangements for transferring data to be processed into a form capable of being handled by the computer; Output arrangements for transferring data from processing unit to output unit, e.g. interface arrangements
- G06F3/01—Input arrangements or combined input and output arrangements for interaction between user and computer
- G06F3/03—Arrangements for converting the position or the displacement of a member into a coded form
- G06F3/041—Digitisers, e.g. for touch screens or touch pads, characterised by the transducing means
- G06F3/044—Digitisers, e.g. for touch screens or touch pads, characterised by the transducing means by capacitive means
-
- H—ELECTRICITY
- H05—ELECTRIC TECHNIQUES NOT OTHERWISE PROVIDED FOR
- H05K—PRINTED CIRCUITS; CASINGS OR CONSTRUCTIONAL DETAILS OF ELECTRIC APPARATUS; MANUFACTURE OF ASSEMBLAGES OF ELECTRICAL COMPONENTS
- H05K5/00—Casings, cabinets or drawers for electric apparatus
- H05K5/0004—Casings, cabinets or drawers for electric apparatus comprising several parts forming a closed casing
-
- H—ELECTRICITY
- H05—ELECTRIC TECHNIQUES NOT OTHERWISE PROVIDED FOR
- H05K—PRINTED CIRCUITS; CASINGS OR CONSTRUCTIONAL DETAILS OF ELECTRIC APPARATUS; MANUFACTURE OF ASSEMBLAGES OF ELECTRICAL COMPONENTS
- H05K5/00—Casings, cabinets or drawers for electric apparatus
- H05K5/0017—Casings, cabinets or drawers for electric apparatus with operator interface units
-
- H—ELECTRICITY
- H05—ELECTRIC TECHNIQUES NOT OTHERWISE PROVIDED FOR
- H05K—PRINTED CIRCUITS; CASINGS OR CONSTRUCTIONAL DETAILS OF ELECTRIC APPARATUS; MANUFACTURE OF ASSEMBLAGES OF ELECTRICAL COMPONENTS
- H05K5/00—Casings, cabinets or drawers for electric apparatus
- H05K5/02—Details
- H05K5/0217—Mechanical details of casings
Landscapes
- Physics & Mathematics (AREA)
- Engineering & Computer Science (AREA)
- Nonlinear Science (AREA)
- General Physics & Mathematics (AREA)
- Microelectronics & Electronic Packaging (AREA)
- Optics & Photonics (AREA)
- Crystallography & Structural Chemistry (AREA)
- Chemical & Material Sciences (AREA)
- Mathematical Physics (AREA)
- General Engineering & Computer Science (AREA)
- Theoretical Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Human Computer Interaction (AREA)
- Devices For Indicating Variable Information By Combining Individual Elements (AREA)
Abstract
The invention discloses an airplane airborne display unit, which comprises a touch liquid crystal module (1), a front shell mounting structure (2) and a reinforced rear shell (3), wherein the touch liquid crystal module (1) comprises a capacitive touch screen and a liquid crystal screen, and the capacitive touch screen is attached to the liquid crystal screen by adopting a full-attachment process; the contact part of the front shell mounting structure (2) and the touch liquid crystal module (1) is buffered and fixed by conductive foam adhesive; the reinforced rear shell (3) and the front shell mounting structure (2) are fixed through peripheral screws. The invention adopts an integral reinforced airborne display unit, so that the developed airborne display unit of the airplane has better anti-vibration effect than the traditional display, and achieves the airborne application target.
Description
Technical Field
The invention belongs to the field of civil aircraft airborne display equipment, and relates to an aircraft airborne display unit arranged in a cockpit in an aircraft cabin.
Background
The aircraft airborne display unit is an operation carrier for assisting a pilot to look up data such as a flight manual or a chart in the flight process, and mainly provides auxiliary flight information for the pilot, and reduces the flight weight and the workload of the pilot. Generally, the conventional airborne display equipment meets the requirement of high vibration on the airplane by wrapping a large number of metal structures or selecting the liquid crystal module of military grade, but the weight cost and the equipment cost of the airplane are undoubtedly increased by the design mode, so that one set of airborne display unit of the airplane needs to be designed and installed, the pilot can conveniently and quickly and accurately look up data, and the purpose of reducing the flight weight and the workload of the pilot is achieved.
Disclosure of Invention
The invention aims to provide an aircraft onboard display unit which is arranged in an aircraft cockpit, and heat dissipation is carried out through an integral reinforced onboard display unit and an internal auxiliary heat dissipation system, so that the developed aircraft onboard display unit has a vibration resisting effect and achieves an onboard application target compared with a traditional display, and the aircraft onboard display unit adopting the design does not adopt excessive metal structures for heat dissipation, so that the overall weight of the aircraft onboard display unit is optimized, the onboard product weight reduction target is achieved, and meanwhile, the production cost can be greatly saved.
The invention aims to be realized by the following technical scheme:
an airplane airborne display unit comprises a touch liquid crystal module 1, a front shell mounting structure 2 and a reinforced rear shell 3;
the touch liquid crystal module 1 comprises a capacitive touch screen and a liquid crystal screen, and the capacitive touch screen is attached to the liquid crystal screen by adopting a full-attachment process, so that the fixing, buffering and vibration-proof effects are achieved, and meanwhile, the dustproof effect is also achieved;
the contact part of the front shell mounting structure 2 and the touch liquid crystal module 1 is buffered and fixed by adopting conductive foam and cotton glue, and buffering silica gel is injected during mounting, so that the connection part of the touch liquid crystal module 1 and the front shell mounting structure 2 is flexibly connected, and the aim of integral vibration resistance is fulfilled;
The reinforced rear shell 3 and the front shell mounting structure 2 are fixed through peripheral screws, and the purpose of integral protection is achieved.
Preferably, the liquid crystal screen adopts an industrial reinforced screen, the capacitive touch screen adopts an AG anti-reflection type capacitive touch screen, and the capacitive touch screen is completely attached to the liquid crystal screen through wide-temperature optical cement.
Preferably, the front shell mounting structure 2 includes 4 quick-release screws 6 on the panel, and the quick-release screws 6 are fixed with the front shell mounting structure 2 by crimping.
Further, the front shell mounting structure 2 and the reinforced rear shell 3 are made of aviation aluminum, and heat dissipation holes are formed in the side surface of the reinforced rear shell 3, so that heat inside the machine can be dissipated quickly; the back of the reinforced rear shell 3 is provided with a heat dissipation groove which can assist the machine to quickly dissipate heat through the shell.
Further, two symmetrical brightness sensors are arranged on the front shell mounting structure 2 and used for sensing the brightness of the surrounding environment and taking the brightness as a reference value for automatically adjusting the brightness of the screen; the front shell mounting structure 2 is also provided with peripheral keys which are symmetrical on two sides, and the peripheral keys are made of fireproof light-transmitting silica gel, so that the keys can be identified in a dark environment; the front shell mounting structure 2 is also provided with a USB interface and an Ethernet interface, and can be used for plugging USB storage equipment or control equipment.
Further, the aircraft airborne display unit further comprises a connector 5, wherein the connector 5 is directly welded on a circuit board inside the aircraft airborne display unit and is fixed on the reinforced rear shell 3 through 4 countersunk head screws.
Preferably, the connector 5 is a D38999 II series aircraft connector.
Further, the aircraft airborne display unit further comprises a core processing unit 4, the core processing unit 4 is installed on the rear shell structure 3 through an integrated installation structure, an Intel high-performance and low-power-consumption CPU is adopted as a processing core of the core processing unit 4, a high-performance processing platform is carried, various types of data bus interfaces can be expanded, and the core processing unit is crosslinked with a front panel USB interface, an Ethernet interface and a connector 5 to achieve data communication.
The invention has the beneficial effects that: the invention adopts an integral reinforced airborne display unit and an internal auxiliary heat dissipation system for heat dissipation, so that the developed airborne display unit of the airplane has better anti-vibration effect than the traditional display and achieves the airborne application target, and on the other hand, the airborne display unit of the airplane adopting the design does not adopt excessive metal structures for heat dissipation, so that the integral weight of the airborne display unit of the airplane is more optimized, the weight reduction target of an airborne product is achieved, and the production cost can be greatly saved.
Drawings
FIG. 1 is a front view of a display unit on-board an aircraft of the present invention;
FIG. 2 is a top view of an onboard display unit of the aircraft of the present invention;
fig. 3 is a schematic view of the interior of the display unit on board the aircraft of the present invention.
Detailed Description
The present invention will be described in further detail with reference to fig. 1, 2 and 3.
Examples
Referring to fig. 1 to 3, the display unit on board an aircraft according to the present embodiment includes a touch liquid crystal module 1, a front case mounting structure 2, a reinforced rear case 3, and the like. The purpose to be achieved by the embodiment is as follows: firstly, the developed airplane airborne display unit has vibration resistance effect compared with the traditional display, and achieves the airborne application target; and secondly, the use of a metal structure for heat dissipation is reduced, so that the overall weight of the airborne display unit of the airplane is optimized, the weight reduction target of an airborne product is achieved, and meanwhile, the production cost can be saved to a great extent.
For the first purpose, the touch liquid crystal module 1 shown in this embodiment includes a capacitive touch screen and a liquid crystal screen, and the capacitive touch screen is attached to the liquid crystal screen by using a full-attachment process, so that the capacitive touch screen has fixing, buffering and vibration-proof functions, and meanwhile, the capacitive touch screen also has a dustproof function. For example, the liquid crystal screen is an industrial reinforced screen, the capacitive touch screen is an AG anti-reflection capacitive touch screen, and the capacitive touch screen is fully attached to the liquid crystal screen through wide-temperature optical adhesive.
T type recess is left with the part of preceding shell mounting structure 2 contact to touch LCD module 1, and it is fixed to inject the electrically conductive bubble cotton-rubber into through the department at T type recess and cushion for touch LCD module 1 is flexonics with the connecting portion of preceding shell mounting structure 2, reaches the purpose of whole anti vibration.
The reinforced rear shell 3 and the front shell mounting structure 2 are fixed through peripheral screws, and the purpose of integral protection is achieved.
The front shell mounting structure 2 comprises 4 quick-release screws 6 on a panel, and the quick-release screws 6 are fixed with the front shell mounting structure 2 in a compression joint mode.
For the second purpose, the front shell mounting structure 2 and the reinforced rear shell 3 in the embodiment are made of aviation aluminum, so that the magnetic resistance is good, and the overall weight is greatly reduced on the basis of ensuring the strength and the vibration resistance. The side surface of the reinforced rear shell 3 is provided with heat dissipation holes, so that heat in the machine can be dissipated quickly; the back of the reinforced rear shell 3 is provided with a heat dissipation groove which can assist the machine to quickly dissipate heat through the shell.
The front shell mounting structure 2 is provided with two symmetrical brightness sensors for sensing the brightness of the surrounding environment and taking the brightness as a reference value for automatically adjusting the brightness of the screen; the front shell mounting structure 2 is also provided with peripheral keys which are symmetrical on two sides, and the peripheral keys are made of fireproof light-transmitting silica gel, so that the keys can be identified in a dark environment; the front shell mounting structure 2 is also provided with a USB interface and an Ethernet interface, and can be used for plugging USB storage equipment or control equipment.
The display unit on board the aircraft further comprises a connector 5, for example, a D38999 II series aircraft connector, and the connector 5 is directly welded on a circuit board inside the display unit on board the aircraft and is fixed on the reinforced rear shell 3 through 4 countersunk head screws.
The aircraft airborne display unit further comprises a core processing unit 4, the core processing unit 4 is installed on the rear shell structure 3 through an integrated installation structure, an Intel high-performance and low-power-consumption CPU is adopted as a processing core of the core processing unit 4, a high-performance processing platform is carried, a plurality of types of data bus interfaces can be expanded, and the core processing unit is crosslinked with a front panel USB interface, an Ethernet interface and a connector 5 to realize data communication.
Claims (8)
1. The utility model provides an aircraft machine carries display element, includes touch liquid crystal module (1), preceding shell mounting structure (2) and consolidates backshell (3), its characterized in that:
the touch liquid crystal module (1) comprises a capacitive touch screen and a liquid crystal screen, and the capacitive touch screen is attached to the liquid crystal screen by adopting a full-attachment process;
the contact part of the front shell mounting structure (2) and the touch liquid crystal module (1) is buffered and fixed by conductive foam adhesive;
the reinforced rear shell (3) and the front shell mounting structure (2) are fixed through peripheral screws.
2. The aircraft-mounted display unit of claim 1, wherein the liquid crystal screen is an industrial ruggedized screen, the capacitive touch screen is an AG anti-reflection capacitive touch screen, and the capacitive touch screen is fully attached to the liquid crystal screen through a wide temperature optical adhesive.
3. An aircraft onboard display unit according to claim 1, characterized in that the front shell mounting structure (2) comprises on its face 4 quick-release screws (6), the quick-release screws (6) being fixed to the front shell mounting structure (2) by means of crimping.
4. An aircraft onboard display unit according to claim 1, characterized in that the front shell mounting structure (2) and the reinforcing rear shell (3) are of aircraft aluminium, the side faces of the reinforcing rear shell (3) being provided with heat dissipation apertures, and the rear face of the reinforcing rear shell (3) being provided with heat dissipation slots.
5. An aircraft on-board display unit as claimed in claim 1, characterized in that the front shell mounting structure (2) is provided with two symmetrical brightness sensors for sensing the brightness of the surrounding environment as a reference value for automatically adjusting the screen brightness; the front shell mounting structure (2) is also provided with peripheral keys which are symmetrical at two sides, and the peripheral keys are made of fireproof light-transmitting silica gel; the front shell mounting structure (2) is also provided with a USB interface and an Ethernet interface.
6. An aircraft on-board display unit according to claim 5, characterized in that it further comprises a connector (5), the connector (5) being soldered directly to a circuit board inside the aircraft on-board display unit and being fixed to the reinforcing rear shell (3) by means of 4 countersunk screws.
7. An aircraft-onboard display unit as claimed in claim 6, characterized in that the connector (5) is a D38999 II series aircraft connector.
8. An aircraft on-board display unit according to claim 6, characterized in that it further comprises a core processing unit (4) mounted on the rear shell structure (3) by means of an integrated mounting structure, cross-linked with the front panel USB interface, Ethernet interface and connector 5, enabling data communication.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010503645.2A CN111856803A (en) | 2020-06-05 | 2020-06-05 | Airborne display unit of airplane |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010503645.2A CN111856803A (en) | 2020-06-05 | 2020-06-05 | Airborne display unit of airplane |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN111856803A true CN111856803A (en) | 2020-10-30 |
Family
ID=72985000
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202010503645.2A Pending CN111856803A (en) | 2020-06-05 | 2020-06-05 | Airborne display unit of airplane |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN111856803A (en) |
Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN203055408U (en) * | 2012-12-18 | 2013-07-10 | 中航华东光电有限公司 | Liquid crystal display allowing backlight to be adjusted automatically |
| CN107478328A (en) * | 2017-09-19 | 2017-12-15 | 珠海格力电器股份有限公司 | Photosensitive device, display brightness adjusting system and display |
| CN110554527A (en) * | 2019-09-10 | 2019-12-10 | 中国航空工业集团公司上海航空测控技术研究所 | Reinforcing structure of airborne display unit of airplane |
-
2020
- 2020-06-05 CN CN202010503645.2A patent/CN111856803A/en active Pending
Patent Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN203055408U (en) * | 2012-12-18 | 2013-07-10 | 中航华东光电有限公司 | Liquid crystal display allowing backlight to be adjusted automatically |
| CN107478328A (en) * | 2017-09-19 | 2017-12-15 | 珠海格力电器股份有限公司 | Photosensitive device, display brightness adjusting system and display |
| CN110554527A (en) * | 2019-09-10 | 2019-12-10 | 中国航空工业集团公司上海航空测控技术研究所 | Reinforcing structure of airborne display unit of airplane |
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| WD01 | Invention patent application deemed withdrawn after publication |
Application publication date: 20201030 |
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