CN209410340U - Flight Transparent Parts system - Google Patents
Flight Transparent Parts system Download PDFInfo
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- CN209410340U CN209410340U CN201822228690.2U CN201822228690U CN209410340U CN 209410340 U CN209410340 U CN 209410340U CN 201822228690 U CN201822228690 U CN 201822228690U CN 209410340 U CN209410340 U CN 209410340U
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- transparent parts
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Abstract
The utility model is about a kind of flight Transparent Parts system.The flight Transparent Parts system, including Transparent Parts and frame, the Transparent Parts are installed on the frame, further include: jet-impingement system is laid on the frame；It includes several nozzles, and it is outer to the Transparent Parts jet-stream wind that the nozzle is set to flight capsule；Gas source connects the jet-impingement system；The gas source includes at least hot gas source；Temperature-sensing element or thermistor are embedded in temperature of the inside of the Transparent Parts to measure the Transparent Parts in advance；Control system connects the temperature of the temperature-sensing element or thermistor to monitor the Transparent Parts；It is also connected with the jet-impingement system to control the jet-impingement system starting or close.The flight Transparent Parts system eliminates the rain brush and electricity heating system of Transparent Parts, thus more suitable for practical by jet-stream wind deicing, defrost and row's rain.
Description
Technical field
The utility model relates to Transparent Parts in Aviation fields, more particularly to a kind of flight Transparent Parts system, the flight
Transparent Parts system eliminates rain brush and electricity heating system by air-flow deicing, defrost and row's rain.
Background technique
Currently, the cockpit Transparent Parts of transporter are by main windscreen, vent window and fixed window (or vent window and solid both at home and abroad
Determine window unification) etc. composition.To guarantee getting a clear view for rainy day, windscreen is equipped with Wiper system；And for guarantee it is round-the-clock can
Flight, windscreen have electricity heating function, and the surface temperature of wind file is automatically controlled by controller.
Rain brush and electricity heating system are the basic configuration of airplane in transportation category windscreen, and technology is highly developed.But its there is also
Defect below:
1, the defect of rain brush:
1) Wiper system occupies certain weight than cumbersome；
2) rain brush and windscreen are bonded problem: as Boeing 787 and the novel wide visual field China C919 are driven
The design in cabin is sailed, windscreen radian is complicated and area is big, therefore windscreen and being bonded for rain brush are more difficult；
3) both high to the weight demands of aircraft for utility helicopter, and the complex contour of Transparent Parts,
It is more difficult to receive Wiper system；For advanced bomber, the Wiper system before windscreen influences to fly
The Stealth Fighter of machine, it is also desirable to remove.
2, the defect of electricity heating system:
The prior art plates heating film by the inner surface of the glass outer in Transparent Parts or lays heater strip, cooperates temperature control
Box processed is realized windscreen and the electricity heating function of other Transparent Parts, is had the following deficiencies:
1) consume energy: heating film or heater strip heat windshield, and every piece of windscreen needs to consume several kilowatts of electric energy；
2) heater strip heating can be used in the exothermic material of Transparent Parts, and there are moire effects for heater strip, will affect winged
The visual field of office staff；
3) exothermic material of Transparent Parts can be used transparent conductive film, based on domestic and international product is heated with transparent conductive film, but
It is that heating film needs to draw by busbar and conducting wire, by circuit connection on temperature control box and machine, and busbar and heating
The contact site of element easily loosens, the easy desoldering of the solder joint of conducting wire, becomes one of the failure cause of Transparent Parts failure；And heating film
There are the failures of arcing.
Based on background above, develops and a kind of do not need rain brush and electricity heating system can deicing, defrost and the flight for arranging rain
Transparent Parts system is necessary.
Utility model content
The main purpose of the utility model is to provide a kind of flight Transparent Parts system, the flight Transparent Parts system is logical
Crossing pre-buried temperature-sensing element or thermistor inside Transparent Parts, with the temperature of real-time monitoring Transparent Parts, set-up of control system has
Rainy day functional control module and Transparent Parts temperature control modules can be automatically controled jet-impingement system jet-stream wind with deicing, change
Frost and row's rain, eliminate the rain brush and electricity heating system of Transparent Parts, and being not take up power supply on machine can be realized Transparent Parts reliably certainly
Dynamic heating function, thus more suitable for practical.
It the purpose of this utility model and solves its technical problem and adopts the following technical solutions to realize.It is practical according to this
A kind of flight Transparent Parts system of novel proposition, including Transparent Parts and frame, the Transparent Parts are installed on the frame,
Its further include: jet-impingement system is laid on the frame；It includes several nozzles, and the nozzle is set to flight
Out of my cabin to the Transparent Parts jet-stream wind；Gas source connects the jet-impingement system；The gas source includes at least
Hot gas source；Temperature-sensing element or thermistor are embedded in the inside of the Transparent Parts to measure the Transparent Parts in advance
Temperature；Control system connects the temperature of the temperature-sensing element or thermistor to monitor the Transparent Parts；It is also
The connection jet-impingement system is to control the jet-impingement system starting or close.
It the purpose of this utility model and solves its technical problem also following technical measures can be used to further realize.
Preferably, flight Transparent Parts system above-mentioned, wherein the Transparent Parts are formed by multi-layer transparent Material cladding.
Preferably, flight Transparent Parts system above-mentioned, wherein the Transparent Parts are successively transparent by second from inside to outside
Material layer, the second bonding material layer, the first transparent material layer, the first bonding material layer and outer layer transparent material layer composition five layers
Structure.
Preferably, flight Transparent Parts system above-mentioned, wherein the Transparent Parts are successively transparent by first from inside to outside
The three-decker of material layer, the first bonding material layer and outer layer transparent material layer composition.
Preferably, flight Transparent Parts system above-mentioned, wherein the material of the outer layer transparent material layer is selected from sodium calcium silicon
Unorganic glass, one kind of aluminosilicate unorganic glass or borosilicate unorganic glass.
Preferably, flight Transparent Parts system above-mentioned, wherein the outer layer transparent material layer with a thickness of 1.5mm-
5mm。
Preferably, flight Transparent Parts system above-mentioned, wherein the temperature-sensing element or thermistor is embedded in institute in advance
Close to the inner surface of the outer layer transparent material layer in the first bonding material layer stated.
Preferably, flight Transparent Parts system above-mentioned, wherein the sensitivity temperature of the temperature-sensing element or thermistor
Spending section is [- 60 DEG C, 130 DEG C].
Preferably, flight Transparent Parts system above-mentioned, wherein the nozzle is set along the shape subregion of the Transparent Parts
It is placed in the periphery of the Transparent Parts；The pipeline of the nozzle connection gas source is set in the frame.
Preferably, flight Transparent Parts system above-mentioned, wherein the set-up of control system has rainy day functional control module,
The jet-impingement system only actuating section jet nozzle air flow can be controlled.
Preferably, flight Transparent Parts system above-mentioned, wherein the set-up of control system has Transparent Parts temperature to control mould
Block；When Transparent Parts temperature is lower than temperature preset value, the control system controls jet-impingement system and sprays heat to Transparent Parts
Air-flow is with heating transparent part；When Transparent Parts temperature is higher than temperature preset value, the control system controls jet-impingement system
Close jet-stream wind；The temperature preset value is 20 DEG C~40 DEG C.
By above-mentioned technical proposal, the utility model proposes a kind of flight Transparent Parts system at least have the advantage that
1, the flight Transparent Parts system eliminates rain brush, is blown and is hit by the air-flow of certain orientation, realizes rainy day water removal
Function, overcome the difficult defect of complex contour Transparent Parts rain brush fitting；
2, the flight Transparent Parts system eliminates rain brush, provides one kind for the helicopter for weight demands harshness
The light-weighted rainy day removes water scheme；
3, the flight Transparent Parts system eliminates rain brush, for for there is the aircraft of stealthy requirement to provide solution party
Case；
4, the flight Transparent Parts system eliminates electricity heating system, and it is transparent that the measure realization hit is blown by high temperature gas flow
Part deicing defrost is insufficient for electric energy but have the aircraft of deicing defrost demand to provide solution；
5, the flight Transparent Parts system eliminates electricity heating system, and film/silk relevant to electricity heating, is led at busbar
The failures such as line no longer exist, and improve reliability and the service life of product；
6, the flight Transparent Parts system is provided with control system, and air-flow arranges rain and the starting of air-flow deicing defrost can
It is automatic to carry out.
The above description is merely an outline of the technical solution of the present invention, in order to better understand the skill of the utility model
Art means, and can be implemented in accordance with the contents of the specification, below on the preferred embodiment of the present invention and the accompanying drawings in detail
It describes in detail bright as after.
Detailed description of the invention
Fig. 1 is the schematic diagram of internal structure of flight Transparent Parts (five-layer structure) system of the utility model；
Fig. 2 is the schematic diagram of internal structure of flight Transparent Parts (three-decker) system of the utility model；
Fig. 3 is the external structure schematic diagram of the flight Transparent Parts system of the utility model.
Specific embodiment
Further to illustrate that the utility model is the technical means and efficacy reaching predetermined goal of the invention and being taken, below
In conjunction with attached drawing and preferred embodiment, to according to the utility model proposes a kind of flight Transparent Parts system its specific embodiment,
Structure, feature and its effect, detailed description is as follows.
As shown in Figure 1 to Figure 3, the utility model proposes a kind of flight Transparent Parts system comprising Transparent Parts and frame
9, it further includes jet-impingement system that the Transparent Parts, which are installed on the frame 9, is laid on the frame 9；Its
Including several nozzles 7, it is outer to the Transparent Parts jet-stream wind that the nozzle 7 is set to flight capsule；Gas source 11, connection
The jet-impingement system；The gas source 11 includes at least hot gas source；Temperature-sensing element or thermistor 6, are embedded in advance
Temperature of the inside of the Transparent Parts to measure the Transparent Parts；Control system 10 connects the temperature sensing member
The temperature of part or thermistor 6 to monitor the Transparent Parts；It is also connected with the jet-impingement system to control
The starting of jet-impingement system or closing stated.
It at least further includes the gas source of room temperature and high temperature two states to the gas source 11, and the gas source 11 passes through when necessary
Gas mixing valve connects the nozzle 7 with pipeline to adjust the temperature for the air-flow that nozzle 7 is sprayed；When the jet-impingement system
After unlatching, the control system 10 also controls the temperature for the air-flow that nozzle 7 is sprayed.
The gas source 11 is obtained from aircraft itself, for example, can introduce from engine.As the engine speed of aircraft increases
Working time increase is summed it up, the air near engine is heated to certain temperature, it can be pumped into gas pipeline by air pump,
Windscreen and other Transparent Parts heating gas sources can be used as.
When the control system 10 is in running order, monitored when the temperature-sensing element or thermistor 6
When temperature value is lower than temperature preset value, the control system 10 controls the jet-impingement system starting；When the temperature
When spending the monitoring temperature value of sensing element or thermistor 6 higher than temperature preset value, the control system 10 controls described
Jet-impingement system is closed.
Under winter or icing condition, the jet-impingement system is integrally dried from the periphery of the Transparent Parts, with
It improves the surface temperature of the Transparent Parts or melts the ice and snow of Transparent Parts outer surface.With the temperature control system of electricity heating windscreen
10 is similar, worked by automatic control Transparent Parts heating film or do not work be adjusted to be automatically controlled by the control system 10 it is described
Jet-impingement system jet-impingement or stop jet-impingement.
Preferably, flight Transparent Parts system above-mentioned, wherein the Transparent Parts are formed by multi-layer transparent Material cladding.
Preferably, flight Transparent Parts system above-mentioned, wherein the Transparent Parts are successively transparent by second from inside to outside
Material layer 1, the second bonding material layer 2, the first transparent material layer 3, the first bonding material layer 4 and outer layer transparent material layer 5 form
Five-layer structure.
Preferably, flight Transparent Parts system above-mentioned, wherein the Transparent Parts are successively transparent by first from inside to outside
The three-decker that material layer 3, the first bonding material layer 4 and outer layer transparent material layer 5 form.
Second transparent material layer 1 and the first transparent material layer 3 is referred to as inner transparent material layer.
The inner transparent material layer choosing is from unorganic glass, polycarbonate or organic glass.
Second bonding material layer 2 and the first bonding material layer 4 is referred to as bonding material layer.
The material of the bonding material layer is selected from polyvinyl butyral film, polyurethane pellicle or other transparent adhesive tapes
Piece.
Preferably, flight Transparent Parts system above-mentioned, wherein the material that the outer layer transparent material layer 5 uses is selected from sodium
Calcium silicon unorganic glass, one kind of aluminosilicate unorganic glass or borosilicate unorganic glass.
Preferably, flight Transparent Parts system above-mentioned, wherein the material that the outer layer transparent material layer 5 uses is using saturating
Bright inorganic material.
Preferably, flight Transparent Parts system above-mentioned, wherein the outer layer transparent material layer 5 with a thickness of 1.5mm-
5mm。
The outer layer transparent material layer 5 unorganic glass good using heat resistance.
Preferably, flight Transparent Parts system above-mentioned, wherein the outer surface coating of the outer layer transparent material layer 5 is hydrophobic
Coating.
The hydrophobic coating is brushed in conjunction with air-flow improving Transparent Parts in the clarity of rainy day, can quick obtaining it is clear
The clear visual field.
Preferably, flight Transparent Parts system above-mentioned, wherein the outer surface coating of the outer layer transparent material layer 5 is hydrophilic
Coating maintains the cleaning on surface convenient for Transparent Parts outer surface by the elements of rainwater.
Preferably, flight Transparent Parts system above-mentioned, wherein the temperature-sensing element or thermistor 6 is embedded in institute in advance
Close to the inner surface of the outer layer transparent material layer 5 in the first bonding material layer 4 stated.
It is viscous that the temperature-sensing element or thermistor 6 is embedded in first contacted with outer layer outer layer transparent material layer 5
It ties in material layer 4, and is laid on outside Transparent Parts key field of vision in order to avoid influencing the visual field；The temperature-sensing element or temperature-sensitive electricity
Resistance 6 need to be located at the region that the air-flow that the nozzle 7 sprays can cover, can sensitively perceive the outer layer transparent material
The hull-skin temperature of layer 5.
The installation site of the temperature-sensing element or thermistor 6 is intended to can be transparent described in quick sensing
The temperature of the outer surface of part.
The quantity and specific placement that the temperature-sensing element or thermistor 6 is laid, can be according to described saturating
The factors such as shape, the area of bright part determine.
Preferably, flight Transparent Parts system above-mentioned, wherein the sensitivity temperature of the temperature-sensing element or thermistor 6
Spending section is [- 60 DEG C, 130 DEG C].
Preferably, flight Transparent Parts system above-mentioned, wherein the sensitivity temperature of the temperature-sensing element or thermistor 6
Spend the section that section includes at least [20 DEG C, 30 DEG C].
The thermistor uses Pt series thermistor, for example, Pt100, Pt500 or Pt1000 etc..
Preferably, flight Transparent Parts system above-mentioned, wherein the nozzle 7 is set along the shape subregion of the Transparent Parts
It is placed in the periphery of the Transparent Parts；The pipeline 8 that the nozzle 7 connects gas source 11 is set in the frame 9.
According to the shape of the Transparent Parts and the pneumatic situation of flight, subregion arranges nozzle 7, the number of the nozzle 7
Amount, spacing and the height on distance transparent part surface are adjustable；The nozzle 7 of the different zones can independent control or whole control
System, to guarantee aircraft in the operating condition, as needed, Transparent Parts surface can orient or uniformly be brushed by air-flow.
According to the shape of the Transparent Parts and the range of primary vision area, the setting of control system 10 should concentrate as far as possible,
It such as concentrates in a control system 10, maximumlly reduces the quantity of control system 10.
The jet-impingement system is arranged in the periphery of Transparent Parts, and the nozzle 7 can design on the frame 9, can also
Design is on the fuselage framework of aircraft.
Preferably, flight Transparent Parts system above-mentioned, wherein the control system 10 is provided with rainy day function control mould
Block can control the jet-impingement system only 7 jet-stream wind of actuating section nozzle.
After the engine start of aircraft, nearby there is abundant air, can be used as the gas source 11 that rainy day windshield surface removes water.
In the rainy day, the control system 10 controls the jet-impingement system and dries from the upper end of Transparent Parts to lower end, blows away glass
The rainwater on glass surface, in case it blocks sight.
Preferably, flight Transparent Parts system above-mentioned, wherein the control system 10 is provided with the control of Transparent Parts temperature
Module；When Transparent Parts temperature is lower than temperature preset value, the control system 10 controls jet-impingement system and sprays to Transparent Parts
Thermal current is penetrated with heating transparent part；When Transparent Parts temperature is higher than temperature preset value, the control system 10 controls air-flow spray
It penetrates system and closes jet-stream wind；The temperature preset value is 20 DEG C~40 DEG C.
It is described when the temperature of the Transparent Parts reaches 20 DEG C~40 DEG C in view of the heat resistance of intermediate layer material
Control system 10 control the jet-impingement system and stop injection；When the temperature of the Transparent Parts is lower than temperature preset value
When, then the control system 10 controls the jet-impingement system starting injection.
The ceiling temperature for the Transparent Parts that the control system 10 controls is no more than 60 DEG C.
Preferably, flight Transparent Parts system above-mentioned, wherein the hand control switch of jet-impingement system can also be set,
The jet-impingement system can be manually controlled as needed to open or close.
Preferably, flight Transparent Parts system above-mentioned, wherein control system 10 and fuselage can form connection signal, control
Switch or control panel are arranged in cockpit, facilitate pilot operator.
Embodiment:
As shown in Figure 1, Figure 2 and Figure 3, using the preparation process of conventional laminated glass.In outer layer transparent material layer 5 and
Temperature-sensing element 6 is laid between one bonding material layer 4, such as thermistor Pt100, Pt500 or Pt1000, with conducting wire by temperature-sensitive
Resistance is drawn.
The preferred unorganic glass of glass of the outer layer transparent material layer 5, such as soda-lime-silica glass or alumina silicate glass；Institute
The optional unorganic glass of inner transparent material layer, organic glass or the polycarbonate plate stated are selected according to the requirements such as weight, intensity；
Polyvinyl butyral or other transparent adhesive materials；First bonding material layer 4 selects polyurethane pellicle.
The Transparent Parts are successively transparent by the second transparent material layer 1, the second bonding material layer 2, first from inside to outside
The five-layer structure that material layer 3, the first bonding material layer 4 and outer layer transparent material layer 5 form；Alternatively, the Transparent Parts are served as reasons
The interior and outer three-decker being successively made of the first transparent material layer 3, the first bonding material layer 4 and outer layer transparent material layer 5.
Above-mentioned multi-layer transparent material is stacked in order with temperature-sensing element, hot pressing is combined with each other, and forms monolithic
Transparent Parts.
Bound edge is carried out to the edge of above-mentioned Transparent Parts, applies figure sealant by tooling and mold；The sealant selection
Silicone or the preferable sealing material of polysulfide class heatproof.
As shown in Figure 1-Figure 3, have frame, the component of upper and lower side frame assembled, by tooling and mold by frame with
Transparent Parts are combined with each other；It should be noted that: during bound edge, protection and insulation processing need to be carried out to conducting wire and draw conducting wire
Come, conducting wire can be in conjunction with plug, convenient for subsequent and control system connection when necessary.
Hot-air duct is set in the frame, pipeline material can bear 100 DEG C to 150 DEG C of high temperature；The air
Pipeline can directly be connected with nozzle, and the nozzle can bear 100 DEG C to 150 DEG C of high temperature.
The temperature controller of electricity heating of the principle and prior art of control system is similar, is that professional unit is entrusted to process.With
The prior art is compared, and bigger Suitable content is: control system is introduced into the gas source switch knot on Transparent Parts periphery with fuselage
It closes, according to the open and close for needing to control gas source.
Technical characteristic in the utility model claims and/or specification can be combined, and a combination thereof mode is unlimited
The combination obtained in claim by adduction relationship.Group is carried out by the technical characteristic in claim and/or specification
Close obtained technical solution and the protection scope of the utility model.
The above descriptions are merely preferred embodiments of the present invention, not makees in any form to the utility model
Limitation, any simple modification, equivalent change and modification made by the above technical examples according to the technical essence of the present invention,
It is still within the scope of the technical solutions of the present invention.
Claims (9)
1. a kind of flight Transparent Parts system, including Transparent Parts and frame, the Transparent Parts are installed on the frame, special
Sign is comprising:
Jet-impingement system is laid on the frame；It includes several nozzles, and the nozzle is set to flight capsule external application
With to the Transparent Parts jet-stream wind；
Gas source connects the jet-impingement system；The gas source includes at least hot gas source；
Temperature-sensing element or thermistor are embedded in temperature of the inside of the Transparent Parts to measure the Transparent Parts in advance
Degree；
Control system connects the temperature of the temperature-sensing element or thermistor to monitor the Transparent Parts；It is also
The connection jet-impingement system is to control the jet-impingement system starting or close.
2. flight Transparent Parts system according to claim 1, which is characterized in that
The Transparent Parts are formed by multi-layer transparent Material cladding.
3. flight Transparent Parts system according to claim 1, which is characterized in that
The Transparent Parts be from inside to outside successively by the second transparent material layer, the second bonding material layer, the first transparent material layer,
The five-layer structure of first bonding material layer and outer layer transparent material layer composition；Alternatively,
The Transparent Parts are from inside to outside successively by the first transparent material layer, the first bonding material layer and outer layer transparent material layer
The three-decker of composition.
4. flight Transparent Parts system according to claim 3, which is characterized in that
The material of the outer layer transparent material layer is selected from sodium calcium silicon unorganic glass, aluminosilicate unorganic glass or borosilicate
One kind of unorganic glass.
5. flight Transparent Parts system according to claim 3, which is characterized in that
The outer layer transparent material layer with a thickness of 1.5mm-5mm.
6. flight Transparent Parts system according to claim 3, which is characterized in that
The temperature-sensing element or thermistor is embedded in saturating close to the outer layer in first bonding material layer in advance
The inner surface of bright material layer.
7. flight Transparent Parts system according to claim 1, which is characterized in that
The sensitive temperature section of the temperature-sensing element or thermistor is [- 60 DEG C, 130 DEG C].
8. flight Transparent Parts system according to claim 1, which is characterized in that
The nozzle is set to the periphery of the Transparent Parts along the shape subregion of the Transparent Parts；The nozzle connection
The pipeline of gas source is set in the frame.
9. flight Transparent Parts system according to claim 1, which is characterized in that
The set-up of control system has rainy day functional control module, can control the jet-impingement system only actuating section
Jet nozzle air flow；
The set-up of control system has Transparent Parts temperature control modules；It is described when Transparent Parts temperature is lower than temperature preset value
Control system control jet-impingement system to Transparent Parts injection thermal current with heating transparent part；When Transparent Parts temperature is higher than temperature
When preset value, the control system control jet-impingement system closes jet-stream wind；
The temperature preset value is 20 DEG C~40 DEG C.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201822228690.2U CN209410340U (en) | 2018-12-28 | 2018-12-28 | Flight Transparent Parts system |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201822228690.2U CN209410340U (en) | 2018-12-28 | 2018-12-28 | Flight Transparent Parts system |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN209410340U true CN209410340U (en) | 2019-09-20 |
Family
ID=67941234
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201822228690.2U Active CN209410340U (en) | 2018-12-28 | 2018-12-28 | Flight Transparent Parts system |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN209410340U (en) |
-
2018
- 2018-12-28 CN CN201822228690.2U patent/CN209410340U/en active Active
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