CN209521886U - Aircraft anti-icing arranges rain system experimental - Google Patents
Aircraft anti-icing arranges rain system experimental Download PDFInfo
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- CN209521886U CN209521886U CN201920137747.XU CN201920137747U CN209521886U CN 209521886 U CN209521886 U CN 209521886U CN 201920137747 U CN201920137747 U CN 201920137747U CN 209521886 U CN209521886 U CN 209521886U
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- wing
- subsystem
- windshield
- icing
- horizontal stabilizer
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Abstract
The utility model discloses aircraft anti-icings to arrange rain system experimental, and wing anti-ice subsystem experimental bench includes gas source, the first diversion pipe, pressure-regulating valve, the second diversion pipe, port wing, starboard wing, puff prot, discharge outlet and wing anti-ice subsystem switch；The anti-icing subsystem experimental bench of horizontal stabilizer includes two electric heating heating modules, horizontal stabilizer, sequence timer, horizontal stabilizer heater switch and relay；The anti-icing subsystem experimental bench of windshield includes windshield, windshield fixed frame, heater strip, transformer and the anti-icing subsystem switch of windshield；Windshield row's rain subsystem experimental bench includes electric wiper, Raindrop sensor and row's rain subsystem switch.The utility model not only devises the teaching equipment of perfect aircraft anti-icing row's rain, reduces instruction cost, while realizing makes air cadet understand the working principle for effectively understanding aircraft anti-icing row's rain.
Description
Technical field
The utility model relates to aircraft experimental bench technical field, especially aircraft anti-icings to arrange rain system experimental.
Background technique
During aircraft flies in the sky, it may appear that icing phenomenon, it is common for water droplet icing, i.e. supercooling in atmosphere
Droplets impact freezes on aircraft surfaces, endangers the safe flight of aircraft maximum.
The position that aircraft freezes is generally in the leading edge of a wing, empennage leading edge, windshield；The harm of corresponding generation are as follows: the wing
Form-drag increases, and leads to drop in lift, critical angle of attack decline；Aircraft controllability reduces；Interfere crew's sight.
Anti- ice raft rain system is designed on existing aircraft, it is therefore prevented that the certain key areas or component of aircraft freeze, and
And in rainy day flight, guarantee the drying of cockpit windscreen, so that it will not interfere the sight of driver.But at present to aeronautics
Member carries out about the teaching equipment about aircraft anti-icing row's rain imperfect in the various simulated experiments of aircraft, if used
Prototype is tested, not only at high cost, and air cadet can not also understand the working principle for effectively understanding aircraft anti-icing row's rain.
Utility model content
Purpose of the utility model is to solve the above problems, devise aircraft anti-icing row's rain system experimental, not only
The teaching equipment for devising perfect aircraft anti-icing row rain, reduces instruction cost, while realizing and understand air cadet to have
Effect understands the working principle of aircraft anti-icing row's rain.
Realize that above-mentioned purpose the technical solution of the utility model is, aircraft anti-icing arranges rain system experimental, including main confluence
Item, wing anti-ice subsystem experimental bench, the anti-icing subsystem experimental bench of horizontal stabilizer, the anti-icing subsystem experimental bench of windshield and
Windshield arranges rain subsystem experimental bench；
The wing anti-ice subsystem experimental bench includes gas source, the first diversion pipe, pressure-regulating valve, the second diversion pipe, a left side
Wing, starboard wing, puff prot, discharge outlet and wing anti-ice subsystem switch；
The gas source is connected with the air inlet of the first diversion pipe, and first diversion pipe is installed far from the side of air inlet
Have pressure-regulating valve, the gas outlet of first diversion pipe is connected with the air inlet of the second diversion pipe, second diversion pipe with
Port wing is mutually fixed with starboard wing, and is run through and extended in the diversion trench on the inside of port wing and starboard wing, is located in diversion trench
The second diversion pipe on offer several puff prots, the diversion trench offers discharge outlet far from one end of the first diversion pipe,
The essential bus and wing anti-ice subsystem switch are electrically connected, the wing anti-ice subsystem switch and pressure-regulating valve electricity
Property connection；
The anti-icing subsystem experimental bench of horizontal stabilizer includes two electric heating heating modules, horizontal stabilizer, sequence meter
When device, horizontal stabilizer heater switch and relay；
The essential bus and relay are electrically connected, and the relay and sequence timer are electrically connected, the sequence
Timer is electrically connected with electric heating heating module and horizontal stabilizer heater switch respectively, and the electric heating heating module is set to level
The front end of stabilizer；
The anti-icing subsystem experimental bench of windshield includes windshield, windshield fixed frame, heater strip, transformer
With the anti-icing subsystem switch of windshield；
The windshield fixed frame is fixedly installed in the outside of windshield, and the inside of the windshield fixed frame
Bottom end and windshield contact position are equipped with heating channel, and the heating channel interior is fixed with heater strip, and the one of the heater strip
End ground connection, the other end connect silicon keyholed back plate, and the silicon keyholed back plate is electrically connected with transformer, and it is anti-that the transformer is electrically connected with windshield
Ice subsystem switch, the anti-icing subsystem switch of windshield are electrically connected with essential bus；
The windshield row rain subsystem experimental bench includes electric wiper, Raindrop sensor and row's rain subsystem switch；
The electric wiper and Raindrop sensor are each attached to the outside of windshield, and the electric wiper and raindrop sense
Device is electrically connected, and the Raindrop sensor and row's rain subsystem switch are electrically connected, row's rain subsystem switch and main confluence
Item is electrically connected.
Further, the wing anti-ice subsystem experimental bench further includes wing temperature sensor and wing temperature instruction
Device, the wing temperature sensor are fixed on the up-front covering of starboard wing, and the wing temperature sensor refers to wing temperature
Show that device is electrically connected.
Further, the wing anti-ice subsystem experimental bench further includes basic busbar, thermocouple and wing overheat police
Lamp is accused, the thermocouple overheats emergency warning lamp with wing respectively and wing temperature sensor is connected, the basic busbar and wing
Overheat emergency warning lamp is electrical connected.
Further, first diversion pipe is fixedly installed with check-valves, second water conservancy diversion close to the side of air inlet
Pipe is V-type, and first diversion pipe and the second diversion pipe are mutually fixedly connected by threeway.
Further, the anti-icing subsystem experimental bench of the horizontal stabilizer further includes current limiter, horizontal stabilizer overheat police
Report device and horizontal stabilizer temperature sensor；
The horizontal stabilizer temperature sensor is set to the front end of horizontal stabilizer, and be set to two electric heating heating modules it
Between, the horizontal stabilizer temperature sensor and horizontal stabilizer temperature alarm are electrically connected, the horizontal stabilizer overheat
Alarm device and sequence timer are electrically connected, and the sequence timer and current limiter are electrically connected.
Further, the windshield includes waterproof coating, glass body and plastic layer, and the waterproof coating uniformly applies
The outside of glass body is overlayed on, inside and the plastic layer stickup of the glass body are mutually fixed.
Compared with prior art, the utility model has the advantage that is with beneficial effect,
1. passing through setting essential bus, wing anti-ice subsystem experimental bench, the anti-icing subsystem experimental bench of horizontal stabilizer, wind
It keeps off the anti-icing subsystem experimental bench of glass and windshield arranges rain subsystem experimental bench, devise the religion of perfect aircraft anti-icing row's rain
Equipment is learned, instruction cost is reduced, while realizing makes air cadet understand the working principle for effectively understanding aircraft anti-icing row's rain.
2. the case where wing is heated can be understood in real time by wing temperature sensor and wing temperature indicator；It is logical
Thermocouple and wing overheat emergency warning lamp are crossed, the case where wing crosses high temperature can be understood in time.
3., can be real-time by setting current limiter, horizontal stabilizer temperature alarm and horizontal stabilizer temperature sensor
Understand the temperature that horizontal stabilizer is heated, while current limliting is carried out to overheat condition, reduces heating temperature, avoid temperature excessively high right
It is damaged caused by horizontal stabilizer；
4. the row's of progress rain operation automatically may be implemented by setting electric wiper and Raindrop sensor；By in glass sheet
The outside of body uniformly coats waterproof coating, and combines electric wiper, may be implemented preferably to arrange rain operation.
Detailed description of the invention
Fig. 1 is the structural representation of wing anti-ice subsystem experimental bench in the utility model aircraft anti-icing row's rain system experimental
Figure；
Fig. 2 is the block diagram signal of wing anti-ice subsystem experimental bench in the utility model aircraft anti-icing row's rain system experimental
Figure；
Fig. 3 is the anti-icing subsystem experimental bench of horizontal stabilizer in aircraft anti-icing row rain system experimental described in the utility model
Structural schematic diagram；
Fig. 4 is the anti-icing subsystem experimental bench of horizontal stabilizer in aircraft anti-icing row rain system experimental described in the utility model
Block diagram representation；
Fig. 5 is the anti-icing subsystem experimental bench of windshield in aircraft anti-icing row rain system experimental described in the utility model
Structural schematic diagram；
Fig. 6 is the anti-icing subsystem experimental bench of windshield in aircraft anti-icing row rain system experimental described in the utility model
Block diagram representation；
Fig. 7 is windshield row's rain subsystem experimental bench in aircraft anti-icing row rain system experimental described in the utility model
Block diagram representation；
Fig. 8 is the structural schematic diagram of windshield in aircraft anti-icing row rain system experimental described in the utility model.
In figure, 1 gas source；2 first diversion pipes；3 pressure-regulating valves；4 second diversion pipes；5 port wings；6 starboard wings；7 jets
Mouthful；8 discharge outlet；9 wing anti-ice subsystems switch；10 diversion trenches；11 wing temperature sensors；12 wing temperature indicators；13
Covering；14 thermocouples；15 wings overheat emergency warning lamp；16 check-valves；17 threeways；18 electric heating heating modules；19 horizontal stabilizers；20
Sequence timer；21 relays；22 windshields；221 waterproof coatings；222 glass bodies；223 plastic layers；23 windshields are solid
Determine frame；24 heater strips.
Specific embodiment
The following will be combined with the drawings in the embodiments of the present invention, carries out the technical scheme in the embodiment of the utility model
Clearly and completely describe, it is clear that the described embodiments are only a part of the embodiments of the utility model, rather than whole
Embodiment.Based on the embodiments of the present invention, those of ordinary skill in the art are without making creative work
Every other embodiment obtained, fall within the protection scope of the utility model.
As shown in figures 1-8, aircraft anti-icing arrange rain system experimental, including essential bus, wing anti-ice subsystem experimental bench,
The anti-icing subsystem experimental bench of horizontal stabilizer, the anti-icing subsystem experimental bench of windshield and windshield row's rain subsystem experiment
Platform；
The wing anti-ice subsystem experimental bench includes gas source 1, the first diversion pipe 2, pressure-regulating valve 3, the second diversion pipe
4, port wing 5, starboard wing 6, puff prot 7, discharge outlet 8 and wing anti-ice subsystem switch 9；
The gas source 1 is connected with the air inlet of the first diversion pipe 2, the side of the first diversion pipe 2 far from air inlet
Pressure-regulating valve 3 is installed, the gas outlet of first diversion pipe 2 is connected with the air inlet of the second diversion pipe 4, and described second leads
Flow tube 4 is fixed with port wing 5 and 6 phase of starboard wing, and is run through and extended in the diversion trench 10 of 6 inside of port wing 5 and starboard wing,
Several puff prots 7 are offered on the second diversion pipe 4 in diversion trench 10, the diversion trench 10 is far from the first diversion pipe 2
One end offer discharge outlet 8, the essential bus and wing anti-ice subsystem switch 9 are electrically connected, and the wing anti-ice is sub
System switching 9 and pressure-regulating valve 3 are electrically connected；The wing anti-ice subsystem experimental bench further includes wing temperature sensor 11
With wing temperature indicator 12, the wing temperature sensor 11 is fixed on the up-front covering 13 of starboard wing 6, the wing temperature
It spends sensor 11 and wing temperature indicator 12 is electrically connected；The wing anti-ice subsystem experimental bench further includes converging substantially
Item, thermocouple 14 and wing overheat emergency warning lamp 15, and emergency warning lamp 15 is overheated with wing respectively for the thermocouple 14 and wing temperature passes
Sensor 11 is connected, and the basic busbar is electrical connected with wing overheat emergency warning lamp 15；First diversion pipe 2 is close to air inlet
Side be fixedly installed with check-valves 16, can prevent gas source 1 from flowing back from the first diversion pipe 2, second diversion pipe 4 be V-type,
And first diversion pipe 2 is fixedly connected with the second diversion pipe 4 by 17 phase of threeway；
The anti-icing subsystem experimental bench of horizontal stabilizer includes two electric heating heating modules 18, horizontal stabilizer 19, sequence
Column timer 20, horizontal stabilizer heater switch and relay 21；The essential bus and relay 21 are electrically connected, it is described after
Electric appliance 21 and sequence timer 20 are electrically connected, the sequence timer 20 respectively with electric heating heating module 18 and horizontal stabilizer
Heater switch is electrically connected, and the electric heating heating module 18 is set to the front end of horizontal stabilizer 19；The horizontal stabilizer is anti-icing
Subsystem experimental bench further includes current limiter, horizontal stabilizer temperature alarm and horizontal stabilizer temperature sensor；The level
Stabilization temperature sensor is set to the front end of horizontal stabilizer 19, and is set between two electric heating heating modules 18, the level
Stabilization temperature sensor and horizontal stabilizer temperature alarm are electrically connected, the horizontal stabilizer temperature alarm and sequence
Timer 20 is electrically connected, and the sequence timer 20 is electrically connected with current limiter；
The anti-icing subsystem experimental bench of windshield include windshield 22, windshield fixed frame 23, heater strip 24,
Transformer and the anti-icing subsystem switch of windshield；The windshield 22 includes waterproof coating 221, glass body 222 and modeling
The bed of material 223, the waterproof coating 221 are coated uniformly on the outside of glass body 222, the inside of the glass body 222 and modeling
The stickup of the bed of material 223 is mutually fixed；The windshield fixed frame 23 is fixedly installed in the outside of windshield 22, and the windscreen glass
The inner bottom of glass fixed frame 23 and 22 contact position of windshield are equipped with heating channel, and the heating channel interior is fixed with heating
Silk 24, one end ground connection of the heater strip 24, the other end connect silicon keyholed back plate, and the silicon keyholed back plate is electrically connected with transformer, the change
Depressor is electrically connected with the anti-icing subsystem switch of windshield, and the anti-icing subsystem switch of windshield electrically connects with essential bus
It connects；
The windshield row rain subsystem experimental bench includes electric wiper, Raindrop sensor and row's rain subsystem switch；
The electric wiper and Raindrop sensor are each attached to the outside of windshield 22, and the electric wiper and Raindrop sensor are electrical
Connection, the Raindrop sensor and row's rain subsystem switch are electrically connected, and row's rain subsystem switch and essential bus are electrical
Connection.
Working principle:
Essential bus, wing anti-ice subsystem experimental bench, the anti-icing subsystem experimental bench of horizontal stabilizer, windshield are anti-icing
Equipment equipment relevant to space shuttle in subsystem experimental bench and windshield row's rain subsystem experimental bench is all made of aviation
Material, to guarantee the authenticity and accuracy of experiment；
When needing to carry out the experiment of wing anti-ice subsystem, operated on wing anti-ice subsystem experimental bench, first
Wing anti-ice subsystem switch 9 is placed on DC power supply, essential bus provides at this time for wing anti-ice subsystem experimental bench
Electric power, then opens pressure-regulating valve 3, and the gas source 1 of the hot-air as engine bleed flows successively through on the first diversion pipe 2
Check-valves 16, pressure-regulating valve 3 and the flow direction of threeway 17 are located at the second diversion pipe 4 in port wing 4 and starboard wing 5, by the
Puff prot 7 on two diversion pipes 4 spurts hot gas into diversion trench 10, heats to port wing 4 and starboard wing 5, hot gas encounters
The lower diversion trench 10 of temperature is converted into liquid and is discharged by the discharge outlet 8 of 10 side of diversion trench；Due in the up-front illiteracy of starboard wing 6
Be fixed with wing temperature sensor 11 on skin 13, temperature on up-front 13 surface of covering of starboard wing 6 detected by it, by with
The wing temperature indicator 12 that wing temperature sensor 11 is electrically connected carries out temperature display, understands machine in real time convenient for air cadet
The case where wing is heated；Basic busbar is electrical connected with wing overheat emergency warning lamp 15, carries out electricity to wing overheat emergency warning lamp 15
Power provides, and thermocouple 14 overheats emergency warning lamp 15 with wing respectively and wing temperature sensor 11 is connected, wing temperature sensor 11
The temperature data on up-front 13 surface of covering of starboard wing 6 measured is transmitted to wing overheat emergency warning lamp 15 via thermocouple 14, when
When the temperature that wing temperature sensor 11 measures is more than 215 °F, progress temperature is lighted by the wing overheat emergency warning lamp 15 in cockpit
High prompting is spent, understands the case where wing crosses high temperature in time convenient for air cadet, it when the temperature is excessively high, can be by turning down or closing
Pressure-regulating valve 3 is closed, is reduced or turned off gas source 1 to the gas supply of the second diversion pipe 4；
It is enterprising in the anti-icing subsystem experimental bench of horizontal stabilizer when needing to carry out horizontal stabilizer anti-icing subsystem experiment
Horizontal stabilizer heater switch, is placed on DC power supply by row operation first, and essential bus is that horizontal stabilizer is anti-icing at this time
Subsystem experimental bench provides electric power, and relay 21 works at this time, is alternately heated by sequence timer 20 connected to it each
A electric heating heating module 18, when the horizontal stabilizer temperature sensor for the front end for being set to horizontal stabilizer 19 detects that electric heating heats
Module 18 carries out overheat report when the temperature is excessively high, by the horizontal stabilizer temperature alarm connecting with horizontal stabilizer temperature sensor
It is alert, current limliting then is carried out to sequence timer 20 by current limiter, heating temperature is reduced, avoids temperature excessively high to horizontal stabilizer 19
Caused by damage；By setting horizontal stabilizer temperature alarm and horizontal stabilizer temperature sensor, water can be understood in real time
The temperature that flat stabilizer 19 is heated；
When needing to carry out windshield anti-icing subsystem experiment, grasped on the anti-icing subsystem experimental bench of windshield
Make, the anti-icing subsystem switch of windshield is placed on DC power supply first, essential bus is the anti-icing son of windshield at this time
System experimental provides electric power, and transformer works at this time, is heated by silicon keyholed back plate to heater strip 24, and then to windshield
The heating channel that the inner bottom of fixed frame 23 is equipped with 22 contact position of windshield is heated, and is completed to windshield 22
Heating, wherein the shape of windshield 22 is the common arc of space shuttle, windshield fixed frame 23 and windshield 22
Fixed form also uses the prior art, and this will not be repeated here；
When needing to carry out windshield row's rain subsystem experiment, grasped on windshield row's rain subsystem experimental bench
Make, row's rain subsystem switch is placed on DC power supply first, essential bus is that windshield arranges the experiment of rain subsystem at this time
Platform provides electric power, and electric wiper is in standby, when Raindrop sensor detects the waterproof coating 221 in 22 outside of windshield
On when having raindrop, then control electric wiper and swing, row's rain operation is carried out to windshield 22, by electric wiper and
The row's of progress rain operation automatically may be implemented in Raindrop sensor；By uniformly coating waterproof coating in the outside of glass body 222
221, and electric wiper is combined, it may be implemented preferably to arrange rain operation.
The utility model passes through setting essential bus, wing anti-ice subsystem experimental bench, the anti-icing subsystem of horizontal stabilizer
The anti-icing subsystem experimental bench of experimental bench, windshield and windshield arrange rain subsystem experimental bench, and it is anti-to devise perfect aircraft
The teaching equipment of ice raft rain reduces instruction cost, while realizing makes air cadet understand that effectively understanding aircraft anti-icing arranges rain
Working principle.
While there has been shown and described that the embodiments of the present invention, for the ordinary skill in the art,
It is understood that these embodiments can be carried out with a variety of variations in the case where not departing from the principles of the present invention and spirit, repaired
Change, replacement and variant, the scope of the utility model is defined by the appended claims and the equivalents thereof.
Claims (6)
1. aircraft anti-icing arranges rain system experimental, which is characterized in that including essential bus, wing anti-ice subsystem experimental bench, water
The anti-icing subsystem experimental bench of flat stabilization, the anti-icing subsystem experimental bench of windshield and windshield arrange rain subsystem experimental bench；
The wing anti-ice subsystem experimental bench include gas source, the first diversion pipe, pressure-regulating valve, the second diversion pipe, port wing,
Starboard wing, puff prot, discharge outlet and wing anti-ice subsystem switch；
The gas source is connected with the air inlet of the first diversion pipe, and first diversion pipe is equipped with pressure far from the side of air inlet
The gas outlet of force regulating valve, first diversion pipe is connected with the air inlet of the second diversion pipe, second diversion pipe and left machine
The wing is mutually fixed with starboard wing, and is run through and extended in the diversion trench on the inside of port wing and starboard wing, and in diversion trench
Several puff prots are offered on two diversion pipes, the diversion trench offers discharge outlet far from one end of the first diversion pipe, described
Essential bus and wing anti-ice subsystem switch are electrically connected, and the wing anti-ice subsystem switch electrically connects with pressure-regulating valve
It connects；
The anti-icing subsystem experimental bench of horizontal stabilizer include two electric heating heating modules, horizontal stabilizer, sequence timer,
Horizontal stabilizer heater switch and relay；
The essential bus and relay are electrically connected, and the relay and sequence timer are electrically connected, the sequence timing
Device is electrically connected with electric heating heating module and horizontal stabilizer heater switch respectively, and the electric heating heating module is set to horizontal stable
The front end of device；
The anti-icing subsystem experimental bench of windshield includes windshield, windshield fixed frame, heater strip, transformer and wind
Keep off the anti-icing subsystem switch of glass；
The windshield fixed frame is fixedly installed in the outside of windshield, and the inner bottom of the windshield fixed frame
It is equipped with heating channel with windshield contact position, the heating channel interior is fixed with heater strip, a termination of the heater strip
Ground, the other end connect silicon keyholed back plate, and the silicon keyholed back plate is electrically connected with transformer, and the transformer is electrically connected with the anti-icing son of windshield
System switching, the anti-icing subsystem switch of windshield are electrically connected with essential bus；
The windshield row rain subsystem experimental bench includes electric wiper, Raindrop sensor and row's rain subsystem switch；
The electric wiper and Raindrop sensor are each attached to the outside of windshield, the electric wiper and Raindrop sensor electricity
Property connection, the Raindrop sensor and row's rain subsystem switch be electrically connected, row's rain subsystem switch and essential bus electricity
Property connection.
2. aircraft anti-icing according to claim 1 arranges rain system experimental, which is characterized in that the wing anti-ice subsystem
Experimental bench further includes wing temperature sensor and wing temperature indicator, and the wing temperature sensor is fixed on starboard wing leading edge
Covering on, the wing temperature sensor and wing temperature indicator are electrically connected.
3. aircraft anti-icing according to claim 1 or 2 arranges rain system experimental, which is characterized in that wing anti-ice
System experimental further includes that basic busbar, thermocouple and wing overheat emergency warning lamp, the thermocouple overheat with wing warn respectively
It accuses lamp to be connected with wing temperature sensor, the basic busbar is electrical connected with wing overheat emergency warning lamp.
4. aircraft anti-icing according to claim 3 arranges rain system experimental, which is characterized in that first diversion pipe is close
The side of air inlet is fixedly installed with check-valves, and second diversion pipe is V-type, and first diversion pipe and the second diversion pipe
It is mutually fixedly connected by threeway.
5. aircraft anti-icing according to claim 1 arranges rain system experimental, which is characterized in that the horizontal stabilizer is anti-icing
Subsystem experimental bench further includes current limiter, horizontal stabilizer temperature alarm and horizontal stabilizer temperature sensor；
The horizontal stabilizer temperature sensor is set to the front end of horizontal stabilizer, and is set between two electric heating heating modules,
The horizontal stabilizer temperature sensor and horizontal stabilizer temperature alarm are electrically connected, the horizontal stabilizer temperature alarm
Device and sequence timer are electrically connected, and the sequence timer and current limiter are electrically connected.
6. aircraft anti-icing according to claim 1 arranges rain system experimental, which is characterized in that the windshield includes anti-
Water coating, glass body and plastic layer, the waterproof coating are coated uniformly on the outside of glass body, the glass body it is interior
Side is mutually fixed with plastic layer stickup.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201920137747.XU CN209521886U (en) | 2019-01-25 | 2019-01-25 | Aircraft anti-icing arranges rain system experimental |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201920137747.XU CN209521886U (en) | 2019-01-25 | 2019-01-25 | Aircraft anti-icing arranges rain system experimental |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN209521886U true CN209521886U (en) | 2019-10-22 |
Family
ID=68230847
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201920137747.XU Expired - Fee Related CN209521886U (en) | 2019-01-25 | 2019-01-25 | Aircraft anti-icing arranges rain system experimental |
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| Country | Link |
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| CN (1) | CN209521886U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114229032A (en) * | 2021-12-17 | 2022-03-25 | 中国航空工业集团公司西安飞机设计研究所 | Ground test bed for windshield heating system of aircraft cockpit |
-
2019
- 2019-01-25 CN CN201920137747.XU patent/CN209521886U/en not_active Expired - Fee Related
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114229032A (en) * | 2021-12-17 | 2022-03-25 | 中国航空工业集团公司西安飞机设计研究所 | Ground test bed for windshield heating system of aircraft cockpit |
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| GR01 | Patent grant | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20191022 Termination date: 20220125 |