CN205738113U - A kind of wing anti-frozen structure and use its aircraft - Google Patents
A kind of wing anti-frozen structure and use its aircraft Download PDFInfo
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- CN205738113U CN205738113U CN201620691613.9U CN201620691613U CN205738113U CN 205738113 U CN205738113 U CN 205738113U CN 201620691613 U CN201620691613 U CN 201620691613U CN 205738113 U CN205738113 U CN 205738113U
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- heat
- wing
- electromotor
- leading edge
- frozen structure
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Abstract
This utility model relates to vehicle technology field, particularly relates to a kind of wing anti-frozen structure and uses its aircraft.Wing anti-frozen structure includes heat collector and heat-transfer device, and described heat collector is arranged on the engine for collecting the heat of electromotor；Described heat-transfer device is arranged on the leading edge of a wing and is connected with heat collector, conducts to the leading edge of a wing for the heat collected by heat collector.Additionally provide the aircraft using above-mentioned wing anti-frozen structure simultaneously.This utility model collects the heat of electromotor by heat collector, is then conducted the heat of electromotor to the leading edge of a wing by heat-transfer device, it is achieved that removes the icing on wing, and has simple in construction, and load is light, the advantage of low cost.
Description
Technical field
This utility model relates to vehicle technology field, particularly relates to a kind of wing anti-frozen structure and uses flying of its
Machine.
Background technology
The advantages such as fixed wing airplane is fast with its speed, mobility is high, loading capacity is big become the topmost fortune of current aircraft industry
Load instrument, but its flight course needs the difficulty overcoming many natural environment to bring.Such as, height above sea level is the highest, and temperature is the lowest, flies
If machine runs into arctic weather when high-altitude flight, owing to wing is higher than the air themperature of surrounding, air will be sublimated at machine
On the wing, and then producing ice condition, especially leading edge of a wing ice condition is the most prominent.
Wind tunnel test shows, when the leading edge of a wing has the accumulated ice of half inch thick, can reduce by the lift of 50% and increase by 60%
Resistance.The speed of accumulated ice is the fastest, and sometimes in the case of serious accumulated ice, within 5 minutes, interior accumulated ice thickness is up to 2-3
Inch.After aircraft freezes, after longitudinal, the static stability in horizontal course and dynamic stability are all subject to corresponding impact to freeze due to aircraft
Change the aerodynamic configuration of wing, thus change the position of aerodynamic centre；And freeze and change the Mass Distribution of aircraft, right
The position of barycenter also has a certain impact, these two Longitudinal static stabilities that all can change aircraft, the change of aerodynamic configuration after icing
Change and have also been changed each aerodynamic derivative that aircraft is longitudinal.This makes the longitudinal dynamic stability of aircraft also there occurs change, during response
Between, peak value all changes.Stick force, the efficiency of manipulation that wing control face is handled after freezing all can change, and sometimes grasp
The gap in vertical face freezes, and not only reduces driving efficiency, there will be stuck phenomenon time serious, makes maneuvering performance complete failure, and then
Cause aviation accident.
The ice-removing and ice-preventing method that at present row is commonly used in the trade has that Electro-Impulse De-icing, electricity heating are anti-icing, liquid is anti-icing, pneumatic de-icing
With the method such as hot air anti-icing, but the equipment that above-mentioned ice-removing and ice-preventing method is required for additionally installing additional a set of complexity realizes, economical become
This height, load are greatly.
The structure existed for a kind of deicing structure that can solve the problem that on existing wing set forth above is complicated, and cost is high, negative
Carry the wing anti-frozen structure of big problem and use its aircraft.
Utility model content
The purpose of this utility model is to propose a kind of wing anti-frozen structure, it is possible to solves existing wing deicing structure and deposits
Structure complicated, cost is high, loads big problem.
Another purpose of the present utility model is to propose a kind of aircraft, and it uses the anti-freeze knot of wing as described above
Structure.
For reaching this purpose, this utility model by the following technical solutions:
A kind of wing anti-frozen structure, it includes that heat collector and heat-transfer device, described heat collector are arranged on electromotor
The upper heat for collecting electromotor；
Described heat-transfer device is arranged on the leading edge of a wing and is connected with heat collector, for the heat collected by heat collector
Conduction is to the leading edge of a wing.
As a kind of preferred version of above-mentioned wing anti-frozen structure, described heat collector is copper heat-conducting block, described in lead
Hot charging is set to copper pipe.
As a kind of preferred version of above-mentioned wing anti-frozen structure, described heat collector is heat collection water tank, described heat conduction
Device is heat pipe, and described heat collection water tank and heat pipe form the closed circuit closed；
Being provided with coolant in described heat collection water tank and heat pipe, described heat pipe is provided with water pump, described water pump is used
Power is provided in the circulation for coolant.
As a kind of preferred version of above-mentioned wing anti-frozen structure, including controlling device and temperature-detecting device, described
Temperature-detecting device is arranged on the leading edge of a wing the temperature for testing machine nose of wing；
Described temperature-detecting device and water pump all electrically connect with control device, the temperature that described temperature-detecting device will detect
Degree information passes to control device, controls device and controls the rotating speed of water pump according to the temperature information received.
As a kind of preferred version of above-mentioned wing anti-frozen structure, described heat collection water tank and heat pipe are copper knot
Structure.
As a kind of preferred version of above-mentioned wing anti-frozen structure, the described leading edge of a wing is the windward side of wing, described
Heat-transfer device is arranged on the rear portion of the leading edge of a wing.
As a kind of preferred version of above-mentioned wing anti-frozen structure, described heat collector arranges the heat radiation position of electromotor
Put.
A kind of aircraft, it includes wing anti-frozen structure as described above.
As a kind of preferred version of above-mentioned aircraft, also include fuselage, and be arranged on the wing of fuselage both sides, both sides
On wing, symmetry is provided with electromotor.
As a kind of preferred version of above-mentioned aircraft, described electromotor is provided with heat collector.
The beneficial effects of the utility model are: this utility model collects the heat of electromotor by heat collector, then leads to
Cross heat-transfer device to conduct the heat of electromotor to the leading edge of a wing, it is achieved that remove the icing on wing, and there is structure letter
Single, load is light, the advantage of low cost.
Accompanying drawing explanation
Fig. 1 is the structural representation being provided with wing anti-frozen structure aircraft that this utility model detailed description of the invention provides
Figure.
Wherein:
1: heat collector；2: heat-transfer device；3: electromotor；4: the leading edge of a wing.
Detailed description of the invention
Further illustrate the technical solution of the utility model below in conjunction with the accompanying drawings and by detailed description of the invention.
As it is shown in figure 1, present embodiments provide for a kind of wing anti-frozen structure, this wing anti-frozen structure includes thermal-arrest
Device 1 and heat-transfer device 2, heat collector 1 is arranged on electromotor 3 for collecting the heat of electromotor 3, and heat-transfer device 2 is arranged
It is connected at the leading edge of a wing 4 and with heat collector 1, conducts to the leading edge of a wing 4 for the heat that heat collector 1 is collected.
In the present embodiment, collected the heat of electromotor 3 by heat collector 1, then will be started by heat-transfer device 2
The heat of machine 3 conducts to the leading edge of a wing 4, it is achieved that removes the icing on wing, and has simple in construction, and load is light, cost
Low advantage.
Provide a kind of version of a kind of heat collector 1 and heat-transfer device 2, heat collector 1 in the present embodiment
For copper heat-conducting block, heat-transfer device 2 is copper pipe.Use copper heat-conducting block and copper pipe can improve the conduction efficiency of heat.
Additionally provide another heat collector 1 and the version of heat-transfer device 2, heat collector in the present embodiment
1 is heat collection water tank, and heat-transfer device 2 is heat pipe, and heat collection water tank and heat pipe form the closed circuit closed, heat collection water tank and leading
Being provided with coolant in heat pipe, heat pipe is provided with water pump, water pump provides power for the circulation for coolant.
By forming circulation waterway between heat collection water tank and heat pipe, it is possible to the effective efficiency improving heat conduction.
Wing anti-frozen structure also includes controlling device and temperature-detecting device, and temperature-detecting device is arranged on the leading edge of a wing
4 and for the temperature of testing machine nose of wing, temperature-detecting device and water pump all electrically connect with control device, temperature-detecting device general
The temperature information detected passes to control device, controls device and controls the rotating speed of water pump according to the temperature information received.
The circulation rate of coolant is controlled by temperature-detecting device, the cooperation that controls between device and water pump, permissible
Realize according to icing amount number control the heat that heat pipe provides for wing, it is possible to effectively reduce the consumption of the energy and carry
High deicing efficiency.
Heat collection water tank and heat pipe are copper structure.Use copper structure can improve heat conduction efficiency.
The leading edge of a wing 4 is the windward side of wing, and heat-transfer device is arranged on the rear portion of the leading edge of a wing 4.Heat-transfer device is arranged
Deicing efficiency can effectively be improved in this position.
Heat collector 1 arranges the heat radiation position of electromotor 3.The heat radiation position that heat collector 1 is arranged on electromotor 3 is permissible
Effective raising heat collection efficiency.
In the present embodiment, additionally providing a kind of aircraft, this aircraft includes wing anti-frozen structure as described above.
Aircraft includes fuselage, and is arranged on the wing of fuselage both sides, symmetrical on the wing of both sides is provided with electromotor
3, electromotor 3 is provided with heat collector 1.It is evenly distributed on aircraft thus, it is possible to realize heat collector 1, will not be right
The self structure of aircraft causes bad impact.
Know-why of the present utility model is described above in association with specific embodiment.These descriptions are intended merely to explain this reality
By novel principle, and the restriction to this utility model protection domain can not be construed to by any way.Based on explanation herein,
Those skilled in the art need not pay performing creative labour can associate other detailed description of the invention of the present utility model,
Within these modes fall within protection domain of the present utility model.
Claims (10)
1. a wing anti-frozen structure, it is characterised in that include heat collector (1) and heat-transfer device (2), described heat collector
(1) heat being used for collecting electromotor (3) on electromotor (3) it is arranged on；
Described heat-transfer device (2) is arranged on the leading edge of a wing (4) and is connected with heat collector (1), for being collected by heat collector (1)
The heat arrived conducts to the leading edge of a wing (4).
Wing anti-frozen structure the most according to claim 1, it is characterised in that described heat collector (1) is copper heat conduction
Block, described heat-transfer device (2) is copper pipe.
Wing anti-frozen structure the most according to claim 1, it is characterised in that described heat collector (1) is heat collection water tank, institute
Stating heat-transfer device (2) is heat pipe, and described heat collection water tank and heat pipe form the closed circuit closed；
Be provided with coolant in described heat collection water tank and heat pipe, described heat pipe be provided with water pump, described water pump be used for be
The circulation of coolant provides power.
Wing anti-frozen structure the most according to claim 3, it is characterised in that include controlling device and temperature-detecting device,
Described temperature-detecting device is arranged on the leading edge of a wing the temperature for testing machine nose of wing；
Described temperature-detecting device and water pump all electrically connect with control device, the temperature letter that described temperature-detecting device will detect
Breath passes to control device, controls device and controls the rotating speed of water pump according to the temperature information received.
Wing anti-frozen structure the most according to claim 3, it is characterised in that described heat collection water tank and heat pipe are copper
Matter structure.
Wing anti-frozen structure the most according to claim 1, it is characterised in that the described leading edge of a wing (4) is meeting of wing
Wind face, described heat-transfer device (2) is arranged on the rear portion of the leading edge of a wing (4).
Wing anti-frozen structure the most according to claim 1, it is characterised in that described heat collector (1) arranges electromotor
(3) heat radiation position.
8. an aircraft, it is characterised in that include the wing anti-frozen structure as described in claim 1-7 any one.
Aircraft the most according to claim 8, it is characterised in that also include fuselage, and it is arranged on the wing of fuselage both sides,
On the wing of both sides, symmetry is provided with electromotor (3).
Aircraft the most according to claim 9, it is characterised in that be provided with heat collector (1) on described electromotor (3).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201620691613.9U CN205738113U (en) | 2016-06-30 | 2016-06-30 | A kind of wing anti-frozen structure and use its aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201620691613.9U CN205738113U (en) | 2016-06-30 | 2016-06-30 | A kind of wing anti-frozen structure and use its aircraft |
Publications (1)
| Publication Number | Publication Date |
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| CN205738113U true CN205738113U (en) | 2016-11-30 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN201620691613.9U Active CN205738113U (en) | 2016-06-30 | 2016-06-30 | A kind of wing anti-frozen structure and use its aircraft |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106005430A (en) * | 2016-06-30 | 2016-10-12 | 天津曙光天成科技有限公司 | Wing anti-freezing structure and aircraft adopting same |
-
2016
- 2016-06-30 CN CN201620691613.9U patent/CN205738113U/en active Active
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106005430A (en) * | 2016-06-30 | 2016-10-12 | 天津曙光天成科技有限公司 | Wing anti-freezing structure and aircraft adopting same |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| TR01 | Transfer of patent right | ||
| TR01 | Transfer of patent right |
Effective date of registration: 20221014 Address after: Room 105, Building 9, Area B3 (formerly Area 2 of Ronghui Business Park), Enterprise Headquarters Base, Binhai-Zhongguancun Science and Technology Park, Economic and Technological Development Zone, Binhai New Area, Tianjin 300457 Patentee after: Tianjin Phoenix Intelligent Technology Co.,Ltd. Address before: Floor 1, block B, No.3, Tengfei Road, Junliang City, Dongli District, Tianjin Patentee before: TIANJIN SHUGUANG TIANCHENG TECHNOLOGY Co.,Ltd. |