CN205805678U - A kind of cooling system of multi-rotor aerocraft electromotor - Google Patents
A kind of cooling system of multi-rotor aerocraft electromotor Download PDFInfo
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- CN205805678U CN205805678U CN201620476179.2U CN201620476179U CN205805678U CN 205805678 U CN205805678 U CN 205805678U CN 201620476179 U CN201620476179 U CN 201620476179U CN 205805678 U CN205805678 U CN 205805678U
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Abstract
Small-sized aviation piston engine in practice, is mainly used in fixed-wing unmanned plane, utilizes fixed wing airplane to put down the high velocity air heat radiation flying to produce, and engine radiating design is simple.Many rotors use small-sized aviation piston engine, do not possess the most flat radiating condition flown of fixed-wing, use general wind cooling blower to carry out heat radiation and can not meet the radiating requirements of electromotor.This utility model devises efficient small-size water-cooling system, solves small-sized aviation piston engine heat dissipation problem.Its weight is little, and heat radiation power is high, promotes unmanned plane reliability, stability and cruising time.Owing to have employed the cylinder sleeve of cladding cylinder, cooling work liquid directly contacts with cylinder, high efficient heat exchanging.Additionally, utilize rotor downwash forced convertion aluminum to arrange heat exchanger, instead of Special heat dissipating blower fan, improve overall efficiency.
Description
Technical field
This utility model belongs to technical field of aerospace, is specifically related to a kind of cooling system flying multi-rotor aerocraft electromotor
System.
Background technology
Small-sized aviation piston engine in practice, is mainly used in fixed-wing unmanned plane, utilizes fixed wing airplane to put down and flies
The high velocity air heat radiation produced, engine radiating design is simple.In recent years, many rotor wing unmanned aerial vehicles develop rapidly, steady with its flight
Fixed, simple in construction, it is easy to the features such as manipulation, aerial survey of taking photo by plane, scout, explore, logistics, the field such as plant protection have obtained widely should
With.The many rotor wing unmanned aerial vehicles using petrol power breach electronic many rotor wing unmanned aerial vehicles short slab in terms of continuation of the journey and load-carrying, beat
Open many rotor wing unmanned aerial vehicles broader practice prospect.Many rotors use small-sized aviation piston engine, do not possess fixed-wing high
The flat radiating condition flown of speed, uses general wind cooling blower to carry out heat radiation and can not meet the radiating requirements of electromotor, nominal situation
Under, several minutes intrinsic motivation is the most overheated, and temperature cylinder is more than 150 DEG C, if quitting work not in time, then electromotor can be caused to draw
The accident such as cylinder, detonation, when greatly constraining reliability and stability and the continuation of the journey of the many rotor wing unmanned aerial vehicles using petrol power
Between.
Summary of the invention
The purpose of this utility model is to provide the cooling system of a kind of multi-rotor aerocraft electromotor, it is possible to effectively solve to dissipate
The problem that heat is the best.
The technical solution of the utility model is: the cooling system of a kind of multi-rotor aerocraft electromotor, it is characterised in that
Including:
Chiller: include the first inlet and the first liquid outlet；
Heat-exchange device: include the second inlet and the second liquid outlet；
Circulating device: include the 3rd inlet and the 3rd liquid outlet；
And the interface channel being connected between said apparatus, it is provided with circulating cooling liquid in described interface channel；
Described interface channel includes main line and at least two parallel branch, and each branch road includes a described chiller,
It is respectively used to cool down the difference cylinder of electromotor.
Preferably, described Control device of liquid cooling is disposed on the cylinder sleeve outside cylinder.
Described electromotor is removed the transformation of at least part of fin by air cooling engine and forms；Described cylinder sleeve be installed on remove scattered
Outside the body of the electromotor after backing；And cylinder sleeve and remaining fin use seal means to combine.
Described cylinder sleeve is annular solid, and the spark plug of described electromotor exposes in the middle part of annular solid.
Another kind of optional mode, is to arrange coil pipe between engine radiating fin as described Control device of liquid cooling.
Preferably, described heat-exchange device is arranged on below the rotor support arm beam of aircraft, the wind-force produced by rotor
Heat-exchange device is dispelled the heat.
The main line of interface channel arranges described heat-exchange device；Or, every branch road of interface channel sets
Put a described heat-exchange device.
Preferably, described heat-exchange device includes the first liquid storage container, is arranged on the Foldable aluminum of the first liquid storage container shell
Paper tinsel heat radiation row, and first control device；Described first control device includes the first temperature sensing unit, the second temperature sensing list
Unit, first threshold comparing unit and the first alarm unit；Described first temperature sensing unit, is arranged on described heat-exchange device
Second inlet, for measuring the coolant temperature of heat-exchange device entrance；Described second temperature sensing unit, is arranged on described
Second liquid outlet of heat-exchange device, for measuring the coolant temperature of heat-exchange device outlet；Described first threshold is more single
Unit, the temperature measuring the first temperature sensing unit and the second temperature sensing unit compares, when the first temperature sensing unit
When the temperature difference that the temperature gathered and the second temperature sensing unit gather is less than first threshold, send the first control signal；Institute
State the first alarm unit, after receiving the first control signal that first threshold comparing unit sends, send alarm signal.
Preferably, described circulating device includes circulating pump and the second liquid storage container, and second control device；Described second
Control device and include the first pressure sensitive unit, Second Threshold comparing unit and the first switch element；Described first pressure sensing
Unit, the pressure in measuring the second liquid storage container；Described Second Threshold comparing unit, when the first pressure sensitive unit is surveyed
When the pressure of amount exceedes Second Threshold, send the second control signal；Described first switch element, compares when receiving Second Threshold
During the second control signal that unit sends, open switch so that the second liquid storage container and atmosphere, discharge pressure.
Preferably, described chiller also includes the 3rd control device, and the described 3rd controls device includes that the 3rd temperature passes
Sense unit, the 3rd threshold value comparing unit and the second alarm unit: the 3rd temperature sensing unit, be arranged on the of described chiller
One liquid outlet, for measuring the chilled liquid temperature of chiller outlet；3rd threshold value comparing unit, when the 3rd temperature sensing list
When the temperature value that unit measures is more than three threshold values, send the 3rd control signal；Second alarm unit, when receiving the 3rd threshold ratio
After the 3rd control signal that relatively unit sends, send alarm signal.
Use the technical solution of the utility model, small-sized aviation piston can be solved by efficient small-size water-cooling system
Engine radiating problem.Meanwhile, the wind-force making full use of rotor self instead of Special heat dissipating blower fan forced convertion, serves joint
The about technique effect of cost.
Accompanying drawing explanation
Fig. 1 is this utility model engine-cooling system schematic diagram.
Fig. 2 is the assembling structural representation of cylinder water vat set in this utility model engine-cooling system.
Fig. 3 is the assembling structural representation of heat exchanger in this utility model engine-cooling system.
Fig. 4 is the structure function figure of first control device in this utility model engine-cooling system.
Fig. 5 is the structure function figure of second control device in this utility model engine-cooling system
Detailed description of the invention
1-4 illustrates detailed description of the invention of the present utility model below in conjunction with the accompanying drawings.
Embodiment one:
As it is shown in figure 1, cooling system of the present utility model mainly include chiller 11,12, heat-exchange device 3, circulation
Device 2 and the interface channel being connected between said apparatus.Wherein chiller includes that the first inlet and first goes out liquid
Mouthful；Heat-exchange device 3 includes the second inlet and the second liquid outlet, and wherein the second inlet is connected to the first of chiller and goes out
Liquid mouth；Circulating device 2 includes the 3rd inlet and the 3rd liquid outlet, and wherein the 3rd inlet is connected to the second of heat-exchange device
Liquid outlet, the 3rd liquid outlet is connected to the first inlet of chiller；And the interface channel being connected between said apparatus.
Circulating cooling liquid it is provided with in described interface channel.Described cooling liquid includes water, ethylene glycol solution and/or silicon
The organic or inorganic solution such as acid salt solution.
For internal combustion engine this kind of for electromotor, the heat that fuel combustion produces, about 20%-30% is converted into mechanical energy,
Exporting machinery by engine shaft, the energy of 70%-80% is converted into heat energy, wherein the heat energy of 30%-40% with tail gas from aerofluxus
Bank of tubes goes out, and the heat radiation of cooling system is supported on about the 30% of fuel gross calorific value, and in engine working process, cylinder is main heat
Source, is also the intended heat position of cooling system.
For ensureing the heat radiation of electromotor multiple cylinder uniformly, the framework in cooling system water route must have specific aim, this practicality
Novel cooling system uses parallel, and each cylinder arranges a chiller, a corresponding branch road；Cooling work liquid is by doing
Road flows to after each branch road completes heat exchange, branch road be pooled to main line, then through over-heat-exchanger 3, complete heat loss through convection, whole system
Unite and carried out pumping pressure by circulating pump 2, maintain coolant circulation.
Alternately, it would however also be possible to employ multiple heat exchangers, at this moment, each heat exchanger is arranged in and engine air
On each branch road that cylinder is corresponding, the quantity of heat exchanger is identical with the number of cylinders of electromotor.
The small-sized aviation piston engine sold in the market, is commonly used to fixed-wing unmanned plane, its radiator structure
Put down for fixed-wing and fly operating condition design, be characterized in that fin area is little, heat exchange Air Quantity Required is big.Be applied to many rotors without
Time man-machine, owing to many rotor wing unmanned aerial vehicles wind speed is low, electromotor is the best by the air-cooled radiating effect that carries out, therefore, and this utility model
The water-cooling means used, need to carry out the air cooling engine on market the transformation of necessity.By air-cooled cylinder
The fin in outside replaces with cylinder liner.The part heat sink outside electromotor is removed, by cylinder sleeve with remaining by processing
Fin uses seal means to stick together, it is ensured that cylinder sleeve is intact except liquid in-out mouth external seal.
Cooling work liquid carries out sufficient heat exchange with cylinder outer wall in cylinder liner 11,12, is guided by interface channel
Hot-fluid flows to heat-exchange device 3, is back to cylinder liner 11,12 through filter 4 and enters after heat-exchange device 3 completes forced convertion
Row recuperated cycle next time.
As in figure 2 it is shown, cylinder liner 11 and cylinder liner 12 are positioned at outside cylinder, with cylinder fin
Connecting, seam takes the seal means of necessity, such as, bind, welding etc. so that it is anti-pressure ability is not less than 5 atmospheric pressure.Cylinder
It is provided with inlet 101, liquid outlet 102 outside cylinder sleeve 11, is provided with inlet, liquid outlet outside cylinder liner 12 respectively with passage even
Connect.Described cylinder sleeve 11 and 12 is annular solid, and the spark plug of described electromotor exposes in the middle part of annular solid.
As another alternative, described chiller can also be disposed on the coil pipe between engine radiating fin.
Embodiment two:
On the basis of embodiment before, heat-exchange device is designed by present embodiment further.
As it is shown on figure 3, heat-exchange device 3 is positioned at below the cantilever beam below unmanned plane rotor, including liquid storage container, pipeline
With folding aluminium foil heat radiation row, heat radiation row's use folds aluminium foil and carrys out increasing heat radiation area, undertakes system radiating load, cooling work liquid
Row sufficient heat exchange is discharged into by pipeline and aluminum.
Heat exchanger one end is respectively equipped with inlet 301, liquid outlet 302.Under heat exchanger utilizes rotor wing rotation to produce
Gas washing stream carries out forced convertion, will reach preferable radiating effect, and forced convertion wind speed should be not less than 8m/s through over-heat-exchanger.
Described heat-exchange device also includes first control device；Described first control device includes the first temperature sensing unit
73, the second temperature sensing unit 74, first threshold comparing unit and the first alarm unit, see shown in Fig. 4, Fig. 5.
Described first temperature sensing unit 73, is arranged on the inlet 301 of described heat-exchange device, is used for measuring heat exchange
The coolant temperature of device import；Described second temperature sensing unit 74, is arranged on the liquid outlet 302 of described heat-exchange device,
For measuring the coolant temperature of heat-exchange device outlet.
Described first threshold comparing unit, the temperature measuring the first temperature sensing unit and the second temperature sensing unit is entered
Row compares, and when cooling system normally works, liquid outlet 302 temperature should be significantly lower than inlet 301 temperature.Therefore, when first
When the temperature difference that the temperature that temperature sensing unit gathers and the second temperature sensing unit gather is less than first threshold, send first
Control signal；Described first alarm unit, after receiving the first control signal that first threshold comparing unit sends, sends report
Alert signal, alarm signal can use optical signal, acoustical signal or the signal of telecommunication etc. as alarm signal.
Embodiment three:
On the basis of embodiment before, circulating device is designed by present embodiment further.Described circulation dress
Put and include circulating pump 2 and liquid storage container 5, and second control device.Described second control device include pressure sensitive unit 10,
Second Threshold comparing unit and switch element 6, see shown in Fig. 4, Fig. 5.
Described pressure sensitive unit, the pressure in measuring the second liquid storage container, can be such as Pressure gauge equal pressure
Measuring mechanism；Described Second Threshold comparing unit, when the pressure that the first pressure sensitive unit is measured exceedes Second Threshold, sends out
Go out the second control signal；Described switch element 6, can be such as valve 6, when receive that Second Threshold comparing unit sends
During two control signals, Open valve so that the second liquid storage container and atmosphere, discharge pressure.This allows for system at pressure
Valve can be triggered time excessive, ensure security of system to air release pressure.By valve 6, also cooling can be injected to liquid storage container 5
Working solution.
Preferably, circulating pump 2 and liquid storage container 5 can use unitary design, for meeting the demand of abundant heat exchange, and circulation
The flow of pump 2 should be not less than the minimum discharge required by engine radiating load, generally, for being applied to the little of unmanned plane
Type aviation piston engine, different according to discharge capacity, its scope is at 300L/h-2500L/h.
Additionally, system has the function of overtemperature protection, i.e. before cooling work liquid exhausts, it is ensured that cylinder will not
It is overheated to produce；Specifically, described chiller also includes the 3rd control device, and the described 3rd controls device includes the 3rd temperature
Sensing unit 71 and the 72, the 3rd threshold value comparing unit and the second alarm unit.
Temperature sensing unit 71,72, is arranged on the first liquid outlet of described chiller 11,12, is used for measuring cooling dress
Put the chilled liquid temperature of 11,12 outlets.3rd threshold value comparing unit, the temperature value measured when temperature sensing unit 71,72 surpasses
Cross the 3rd threshold value (when such as 120 DEG C), send the 3rd control signal.Second alarm unit, when receiving, the 3rd threshold ratio is more single
After the 3rd control signal that unit sends, send alarm signal.
Additionally, cooling system also includes filter 4, regulate the assemblies such as valve 81,82,91,92.
This utility model devises efficient small-size water-cooling system, solves small-sized aviation piston engine heat dissipation problem.Its
Weight is little, and heat radiation power is high, promotes unmanned plane reliability, stability and cruising time.Owing to have employed cladding cylinder
Cylinder sleeve, cooling work liquid directly contacts with cylinder, high efficient heat exchanging.Additionally, utilize rotor downwash forced convertion aluminum row to change
Hot device, instead of Special heat dissipating blower fan, improves overall efficiency.
Embodiment described above is only preferred implementation of the present utility model, not enters scope of the present utility model
Row limits, and on the premise of without departing from this utility model design spirit, those of ordinary skill in the art are to skill of the present utility model
Various deformation that art scheme is made and improvement, all should fall in the protection domain that claims of the present utility model determine.
Claims (10)
1. the cooling system of a multi-rotor aerocraft electromotor, it is characterised in that including:
Chiller: include the first inlet and the first liquid outlet；
Heat-exchange device: include the second inlet and the second liquid outlet；
Circulating device: include the 3rd inlet and the 3rd liquid outlet；
And the interface channel being connected between said apparatus, it is provided with circulating cooling liquid in described interface channel；
Described interface channel includes main line and at least two parallel branch, and each branch road includes a described chiller, respectively
For cooling down the difference cylinder of electromotor.
2. cooling system as claimed in claim 1, it is characterised in that:
Described chiller includes the cylinder sleeve being arranged at outside cylinder.
3. cooling system as claimed in claim 2, it is characterised in that:
Described electromotor is removed the transformation of at least part of fin by air cooling engine and forms；
Described cylinder sleeve is installed on outside the body of the electromotor after removing fin；
And cylinder sleeve and remaining fin use seal means to combine.
4. cooling system as claimed in claim 2, it is characterised in that:
Described cylinder sleeve is annular solid, and the spark plug of described electromotor exposes in the middle part of annular solid.
5. cooling system as claimed in claim 1, it is characterised in that:
Described chiller includes the coil pipe being arranged between engine radiating fin.
6. the cooling system as described in any one of claim 1-5, it is characterised in that:
Described heat-exchange device is arranged on below the rotor support arm beam of aircraft, and the wind-force produced by rotor is to heat-exchange device
Dispel the heat.
7. cooling system as claimed in claim 6, it is characterised in that:
The main line of interface channel arranges described heat-exchange device；
Or, every branch road of interface channel arranges a described heat-exchange device.
8. cooling system as claimed in claim 1, it is characterised in that:
Described heat-exchange device includes the first liquid storage container, folds aluminium foil heat radiation row, and first control device；
Described first control device include the first temperature sensing unit, the second temperature sensing unit, first threshold comparing unit and
First alarm unit；
Described first temperature sensing unit, is arranged on the second inlet of described heat-exchange device, is used for measuring heat-exchange device
The coolant temperature of entrance；
Described second temperature sensing unit, is arranged on the second liquid outlet of described heat-exchange device, is used for measuring heat-exchange device
The coolant temperature of outlet；
Described first threshold comparing unit, the temperature measuring the first temperature sensing unit and the second temperature sensing unit compares
Relatively, when the temperature of the first temperature sensing unit collection and the temperature difference of the second temperature sensing unit collection are less than first threshold
Time, send the first control signal；
Described first alarm unit, after receiving the first control signal that first threshold comparing unit sends, sends alarm signal
Number.
9. cooling system as claimed in claim 8, it is characterised in that:
Described circulating device includes circulating pump and the second liquid storage container, and second control device；
Described second control device includes the first pressure sensitive unit, Second Threshold comparing unit and the first switch element；
Described first pressure sensitive unit, the pressure in measuring the second liquid storage container；
Described Second Threshold comparing unit, when the pressure that the first pressure sensitive unit is measured exceedes Second Threshold, sends second
Control signal；
Described first switch element, when receiving the second control signal that Second Threshold comparing unit sends, opens switch, makes
Obtain the second liquid storage container and atmosphere, discharge pressure.
10. cooling system as claimed in claim 8, it is characterised in that:
Described chiller also include the 3rd control device, described 3rd control device include the 3rd temperature sensing unit, the 3rd
Threshold value comparing unit and the second alarm unit:
3rd temperature sensing unit, is arranged on the first liquid outlet of described chiller, for measuring the cold of chiller outlet
But temperature of liquid；
3rd threshold value comparing unit, when the temperature value that the 3rd temperature sensing unit is measured is more than three threshold values, sends the 3rd control
Signal processed；
Second alarm unit, after receiving the 3rd control signal that the 3rd threshold value comparing unit sends, sends alarm signal.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201620476179.2U CN205805678U (en) | 2016-05-24 | 2016-05-24 | A kind of cooling system of multi-rotor aerocraft electromotor |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201620476179.2U CN205805678U (en) | 2016-05-24 | 2016-05-24 | A kind of cooling system of multi-rotor aerocraft electromotor |
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| Publication Number | Publication Date |
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| CN205805678U true CN205805678U (en) | 2016-12-14 |
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| CN201620476179.2U Active CN205805678U (en) | 2016-05-24 | 2016-05-24 | A kind of cooling system of multi-rotor aerocraft electromotor |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105781703A (en) * | 2016-05-24 | 2016-07-20 | 北京浩恒征途航空科技有限公司 | Cooling system for engine of multi-rotor aircraft |
| CN109896047A (en) * | 2019-04-03 | 2019-06-18 | 西安飞机工业（集团）有限责任公司 | A kind of aircraft flap slat PDU execution unit protective housing |
-
2016
- 2016-05-24 CN CN201620476179.2U patent/CN205805678U/en active Active
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105781703A (en) * | 2016-05-24 | 2016-07-20 | 北京浩恒征途航空科技有限公司 | Cooling system for engine of multi-rotor aircraft |
| CN109896047A (en) * | 2019-04-03 | 2019-06-18 | 西安飞机工业（集团）有限责任公司 | A kind of aircraft flap slat PDU execution unit protective housing |
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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 |
Effective date of registration: 20180525 Address after: 100080 2106-030, 9 North Fourth Ring Road, Haidian District, Beijing. Co-patentee after: BEIJING GUOZHICHUANGTOU TECHNOLOGY CO., LTD. Patentee after: The fast online Science and Technology Ltd. in Beijing three Address before: 100191 Beijing Haidian District Haidian Avenue 3 1 1 10 story 1001-52 Co-patentee before: BEIJING GUOZHICHUANGTOU TECHNOLOGY CO., LTD. Patentee before: BEIJING HAOHENG JOURNEY AVIATION TECHNOLOGY CO., LTD. |
|
| TR01 | Transfer of patent right |