CN207106918U - A kind of unmanned plane battery compartment cooling device - Google Patents
A kind of unmanned plane battery compartment cooling device Download PDFInfo
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- CN207106918U CN207106918U CN201721146753.9U CN201721146753U CN207106918U CN 207106918 U CN207106918 U CN 207106918U CN 201721146753 U CN201721146753 U CN 201721146753U CN 207106918 U CN207106918 U CN 207106918U
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- battery compartment
- engine
- cooling water
- unmanned plane
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- 238000001816 cooling Methods 0.000 title claims abstract description 48
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 claims abstract description 166
- 239000000498 cooling water Substances 0.000 claims abstract description 76
- 125000004122 cyclic group Chemical group 0.000 claims abstract description 30
- 239000002826 coolant Substances 0.000 claims abstract description 20
- RYGMFSIKBFXOCR-UHFFFAOYSA-N Copper Chemical compound [Cu] RYGMFSIKBFXOCR-UHFFFAOYSA-N 0.000 claims description 4
- 229910052802 copper Inorganic materials 0.000 claims description 4
- 239000010949 copper Substances 0.000 claims description 4
- WHXSMMKQMYFTQS-UHFFFAOYSA-N Lithium Chemical compound [Li] WHXSMMKQMYFTQS-UHFFFAOYSA-N 0.000 description 10
- 229910052744 lithium Inorganic materials 0.000 description 10
- 230000000694 effects Effects 0.000 description 8
- 238000009434 installation Methods 0.000 description 7
- 239000000463 material Substances 0.000 description 5
- BQCADISMDOOEFD-UHFFFAOYSA-N Silver Chemical compound [Ag] BQCADISMDOOEFD-UHFFFAOYSA-N 0.000 description 4
- 229910052709 silver Inorganic materials 0.000 description 4
- 239000004332 silver Substances 0.000 description 4
- 230000008901 benefit Effects 0.000 description 3
- 238000010586 diagram Methods 0.000 description 3
- 230000008450 motivation Effects 0.000 description 3
- 239000006185 dispersion Substances 0.000 description 2
- 230000017525 heat dissipation Effects 0.000 description 2
- 238000000034 method Methods 0.000 description 2
- 229910000831 Steel Inorganic materials 0.000 description 1
- 230000002411 adverse Effects 0.000 description 1
- 230000032683 aging Effects 0.000 description 1
- 239000004411 aluminium Substances 0.000 description 1
- XAGFODPZIPBFFR-UHFFFAOYSA-N aluminium Chemical compound [Al] XAGFODPZIPBFFR-UHFFFAOYSA-N 0.000 description 1
- 229910052782 aluminium Inorganic materials 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000005540 biological transmission Effects 0.000 description 1
- 238000007664 blowing Methods 0.000 description 1
- 210000000476 body water Anatomy 0.000 description 1
- 230000008859 change Effects 0.000 description 1
- 238000006243 chemical reaction Methods 0.000 description 1
- 238000010276 construction Methods 0.000 description 1
- 235000019628 coolness Nutrition 0.000 description 1
- 230000007812 deficiency Effects 0.000 description 1
- 235000013399 edible fruits Nutrition 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 238000010438 heat treatment Methods 0.000 description 1
- 239000007788 liquid Substances 0.000 description 1
- 230000007246 mechanism Effects 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000008569 process Effects 0.000 description 1
- 230000005855 radiation Effects 0.000 description 1
- 239000010959 steel Substances 0.000 description 1
- 238000006467 substitution reaction Methods 0.000 description 1
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- Cooling, Air Intake And Gas Exhaust, And Fuel Tank Arrangements In Propulsion Units (AREA)
Abstract
The utility model discloses a kind of unmanned plane battery compartment cooling device, including multi-rotor unmanned aerial vehicle body, engine is provided with propeller, water storage box is provided with the fuselage of multi-rotor unmanned aerial vehicle body, water storage box is provided with coolant intake and cooling water outlet mouth, and the cooling water outlet mouth of water storage box is provided with suction pump；Engine cooling water cyclic water jacket is provided with the outside of engine, suction pump is connected by water inlet pipe with the water inlet of engine cooling water cyclic water jacket, and the delivery port of engine cooling water cyclic water jacket is connected by outlet pipe with the coolant intake on water storage box；Outlet pipe is provided with radiator, and radiator is arranged on the top surface of rotor arm；Battery compartment cooling water circulation water jacket is provided with the outside of battery compartment, suction pump cools down water inlet pipe by battery compartment and is connected with the entrance of battery compartment cooling water circulation water jacket, and the outlet of battery compartment cooling water circulation water jacket is connected by the radiating water inlet pipe mouth of battery compartment cooling water outlet pipe and radiator.
Description
Technical field
It the utility model is related to a kind of unmanned air vehicle technique field, and in particular to a kind of unmanned plane battery compartment cooling device.
Background technology
In recent years, multi-rotor unmanned aerial vehicle develops rapidly, simple in construction with its flight stability, the features such as being easy to manipulate, is navigating
The fields such as aerial survey, scouting, exploration, logistics, plant protection are clapped to be widely used.Using the multi-rotor unmanned aerial vehicle of electric motor
Short slab of the multi-rotor unmanned aerial vehicle in terms of continuing a journey with load-carrying is breached, opens multi-rotor unmanned aerial vehicle broader practice prospect.
In the course of the work, particularly loading capacity is big for the existing multi-rotor unmanned aerial vehicle with the multiple rotors of engine driving
Unmanned plane, the operating of its high engine speeds can produce amount of heat, only can not carry out sufficient natural wind with the high-speed mobile of body
It is cold, it such as can not timely and effectively radiate, easily make engine overheat and break down, or even cause the pendant of multi-rotor unmanned aerial vehicle
Ruin, produce huge economic loss.
Therefore, in order to obtain good radiating effect, it usually needs install complicated cooling system additional for engine, not only increase
The unnecessary heavy burden of unmanned plane is added, has reduced the efficiency of unmanned plane, reduced unmanned plane cruising time, and safeguarded very not
Just.
And in existing multi-rotor unmanned aerial vehicle structure rotor arm be mainly designed to rotor is installed, rotor arm generally passes through
Canalis pterygoideus is connected with fuselage, has certain length, and the transmission mechanism of each rotor is each independently arranged in corresponding rotor arm.
But the space at this design rotor arm is not utilized completely, only serves the effect of support rotor.
Meanwhile the engine of multi-rotor unmanned aerial vehicle is mainly used as power source by lithium battery, battery is in discharge process
Caused heat is also more and more, but battery needs could have an optimal performance and longer within the scope of certain temperature
Service life, and when battery temperature oversteps the extreme limit, a reaction chain can be created and destroy battery, short circuit is caused, so as to trigger
Fire or blast, so inevitably needing to cool down in some usage scenarios of battery, avoid producing because battery temperature is too high
Raw adverse effect.
The aging speed of lithium battery is determined by temperature and charged state.If lithium battery is in too high or too low ring
Border is all unfavorable for its performance.
Utility model content
The purpose of this utility model is to overcome prior art deficiency, and it is an object of the present invention to provide a kind of unmanned plane battery compartment is cold
But device, solves the power-supply battery cooling problem of unmanned plane.
The utility model is achieved through the following technical solutions：
A kind of unmanned plane battery compartment cooling device, including multi-rotor unmanned aerial vehicle body, the multi-rotor unmanned aerial vehicle body bag
Fuselage, rotor arm, engine and battery compartment are included, the engine is provided with propeller, the machine of the multi-rotor unmanned aerial vehicle body
Water storage box is provided with body, the water storage box is provided with coolant intake and cooling water outlet mouth, the cooling water outlet mouth of the water storage box
It is provided with suction pump；
Engine cooling water cyclic water jacket is provided with the outside of the engine, the suction pump is cold with engine by water inlet pipe
But the water inlet connection of water circulation water jacket, the delivery port of the engine cooling water cyclic water jacket pass through on outlet pipe and water storage box
Coolant intake connection；The outlet pipe is provided with radiator, and the radiator is arranged on the top surface of rotor arm；
Battery compartment cooling water circulation water jacket is provided with the outside of the battery compartment, the suction pump cools down water inlet pipe by battery compartment
It is connected with the entrance of battery compartment cooling water circulation water jacket, the outlet of the battery compartment cooling water circulation water jacket is cooled down by battery compartment
The radiating water inlet pipe mouth of outlet pipe and radiator connects.
Further, the radiator is embedded in above rotor arm, and the radiator is arranged on below propeller simultaneously.
Further, the delivery port is arranged on the upper end of engine cooling water cyclic water jacket；The water inlet is arranged on
The lower end of engine cooling water cyclic water jacket.
Further, engine cooling water cyclic water jacket and battery compartment the cooling water circulation water jacket is that helix tube is copper
Road structure.
Further, temperature monitor is provided with the battery compartment, the temperature monitor passes through controller and suction pump
Control connection.
Further, the pipeline between the radiator and delivery port is provided with three-way control valve, the three-way control valve
It is connected by circulating hot water pipe with the entrance of battery compartment cooling water circulation water jacket, the three-way control valve connects with controller control
Connect.
Further, the battery compartment cooling water inlet pipe is provided with control valve, and the control valve connects with controller control.
Further, the coolant intake is arranged on the upper end of water storage box.
Further, the cooling water outlet mouth is arranged on the lower end of water storage box.
Further, the radiator includes water inlet supervisor, water outlet main pipe and fin, the water inlet supervisor and water outlet master
Connected between pipe by more than one piece fin, the outside of the water inlet supervisor is provided with radiating water inlet pipe mouth, the water outlet main pipe outside
Provided with radiating effluent pipe mouth, the water inlet supervisor is the camber structure that is engaged with rotor arm profile with water outlet main pipe.
The utility model compared with prior art, has the following advantages and advantages：
1st, a kind of unmanned plane battery compartment cooling device of the utility model, because all comparing for unmanned plane total design is tight
To gather, structure is relatively small, thus it is relatively short to engine radiating water cooling pipeline, according to the characteristic of multi-rotor unmanned aerial vehicle, more
In rotor wing unmanned aerial vehicle flight course, the propeller of multi-rotor unmanned aerial vehicle, which must produce, to be vortexed downwards distinguished and admirable, passes through distinguished and admirable make that be vortexed
Unmanned plane during flying, so can effectively utilize propeller caused air-flow downwards in the radiating to engine, pass through propeller
Air-flow caused by downwards radiates to the radiator being arranged on above rotor arm, can effectively improve the radiating effect of radiator
Rate, so as to reduce the radiator structure of radiator；
2nd, a kind of unmanned plane battery compartment cooling device of the utility model, the design of above-mentioned disengaging coolant mouth, mainly it is
Increase is to the effect of engine, for example, delivery port is arranged on the upper end of engine cooling water cyclic water jacket.Water inlet is arranged on
The lower end of engine cooling water cyclic water jacket.Engine cooling water cyclic water jacket is helical pipe structure.Engine cooling water follows
Ring water jacket be helical pipe can will be entirely as in engine cooling water cyclic water jacket, during design, engine cool water circulation
Water jacket is embedded in the installation set of engine, and the helical pipe disk of engine cooling water cyclic water jacket is located in installation set, no
The structural strength of installation set can be influenceed；
3rd, a kind of unmanned plane battery compartment cooling device of the utility model, relatively simple for structure, the radiating effect of whole radiator
Fruit is good, in order to improve the heat dispersion of fin, is preferably provided with floating-point in the part on rotor arm surface exposed, scattered so as to increase
Hot area, because the cooling circuit of whole unmanned plane is relatively short, 90% heat needs to complete by radiator heat-dissipation；
4th, a kind of unmanned plane battery compartment cooling device of the utility model, by being followed on engine and battery compartment provided with cooling
Loop system, engine and battery compartment can be cooled down simultaneously, so as to ensure the work safety of engine and power-supply battery；
5th, a kind of unmanned plane battery compartment cooling device of the utility model, the lithium battery requirement in battery compartment are held in one
There could be good service behaviour in temperature range, in the environment of cold, battery compartment is avoided the need for being cooled down, also needed on the contrary
Heat and ensure lithium battery operating temperature, and engine can continue to produce heat, in order to rationally save and effectively utilize energy, this
Invention will be incorporated into battery compartment to the high temperature coolant after engine cool, so as to ensure that battery compartment at low ambient temperatures
Optimum working temperature can be kept to require.
Brief description of the drawings
Accompanying drawing described herein is used for providing further understanding the utility model embodiment, forms the one of the application
Part, the restriction to the utility model embodiment is not formed.In the accompanying drawings：
Fig. 1 is a kind of overlooking the structure diagram of unmanned plane battery compartment cooling device of the utility model；
Fig. 2 is a kind of main structure diagram of unmanned plane battery compartment cooling device of the utility model；
Fig. 3 is the theory structure schematic diagram of the utility model water-cooling system control；
Fig. 4 is the structural representation of the utility model radiator；
Mark and corresponding parts title in accompanying drawing：
1- multi-rotor unmanned aerial vehicle bodies, 2- fuselages, 3- rotor arms, 4- engines, 5- propellers, 6- water storage boxes, 7- coolings
Water inlet, 8- cooling water outlet mouths, 9- suction pumps, 10- engine cooling water cyclic water jackets, 11- water inlet pipes, 12- water inlets, 13-
Delivery port, 14- outlet pipes, 15- radiators, 16- temperature monitors, 17- controllers, 18- water inlet supervisors, 19- water outlet main pipes,
20- fin, 21- radiating water inlet pipe mouths, 22- radiating effluent pipe mouths, 23- battery compartments, 24- battery compartment cooling water circulation water jackets,
25- battery compartments cool down water inlet pipe, and 26- is exported, 27- battery compartment cooling water outlet pipes, 28- three-way control valves, 29- circulating hot water pipes,
30- control valves, 31- entrances.
Embodiment
For the purpose of this utility model, technical scheme and advantage is more clearly understood, with reference to embodiment and accompanying drawing,
The utility model is described in further detail, and exemplary embodiment of the present utility model and its explanation are only used for explaining this
Utility model, it is not intended as to restriction of the present utility model.
Embodiment 1
As Figure 1-4, a kind of unmanned plane battery compartment cooling device of the utility model, a kind of unmanned plane battery compartment cooling dress
Put, including multi-rotor unmanned aerial vehicle body 1, the multi-rotor unmanned aerial vehicle body 1 include fuselage 2, rotor arm 3, engine 4 and battery
Storehouse 23, multi-rotor unmanned aerial vehicle body 1 is identical with existing multi-rotor unmanned aerial vehicle structure, and the present invention can be in load-carrying more than 50 kilograms
Used in the multi-rotor unmanned aerial vehicle of (unmanned plane less than 50 kilograms of load-carrying can be realized by engine self-radiating), or existing
Improve and realize in multi-rotor unmanned aerial vehicle of some load-carryings more than 50 kilograms, engine 4 is provided with propeller 5, it is characterised in that：Institute
State and water storage box 6 is provided with the fuselage 2 of multi-rotor unmanned aerial vehicle body 1, the water storage box 6 is provided with coolant intake 7 and cooled down out
The mouth of a river 8, the cooling water outlet mouth 8 of the water storage box 6 are provided with suction pump 9；Coolant intake 7 is arranged on the upper end of water storage box 6.It is cold
But delivery port 8 is arranged on the lower end of water storage box 6.The design of above-mentioned disengaging coolant mouth, primarily to increase is to engine 4
Effect, for example, delivery port 13 is arranged on the upper end of engine cooling water cyclic water jacket 10.Water inlet 12 is arranged on engine cool
The lower end of water circulation water jacket 10.
The outside of engine 4 is provided with engine cooling water cyclic water jacket 10, and the suction pump 9 passes through water inlet pipe 11 and hair
The water inlet 12 of motivation cooling water circulation water jacket 10 connects, and the delivery port 13 of the engine cooling water cyclic water jacket 10 is by going out
Water pipe 14 connects with the coolant intake 7 on water storage box 6；The outlet pipe 14 is provided with radiator 15, and the radiator 15 is set
Put the top surface in rotor arm 3.
According to the structure of multi-rotor unmanned aerial vehicle in itself, need to set the water-cooling system of engine 4 on each rotor, each start
The water-cooling system of machine 4 is collected on water storage box 6, and water cooling is synchronously realized by a can of suction pump 9.Only need to be by suction pump 9
Delivery port is arranged to multiple, is connected respectively with each rotation water-cooling system of wing engine 4.
The outside of battery compartment 23 is provided with battery compartment cooling water circulation water jacket 24, and the suction pump 9 is cooled down by battery compartment
Water inlet pipe 25 is connected with the entrance 31 of battery compartment cooling water circulation water jacket 24, the outlet of the battery compartment cooling water circulation water jacket 24
26 are connected by battery compartment cooling water outlet pipe 27 with the radiating water inlet pipe mouth 21 of radiator 15.
While being cooled down to engine 4, battery compartment 23 can also be cooled down.
Radiator 15 is embedded in above rotor arm 3, and the radiator 15 is arranged on below propeller 5 simultaneously.
Due to unmanned plane total design it is all compact, structure is relatively small, thus to engine 4 radiate water cooling
Pipeline is relatively short, according to the characteristic of multi-rotor unmanned aerial vehicle, in multi-rotor unmanned aerial vehicle flight course, the spiral shell of multi-rotor unmanned aerial vehicle
Rotation oar 5 must produce be vortexed downwards it is distinguished and admirable, by be vortexed it is distinguished and admirable make unmanned plane during flying, so can in the radiating to engine 4
Effectively to utilize the caused air-flow downwards of propeller 5, by propeller 5 downwards caused air-flow to being arranged on above rotor arm 3
Radiator 15 radiated, the radiating efficiency of radiator 15 can be effectively improved, so as to reduce the radiating of radiator 15
Structure.
In design, there is relevance in water storage box 6, radiator 15 and unmanned plane load-carrying, in order to not influence nobody load-carrying
It is required that water storage box 6 is tried one's best and designs smaller, so as to reduce the deadweight of unmanned plane, but 6 too small recirculated water of water storage box is again not
Cooling requirements can be realized, because the cooling circuit of whole unmanned plane is relatively short, 90% heat needs to dissipate by radiator 15
Heat is completed, so in design, ensureing that water storage box 6 is as far as possible small, radiator 15 is as far as possible big, because the size of propeller 5 is limited, by
Mainly radiated in the radiating of radiator 15 by the blowing of propeller 5, the radiator 15 will be arranged on the wind of propeller 5 covering
Rotor arm 3 on.
A kind of unmanned plane battery compartment cooling device of the utility model, by being provided with cooling circulation on engine and battery compartment
System, engine and battery compartment can be cooled down simultaneously, so as to ensure the work safety of engine and power-supply battery.
Embodiment 2
As Figure 1-4, a kind of unmanned plane battery compartment cooling device of the utility model, on the basis of embodiment 1, water outlet
Mouth 13 is arranged on the upper end of engine cooling water cyclic water jacket 10；The water inlet 12 is arranged on engine cooling water cyclic water jacket
10 lower end.
Engine cooling water cyclic water jacket 10 and battery compartment cooling water circulation water jacket 24 are the copper road structure of helix tube.Hair
Motivation cooling water circulation water jacket 10 and battery compartment cooling water circulation water jacket 24 are helical pipe, will can entirely be placed in engine
In cooling water circulation water jacket 10, while also whole battery compartment 23 is placed in battery compartment cooling water circulation water jacket 24, during design, hair
Motivation cooling water circulation water jacket 10 is embedded in the installation set of engine 4, the helix tube of engine cooling water cyclic water jacket 10
Road disk is located in installation set, does not interfere with the structural strength of installation set.Battery compartment cooling water circulation water jacket 24 is embedded in battery compartment
In 23 housings, the structural strength of installation set is not interfered with yet.
Delivery port 13 is arranged on the upper end of engine cooling water cyclic water jacket 10.Water inlet 12 is arranged on engine cooling water
The lower end of cyclic water jacket 10.By upruss under recirculated water, coolant can be made fully to be handed over heat caused by engine 4
Change, be easy to improve radiating efficiency.
Embodiment 3
As Figure 1-4, a kind of unmanned plane battery compartment cooling device of the utility model, on the basis of embodiment 1,
Temperature monitor 16 is provided with battery compartment, the temperature monitor 16 is connected by controller 17 and the control of suction pump 9
Connect.Controller 17 uses model:SSZD-SUN60 control chips are realized.
Pipeline between radiator 15 and delivery port 13 is provided with three-way control valve 28, and the three-way control valve 28 is by following
Ring hot-water line 29 is connected with the entrance 31 of battery compartment cooling water circulation water jacket 24, and the three-way control valve 28 controls with controller 17
Connection.
Battery compartment cooling water inlet pipe 25 is provided with control valve 30, and the control valve 30 connects with the control of controller 17.
Lithium battery requirement in battery compartment, which is held in a temperature range, could have good service behaviour, cold
Cold environment, battery compartment are avoided the need for being cooled down, and also need to heating on the contrary and ensure lithium battery operating temperature, and engine can be held
Continuous to produce heat, in order to rationally save and effectively utilize energy, the present invention will introduce to the high temperature coolant after engine cool
Into battery compartment, so as to ensure that battery compartment can also keep optimum working temperature to require at low ambient temperatures.
By the technical scheme of the present embodiment, a kind of unmanned plane battery compartment cooling device of the utility model, according to unmanned plane
Flight environment of vehicle, cold space flight, if lithium battery can pass through the cooling system of itself effectively control caused by heat
Amount, the safe operation of lithium battery is not influenceed, lithium battery avoids the need for using cooling system, or reduces the circulation speed of coolant
Degree, above-mentioned control is all to realize control by controller 17 by temperature monitor 16, and controller 17 is according to temperature monitor
16 detect the temperature of battery compartment 23, so as to come control suction pump 9 aspirate coolant amount.
When temperature monitor 16 detects that the environment temperature of battery compartment 23 is less than job requirement temperature, stop temperature after cooling
Degree is also unable to reach when requiring temperature, and controller 17 can control three-way control valve 28, make in engine cooling water cyclic water jacket 10
Liquid cooled heat not inflow radiator 15, and pass through the entrance that circulating hot water pipe 29 enters battery compartment cooling water circulation water jacket 24
31, what it is hence into battery compartment cooling water circulation water jacket 24 is exactly heated coolant.Meanwhile controller 17 can control
Valve 30 processed is closed, and suction pump 9 can not be supplied coolant to battery compartment cooling water circulation water jacket 24.
Embodiment 4
As Figure 1-3, a kind of unmanned plane battery compartment cooling device of the utility model, on the basis of embodiment 1, radiating
Device 15 includes water inlet supervisor 18, water outlet main pipe 19 and fin 20, by more between the water inlet supervisor 18 and water outlet main pipe 19
Part fin 20 connects, and the outside of the water inlet supervisor 18 is provided with radiating water inlet pipe mouth 21, and the outside of water outlet main pipe 19 is provided with
Radiated effluent pipe mouth 22, and radiating water inlet pipe mouth 21 and radiating effluent pipe mouth 22 are connected respectively on the loop of outlet pipe 14,
The fin 20 is made of silver material；Fin material refers to specific material used in fin.Every kind of material its
Heat conductivility is different, is arranged from high to low by heat conductivility, be respectively silver, copper, aluminium, steel.But if dissipated with silver
Backing may be too expensive, but due to its good thermal diffusivity, and because the structure of fin 20 used on radiator 15 is fewer,
In order to ensure the safe to use of unmanned plane, it is made in design or using silver material, water inlet supervisor 18 is equal with water outlet main pipe 19
For the camber structure being engaged with the profile of rotor arm 3.
Fin 20 is that list structure is easy to be embedded in rotor arm 3, in order that the structure of whole radiator 15 is non-bulging
The outer surface of rotor arm 3, it otherwise can increase the flight resistance of unmanned plane, so water inlet supervisor 18 with water outlet main pipe 19 to be and revolve
The camber structure that the profile of wing arm 3 is engaged.So water inlet supervisor 18 can also be set with water outlet main pipe 19 is embedded in rotor arm 3
It is interior.Relatively simple for structure, the good heat dissipation effect of whole radiator 15, in order to improve the heat dispersion of fin 20, preferably naked
The part for being exposed at the surface of rotor arm 3 is provided with floating-point, so as to increasing heat radiation area, due to whole unmanned plane cooling circuit relatively
Short, 90% heat, which needs to radiate by radiator 15, to be completed.
Above-described embodiment, the purpose of the present invention, technical scheme and beneficial effect are carried out further
Describe in detail, should be understood that the embodiment that the foregoing is only the present invention, be not intended to limit the present invention
Protection domain, within the spirit and principles of the invention, any modification, equivalent substitution and improvements done etc., all should include
Within protection scope of the present invention.
Claims (10)
1. a kind of unmanned plane battery compartment cooling device, including multi-rotor unmanned aerial vehicle body (1), the multi-rotor unmanned aerial vehicle body
(1) fuselage (2), rotor arm (3), engine (4) and battery compartment (23) are included, the engine (4) is provided with propeller (5),
It is characterized in that：Water storage box (6) is provided with the fuselage (2) of the multi-rotor unmanned aerial vehicle body (1), is set on the water storage box (6)
There are coolant intake (7) and cooling water outlet mouth (8), the cooling water outlet mouth (8) of the water storage box (6) is provided with suction pump (9)；
Engine cooling water cyclic water jacket (10) is provided with the outside of the engine (4), the suction pump (9) passes through water inlet pipe (11)
It is connected with the water inlet (12) of engine cooling water cyclic water jacket (10), the water outlet of the engine cooling water cyclic water jacket (10)
Mouth (13) is connected by outlet pipe (14) with the coolant intake (7) on water storage box (6)；The outlet pipe (14) is provided with radiating
Device (15), the radiator (15) are arranged on the top surface of rotor arm (3)；
Battery compartment cooling water circulation water jacket (24) is provided with the outside of the battery compartment (23), the suction pump (9) is cold by battery compartment
But water inlet pipe (25) is connected with the entrance (31) of battery compartment cooling water circulation water jacket (24), the battery compartment cooling water circulation water jacket
(24) outlet (26) is connected by battery compartment cooling water outlet pipe (27) with the radiating water inlet pipe mouth (21) of radiator (15).
A kind of 2. unmanned plane battery compartment cooling device according to claim 1, it is characterised in that：Radiator (15) edge
Above rotor arm (3), the radiator (15) while propeller (5) is arranged on below.
A kind of 3. unmanned plane battery compartment cooling device according to claim 1, it is characterised in that：The delivery port (13) sets
Put in the upper end of engine cooling water cyclic water jacket (10)；The water inlet (12) is arranged on engine cooling water cyclic water jacket
(10) lower end.
A kind of 4. unmanned plane battery compartment cooling device according to claim 1, it is characterised in that：The engine cooling water
Cyclic water jacket (10) and battery compartment cooling water circulation water jacket (24) are the copper road structure of helix tube.
A kind of 5. unmanned plane battery compartment cooling device according to claim 1, it is characterised in that：It is provided with the battery compartment
Temperature monitor (16), the temperature monitor (16) are connected by controller (17) and suction pump (9) control.
A kind of 6. unmanned plane battery compartment cooling device according to claim 5, it is characterised in that：The radiator (15) with
Pipeline between delivery port (13) is provided with three-way control valve (28), and the three-way control valve (28) passes through circulating hot water pipe (29)
It is connected with the entrance (31) of battery compartment cooling water circulation water jacket (24), the three-way control valve (28) connects with controller (17) control
Connect.
A kind of 7. unmanned plane battery compartment cooling device according to claim 6, it is characterised in that：The battery compartment cool down into
Water pipe (25) is provided with control valve (30), and the control valve (30) connects with controller (17) control.
A kind of 8. unmanned plane battery compartment cooling device according to claim 1, it is characterised in that：The coolant intake
(7) it is arranged on the upper end of water storage box (6).
A kind of 9. unmanned plane battery compartment cooling device according to claim 1, it is characterised in that：The cooling water outlet mouth
(8) it is arranged on the lower end of water storage box (6).
A kind of 10. unmanned plane battery compartment cooling device according to claim any one of 1-9, it is characterised in that：It is described to dissipate
Hot device (15) includes water inlet supervisor (18), water outlet main pipe (19) and fin (20), the water inlet supervisor (18) and water outlet main pipe
(19) connected between by more than one piece fin (20), the outside of the water inlet supervisor (18) is provided with radiating water inlet pipe mouth (21), institute
State and radiating effluent pipe mouth (22) is provided with the outside of water outlet main pipe (19), the water inlet supervisor (18) with water outlet main pipe (19) is and revolved
The camber structure that wing arm (3) profile is engaged.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201721146753.9U CN207106918U (en) | 2017-09-08 | 2017-09-08 | A kind of unmanned plane battery compartment cooling device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201721146753.9U CN207106918U (en) | 2017-09-08 | 2017-09-08 | A kind of unmanned plane battery compartment cooling device |
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| Publication Number | Publication Date |
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| CN207106918U true CN207106918U (en) | 2018-03-16 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201721146753.9U Expired - Fee Related CN207106918U (en) | 2017-09-08 | 2017-09-08 | A kind of unmanned plane battery compartment cooling device |
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Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108306079A (en) * | 2018-03-29 | 2018-07-20 | 成都纵横大鹏无人机科技有限公司 | Unmanned plane battery thermal device and heat preserving method |
| CN110667864A (en) * | 2019-10-11 | 2020-01-10 | 扬州翊翔航空科技有限公司 | Hybrid power multi-rotor unmanned aerial vehicle water cooling system and application method thereof |
| CN112758312A (en) * | 2020-12-30 | 2021-05-07 | 阿坝师范学院 | Plateau is with many rotor unmanned aerial vehicle |
| CN113165548A (en) * | 2018-12-12 | 2021-07-23 | 威斯克航空有限责任公司 | Battery with liquid temperature control system |
| CN120207628A (en) * | 2025-04-03 | 2025-06-27 | 中国煤炭地质总局勘查研究总院 | A geological disaster monitoring device for coal mining subsidence areas |
-
2017
- 2017-09-08 CN CN201721146753.9U patent/CN207106918U/en not_active Expired - Fee Related
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108306079A (en) * | 2018-03-29 | 2018-07-20 | 成都纵横大鹏无人机科技有限公司 | Unmanned plane battery thermal device and heat preserving method |
| CN108306079B (en) * | 2018-03-29 | 2023-08-11 | 成都纵横大鹏无人机科技有限公司 | Heat preservation device and heat preservation method for unmanned aerial vehicle battery |
| CN113165548A (en) * | 2018-12-12 | 2021-07-23 | 威斯克航空有限责任公司 | Battery with liquid temperature control system |
| CN110667864A (en) * | 2019-10-11 | 2020-01-10 | 扬州翊翔航空科技有限公司 | Hybrid power multi-rotor unmanned aerial vehicle water cooling system and application method thereof |
| CN112758312A (en) * | 2020-12-30 | 2021-05-07 | 阿坝师范学院 | Plateau is with many rotor unmanned aerial vehicle |
| CN120207628A (en) * | 2025-04-03 | 2025-06-27 | 中国煤炭地质总局勘查研究总院 | A geological disaster monitoring device for coal mining subsidence areas |
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