CN211969749U - Unmanned aerial vehicle cabin heat abstractor - Google Patents
Unmanned aerial vehicle cabin heat abstractor Download PDFInfo
- Publication number
- CN211969749U CN211969749U CN202020446462.7U CN202020446462U CN211969749U CN 211969749 U CN211969749 U CN 211969749U CN 202020446462 U CN202020446462 U CN 202020446462U CN 211969749 U CN211969749 U CN 211969749U
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- heat
- cabin
- fin
- heat dissipation
- aerial vehicle
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- 230000017525 heat dissipation Effects 0.000 claims abstract description 67
- 238000004321 preservation Methods 0.000 claims abstract description 31
- 238000001816 cooling Methods 0.000 claims abstract description 10
- 229920001296 polysiloxane Polymers 0.000 claims description 4
- 239000004793 Polystyrene Substances 0.000 claims description 3
- 229920002223 polystyrene Polymers 0.000 claims description 3
- 230000005855 radiation Effects 0.000 abstract description 3
- 230000000694 effects Effects 0.000 description 4
- 238000010586 diagram Methods 0.000 description 3
- 238000000034 method Methods 0.000 description 3
- 230000008569 process Effects 0.000 description 3
- 238000005299 abrasion Methods 0.000 description 2
- 238000009413 insulation Methods 0.000 description 2
- 229920006389 polyphenyl polymer Polymers 0.000 description 2
- 230000009471 action Effects 0.000 description 1
- 230000006978 adaptation Effects 0.000 description 1
- 230000009977 dual effect Effects 0.000 description 1
- 230000002093 peripheral effect Effects 0.000 description 1
- 230000004044 response Effects 0.000 description 1
- 238000000926 separation method Methods 0.000 description 1
- 230000009466 transformation Effects 0.000 description 1
- 238000000844 transformation Methods 0.000 description 1
Images
Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U20/00—Constructional aspects of UAVs
- B64U20/90—Cooling
- B64U20/96—Cooling using air
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D33/00—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for
- B64D33/08—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for of power plant cooling systems
- B64D33/10—Radiator arrangement
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D9/00—Equipment for handling freight; Equipment for facilitating passenger embarkation or the like
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- H—ELECTRICITY
- H05—ELECTRIC TECHNIQUES NOT OTHERWISE PROVIDED FOR
- H05K—PRINTED CIRCUITS; CASINGS OR CONSTRUCTIONAL DETAILS OF ELECTRIC APPARATUS; MANUFACTURE OF ASSEMBLAGES OF ELECTRICAL COMPONENTS
- H05K7/00—Constructional details common to different types of electric apparatus
- H05K7/20—Modifications to facilitate cooling, ventilating, or heating
Abstract
The utility model discloses an unmanned aerial vehicle cabin heat abstractor belongs to unmanned air vehicle technical field. Wherein, unmanned aerial vehicle cabin heat abstractor includes: the heat-insulating cabin comprises an engine cabin inner cylinder, an engine cabin outer cylinder, a first cooling fin, a first heat-insulating fin, a second cooling fin and a second heat-insulating fin. Along with the relative rotation of the engine room inner cylinder and the engine room outer cylinder, when the first radiating fin and the second radiating fin are overlapped, the heat in the engine room inner cylinder is quickly conducted and radiated through the first radiating fin and the second radiating fin, so that the heat radiation is promoted; when the first radiating fins and the second radiating fins are distributed in a staggered mode, the first heat preservation pieces and the second heat preservation pieces preserve heat inside the inner barrel of the engine room, and the heat dissipation speed is reduced. Compared with the prior art, the utility model provides an unmanned aerial vehicle cabin heat abstractor can improve the inside heat of engine compartment and give off speed, still compromise the heat preservation function simultaneously, makes unmanned aerial vehicle adapt to the flight demand under the different environment.
Description
Technical Field
The utility model belongs to the technical field of unmanned aerial vehicle, especially, unmanned aerial vehicle cabin heat abstractor.
Background
The unmanned plane is an unmanned plane for short, and is an unmanned plane operated by radio remote control equipment and a self-contained program control device. The unmanned aerial vehicle as a new concept device has the advantages of flexibility, quick response, unmanned flight and easy operation, and is widely applied to the fields of meteorology, exploration, photography and the like.
During the flying process of the unmanned aerial vehicle, the integrated circuit assembly inside the cabin can generate a large amount of heat, if the heat can not be distributed in time, the circuit board is extremely easy to overheat, and the flying stability of the unmanned aerial vehicle is influenced. Therefore, it is necessary to provide a heat dissipation device in the cabin of the unmanned aerial vehicle to promote rapid heat dissipation.
However, the unmanned aerial vehicle sometimes needs to fly in severe working environments such as severe cold, the temperature of these regions is low, the power supply instability and insufficient flight force of the unmanned aerial vehicle can be caused, and the risk that the unmanned aerial vehicle stops flying and falls off is easily caused.
SUMMERY OF THE UTILITY MODEL
Utility model purpose: the utility model provides an unmanned aerial vehicle cabin heat abstractor to solve the above-mentioned problem that prior art exists.
In order to achieve the above object, the present invention provides the following technical solutions:
an unmanned aerial vehicle cabin heat abstractor, includes: the heat dissipation device comprises an outer cabin barrel fixed on the unmanned aerial vehicle and an inner cabin barrel inserted into the outer cabin barrel, wherein the top of the outer cabin barrel is closed, one end, close to the bottom, of the outer side wall of the outer cabin barrel is provided with a fixing part for fixing the heat dissipation device, and a plurality of arc-shaped first cooling fins and first heat preservation fins are attached to the inner side wall of the outer cabin barrel; the top of the cabin inner cylinder is closed, a supporting plate for fixing an integrated circuit board is fixed in the cabin inner cylinder, the bottom of the cabin inner cylinder is in threaded connection with a bottom plate, and a plurality of second radiating fins and second heat-insulating fins are attached to the outer wall of the side face of the cabin inner cylinder; the engine room outer cylinder is rotatably connected with the engine room inner cylinder.
In a further embodiment, the first heat sink, the first heat-insulating sheet, the second heat sink and the second heat-insulating sheet are all arc structures, and the angles of the arc surfaces are equal; the first radiating fin and the second heat-preservation fin are arranged at intervals, and the second radiating fin and the second heat-preservation fin are arranged at intervals; the inner diameter of the first radiating fin or the first heat-preserving fin is equal to the outer diameter of the second radiating fin or the second heat-preserving fin; along with the relative rotation of the cabin outer barrel and the cabin contents, the heat dissipation device has two states of heat dissipation and heat preservation; when the heat dissipation device is in a heat dissipation state, the first heat dissipation fin is overlapped with the second heat dissipation fin, and heat in the inner barrel of the engine room is quickly dissipated through heat conduction of the first heat dissipation fin and the second heat dissipation fin; when heat abstractor is in the heat preservation state, first fin and second fin are in crisscross distribution, and first heat preservation piece second heat preservation piece interval setting this moment carries out the separation to the heat in the cabin inner tube, reduces thermal speed of giving off, can make unmanned aerial vehicle's cabin have heat dissipation and heat retaining dual function through this setting, flight demand under the different environment of adaptation.
In a further embodiment, the first heat sink and the second heat sink are made of a heat-conducting silicone sheet, and the heat-conducting silicone sheet has excellent heat-conducting property and can ensure the heat dissipation effect of the heat dissipation device.
In a further embodiment, first heat preservation piece and second heat preservation piece adopt the polyphenyl board to make, and the polyphenyl board has certain thermal insulation performance, can make heat abstractor have certain thermal insulation performance to make unmanned aerial vehicle adapt to the flight in alpine environment.
In a further embodiment, a fan is fixed on the inner wall of the top of the cabin inner cylinder, a plurality of heat dissipation holes are formed in the bottom plate in the vertical direction, the fan rotates to promote convection of hot air and external cold air in the cabin inner cylinder, the hot air is dissipated to the outside of the heat dissipation device through the heat dissipation holes, and the cold air outside the heat dissipation device enters the cabin inner cylinder through the heat dissipation holes, so that the heat dissipation of the heat dissipation device is realized quickly.
In a further embodiment, the heat dissipation hole comprises a first through hole close to the middle of the bottom plate and a second through hole close to the edge of the bottom plate, and the diameter of the top end of the first through hole is larger than that of the bottom end of the first through hole; the diameter of the top end of the second through hole is smaller than that of the bottom end of the second through hole; through the arrangement, the convection of air inside the inner barrel of the engine room and outside the heat dissipation device is promoted, and the heat dissipation effect of the heat dissipation device is improved.
In a further embodiment, a first annular groove is formed in one end, close to the bottom, of the side inner wall of the cabin outer cylinder, a second annular groove is formed in one end, close to the bottom, of the side outer wall of the cabin inner cylinder, the first annular groove and the second annular groove are arranged oppositely, and a plurality of balls are arranged in the first annular groove and the second annular groove; through the arrangement, the relative rotation of the inner cabin cylinder and the outer cabin cylinder is promoted, and the friction and the abrasion during the relative rotation between the inner cabin cylinder and the outer cabin cylinder are reduced.
Has the advantages that: the utility model provides an unmanned aerial vehicle cabin heat abstractor includes: the heat-insulating cabin comprises an engine cabin inner cylinder, an engine cabin outer cylinder, a first cooling fin, a first heat-insulating fin, a second cooling fin and a second heat-insulating fin. The engine room inner cylinder and the engine room outer cylinder can rotate relatively, so that the first radiating fins and the second radiating fins are in different distribution states, when the first radiating fins and the second radiating fins are overlapped, heat in the engine room inner cylinder is quickly conducted and radiated through the first radiating fins and the second radiating fins, and heat radiation is promoted; when the first radiating fins and the second radiating fins are distributed in a staggered mode, the first heat preservation pieces and the second heat preservation pieces preserve heat inside the inner barrel of the engine room, and the heat dissipation speed is reduced. Compared with the prior art, the utility model provides an unmanned aerial vehicle cabin heat abstractor can improve the inside heat of engine compartment and give off speed, still compromise the heat preservation function simultaneously, makes unmanned aerial vehicle adapt to the flight demand under the different environment.
Drawings
Fig. 1 is the utility model discloses an unmanned aerial vehicle cabin heat abstractor's schematic structure diagram.
Fig. 2 is a sectional view of the heat dissipating device of the present invention.
Fig. 3 is a partial view of the present invention at a of fig. 2.
Fig. 4 is a distribution diagram of the first heat sink, the first heat-insulating sheet, the second heat sink, and the second heat-insulating sheet when the heat dissipation device of the present invention is in a heat dissipation state.
Fig. 5 is a distribution diagram of the first heat sink, the first heat-insulating sheet, the second heat sink, and the second heat-insulating sheet when the heat dissipation device of the present invention is in a heat-insulating state.
Fig. 6 is a structural sectional view of the bottom plate of the present invention.
The labels in fig. 1 to 6 are: the engine room outer cylinder 10, a fixing part 11, a first annular groove 12, a first radiating fin 13, a first heat preservation fin 14, an engine room inner cylinder 20, a second annular groove 21, a second radiating fin 22, a second heat preservation fin 23, a bottom plate 30, a radiating hole 31, a first through hole 311, a second through hole 312, a supporting plate 40, a ball 50 and a fan 60.
Detailed Description
In the following description, numerous specific details are set forth in order to provide a more thorough understanding of the present invention. It will be apparent, however, to one skilled in the art, that the present invention may be practiced without one or more of these specific details. In other instances, well-known features have not been described in order to avoid obscuring the present invention.
Research of researchers discovers that the unmanned aerial vehicle is extremely wide in application. During the flying process of the unmanned aerial vehicle, the integrated circuit assembly inside the cabin generates a large amount of heat which is discharged in time, so that the circuit board is easy to overheat, and the flying stability of the unmanned aerial vehicle is influenced. Meanwhile, the unmanned aerial vehicle needs to adapt to the flight environment of alpine regions sometimes, the temperature of the regions is low, the unmanned aerial vehicle is extremely easy to supply power and unstable, the unmanned aerial vehicle is enabled to have insufficient flight force, and even the unmanned aerial vehicle can be stopped flying and dropped. Therefore, how to improve the heat dissipation device, which has the heat preservation function while ensuring the heat dissipation effect, is a problem that needs to be solved urgently.
In order to solve the above problem, the utility model provides an unmanned aerial vehicle cabin heat abstractor, as shown in fig. 1 and fig. 2, this unmanned aerial vehicle cabin heat abstractor includes: a nacelle outer barrel 10 and a nacelle inner barrel 20.
Specifically, referring to fig. 3 and the drawings, the nacelle outer barrel 10 is a cylindrical structure, the top of the nacelle outer barrel 10 is closed, and one end of the lateral outer wall of the nacelle outer barrel 10, which is close to the bottom, is provided with a plurality of fixing portions 11. The fixed part 11 in this embodiment includes the engaging lug, and it has connect the through-hole to open on the engaging lug, fixes cabin urceolus 10 on unmanned aerial vehicle through set up screw or bolt in connect the through-hole. The cabin inner cylinder 20 is also of a cylindrical structure, the top of the cabin inner cylinder 20 is closed, internal threads are formed in the inner wall of the bottom of the cabin inner cylinder 20, a circular bottom plate 30 is screwed to the bottom of the cabin inner cylinder 20, external threads are formed in the side face of the bottom plate 30, and the external threads are matched with the internal threads in the bottom of the cabin inner cylinder 20. Cabin inner tube 20 and bottom plate 30 surround and form the confined chamber of acceping (not marking in the figure), accept the intracavity and be equipped with the backup pad 40, the side inner wall fixed connection of this backup pad 40 and cabin content, unmanned aerial vehicle's integrated circuit just sets up with this backup pad 40 on. The engine room inner cylinder 20 and the engine room outer cylinder 10 can rotate relatively, and one end of the side inner wall of the engine room outer cylinder 10 close to the bottom is a first annular groove 12 along the circumferential direction; and one end of the outer wall of the side surface of the cabin content, which is close to the bottom, is provided with a second annular groove 21 along the direction of the peripheral surface of the cabin content, the first annular groove 12 and the second annular groove 21 are arranged oppositely, a plurality of balls 50 are arranged in the first annular groove 12 and the second annular groove 21, and when the cabin inner cylinder 20 rotates relative to the cabin outer cylinder 10, the balls 50 roll in the first annular groove 12 and the second annular groove 21, so that the friction and the abrasion between the cabin inner cylinder 20 and the cabin outer cylinder 10 are reduced.
Referring to fig. 4 and 5, a plurality of first heat dissipating fins 13 and first heat insulating fins 14 having an arc-shaped structure are attached to the inner side wall of the nacelle outer cylinder 10. Meanwhile, a plurality of second radiating fins 22 and second heat-insulating fins 23 with arc structures are attached to the outer wall of the side surface of the nacelle inner barrel 20. The cambered surface angles of the first heat sink 13, the first heat preservation fin 14, the second heat sink 22 and the second heat preservation fin 23 are equal and are all 30 degrees. Meanwhile, the lengths of the first heat sink 13, the first heat insulating sheet 14, the second heat sink 22, and the second heat insulating sheet 23 in the vertical direction are also equal. The number of the first radiating fins 13 is equal to that of the first heat-preserving fins 14, and the number of the first radiating fins is 6; the first heat sink 13 and the first heat insulating fin 14 are disposed at an interval so as to be adhered to the inner wall of the side surface of the nacelle outer casing 10. The number of the second radiating fins 22 and the number of the second heat-preservation fins 23 are also equal, and are both 6; the second heat radiating fins 22 and the second heat insulating fins 23 are arranged at intervals to be attached to the outer wall of the side face of the cabin inner barrel 20. The inner diameter of the first heat sink 13 or the first heat-insulating fin 14 is equal to the outer diameter of the second heat sink 22 or the second heat-insulating fin 23. Along with the relative rotation of the engine room outer cylinder 10 and the engine room inner cylinder 20, the heat dissipation device has two states of heat dissipation and heat preservation. When the first heat dissipation fin 13 and the second heat dissipation fin 22 are overlapped, the first heat dissipation fin 13 and the second heat dissipation fin 22 form a connected thermal bridge, and because the first heat dissipation fin 13 and the second heat dissipation fin 22 have higher heat conductivity coefficients, heat of the cabin content is quickly conducted and dissipated through the second heat dissipation fin 22 and the first heat dissipation fin 13, so that quick heat dissipation is realized, and at the moment, the heat dissipation device is in a heat dissipation state. When the first radiating fins 13 and the second radiating fins 22 are staggered, the first heat-insulating fins 14 and the second heat-insulating fins 23 are also staggered, a thermal bridge formed by the first radiating fins 13 and the second radiating fins 22 is interrupted, and the first heat-insulating fins 14 and the second heat-insulating fins 23 form a linked heat-insulating layer to block heat in the cabin inner cylinder 20, so that the heat dissipation speed is reduced, and the heat dissipation device is in a heat-insulating state. Make unmanned aerial vehicle's cabin can dispel the heat fast and still have the heat preservation function simultaneously concurrently through such setting up, and then make unmanned aerial vehicle adapt to different flight annular. In the present embodiment, the first heat sink 13 and the second heat sink 22 are both made of JRF-PM800 thermal conductive silicone sheets, and the thermal conductivity thereof can reach 8.0W/(M.K), so that the heat sink has excellent thermal conductivity and can ensure rapid heat dissipation. The heat preservation sheet in this embodiment is made of polystyrene board (or polystyrene board), and its thermal conductivity is not more than 0.041W/(M.K), has certain heat preservation performance to make heat abstractor have the heat preservation function, so that unmanned aerial vehicle adapts to the high and cold environment.
The heat in the inner barrel 20 of the engine room is a passive heat dissipation manner by a heat conduction manner, and the heat is dissipated by a conduction and radiation manner. The heat in the cabin inner barrel 20 needs to be transmitted and dissipated through the heat conduction of the air and then through the second cooling fin 22 and the first cooling fin 13, and the heat dissipation process needs to pass through a plurality of heat-conducting media, so that a certain heat conduction time is needed. Therefore, the heat dissipation device provided by the utility model has an improved space, and in order to further improve the heat dissipation performance of the heat dissipation device, the fan 60 is fixed on the inner wall of the top of the engine room inner cylinder 20; meanwhile, the bottom plate 30 is provided with a plurality of heat dissipation holes 31 along the vertical direction. Through the incessant rotation of fan 60, promote the convection current of the hot-air in cabin inner tube 20 and the outside hot-air, promote the heat exchange, make the hot-air distribute away through louvre 31, the cold air gets into the inside of cabin inner tube 20 through louvre 31 simultaneously, through this kind of initiative radiating mode, realizes heat abstractor's quick heat dissipation.
To facilitate convection of the hot air within the nacelle inner barrel 20 with the cold air outside the heat sink, in a further embodiment, in conjunction with fig. 2 and 6, the heat sink 31 includes a first through hole 311 near the middle of the base plate 30 and a second through hole 312 near the edge of the base plate 30. Wherein, the top diameter of the first through hole 311 is larger than the bottom diameter of the first through hole 311, under the action of the fan 60, the hot air of the nacelle inner barrel 20 can easily flow out from the first through hole 311, and the outside cold air is difficult to enter the inside of the nacelle inner barrel 20 from the first through hole 311. The diameter of the top end of the second through hole 312 is smaller than the diameter of the bottom end of the second through hole 312, so that the outside cold air easily enters the inside of the nacelle inner barrel 20 through the second through hole 312, and the hot air in the nacelle inner barrel 20 is difficult to be discharged through the second through hole 312. Therefore, cold air enters the cabin inner barrel 20 from the second through hole 312 close to the side surface, and hot air in the cabin inner barrel 20 is discharged from the first through hole 311 close to the middle part, so that a stable air circulation loop is formed, convection of air inside and outside the cabin inner barrel 20 is improved, and the heat dissipation effect of the heat dissipation device is improved.
The preferred embodiments of the present invention have been described in detail with reference to the accompanying drawings, however, the present invention is not limited to the details of the above embodiments, and the technical concept of the present invention can be modified to perform various equivalent transformations, which all belong to the protection scope of the present invention.
Claims (7)
1. An unmanned aerial vehicle cabin heat abstractor, its characterized in that includes: the heat dissipation device comprises an outer cabin barrel fixed on the unmanned aerial vehicle and an inner cabin barrel inserted into the outer cabin barrel, wherein the top of the outer cabin barrel is closed, one end, close to the bottom, of the outer side wall of the outer cabin barrel is provided with a fixing part for fixing the heat dissipation device, and a plurality of arc-shaped first cooling fins and first heat preservation fins are attached to the inner side wall of the outer cabin barrel; the top of the cabin inner cylinder is closed, a supporting plate for fixing an integrated circuit board is fixed in the cabin inner cylinder, the bottom of the cabin inner cylinder is in threaded connection with a bottom plate, and a plurality of second radiating fins and second heat-insulating fins are attached to the outer wall of the side face of the cabin inner cylinder; the engine room outer cylinder is rotatably connected with the engine room inner cylinder.
2. The heat dissipating device of claim 1, wherein the first heat sink, the first heat retaining sheet, the second heat sink and the second heat retaining sheet are all arc structures and have equal angles of arc surfaces; the first radiating fin and the second heat-preservation fin are arranged at intervals, and the second radiating fin and the second heat-preservation fin are arranged at intervals; the inner diameter of the first radiating fin or the first heat-preserving fin is equal to the outer diameter of the second radiating fin or the second heat-preserving fin; along with the relative rotation of the cabin outer barrel and the cabin contents, the heat dissipation device has two states of heat dissipation and heat preservation; when the heat dissipation device is in a heat dissipation state, the first heat dissipation sheet is overlapped with the second heat dissipation sheet; when the heat dissipation device is in a heat preservation state, the first cooling fins and the second cooling fins are in staggered distribution.
3. The heat dissipating device of claim 1, wherein the first and second fins are made of thermally conductive silicone sheets.
4. The heat dissipating device of claim 1, wherein the first insulating sheet and the second insulating sheet are made of polystyrene board.
5. The heat dissipating device of claim 1, wherein a fan is fixed to the inner wall of the top of the inner barrel of the nacelle, and the bottom plate has a plurality of heat dissipating holes formed therein along a vertical direction.
6. The heat dissipating device of claim 5, wherein the heat dissipating holes comprise a first through hole near the middle of the base plate and a second through hole near the edge of the base plate, and the top diameter of the first through hole is larger than the bottom diameter of the first through hole; the diameter of the top end of the second through hole is smaller than that of the bottom end of the second through hole.
7. The heat dissipating device of claim 1, wherein a first annular groove is formed at an end of the inner side wall of the outer cylinder of the nacelle near the bottom, a second annular groove is formed at an end of the outer side wall of the inner cylinder of the nacelle near the bottom, the first annular groove and the second annular groove are arranged oppositely, and a plurality of balls are arranged in the first annular groove and the second annular groove.
Priority Applications (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202020446462.7U CN211969749U (en) | 2020-03-31 | 2020-03-31 | Unmanned aerial vehicle cabin heat abstractor |
| PCT/CN2020/083043 WO2021196138A1 (en) | 2020-03-31 | 2020-04-02 | Heat dissipation device for cabin of unmanned aerial vehicle |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202020446462.7U CN211969749U (en) | 2020-03-31 | 2020-03-31 | Unmanned aerial vehicle cabin heat abstractor |
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| Publication Number | Publication Date |
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| CN211969749U true CN211969749U (en) | 2020-11-20 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN202020446462.7U Active CN211969749U (en) | 2020-03-31 | 2020-03-31 | Unmanned aerial vehicle cabin heat abstractor |
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| Country | Link |
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| CN (1) | CN211969749U (en) |
| WO (1) | WO2021196138A1 (en) |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| CN114265331A (en) * | 2021-12-21 | 2022-04-01 | 重庆交通大学 | Thermal simulation method for engine compartment of unmanned aerial vehicle |
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20130112805A1 (en) * | 2011-07-06 | 2013-05-09 | Borealis Technical Limited | Method for reducing requirements for aircraft brake size, complexity, and heat dissipation |
| US9475574B2 (en) * | 2011-09-14 | 2016-10-25 | Borealis Technical Limited | Heat dissipation system for aircraft drive wheel drive assembly |
| CN104670499B (en) * | 2015-02-28 | 2017-09-01 | 广州快飞计算机科技有限公司 | A kind of plant protection unmanned plane |
| CN105836116B (en) * | 2016-04-07 | 2019-02-19 | 易瓦特科技股份公司 | Cooling type unmanned plane |
| CN106628151B (en) * | 2016-12-30 | 2019-11-19 | 易瓦特科技股份公司 | Casing fast disassembly type unmanned plane |
| CN108216652B (en) * | 2018-01-17 | 2020-12-11 | 安徽中骄智能科技有限公司 | Motor heat dissipation rack for unmanned aerial vehicle |
| CN209661174U (en) * | 2019-03-15 | 2019-11-22 | 南京机电职业技术学院 | A kind of vacuum cup |
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2020
- 2020-03-31 CN CN202020446462.7U patent/CN211969749U/en active Active
- 2020-04-02 WO PCT/CN2020/083043 patent/WO2021196138A1/en active Application Filing
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| WO2021196138A1 (en) | 2021-10-07 |
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Address after: 226100 No.588, Hong Kong Road, Haimen Economic and Technological Development Zone, Nantong City, Jiangsu Province Patentee after: Nantong Guoyi Aviation Technology Co.,Ltd. Address before: 211100 37 general road, Jiangning economic and Technological Development Zone, Nanjing, Jiangsu Patentee before: NANJING DASSAULT AVIATION TECHNOLOGY Co.,Ltd. |
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