CN113675501A - Unmanned aerial vehicle battery cooling system, unmanned aerial vehicle battery and unmanned aerial vehicle - Google Patents
Unmanned aerial vehicle battery cooling system, unmanned aerial vehicle battery and unmanned aerial vehicle Download PDFInfo
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- CN113675501A CN113675501A CN202110937717.9A CN202110937717A CN113675501A CN 113675501 A CN113675501 A CN 113675501A CN 202110937717 A CN202110937717 A CN 202110937717A CN 113675501 A CN113675501 A CN 113675501A
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- unmanned aerial
- aerial vehicle
- vehicle battery
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- H—ELECTRICITY
- H01—ELECTRIC ELEMENTS
- H01M—PROCESSES OR MEANS, e.g. BATTERIES, FOR THE DIRECT CONVERSION OF CHEMICAL ENERGY INTO ELECTRICAL ENERGY
- H01M10/00—Secondary cells; Manufacture thereof
- H01M10/60—Heating or cooling; Temperature control
- H01M10/61—Types of temperature control
- H01M10/613—Cooling or keeping cold
-
- 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
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U50/00—Propulsion; Power supply
- B64U50/10—Propulsion
- B64U50/19—Propulsion using electrically powered motors
-
- H—ELECTRICITY
- H01—ELECTRIC ELEMENTS
- H01M—PROCESSES OR MEANS, e.g. BATTERIES, FOR THE DIRECT CONVERSION OF CHEMICAL ENERGY INTO ELECTRICAL ENERGY
- H01M10/00—Secondary cells; Manufacture thereof
- H01M10/42—Methods or arrangements for servicing or maintenance of secondary cells or secondary half-cells
- H01M10/48—Accumulators combined with arrangements for measuring, testing or indicating the condition of cells, e.g. the level or density of the electrolyte
- H01M10/486—Accumulators combined with arrangements for measuring, testing or indicating the condition of cells, e.g. the level or density of the electrolyte for measuring temperature
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- H—ELECTRICITY
- H01—ELECTRIC ELEMENTS
- H01M—PROCESSES OR MEANS, e.g. BATTERIES, FOR THE DIRECT CONVERSION OF CHEMICAL ENERGY INTO ELECTRICAL ENERGY
- H01M10/00—Secondary cells; Manufacture thereof
- H01M10/60—Heating or cooling; Temperature control
- H01M10/65—Means for temperature control structurally associated with the cells
- H01M10/655—Solid structures for heat exchange or heat conduction
-
- H—ELECTRICITY
- H01—ELECTRIC ELEMENTS
- H01M—PROCESSES OR MEANS, e.g. BATTERIES, FOR THE DIRECT CONVERSION OF CHEMICAL ENERGY INTO ELECTRICAL ENERGY
- H01M10/00—Secondary cells; Manufacture thereof
- H01M10/60—Heating or cooling; Temperature control
- H01M10/65—Means for temperature control structurally associated with the cells
- H01M10/655—Solid structures for heat exchange or heat conduction
- H01M10/6556—Solid parts with flow channel passages or pipes for heat exchange
-
- H—ELECTRICITY
- H01—ELECTRIC ELEMENTS
- H01M—PROCESSES OR MEANS, e.g. BATTERIES, FOR THE DIRECT CONVERSION OF CHEMICAL ENERGY INTO ELECTRICAL ENERGY
- H01M10/00—Secondary cells; Manufacture thereof
- H01M10/60—Heating or cooling; Temperature control
- H01M10/65—Means for temperature control structurally associated with the cells
- H01M10/656—Means for temperature control structurally associated with the cells characterised by the type of heat-exchange fluid
- H01M10/6561—Gases
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02E—REDUCTION OF GREENHOUSE GAS [GHG] EMISSIONS, RELATED TO ENERGY GENERATION, TRANSMISSION OR DISTRIBUTION
- Y02E60/00—Enabling technologies; Technologies with a potential or indirect contribution to GHG emissions mitigation
- Y02E60/10—Energy storage using batteries
Abstract
The invention provides an unmanned aerial vehicle battery cooling system, an unmanned aerial vehicle battery and an unmanned aerial vehicle, which comprise a plurality of cooling fins, wherein each cooling fin is correspondingly attached to the surface of an unmanned aerial vehicle battery cell; the gas storage tank is connected with the unmanned aerial vehicle body and used for storing liquid pressurized gas; a header pipe having one end communicating with the gas storage tank; one end of each branch pipe assembly is communicated with the main pipe, and the other end of each branch pipe assembly correspondingly extends into a gap between two adjacent unmanned aerial vehicle battery cells; and each temperature sensor is correspondingly arranged in a gap between two adjacent unmanned aerial vehicle battery cells and is used for acquiring temperature information in the gap in real time. It combines the radiating mode of liquid pressurized gas initiative to realize the abundant heat dissipation to unmanned aerial vehicle battery electricity core through the passive heat dissipation of fin, guarantees from this that the holistic operating temperature of unmanned aerial vehicle battery electricity core is in suitable scope, prolongs the holistic working life of electric core.
Description
Technical Field
The invention relates to the field of unmanned aerial vehicles, in particular to an unmanned aerial vehicle battery cooling system, an unmanned aerial vehicle battery and an unmanned aerial vehicle.
Background
In the unmanned aerial vehicle system, the unmanned aerial vehicle battery is high power, high energy density battery, adopts many electric cores to connect in series and in parallel to use usually, if heat dissipation or heat conduction are unbalanced, can have that inside electric core temperature is unbalanced or the high temperature, leads to partial electric core to decline with higher speed, and available capacity reduces, and battery cycle life attenuates by a wide margin.
And to the serious problem that generates heat of unmanned aerial vehicle battery high magnification during operation, the radiating structure design radiating effect that adopts at present is not good, needs further strengthen its radiating effect.
Disclosure of Invention
The invention aims to provide an unmanned aerial vehicle battery cooling system, an unmanned aerial vehicle battery and an unmanned aerial vehicle, which realize sufficient cooling of an unmanned aerial vehicle battery cell by combining passive cooling of a cooling fin with active cooling of liquid pressurized gas, so that the whole working temperature of the unmanned aerial vehicle battery cell is ensured to be in a proper range, and the whole working life of the cell is prolonged.
Specifically, the invention provides an unmanned aerial vehicle battery cooling system, which comprises:
the cooling fins are correspondingly attached to the surface of the unmanned aerial vehicle battery cell;
the gas storage tank is connected with the unmanned aerial vehicle body and used for storing liquid pressurized gas;
a header pipe having one end communicating with the gas storage tank;
one end of each branch pipe assembly is communicated with the main pipe, and the other end of each branch pipe assembly correspondingly extends into a gap between two adjacent unmanned aerial vehicle battery cells;
the temperature sensors are correspondingly arranged in a gap between two adjacent unmanned aerial vehicle battery cells and used for acquiring temperature information in the gap in real time;
according to temperature information control gas storage jar in the gap, house steward and the branch pipe subassembly intercommunication that corresponds to make the liquid pressurized gas in the gas storage jar enter into the gap that corresponds through house steward, branch pipe subassembly in, in order to take away the heat that unmanned aerial vehicle battery electricity core during operation produced.
Preferably, the heat sink is an L-shaped structure having a transverse portion and a longitudinal portion perpendicular to each other, wherein the transverse portion is attached to the front surface of the unmanned aerial vehicle battery cell, and the longitudinal portion is attached to the side surface of the unmanned aerial vehicle battery cell.
Preferably, the length of the radiating fin is 80-90% of the length of the battery cell of the unmanned aerial vehicle.
Preferably, when the temperature in the gap acquired by the temperature sensor exceeds a threshold value, the gas storage tank, the main pipe and the branch pipe assembly are controlled to be communicated according to the temperature information in the gap.
Preferably, the manifold assembly comprises: the electromagnetic valve is arranged on the branch pipe; the air outlet nozzle extends into the gap.
Preferably, the air outlet nozzle is of a fan-shaped structure, the corresponding central angle alpha is 30-60 degrees, and the length of the air outlet nozzle is 20-50% of the length of the battery cell of the unmanned aerial vehicle.
Preferably, unmanned aerial vehicle battery cooling system still includes: and the flow control valve is arranged on the main pipe and is opened when the electromagnetic valve and the flow control valve are controlled according to the temperature information in the gap.
Preferably, the unmanned aerial vehicle battery cooling system further includes: and the spacer blocks are arranged in gaps between adjacent unmanned aerial vehicle battery cells.
Still provide an unmanned aerial vehicle battery, it includes: the unmanned aerial vehicle battery cells are connected in parallel, and gaps are formed between adjacent unmanned aerial vehicle battery cells; and the unmanned aerial vehicle battery cooling system.
There is also provided a drone, comprising: the unmanned aerial vehicle battery is connected with the unmanned aerial vehicle body, and the air outlet nozzle is enabled to discharge air towards the lower part of the unmanned aerial vehicle body; and the comprehensive control system acquires the information of the reaction force applied to the whole unmanned aerial vehicle when the air outlet nozzle gives air out, and adjusts the rotating speed of the motor of the unmanned aerial vehicle according to the information of the reaction force.
According to the invention, the full heat dissipation of the battery cell of the unmanned aerial vehicle can be realized by combining the passive heat dissipation of the heat dissipation fins with the active heat dissipation of the liquid pressurized gas, and each branch pipe assembly can independently convey the liquid pressurized gas to the corresponding gap for heat dissipation, so that the working temperature of the whole battery cells of a plurality of unmanned aerial vehicles can be ensured to be in a proper range on one hand, and the temperature difference among the battery cells of the unmanned aerial vehicles can be ensured to be stabilized in a preset range on the other hand, thereby prolonging the service life of the whole battery cells; further, the comprehensive control system of the unmanned aerial vehicle can also acquire the information of the reaction force applied to the whole unmanned aerial vehicle when the air outlet nozzle gives air according to the flow of the flow control valve, and adjust the rotating speed of the motor of the unmanned aerial vehicle according to the information of the reaction force so as to save the power consumption of the power system in flight.
Drawings
Fig. 1 is an overall structural diagram of a battery cooling system of an unmanned aerial vehicle according to the present invention;
fig. 2 is a front view of a battery cooling system of the drone in accordance with the present invention;
FIG. 3 is an overall structural view of a heat sink in the present invention;
figure 4 is a front view of the nozzle of the present invention.
Detailed Description
In order to make the objects, technical solutions and advantages of the present invention more apparent, embodiments of the present invention will be further described with reference to the accompanying drawings.
Example 1:
as shown in fig. 1-4, this embodiment provides an unmanned aerial vehicle battery cooling system, and it includes:
a plurality of radiating fins 1, wherein each radiating fin 1 is correspondingly attached to the surface of an unmanned aerial vehicle battery cell 100; in this embodiment, the heat sink 1 has an L-shaped structure, which has a transverse portion 11 and a longitudinal portion 12 perpendicular to each other, wherein the transverse portion 11 is attached to the front of the unmanned aerial vehicle battery cell 100, the longitudinal portion 12 is attached to the side of the unmanned aerial vehicle battery cell 100, meanwhile, as shown in fig. 2, in this embodiment, the length H of the heat sink 1 is 80-90% of the length H of the battery electric core 100 of the drone battery, and the distance from the upper end surface of the radiating fin 1 to the upper end surface of the unmanned aerial vehicle battery cell 100 is the same as the distance from the lower end surface of the radiating fin 1 to the lower end surface of the unmanned aerial vehicle battery cell 100, thereby ensuring that the radiating fins 1 can cover most of the surface of the battery cell 100 of the unmanned aerial vehicle and are positioned in the middle of the battery cell 100 of the unmanned aerial vehicle, ensuring uniform heat radiation, and further, the whole radiating fin 1 is made of an aluminum material and has the characteristics of light weight, thinness, good heat-conducting property and the like;
it should be noted that, when a person skilled in the art normally uses and observes the unmanned aerial vehicle battery cell 100 (i.e., the viewing angle in fig. 2), a face directly facing the person skilled in the art is a front face of the unmanned aerial vehicle battery cell 100, and on this basis, a rear face, a side face, an upper surface, and a lower surface of the unmanned aerial vehicle battery cell 100 are determined, where the front face, the rear face, the side face, the upper surface, and the lower surface are only used for illustrating implementation of the solution of the embodiment and do not form a specific limitation on a protection scope; meanwhile, as shown in fig. 2, there are a plurality of unmanned aerial vehicle battery cells 100, and a gap S having a width W of 2.0 to 3.0mm is formed between two adjacent unmanned aerial vehicle battery cells 100;
the gas storage tank 2 is connected with the unmanned aerial vehicle body and used for storing liquid pressurized gas; in the embodiment, the gas storage tank 2 is made of high-strength plastic, so that the gas storage tank 2 has better mechanical strength and cannot be torn or cracked when falling from a height of 150 m; the liquid pressurized gas comprises liquid carbon dioxide;
a header pipe 3 having one end communicating with the gas storage tank 2;
a plurality of branch pipe assemblies 5, wherein one end of each branch pipe assembly 5 is communicated with the header pipe 3, and the other end of each branch pipe assembly 5 correspondingly extends into a gap S between two adjacent unmanned aerial vehicle battery cells 100;
the temperature sensors 6 are arranged in a gap S between two adjacent battery cells 100 of the unmanned aerial vehicle, and each temperature sensor 6 is used for acquiring temperature information in the gap S in real time and sending the temperature information to a comprehensive control system of the unmanned aerial vehicle;
unmanned aerial vehicle' S comprehensive control system controls gaseous storage jar 2, house steward 3 and the 5 intercommunications of branch pipe subassembly that correspond according to the temperature information in the gap S to make liquid pressurized gas in the gaseous storage jar 2 enter into the gap S that corresponds through house steward 3, branch pipe subassembly 5, in order to take away the heat that unmanned aerial vehicle battery electric core 100 during operation produced, realize the heat dissipation to unmanned aerial vehicle battery electric core 100.
Preferably, after the unmanned aerial vehicle takes off, the temperature of the battery electric core 100 of the unmanned aerial vehicle is gradually increased, the heat dissipation can be directly performed through the heat dissipation fins 1 in the initial stage, the heat dissipation is not required through liquid pressurized gas, and only when the temperature in the gap S acquired by the temperature sensor 6 exceeds a threshold value (such as 50 ℃), the integrated control system of the unmanned aerial vehicle controls the communication of the gas storage tank 2, the header pipe 3 and the branch pipe assembly 5 according to the temperature information in the gap S, so that the liquid pressurized gas in the gas storage tank 2 enters the corresponding gap S through the header pipe 3 and the branch pipe assembly 5 to perform the active heat dissipation.
From this, in this embodiment, the passive heat dissipation of accessible fin combines the radiating mode of liquid pressurized gas initiative to realize the abundant heat dissipation to unmanned aerial vehicle battery electric core 100, and the liquid pressurized gas of the transport that every branch pipe assembly 5 can be independent dispels the heat in to the gap S that corresponds, can guarantee on the one hand that the holistic operating temperature of a plurality of unmanned aerial vehicle battery electric cores 100 is in suitable scope, on the other hand can guarantee that the temperature difference between each unmanned aerial vehicle battery electric core 100 also stabilizes at the predetermined range, if within 2 ℃, can prolong the holistic working life of electric core from this.
Example 2:
the present embodiment differs from embodiment 1 in that the branch pipe assembly 5 includes: the unmanned aerial vehicle comprises a branch pipe 51, an electromagnetic valve 52 and an air outlet nozzle 53, wherein two ends of the branch pipe 51 are respectively communicated with the main pipe 3 and the air outlet nozzle 53, and the electromagnetic valve 52 is installed on the branch pipe 51 and is simultaneously connected with a comprehensive control system of the unmanned aerial vehicle; the air outlet nozzle 53 extends into the gap S;
when the temperature in the gap S obtained by the temperature sensor 6 exceeds a threshold value (for example, 50 ℃), the integrated control system of the unmanned aerial vehicle controls the electromagnetic valve 52 to be opened according to the temperature information in the gap S (the electromagnetic valve coil can be controlled to be switched on and off through the single-chip microcomputer I/O port of the integrated control system of the unmanned aerial vehicle), so that the liquid pressurized gas in the gas storage tank 2 enters the corresponding gap S through the main pipe 3, the branch pipe 51 and the gas outlet nozzle 53 to actively dissipate heat.
Further, as shown in fig. 4, the air outlet nozzle 53 is integrally of a fan-shaped structure, the corresponding central angle α is 30-60 ° (preferably 45 °), and the length H1 of the air outlet nozzle 53 is 20-50% (preferably 45%) of the length H of the unmanned aerial vehicle battery cell 100, and meanwhile, when the air outlet nozzle 53 extends into the corresponding gap S, the length extending direction of the air outlet nozzle is consistent with the length extending direction of the unmanned aerial vehicle battery cell 100, so that the unmanned aerial vehicle battery cell 100 can be sufficiently cooled in the length direction.
Meanwhile, in the embodiment, the header pipe 3 and/or the branch pipe 51 are made of teflon, and have the characteristics of oil resistance, heat insulation, wear resistance, shock absorption, water resistance, long service life and the like, and the radiating fins 1 adopt a fillet design to prevent sharp protruding parts from hurting people.
Example 3:
the difference between this embodiment and embodiment 1 or 2 is only that, as shown in fig. 1, the unmanned aerial vehicle battery cooling system in this embodiment further includes: the flow control valve 4 is arranged on the main pipe 3 and is connected with a comprehensive control system of the unmanned aerial vehicle;
when the temperature in the gap S obtained by the temperature sensor 6 exceeds a threshold (for example, 50 ℃), the integrated control system of the unmanned aerial vehicle controls the electromagnetic valve 52 and the flow control valve 4 to be opened according to the temperature information in the gap S, so that the liquid pressurized gas in the gas storage tank 2 enters the corresponding gap S through the header pipe 3, the branch pipe 51 and the gas outlet nozzle 53 to perform active heat dissipation, and the flow control valve 4 changes local resistance by adjusting the size of the through-flow section of the throttling port under the control of the integrated control system of the unmanned aerial vehicle, thereby realizing the control of the gas flow, realizing more accurate heat dissipation, further realizing independent control of the working temperature of each unmanned aerial vehicle battery cell 100, and ensuring that the temperature difference among each unmanned aerial vehicle battery cell 100 is also stabilized within a predetermined range;
and the spacer 7 is arranged in the gap S between the adjacent unmanned aerial vehicle battery cells 100 and used for keeping the width of the gap S stable so as to fully exert the heat dissipation function of the heat dissipation fin 1, and preferably, the spacer 7 is made of a heat conduction material.
Example 4:
this embodiment provides an unmanned aerial vehicle battery, as shown in fig. 1, it includes: a plurality of unmanned aerial vehicle battery cells 100 connected in parallel, and adjacent unmanned aerial vehicle battery cells 100 have a gap S with a width W of 2.0-3.0 mm; and the unmanned aerial vehicle battery cooling system of any of embodiments 1-3.
Example 5:
this embodiment provides an unmanned aerial vehicle, it includes: unmanned aerial vehicle organism, embodiment 4 unmanned aerial vehicle battery and comprehensive control system, embodiment 4 the unmanned aerial vehicle battery connect the unmanned aerial vehicle organism, and make the gas outlet nozzle 53 give vent to anger towards the below of unmanned aerial vehicle organism, simultaneously, comprehensive control system acquires the whole reaction force information of applying to unmanned aerial vehicle when giving vent to anger of gas outlet nozzle 53 according to the flow of flow control valve 4, and adjusts the rotational speed of unmanned aerial vehicle motor according to this reaction force information to save the driving system consumption in flight.
In summary, the invention can realize sufficient heat dissipation of the battery cells of the unmanned aerial vehicle by combining the passive heat dissipation of the heat dissipation fins with the active heat dissipation of the liquid pressurized gas, and each branch pipe assembly can independently convey the liquid pressurized gas to the corresponding gap for heat dissipation, so that on one hand, the working temperature of the whole battery cells of the unmanned aerial vehicle can be ensured to be in a proper range, and on the other hand, the temperature difference among the battery cells of the unmanned aerial vehicle can be ensured to be stabilized in a preset range, thereby prolonging the service life of the whole battery cells; further, the comprehensive control system of the unmanned aerial vehicle can also acquire the information of the reaction force applied to the whole unmanned aerial vehicle when the air outlet nozzle gives air according to the flow of the flow control valve, and adjust the rotating speed of the motor of the unmanned aerial vehicle according to the information of the reaction force so as to save the power consumption of the power system in flight.
The above description is only for the purpose of illustrating the preferred embodiments of the present invention and is not to be construed as limiting the invention, and any modifications, equivalents, improvements and the like that fall within the spirit and principle of the present invention are intended to be included therein.
Claims (10)
1. The utility model provides an unmanned aerial vehicle battery cooling system which characterized in that includes:
the cooling fins are correspondingly attached to the surface of the unmanned aerial vehicle battery cell;
the gas storage tank is connected with the unmanned aerial vehicle body and used for storing liquid pressurized gas;
a header pipe having one end communicating with the gas storage tank;
one end of each branch pipe assembly is communicated with the main pipe, and the other end of each branch pipe assembly correspondingly extends into a gap between two adjacent unmanned aerial vehicle battery cells;
the temperature sensors are correspondingly arranged in a gap between two adjacent unmanned aerial vehicle battery cells and used for acquiring temperature information in the gap in real time;
according to temperature information control gas storage jar in the gap, house steward and the branch pipe subassembly intercommunication that corresponds to make the liquid pressurized gas in the gas storage jar enter into the gap that corresponds through house steward, branch pipe subassembly in, in order to take away the heat that unmanned aerial vehicle battery electricity core during operation produced.
2. The unmanned aerial vehicle battery cooling system of claim 1, wherein the heat sink is an L-shaped structure having a transverse portion and a longitudinal portion that are perpendicular to each other, wherein the transverse portion is attached to a front face of the unmanned aerial vehicle battery cell, and the longitudinal portion is attached to a side face of the unmanned aerial vehicle battery cell.
3. The unmanned aerial vehicle battery cooling system of claim 1, wherein the length of the heat sink is 80-90% of the length of the unmanned aerial vehicle battery cell.
4. The unmanned aerial vehicle battery cooling system of claim 1, wherein when the temperature in the gap obtained by the temperature sensor exceeds a threshold value, the gas storage tank, the main pipe and the branch pipe assembly are controlled to be communicated according to temperature information in the gap.
5. The unmanned aerial vehicle battery cooling system of claim 1, wherein the manifold assembly comprises: the electromagnetic valve is arranged on the branch pipe; the air outlet nozzle extends into the gap.
6. The unmanned aerial vehicle battery cooling system of claim 5, wherein the outlet nozzle is a fan-shaped structure, and the corresponding central angle α is 30-60 °, and the length of the outlet nozzle is 20-50% of the length of the battery cell of the unmanned aerial vehicle.
7. The drone battery cooling system of claim 1, further comprising: and the flow control valve is arranged on the main pipe and is opened when the electromagnetic valve and the flow control valve are controlled according to the temperature information in the gap.
8. The drone battery cooling system of claim 1, further comprising: and the spacer blocks are arranged in gaps between adjacent unmanned aerial vehicle battery cells.
9. An unmanned aerial vehicle battery, comprising: the unmanned aerial vehicle battery cells are connected in parallel, and gaps are formed between adjacent unmanned aerial vehicle battery cells; and the unmanned aerial vehicle battery cooling system of any of claims 1-8.
10. An unmanned aerial vehicle, comprising: the unmanned aerial vehicle body, the unmanned aerial vehicle battery and the comprehensive control system are connected, and the unmanned aerial vehicle battery is connected with the unmanned aerial vehicle body, and the air outlet nozzle is made to be air outlet towards the lower part of the unmanned aerial vehicle body; and the comprehensive control system acquires the information of the reaction force applied to the whole unmanned aerial vehicle when the air outlet nozzle gives air out, and adjusts the rotating speed of the motor of the unmanned aerial vehicle according to the information of the reaction force.
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| Application Number | Priority Date | Filing Date | Title |
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| CN202110937717.9A CN113675501B (en) | 2021-08-16 | 2021-08-16 | Unmanned aerial vehicle battery cooling system, unmanned aerial vehicle battery and unmanned aerial vehicle |
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| CN202110937717.9A CN113675501B (en) | 2021-08-16 | 2021-08-16 | Unmanned aerial vehicle battery cooling system, unmanned aerial vehicle battery and unmanned aerial vehicle |
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| CN113675501B CN113675501B (en) | 2023-03-31 |
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| CN113675501B (en) | 2023-03-31 |
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