CN108110274B - Hydrogen fuel cell, automobile and unmanned aerial vehicle - Google Patents
Hydrogen fuel cell, automobile and unmanned aerial vehicle Download PDFInfo
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- CN108110274B CN108110274B CN201710082632.0A CN201710082632A CN108110274B CN 108110274 B CN108110274 B CN 108110274B CN 201710082632 A CN201710082632 A CN 201710082632A CN 108110274 B CN108110274 B CN 108110274B
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- 239000001257 hydrogen Substances 0.000 title claims abstract description 52
- 229910052739 hydrogen Inorganic materials 0.000 title claims abstract description 52
- UFHFLCQGNIYNRP-UHFFFAOYSA-N Hydrogen Chemical compound [H][H] UFHFLCQGNIYNRP-UHFFFAOYSA-N 0.000 title claims abstract description 51
- 239000000446 fuel Substances 0.000 title claims abstract description 44
- 229910052751 metal Inorganic materials 0.000 claims abstract description 75
- 239000002184 metal Substances 0.000 claims abstract description 75
- OKTJSMMVPCPJKN-UHFFFAOYSA-N Carbon Chemical compound [C] OKTJSMMVPCPJKN-UHFFFAOYSA-N 0.000 claims abstract description 69
- 229910052799 carbon Inorganic materials 0.000 claims abstract description 55
- 238000003825 pressing Methods 0.000 claims abstract description 31
- 239000012528 membrane Substances 0.000 claims abstract description 18
- 229910002804 graphite Inorganic materials 0.000 claims abstract description 14
- 239000010439 graphite Substances 0.000 claims abstract description 14
- 238000007599 discharging Methods 0.000 claims abstract description 8
- 238000000034 method Methods 0.000 claims description 28
- 238000007789 sealing Methods 0.000 claims description 22
- QVGXLLKOCUKJST-UHFFFAOYSA-N atomic oxygen Chemical compound [O] QVGXLLKOCUKJST-UHFFFAOYSA-N 0.000 claims description 9
- 239000001301 oxygen Substances 0.000 claims description 9
- 229910052760 oxygen Inorganic materials 0.000 claims description 9
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 claims description 4
- -1 hydrogen ions Chemical class 0.000 claims description 3
- 230000000149 penetrating effect Effects 0.000 claims description 3
- 230000002093 peripheral effect Effects 0.000 claims description 3
- 239000007789 gas Substances 0.000 abstract description 8
- 238000009826 distribution Methods 0.000 abstract description 4
- 230000000903 blocking effect Effects 0.000 abstract description 2
- 238000009792 diffusion process Methods 0.000 abstract description 2
- 239000007770 graphite material Substances 0.000 abstract description 2
- 238000004519 manufacturing process Methods 0.000 abstract description 2
- 238000005516 engineering process Methods 0.000 abstract 1
- 238000001179 sorption measurement Methods 0.000 description 32
- 238000005457 optimization Methods 0.000 description 16
- 230000007246 mechanism Effects 0.000 description 15
- 230000008569 process Effects 0.000 description 10
- 230000005540 biological transmission Effects 0.000 description 9
- 238000004891 communication Methods 0.000 description 8
- 230000005611 electricity Effects 0.000 description 7
- 238000005286 illumination Methods 0.000 description 7
- 239000010410 layer Substances 0.000 description 7
- 239000000725 suspension Substances 0.000 description 7
- WHXSMMKQMYFTQS-UHFFFAOYSA-N Lithium Chemical compound [Li] WHXSMMKQMYFTQS-UHFFFAOYSA-N 0.000 description 6
- 229910052744 lithium Inorganic materials 0.000 description 6
- 238000000926 separation method Methods 0.000 description 5
- 238000010586 diagram Methods 0.000 description 3
- 230000000694 effects Effects 0.000 description 3
- 230000009286 beneficial effect Effects 0.000 description 2
- 238000007664 blowing Methods 0.000 description 2
- 238000005265 energy consumption Methods 0.000 description 2
- 230000002349 favourable effect Effects 0.000 description 2
- 230000000087 stabilizing effect Effects 0.000 description 2
- 238000003860 storage Methods 0.000 description 2
- 238000009966 trimming Methods 0.000 description 2
- 229910052782 aluminium Inorganic materials 0.000 description 1
- XAGFODPZIPBFFR-UHFFFAOYSA-N aluminium Chemical compound [Al] XAGFODPZIPBFFR-UHFFFAOYSA-N 0.000 description 1
- 230000008859 change Effects 0.000 description 1
- 230000000295 complement effect Effects 0.000 description 1
- 238000007405 data analysis Methods 0.000 description 1
- 239000003822 epoxy resin Substances 0.000 description 1
- 239000002737 fuel gas Substances 0.000 description 1
- 150000002431 hydrogen Chemical class 0.000 description 1
- 230000002209 hydrophobic effect Effects 0.000 description 1
- 239000000463 material Substances 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 229920000647 polyepoxide Polymers 0.000 description 1
- 238000010248 power generation Methods 0.000 description 1
- 230000002035 prolonged effect Effects 0.000 description 1
- 230000004044 response Effects 0.000 description 1
- 239000002356 single layer Substances 0.000 description 1
- 230000001360 synchronised effect Effects 0.000 description 1
- 238000003466 welding Methods 0.000 description 1
- 238000004804 winding Methods 0.000 description 1
Classifications
-
- H—ELECTRICITY
- H01—ELECTRIC ELEMENTS
- H01M—PROCESSES OR MEANS, e.g. BATTERIES, FOR THE DIRECT CONVERSION OF CHEMICAL ENERGY INTO ELECTRICAL ENERGY
- H01M8/00—Fuel cells; Manufacture thereof
- H01M8/02—Details
- H01M8/0202—Collectors; Separators, e.g. bipolar separators; Interconnectors
-
- H—ELECTRICITY
- H01—ELECTRIC ELEMENTS
- H01M—PROCESSES OR MEANS, e.g. BATTERIES, FOR THE DIRECT CONVERSION OF CHEMICAL ENERGY INTO ELECTRICAL ENERGY
- H01M8/00—Fuel cells; Manufacture thereof
- H01M8/02—Details
-
- H—ELECTRICITY
- H01—ELECTRIC ELEMENTS
- H01M—PROCESSES OR MEANS, e.g. BATTERIES, FOR THE DIRECT CONVERSION OF CHEMICAL ENERGY INTO ELECTRICAL ENERGY
- H01M8/00—Fuel cells; Manufacture thereof
- H01M8/02—Details
- H01M8/0271—Sealing or supporting means around electrodes, matrices or membranes
- H01M8/0276—Sealing means characterised by their form
- H01M8/0278—O-rings
-
- 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
- Y02E60/30—Hydrogen technology
- Y02E60/50—Fuel cells
-
- 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
- Y02P—CLIMATE CHANGE MITIGATION TECHNOLOGIES IN THE PRODUCTION OR PROCESSING OF GOODS
- Y02P70/00—Climate change mitigation technologies in the production process for final industrial or consumer products
- Y02P70/50—Manufacturing or production processes characterised by the final manufactured product
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- Life Sciences & Earth Sciences (AREA)
- Engineering & Computer Science (AREA)
- Manufacturing & Machinery (AREA)
- Sustainable Development (AREA)
- Sustainable Energy (AREA)
- Chemical & Material Sciences (AREA)
- Chemical Kinetics & Catalysis (AREA)
- Electrochemistry (AREA)
- General Chemical & Material Sciences (AREA)
- Fuel Cell (AREA)
- Electric Propulsion And Braking For Vehicles (AREA)
Abstract
The invention relates to a hydrogen fuel cell, an automobile and an unmanned aerial vehicle, wherein the hydrogen fuel cell comprises the following components: at least one battery unit arranged between the upper pressing plate and the lower pressing plate, which is characterized in that: the battery unit comprises the following components in a laminated mode: metal corrugated sheet, graphite paper, grooved carbon paper, upper carbon paper, membrane electrode, lower carbon paper and metal mesh; the upper pressing plate is provided with an air inlet and an air outlet, the grooved carbon paper comprises at least one layer of carbon paper, a plurality of grooves which are distributed in parallel are distributed on the grooved carbon paper, and the grooves are suitable for exhausting air from the air inlet to the air outlet. The grooves of the grooved carbon paper are used for uniformly distributing hydrogen and discharging moisture on the hydrogen side so as to prevent the moisture from blocking the hydrogen side. Compared with the current technology, the baffle made of graphite material has small volume, light weight, good gas diffusion and even gas distribution. The volume and weight of the hydrogen fuel cell are greatly reduced, and the production and use costs are reduced.
Description
Technical Field
The invention relates to a hydrogen fuel cell, an automobile and an unmanned aerial vehicle.
Background
The existing hydrogen fuel cell has large volume and weight, and is mainly formed by engraving materials such as a guide plate for guiding fuel hydrogen and the like by graphite.
Therefore, how to reduce the volume and weight of the hydrogen fuel cell is a technical problem in the art.
Disclosure of Invention
The invention aims to provide a hydrogen fuel cell with small volume and weight, and an automobile and an unmanned aerial vehicle applying the hydrogen fuel cell.
A hydrogen fuel cell for achieving the object of the present invention comprises: at least one battery unit arranged between the upper pressing plate and the lower pressing plate, wherein the battery unit comprises a plurality of battery units which are sequentially laminated: metal corrugated sheet, graphite paper, grooved carbon paper, upper carbon paper, membrane electrode, lower carbon paper and metal mesh; the upper pressing plate is provided with an air inlet and an air outlet, the grooved carbon paper comprises at least one layer of carbon paper, a plurality of grooves which are distributed in parallel are distributed on the grooved carbon paper, and the grooves are suitable for exhausting air from the air inlet to the air outlet.
The plurality of battery cell pairs Ji Dieceng are connected in series between the upper and lower pressure plates.
The metal corrugated sheet includes: a planar metal sheet and a corrugated metal sheet fixed to the planar metal sheet; the metal corrugated sheets, the graphite paper, the grooved carbon paper, the upper carbon paper, the membrane electrode, the lower carbon paper and the metal mesh are arranged in a laminated manner, through holes are formed in two ends of the metal corrugated sheets, the graphite paper, the grooved carbon paper, the upper carbon paper, the membrane electrode, the lower carbon paper and the metal mesh, and sealing rings are arranged on the oxygen supply side of the membrane electrode in a penetrating manner in the through holes at the end parts of the lower carbon paper and the metal mesh; the end part of the sealing ring, which extends out of the through hole, is matched with the top edge of the through hole on the plane metal sheet in another battery unit below in a pressure sealing way, and the through holes on the same side in each battery unit are coaxially distributed to form an air passage.
The bottom surfaces of the air inlet and the air outlet of the upper pressing plate are respectively in sealing fit with the top surfaces of a pair of through holes on the planar metal sheets in the adjacent metal corrugated sheets through sealing rings, so that each air passage is respectively communicated with the air inlet and the air outlet in a sealing way.
The air inlet and the air outlet are respectively arranged at two sides adjacent to the upper pressing plate; the through holes on the plane metal sheet and the corrugated metal sheet are coaxially distributed, and the diameter of the through hole on the plane metal sheet is smaller than that of the through hole on the corrugated metal sheet, so that the sealing ring can conveniently pass through the through hole on the corrugated metal sheet to be in sealing fit with the edge of the through hole on the plane metal sheet.
The peripheral edges of the upper and lower pressing plates are fixed with each other by bolts.
The working method of the hydrogen fuel cell comprises the following steps:
A. when the hydrogen fuel cell is installed, the metal corrugated sheets are basically vertically distributed, and spaces are arranged above and below the hydrogen fuel cell and are communicated with the outside air;
B. connecting the two electrodes of the load with an upper pressing plate and a lower pressing plate respectively;
C. the air inlet is communicated with a hydrogen gas source, and voltage is generated between the upper pressing plate and the lower pressing plate and drives a load; the oxygen in each strip-shaped groove passes through the metal mesh and the carbon paper and then is combined with hydrogen ions passing through the membrane electrode to generate water, voltage and driving load are generated, and the hydrogen fuel cell is heated, so that air flows upwards in each strip-shaped groove on each corrugated metal sheet, and the air is updated.
The unmanned aerial vehicle adopts the hydrogen fuel cell as a power source, and meanwhile, the unmanned aerial vehicle is also provided with a lithium battery as the power source.
The invention further provides the vertical take-off power supply system and the working method of the unmanned aerial vehicle, so that the self-power consumption of the unmanned aerial vehicle during vertical take-off is effectively reduced.
In order to solve the above technical problems, the present invention provides a vertical takeoff power supply system in the unmanned aerial vehicle, including: the power supply device is positioned on the ground; the power supply device is suitable for keeping supplying power to the unmanned aerial vehicle when the unmanned aerial vehicle vertically takes off; and when the unmanned aerial vehicle reaches a preset height, the unmanned aerial vehicle is separated from the power supply device to supply power.
Further, the vertical take-off power supply system of the unmanned aerial vehicle further comprises: the adsorption device and the charging end; the adsorption device is suitable for enabling a plug of the charging end to be inserted into the charging interface of the unmanned aerial vehicle, and when the unmanned aerial vehicle reaches a preset height, the adsorption device drives the charging end to fall off, so that the unmanned aerial vehicle is separated from the power supply device to supply power; and a wire wheel for coiling the transmission wire is arranged at the power supply device.
Further, the power supply device includes: the main processor module is connected with the main power line carrier module; the adsorption device comprises: the slave processor module is connected with the slave power line carrier module and is used for controlling the electromagnet which is powered on or powered off by the slave processor; the secondary processor module is further suitable for acquiring real-time height data of the unmanned aerial vehicle, and after the unmanned aerial vehicle reaches a preset height, the secondary processor module controls the electromagnet to lose electricity so as to realize automatic separation of the charging end and the unmanned aerial vehicle; the adsorption device is also suitable for sending the real-time height data to the power supply device through a power line carrier mode; if after the unmanned aerial vehicle reaches the preset height, the charging end is not separated from the unmanned aerial vehicle, a power line carrier signal for enabling the electromagnet to lose electricity is sent to the adsorption device through the power supply device, and the charging end is manually separated from the unmanned aerial vehicle.
In still another aspect, the invention further provides a working method of the vertical take-off power supply system of the unmanned aerial vehicle.
The vertical take-off power supply system of the unmanned aerial vehicle comprises: the power supply device is positioned on the ground;
the working method comprises the following steps: the power supply device is suitable for keeping supplying power to the unmanned aerial vehicle when the unmanned aerial vehicle vertically takes off; and when the unmanned aerial vehicle reaches a preset height, the unmanned aerial vehicle is separated from the power supply device to supply power.
Further, the vertical takeoff power supply system further includes: the adsorption device and the charging end; the adsorption device is suitable for enabling a plug of the charging end to be inserted into the charging interface of the unmanned aerial vehicle, and when the unmanned aerial vehicle reaches a preset height, the adsorption device drives the charging end to fall off; the unmanned aerial vehicle is separated from the power supply device to supply power; a wire wheel for coiling the transmission wire is arranged at the power supply device; the power supply device includes: the main processor module is connected with the main power line carrier module; the adsorption device comprises: the slave processor module is connected with the slave power line carrier module and is used for controlling the electromagnet which is powered on or powered off by the slave processor; the secondary processor module is further suitable for acquiring real-time height data of the unmanned aerial vehicle, and after the unmanned aerial vehicle reaches a preset height, the secondary processor module controls the electromagnet to lose electricity so as to realize automatic separation of the charging end and the unmanned aerial vehicle; the adsorption device is also suitable for sending the real-time height data to the power supply device through a power line carrier mode; if after the unmanned aerial vehicle reaches the preset height, the charging end is not separated from the unmanned aerial vehicle, a power line carrier signal for enabling the electromagnet to lose electricity is sent to the adsorption device through the power supply device, and the charging end is manually separated from the unmanned aerial vehicle.
The vertical take-off power supply system and the working method thereof have the beneficial effects that: when unmanned aerial vehicle takes off perpendicularly through power supply unit, last to supply power to unmanned aerial vehicle, satisfy perpendicular electric energy demand of taking off, greatly reduced unmanned aerial vehicle self's electric energy consumption, prolonged unmanned aerial vehicle mileage and time of cruising.
In a third aspect, the present invention also provides an unmanned aerial vehicle, comprising: the system comprises an airborne processor module, an unmanned aerial vehicle power system controlled by the airborne processor module and the vertical take-off power supply system; when the unmanned aerial vehicle is separated from the power supply device for supplying power, the power supply system in the unmanned aerial vehicle is switched to supply power.
Further, the unmanned aerial vehicle power system includes: a horizontal power subsystem and a vertical power subsystem controlled by an onboard processor module; wherein the horizontal power subsystem is located at the fuselage and comprises: a horizontal propeller mechanism; the vertical power subsystem includes: vertical propeller mechanisms symmetrically arranged at the left wing and the right wing; and the onboard processor module is further connected with a gyroscope for detecting the flight attitude of the unmanned aerial vehicle and a GPS module for positioning the unmanned aerial vehicle.
Further, the vertical propeller mechanism comprises at least one vertical propeller, a suspension device used for suspending the vertical propeller mechanism below the wing, and the vertical propeller is suitable for being driven to rotate by a corresponding micro motor; the suspension device includes: a first angle trim motor adapted to tilt the vertical propeller forward or backward, and a second angle trim motor to tilt the vertical propeller left or right; the first angle fine-tuning motor, the second angle fine-tuning motor and the miniature motor are controlled by an onboard processor module to adjust the inclination angle of the vertical propeller and the rotating speed of the vertical propeller according to the flying gesture.
Further, the unmanned aerial vehicle is also provided with a wind direction sensor and a wind speed sensor for detecting the crosswind in the flying process, and the wind direction sensor and the wind speed sensor are suitable for sending the wind direction and wind speed data of the crosswind born by the current unmanned aerial vehicle to an airborne processor module; the machine-mounted processor module is suitable for adjusting the inclination angle of the vertical propeller and the rotating speeds of the vertical and horizontal propellers according to the wind direction and the wind speed data of the crosswind so as to stabilize the current flight attitude.
In a fourth aspect, the invention further provides a working method of the unmanned aerial vehicle.
When the unmanned aerial vehicle vertically takes off, the unmanned aerial vehicle keeps supplying power to the unmanned aerial vehicle through a power supply device; and when the unmanned aerial vehicle reaches a preset height, the unmanned aerial vehicle is separated from the power supply device to supply power.
An electric vehicle using the hydrogen fuel cell as a power source.
The aircraft adopts the hydrogen fuel cell as a power supply, the aircraft needs manual driving, an electric engine is adopted, and meanwhile, the aircraft is also provided with a lithium battery as a power source.
The hydrogen fuel cell of the invention has the beneficial effects that: (1) The concave-convex on the metal corrugated sheet is used for forming a strip-shaped groove, discharging water of the oxygen electrode and flowing air to provide oxygen and dissipate heat. The grooves of the grooved carbon paper are used for uniformly distributing hydrogen and discharging moisture on the hydrogen side so as to prevent the moisture from blocking the hydrogen side. The metal plate, the grooved carbon paper and the membrane electrode share a through hole, and a sealing ring is adhered to the oxygen side of the membrane electrode and then is sealed with the metal plate of the next single cell by pressure. Thus, the air flowing channels are formed in series. The carbon paper is used for conducting, hydrophobic and gas distribution; the carbon paper has good gas diffusion and uniform gas distribution. (2) Compared with the gas guide plate made of graphite materials or epoxy resin plates in the prior art, the slotted carbon paper is used for realizing the effect of guiding fuel gas, and has the advantages of small volume, light weight, good gas diffusivity and uniform gas distribution. The volume and weight of the hydrogen fuel cell are greatly reduced, and the production and use cost is reduced (taking a 500W hydrogen fuel cell as an example, compared with the traditional hydrogen fuel cell, the invention has the advantages of 30-40% lighter weight, 35-50% smaller volume and 35% lower cost). (3) The unmanned aerial vehicle and the working method thereof can stabilize the flight attitude of the unmanned aerial vehicle in the take-off or cruising process, and when encountering side wind, the function is particularly suitable for aerial photography by adjusting the inclination angle of the vertical propeller and the rotating speeds of the vertical and horizontal propellers so as to stabilize the current flight attitude.
Drawings
The invention is further illustrated by the following examples in conjunction with the accompanying drawings:
fig. 1 is a schematic cross-sectional exploded structure of a cell unit in a hydrogen fuel cell of the present invention;
fig. 2 is a schematic cross-sectional structure of a hydrogen fuel cell of the present invention;
fig. 3 is a schematic view of a sectional assembly structure of the battery cell;
FIG. 4 is a schematic cross-sectional view of a corrugated metal sheet of the present invention;
FIG. 5 is a schematic view of a hydrogen fuel cell of the present invention in use;
FIG. 6 is a rear view of the metal corrugated sheet of the present invention;
FIG. 7 is a schematic diagram of the operation of the vertical takeoff power system of the present invention;
FIG. 8 is a schematic block diagram of a vertical takeoff power supply system of the present invention;
FIG. 9 is a control schematic of the drone of the present invention;
fig. 10 is a schematic structural view of the unmanned aerial vehicle of the present invention;
FIG. 11 is a block diagram of the vertical propeller mechanism of the present invention;
in the figure: the graphite paper comprises a metal corrugated sheet 1, graphite paper 2, slotted carbon paper 3, upper carbon paper 4, a membrane electrode 5, a metal mesh 7, an upper pressing plate 8, an exhaust port 9, a planar metal sheet 11, a corrugated metal sheet 12, a sealing ring 13 and an air inlet 14; the power supply device 10, the adsorption device 101, the plug 102, the power transmission wire 103, the wire wheel 104, the unmanned aerial vehicle 20, the horizontal power subsystem 30, the horizontal propeller 301, the vertical power subsystem 40, the vertical propeller 401, the micro motor 402, the wing 50, the suspension device 60, the first angle fine adjustment motor 601 and the second angle fine adjustment motor 602.
Description of the embodiments
The invention will now be described in further detail with reference to the accompanying drawings. The drawings are simplified schematic representations which merely illustrate the basic structure of the invention and therefore show only the structures which are relevant to the invention.
Examples
As shown in fig. 1, a hydrogen fuel cell includes: one or more battery cells 100 disposed between upper and lower pressure plates (typically of aluminum) comprising, in order: the graphite paper comprises a metal corrugated sheet 1, graphite paper 2, slotted carbon paper 3, upper carbon paper 4, a membrane electrode 5, lower carbon paper and a metal mesh 7; the upper pressing plate is provided with an air inlet and an air outlet, the grooved carbon paper 3 comprises at least one layer of carbon paper, a plurality of parallel grooves are distributed on the grooved carbon paper, and the grooves are suitable for discharging air from the air inlet to the air outlet.
Hereinafter, a plurality of the battery cell pairs Ji Dieceng are exemplified as being connected in series between the upper and lower pressing plates.
As shown in fig. 4, the metal corrugated sheet 1 includes: a planar metal sheet 11 and a corrugated metal sheet 12 fixed to the planar metal sheet 11 by spot welding; the metal corrugated sheet 1, the graphite paper 2, the slotted carbon paper 3, the upper carbon paper 4, the membrane electrode 5, the lower carbon paper and the metal mesh 7 which are arranged in a laminated way are provided with through holes at two ends, and a sealing ring 13 is arranged on the oxygen supply side of the membrane electrode 5 and in the through holes at the end parts of the lower carbon paper and the metal mesh 7 in a penetrating way; the end of the sealing ring 13 extending out of the through hole is in press-sealing fit with the top edge of the through hole on the plane metal sheet in another battery unit below, and the through holes on the same side in each battery unit are coaxially distributed to form an air passage. The upper carbon paper 4 and the lower carbon paper are single-layer or multi-layer carbon paper.
The bottom surfaces of the air inlet and the air outlet of the upper pressing plate are respectively matched with the top surfaces of a pair of through holes on the plane metal sheet 11 in the adjacent metal corrugated sheet 1 in a sealing way through sealing rings, so that each air passage is respectively communicated with the air inlet and the air outlet in a sealing way.
The air inlet and the air outlet are respectively arranged at two sides adjacent to the upper pressing plate; the through holes on the plane metal sheet and the corrugated metal sheet are coaxially distributed, and the diameter of the through hole on the plane metal sheet is smaller than that of the through hole on the corrugated metal sheet, so that the sealing ring can conveniently pass through the through hole on the corrugated metal sheet to be in sealing fit with the edge of the through hole on the plane metal sheet.
The peripheral edges of the upper and lower pressing plates are fixed with each other by bolts.
The working method of the hydrogen fuel cell comprises the following steps:
A. when the hydrogen fuel cell is installed, the metal corrugated sheet 1 is basically vertically distributed, and spaces are arranged above and below the hydrogen fuel cell and are communicated with the outside air;
B. connecting the two electrodes of the load with an upper pressing plate and a lower pressing plate respectively;
C. the air inlet is communicated with a hydrogen gas source, and voltage is generated between the upper pressing plate and the lower pressing plate and drives a load; the oxygen in each strip-shaped groove passes through the metal mesh 7 and the carbon paper and then is combined with hydrogen ions passing through the membrane electrode to generate water, voltage and driving load are generated, and the hydrogen fuel cell is heated, so that air flows upwards in each strip-shaped groove on each corrugated metal sheet, and the air is updated.
In order to increase the air flow rate and the power of the hydrogen fuel cell, a fan or a high-pressure air flow nozzle is arranged on one side of the metal corrugated sheet 1 and at the end part of the strip-shaped groove, and the high-pressure air flow nozzle is connected with a compressed air source.
Examples
The unmanned aerial vehicle adopts the hydrogen fuel cell of the embodiment 1 as a power source, and meanwhile, a lithium battery is further arranged on the unmanned aerial vehicle and is used as the power source.
Examples
An automobile adopts the hydrogen fuel cell of the embodiment 1 as a power source, and a lithium battery is also arranged on the unmanned aerial vehicle as the power source.
The vehicle may also be a hybrid vehicle.
Examples
As shown in fig. 6-10, the present embodiment provides a vertical takeoff power supply system in an unmanned aerial vehicle of embodiment 2, including: a power supply unit 10 located on the ground; the power supply device 10 is suitable for keeping supplying power to the unmanned aerial vehicle 20 when the unmanned aerial vehicle 20 vertically takes off; and when the unmanned aerial vehicle 20 reaches the preset height, the unmanned aerial vehicle 20 is separated from the power supply device 10 to supply power.
As an alternative embodiment of the vertical takeoff power supply system, the vertical takeoff power supply system further includes: the adsorption device and the charging end; the adsorption device is suitable for enabling the plug 102 of the charging end to be inserted into the charging interface of the unmanned aerial vehicle, and when the unmanned aerial vehicle reaches a preset height, the adsorption device drives the charging end to fall off, so that the unmanned aerial vehicle is separated from the power supply device to supply power; and a reel 104 for winding the power transmission line 103 is provided at the power supply device 10.
Specifically, the power supply device includes: the main processor module is connected with the main power line carrier module; the adsorption device comprises: and the slave processor module is connected with the slave power line carrier module and is used for controlling the electromagnet which is powered on or powered off by the slave processor.
In order to make unmanned aerial vehicle reach predetermined height after, can automatic and charge the end separation, follow the processor module and still be suitable for obtaining unmanned aerial vehicle's real-time height data, and after unmanned aerial vehicle reached predetermined height, by follow processor module control electro-magnet loss of power, realize charging end and unmanned aerial vehicle autosegregation.
If the automatic separation fails, adopting corresponding emergency measures, wherein the adsorption device is also suitable for sending the real-time height data to the power supply device in a power line carrier mode; if after the unmanned aerial vehicle reaches the preset height, the charging end is not separated from the unmanned aerial vehicle, a power line carrier signal for enabling the electromagnet to lose electricity is sent to the adsorption device through the power supply device, and the charging end is manually separated from the unmanned aerial vehicle.
For example, the adsorption device is provided with an emergency release button, and when the emergency release button is pressed, the main processor module is suitable for sending a power line carrier signal for powering down the electromagnet to the adsorption device.
The real-time height data of unmanned aerial vehicle is suitable for obtaining the flight height through MS5540C digital atmospheric pressure sensor, including carrying out data communication's data communication mouth with unmanned aerial vehicle in the adsorption equipment, and carry out data transmission through this data communication mouth, when adsorption equipment and aircraft disconnect-type, this data communication mouth also breaks off thereupon, further, can make power supply unit obtain aircraft corresponding parameter through this data communication mouth, this mode is more reliable than wireless mode, guarantees that unmanned aerial vehicle can be stable, reliable when vertical take off reaches predetermined height. The flight response data includes, but is not limited to: altitude, current aircraft power, attitude, altitude wind direction, and wind speed (described in detail in examples 3 and 4).
The adsorption device and the charging end are powered by a direct current mode or an alternating current mode as a power supply device.
If a direct current transmission mode is adopted, the power supply device is suitable for converting commercial power voltage into direct current and then transmitting the direct current to the adsorption device and the charging end through the boosting module, the electromagnet in the adsorption device is suitable for adopting a direct current electromagnet, and the charging end comprises the boosting module and is used for boosting the direct current voltage which is reduced by the transmission wire and connecting the charging and discharging control module in the unmanned aerial vehicle through the plug.
If an alternating current mode is adopted, an AD-DC module is arranged at the charging end to convert alternating current into direct current to provide a non-unmanned aerial vehicle charging and discharging control module if an alternating current transmission mode is adopted; and said electromagnet is adapted to use an alternating current electromagnet.
The master and slave power line carrier modules are used for example and not limited to SENS-00 power line carrier modules, the master and slave processor modules are used for example and not limited to STC series singlechips, and the embedded processor can be used for controlling the electromagnet to obtain or lose power by controlling an electronic switch of a power supply end of the electromagnet.
Examples
On the basis of embodiment 4, embodiment 5 also provides a working method of the vertical take-off power supply system, namely, the power supply device is suitable for keeping supplying power to the unmanned aerial vehicle during vertical take-off of the unmanned aerial vehicle; and when the unmanned aerial vehicle reaches a preset height, the unmanned aerial vehicle is separated from the power supply device to supply power.
The vertical takeoff power supply system further comprises: the adsorption device and the charging end; the adsorption device is suitable for enabling a plug of the charging end to be inserted into the charging interface of the unmanned aerial vehicle, and when the unmanned aerial vehicle reaches a preset height, the adsorption device drives the charging end to fall off; the unmanned aerial vehicle is separated from the power supply device to supply power; the power supply device is provided with a wire wheel for coiling the transmission wire.
The power supply device includes: the main processor module is connected with the main power line carrier module; the adsorption device comprises: the slave processor module is connected with the slave power line carrier module and is used for controlling the electromagnet which is powered on or powered off by the slave processor; the secondary processor module is further suitable for acquiring real-time height data of the unmanned aerial vehicle, and after the unmanned aerial vehicle reaches a preset height, the secondary processor module controls the electromagnet to lose electricity so as to realize automatic separation of the charging end and the unmanned aerial vehicle; the adsorption device is also suitable for sending the real-time height data to the power supply device through a power line carrier mode; if after the unmanned aerial vehicle reaches the preset height, the charging end is not separated from the unmanned aerial vehicle, a power line carrier signal for enabling the electromagnet to lose electricity is sent to the adsorption device through the power supply device, and the charging end is manually separated from the unmanned aerial vehicle.
Examples
On the basis of embodiment 4 or 5, this embodiment 6 also provides an unmanned aerial vehicle.
The unmanned aerial vehicle includes: the system comprises an airborne processor module, an unmanned aerial vehicle power system controlled by the airborne processor module and the vertical take-off power supply system; when the unmanned aerial vehicle is separated from the power supply device for supplying power, the power supply system in the unmanned aerial vehicle is switched to supply power.
The power supply system in the unmanned aerial vehicle includes: and the charge and discharge control module and the lithium battery. The hydrogen fuel cell charges the lithium battery through the charge-discharge control module.
The unmanned aerial vehicle power system includes: a horizontal power subsystem 30 and a vertical power subsystem 40 controlled by an on-board processor module; wherein the horizontal power subsystem 30 is located at the fuselage and comprises: a horizontal propeller mechanism; the vertical power subsystem 40 includes: vertical propeller 401 mechanism symmetrically arranged at the left and right wings 50; and the onboard processor module is further connected with a gyroscope for detecting the flight attitude of the unmanned aerial vehicle and a GPS module for positioning the unmanned aerial vehicle.
The vertical propeller 401 mechanism comprises at least one vertical propeller 401, a suspension device 60 for suspending the vertical propeller 401 mechanism below the wing 50, the vertical propeller 401 being adapted to be driven in rotation by a corresponding micro-motor 402; the suspension device 60 includes: a first angle trim motor 601 adapted to tilt the vertical propeller 401 forward or backward (as in the direction F1 in fig. 11), and a second angle trim motor 602 adapted to tilt the vertical propeller 401 left or right (as in the direction F2 in fig. 11); wherein the first and second angle fine tuning motors and the micro motor 402 are controlled by an on-board processor module to adjust the inclination angle of the vertical propeller 401 and the rotation speed of the vertical propeller 401 according to the flight attitude.
In fig. 11 a vertical propeller 401 comprises two vertical propellers 401 and is arranged symmetrically back and forth, and therefore also comprises two second angle trim motors 602, which second angle trim motors 602 are controlled by the on-board processor module to be adapted for synchronous rotation.
The unmanned aerial vehicle is further provided with a wind direction sensor and a wind speed sensor for detecting crosswind in the flight process, and the wind direction sensor and the wind speed sensor are suitable for sending wind direction and wind speed data of the crosswind born by the current unmanned aerial vehicle to the airborne processor module; the on-board processor module is adapted to adjust the inclination angle of the vertical propeller 401 and the rotational speed of the vertical and horizontal propellers according to the wind direction and wind speed data of the crosswind, so as to stabilize the current flight attitude.
Specifically, the wind direction sensor and the wind speed sensor are used for measuring wind direction and wind speed data of the side wind actually obtained by the unmanned aerial vehicle in the flight process, and further, the inclination angle of the vertical propeller 401, namely front or back, left or right, is adjusted, and the rotating speeds of the vertical propeller and the horizontal propeller are combined, so that the effect of stabilizing the flight attitude is achieved, and if the side wind is favorable for flight, the flight efficiency is improved.
For example, the unmanned aerial vehicle flies from east to west, if a cross wind in the southwest direction is encountered, the on-board processor module is adapted to adjust the inclination angle of the vertical propeller 401, i.e. to incline in the southwest direction, so as to counteract the influence of the cross wind in the southwest direction on the flight path of the unmanned aerial vehicle; and, the rotational speed of the vertical propeller 401 is changed according to the wind speed.
Wherein the onboard processor module is, for example but not limited to, a single-chip microcomputer or an ARM processor.
Examples
On the basis of embodiment 6, the invention also provides a working method of the unmanned aerial vehicle.
Wherein the unmanned aerial vehicle is as described in embodiment 6, and the unmanned aerial vehicle keeps supplying power to the unmanned aerial vehicle through the power supply device when the unmanned aerial vehicle vertically takes off; and when the unmanned aerial vehicle reaches a preset height, the unmanned aerial vehicle is separated from the power supply device to supply power.
Preferably, the on-board processor module is further connected with a gyroscope for detecting the flight attitude of the unmanned aerial vehicle and a GPS module for positioning the unmanned aerial vehicle; the unmanned aerial vehicle power system includes: a horizontal power subsystem 30 and a vertical power subsystem 40 controlled by an on-board processor module; wherein the horizontal power subsystem 30 is located at the fuselage and includes a horizontal propeller mechanism; the vertical power subsystem 40 includes: vertical propeller 401 mechanism symmetrically arranged at the left and right wings 50; the vertical propeller 401 mechanism comprises at least one vertical propeller 401, a suspension device 60 for suspending the vertical propeller 401 mechanism below the wing 50, the vertical propeller 401 being adapted to be driven in rotation by a corresponding micro-motor 402; the suspension device 60 includes: a first angle trimming motor 601 adapted to tilt the vertical propeller 401 forward or backward, and a second angle trimming motor 602 to tilt the vertical propeller 401 leftward or rightward; wherein the first and second angle fine tuning motors and the micro motor 402 are controlled by an on-board processor module to adjust the inclination angle of the vertical propeller 401 and the rotation speed of the vertical propeller 401 according to the flight attitude.
The method for adjusting the inclination angle and the rotation speed of the vertical propeller 401 according to the flying posture includes: the on-board processor module is suitable for controlling the first angle fine adjustment motor 601 to drive the vertical propeller 401 to incline forwards, and simultaneously controlling the horizontal propeller in the horizontal propeller mechanism to work so as to shorten the time for the unmanned aerial vehicle to reach the set cruising height, and meet the cruising speed of the unmanned aerial vehicle when the unmanned aerial vehicle reaches the cruising height.
The unmanned aerial vehicle is further provided with a wind direction sensor and a wind speed sensor for detecting crosswind in the flight process, and the wind direction sensor and the wind speed sensor are suitable for sending wind direction and wind speed data of the crosswind born by the current unmanned aerial vehicle to the airborne processor module; the on-board processor module is adapted to adjust the inclination angle of the vertical propeller 401 and the rotational speeds of the vertical and horizontal propellers according to the wind direction and wind speed data of the crosswind, so as to stabilize the current flight attitude.
Specifically, the on-board processor module is adapted to adjust the inclination angle of the vertical propeller 401 and the rotational speeds of the vertical and horizontal propellers according to the wind direction and wind speed data of the crosswind, so as to stabilize the current flight attitude, and the method comprises the following steps: if the unmanned aerial vehicle hovers in the air, the horizontal propeller stops working, and the vertical propeller 401 works, and the on-board processor module is suitable for changing the inclination angle and the rotating speed of the vertical propeller 401 according to the wind direction and the wind speed data of the crosswind so as to stabilize the hovering gesture; if the unmanned aerial vehicle is cruising, the on-board processor module is adapted to change the inclination angle and the rotation speed of the vertical propeller 401 according to the wind direction and the wind speed data of the crosswind so as to maintain the cruising altitude.
The specific implementation process comprises the following steps: if the unmanned aerial vehicle is hovering under control, if the unmanned aerial vehicle encounters a crosswind from east to west, the inclination angle of the vertical propeller 401 corresponds to the direction of the crosswind so as to offset the influence of the crosswind on the flight attitude of the unmanned aerial vehicle, and the rotating speed of the vertical propeller 401 is adjusted according to the wind speed of the crosswind.
The on-board processor module is suitable for judging whether the wind direction and the wind speed of the crosswind are conducive to flying, if so, the rotating speed of the vertical propeller 401 and/or the horizontal propeller is reduced, and the cruising mileage of the unmanned aerial vehicle is improved.
The unmanned aerial vehicle's control system includes: the system comprises a processor module, a first GPS module, a second GPS module, a first control module, a second control module and a control module, wherein the processor module is used for controlling the unmanned aerial vehicle to fly according to a corresponding path;
the working method of the unmanned aerial vehicle further comprises the following steps: selecting a path from the unmanned aerial vehicle to a destination to obtain an optimal path;
the method for selecting the path from the unmanned aerial vehicle to the destination to obtain the optimal path comprises the following steps:
acquiring real-time data of wind between buildings, and establishing an air duct network between city buildings;
after the unmanned aerial vehicle sets a flight destination, a processor module in the unmanned aerial vehicle is suitable for selecting an optimal path for the unmanned aerial vehicle to fly to the destination according to an inter-building air duct network of a city through a path optimization subsystem; and is also provided with
The photovoltaic cells are covered on the wings of the unmanned aerial vehicle, and the path optimization subsystem is further suitable for obtaining the real-time illumination intensity among the buildings;
when the path optimization subsystem selects an optimal path, if two or more road sections have inter-building wind with the same data, selecting the road section with the highest real-time illumination intensity into the optimal path; and
the path optimization subsystem is also suitable for obtaining cloud layer data of the urban upper air, and avoiding a road section of a cloud layer coverage area when an optimal path is selected;
the unmanned aerial vehicle is further provided with a camera device for shooting the panorama of the building, the camera device is connected with the processor module, and the processor module is suitable for recognizing the height of the building according to the panorama of the building;
when the unmanned aerial vehicle flies in rainy and snowy weather, the path optimization subsystem is suitable for selecting a leeward road section of a building as a path selection of the unmanned aerial vehicle in an optimal path; and making the flying height of the unmanned aerial vehicle lower than the height of the building so as to shield the building from rain and snow;
the working method further comprises the following steps: the method comprises the steps that according to the flight attitude, the inclination angle and the rotation speed of the vertical propeller are adjusted, namely, the processor module is suitable for controlling the first angle fine adjustment motor to drive the vertical propeller to incline forwards, and simultaneously controlling the horizontal propeller in the horizontal propeller mechanism to work, so that the time for the unmanned aerial vehicle to reach the set cruising height is shortened, and the cruising speed of the unmanned aerial vehicle is met when the unmanned aerial vehicle reaches the cruising height; and
if the unmanned aerial vehicle hovers in the air, the horizontal propeller stops working, and the vertical propeller works, and the processor module is suitable for changing the inclination angle and the rotating speed of the vertical propeller according to the wind direction and the wind speed data of the side wind so as to stabilize the hovering gesture;
if the unmanned aerial vehicle is in cruising flight, the processor module is suitable for changing the inclination angle and the rotating speed of the vertical propeller according to the wind direction and the wind speed data of the crosswind so as to keep the cruising altitude;
the processor module is connected with a charge-discharge control module in the machine, the charge-discharge control module is suitable for sending the electric quantity of the onboard battery to the processor module, and when the electric quantity of the onboard battery is lower than a set value, the processor module controls the unmanned aerial vehicle to stop to an area with high illumination intensity so as to charge the onboard battery through the photovoltaic battery; or (b)
The processor module controls the unmanned aerial vehicle to stop to an area with larger wind power so as to generate electric energy to charge the airborne battery by blowing the horizontal propeller and/or the vertical propeller by wind; wherein the method comprises the steps of
The vertical propeller is suitable for adjusting the inclination angle through the first angle fine adjustment motor and the second angle fine adjustment motor so as to enable the vertical propeller to rotate in windward.
The unmanned aerial vehicle control system further comprises: a path optimization subsystem coupled to the processor module; the path optimization subsystem is suitable for obtaining real-time data of wind between buildings and establishing an air duct network between the city buildings; when the unmanned aerial vehicle sets a flight destination, the path optimization subsystem is suitable for selecting an optimal path for the unmanned aerial vehicle to fly to the destination according to the air duct network among the urban buildings.
The optimal path of the unmanned aerial vehicle to the destination is obtained through the path optimization subsystem, the wind direction of the inter-building wind in each inter-building wind channel is fully utilized, the flying speed is improved, and the flying energy consumption is reduced.
Specifically, real-time data of wind between each building is suitable for being obtained through the wind channel data acquisition node that distributes between each high building, wind channel data acquisition node includes: the system comprises a wind speed sensor and a wind direction sensor, wherein the wind speed sensor is arranged between buildings and used for detecting wind speed and wind direction between buildings, and a node processor and a wireless module (the wireless module is preferably a 3G or 4G communication module and/or a Wifi communication module) are connected with the wind speed sensor and the wind direction sensor, namely wind speed and wind direction data are transmitted to an unmanned aerial vehicle in a wireless mode so as to carry out data analysis through a path optimization subsystem, and then an urban inter-building air duct is established.
After the unmanned aerial vehicle sets the flight destination, the path optimization subsystem or the remote server analyzes the air duct among corresponding buildings of the city which the flight path experiences, and plans out the most reasonable flight route, namely the optimal path.
Specifically, the inter-building air duct network in the city takes the intersection point of each inter-building air duct as a node, and carries out path selection according to the wind speed and wind direction data of the inter-building air duct between two adjacent nodes, namely, the corresponding inter-building air duct with the wind direction matched with the flight path is selected as a selected road section of the optimal path, so that the unmanned aerial vehicle reaches a destination as far as possible under the condition of downwind, and the purposes of improving the flight speed and reducing the fuel consumption are achieved; or selecting a road section which is upwind but has small wind speed and short distance. The specific wind speed level can be digitalized, for example, 1 level, 2 level or the like by setting a corresponding limiting value, for example, when the upwind state is met, the distance can also be set to be 10 meters, 20 meters or 30 meters or the like, for example, the road section selection condition is set to be not more than 2 level of wind speed, when the distance is not more than 20 meters, the road section can be selected, and in the optimal path planning process, if a certain road section meets the condition, the road section can be selected to be added into the optimal path.
The unmanned aerial vehicle is suitable for receiving real-time data of inter-building wind sent by the wind channel data acquisition node through the airborne wireless communication module, and the path optimization subsystem obtains an optimal path, so that the unmanned aerial vehicle flies to a target address according to the path.
The unmanned aerial vehicle control system further comprises: the map storage module is connected with the processing module, the gyroscope is used for detecting the flight attitude of the unmanned aerial vehicle, and the aircraft power subsystem is controlled by the processing module; specifically, the processor module in the unmanned aerial vehicle is also connected with a map storage module, and the processor module is suitable for matching the received optimal path with map information so as to enable the unmanned aerial vehicle to fly according to the optimal path, and the flight path and the flight gesture are corrected through the corresponding GPS module and the gyroscope in the flight process.
The unmanned aerial vehicle is further provided with a wind direction sensor and a wind speed sensor for detecting the crosswind in the flying process, and the wind direction sensor and the wind speed sensor are suitable for sending wind direction and wind speed data of the crosswind of the current unmanned aerial vehicle to the processor module; the processor module is suitable for adjusting the inclination angle of the vertical propeller and the rotating speeds of the vertical and horizontal propellers according to the wind direction and the wind speed data of the crosswind so as to stabilize the current flight attitude.
If the unmanned aerial vehicle flies among buildings in the city, the crosswind belongs to one of the wind among the buildings.
Specifically, the wind direction sensor and the wind speed sensor on the unmanned aerial vehicle are used for measuring the wind direction and the wind speed data of the side wind actually obtained by the unmanned aerial vehicle in the flight process, and then the wind direction and the wind speed data of the side wind are adjusted through the inclination angle of the vertical propeller, namely front or back, left or right, and the rotation speeds of the vertical propeller and the horizontal propeller are combined to play the effect of stabilizing the flight posture, and if the side wind is favorable for the flight, the rotation speed of the horizontal propeller can be properly reduced to save the electric energy.
For example, the unmanned aerial vehicle flies from east to west, if the unmanned aerial vehicle encounters a crosswind in the southwest direction, the processor module is suitable for adjusting the inclination angle of the vertical propeller, namely, inclining in the southwest direction so as to counteract the influence of the crosswind in the southwest direction on the flight path of the unmanned aerial vehicle; and the rotating speed of the vertical propeller is changed according to the wind speed. Or when the unmanned aerial vehicle is utilized to transport express delivery, the unmanned aerial vehicle can keep stable hovering gesture to guarantee that the flight height is matched with the delivery floor, improve the accuracy of delivery, reduce unmanned aerial vehicle collision probability.
The photovoltaic cells are covered on the wings of the unmanned aerial vehicle, the path optimization subsystem is further suitable for obtaining real-time illumination intensity among all buildings, and when the path optimization subsystem or the remote server selects an optimal path, if two or more road sections have the same data of inter-building wind, the road section with the maximum real-time illumination intensity is selected into the optimal path. The real-time illumination intensity of a road section is calculated according to the geographical position of the road section, the sun position of the time period when the unmanned aerial vehicle passes through the road section, the corresponding weather condition and other factors.
Further, the path optimization subsystem is further adapted to obtain cloud layer data of the urban overhead, and avoid a road section of the cloud layer coverage area when an optimal path is selected; and the processor module is also connected with an image pick-up device for shooting the panorama of the building, and the processor module is suitable for identifying the height of the building according to the panorama of the building; when the unmanned aerial vehicle flies in rainy and snowy weather, the path optimization subsystem is suitable for selecting a leeward road section of a building as a path selection of the unmanned aerial vehicle in an optimal path; and the flying height of the unmanned aerial vehicle is made lower than the height of the building (preferably 3-10 m lower than the top level of the building and 3-5 m from the outer wall of the building) so as to shield the building from rain and snow.
Preferably, the processor module is further connected to a charge-discharge control module in the machine, and the charge-discharge control module is adapted to send the electric quantity of the onboard battery to the processor module, and when the electric quantity of the onboard battery is lower than a set value, the processor module controls the unmanned aerial vehicle to stop to an area with high illumination intensity, so as to charge the onboard battery through the photovoltaic cell; or the processor module controls the unmanned aerial vehicle to stop to an area with larger wind power so as to generate electric energy to charge the airborne battery by blowing the horizontal propeller and/or the vertical propeller by wind; the vertical propeller is suitable for adjusting the inclination angle through the first angle fine-tuning motor and the second angle fine-tuning motor so as to obtain maximum wind power and improve wind power generation efficiency. Specifically, the unmanned aerial vehicle control system further includes: the charging and discharging control module is suitable for charging the airborne battery after complementing electric energy generated by wind power and solar energy, and can be realized through a corresponding wind-solar complementary module in the prior art
With the above-described preferred embodiments according to the present invention as an illustration, the above-described descriptions can be used by persons skilled in the relevant art to make various changes and modifications without departing from the scope of the technical idea of the present invention. The technical scope of the present invention is not limited to the description, but must be determined according to the scope of claims.
Claims (5)
1. A hydrogen fuel cell comprising: at least one battery unit (100) arranged between the upper and lower pressing plates, characterized in that: the battery unit comprises the following components in a laminated mode: the graphite paper comprises a metal corrugated sheet (1), graphite paper (2), slotted carbon paper (3), upper carbon paper (4), a membrane electrode (5), lower carbon paper and a metal mesh (7);
an air inlet (14) and an air outlet (9) are arranged on the upper pressing plate (8), the grooved carbon paper (3) comprises at least one layer of carbon paper, a plurality of parallel grooves are distributed on the grooved carbon paper, and the grooves are suitable for discharging air from the air inlet to the air outlet;
a plurality of battery cell pairs Ji Dieceng are connected in series between the upper and lower pressure plates;
the metal corrugated sheet (1) comprises: a planar metal sheet and a corrugated metal sheet fixed to the planar metal sheet;
the metal corrugated sheet (1), the graphite paper (2), the slotted carbon paper (3), the upper carbon paper (4), the membrane electrode (5), the lower carbon paper and the metal mesh (7) are arranged in a laminated manner, through holes are formed in two ends of the metal corrugated sheet, the graphite paper (2), the slotted carbon paper (3), the upper carbon paper, the membrane electrode (5) and the metal mesh (7), and sealing rings are arranged in the through holes at the oxygen supply side of the membrane electrode (5) in a penetrating manner at the end parts of the lower carbon paper and the metal mesh (7);
the end of the sealing ring, which extends out of the through hole, is matched with the top edge of the through hole on the plane metal sheet in the other battery unit below in a sealing mode through pressure;
each air passage is respectively communicated with the air inlet and the air outlet in a sealing way;
the air inlet and the air outlet are respectively arranged at two sides adjacent to the upper pressing plate;
the through holes on the planar metal sheet and the corrugated metal sheet are coaxially distributed, and the diameter of the through holes on the planar metal sheet is smaller than that of the through holes on the corrugated metal sheet;
the peripheral edges of the upper and lower pressing plates are fixed with each other by bolts.
2. A method of operating a hydrogen fuel cell according to claim 1, comprising the steps of:
A. when the hydrogen fuel cell is installed, the metal corrugated sheet (1) is basically vertically distributed, and spaces are arranged above and below the hydrogen fuel cell and are communicated with the outside air;
B. connecting the two electrodes of the load with an upper pressing plate and a lower pressing plate respectively;
C. the air inlet is communicated with a hydrogen gas source, and voltage is generated between the upper pressing plate and the lower pressing plate and drives a load; the oxygen in each strip-shaped groove passes through the metal mesh (7) and the lower carbon paper and then is combined with hydrogen ions passing through the membrane electrode to generate water, voltage and driving load are generated, and the hydrogen fuel cell is heated, so that air flows upwards in each strip-shaped groove on each corrugated metal sheet, and the air is updated.
3. A drone employing the hydrogen fuel cell of claim 1 as a power source.
4. An automobile, wherein the automobile is an electric automobile using the hydrogen fuel cell according to claim 1 as a power source.
5. An aircraft employing the hydrogen fuel cell of claim 1 as a power source.
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| CN111162303B (en) * | 2019-12-31 | 2021-05-07 | 中国矿业大学 | Solid oxide fuel cell stack, and unmanned aerial vehicle range extending control system and method based on solid oxide fuel cell stack |
| CN111146472B (en) * | 2020-01-09 | 2023-09-22 | 李肖宏 | Hydrogen fuel cell |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2006302529A (en) * | 2005-04-15 | 2006-11-02 | Dainatsukusu:Kk | Manufacturing method of separator for solid polymer fuel cell |
| CN102110831A (en) * | 2009-12-24 | 2011-06-29 | 邱诗盈 | Fuel cell device |
| CN105336897A (en) * | 2015-11-20 | 2016-02-17 | 简式国际汽车设计（北京）有限公司 | Power battery box of electric vehicle |
| CN206422152U (en) * | 2016-11-25 | 2017-08-18 | 江苏冰城氢能科技有限公司 | Hydrogen fuel cell, automobile and unmanned plane |
-
2017
- 2017-02-16 CN CN201710082632.0A patent/CN108110274B/en active Active
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2006302529A (en) * | 2005-04-15 | 2006-11-02 | Dainatsukusu:Kk | Manufacturing method of separator for solid polymer fuel cell |
| CN102110831A (en) * | 2009-12-24 | 2011-06-29 | 邱诗盈 | Fuel cell device |
| CN105336897A (en) * | 2015-11-20 | 2016-02-17 | 简式国际汽车设计（北京）有限公司 | Power battery box of electric vehicle |
| CN206422152U (en) * | 2016-11-25 | 2017-08-18 | 江苏冰城氢能科技有限公司 | Hydrogen fuel cell, automobile and unmanned plane |
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Effective date of registration: 20240521 Address after: 212300 south of Qingfeng Road, Yunyang street, Danyang, Zhenjiang, Jiangsu Patentee after: Jiangsu Hydrogen Tai New Energy Co.,Ltd. Country or region after: China Address before: 212300 south of Qingfeng Road, Yunyang street, Danyang, Zhenjiang, Jiangsu Patentee before: JIANGSU BINGCHENG HYDROGEN ENERGY TECHNOLOGY CO.,LTD. Country or region before: China |