CN108470928A - Fuel system and its detection method for unmanned plane fuel cell - Google Patents
Fuel system and its detection method for unmanned plane fuel cell Download PDFInfo
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- CN108470928A CN108470928A CN201710090811.9A CN201710090811A CN108470928A CN 108470928 A CN108470928 A CN 108470928A CN 201710090811 A CN201710090811 A CN 201710090811A CN 108470928 A CN108470928 A CN 108470928A
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- 239000000446 fuel Substances 0.000 title claims abstract description 438
- 238000001514 detection method Methods 0.000 title claims description 37
- 238000012544 monitoring process Methods 0.000 claims abstract description 25
- UFHFLCQGNIYNRP-UHFFFAOYSA-N Hydrogen Chemical compound [H][H] UFHFLCQGNIYNRP-UHFFFAOYSA-N 0.000 claims description 116
- 239000001257 hydrogen Substances 0.000 claims description 103
- 229910052739 hydrogen Inorganic materials 0.000 claims description 103
- 238000010248 power generation Methods 0.000 claims description 29
- 238000012806 monitoring device Methods 0.000 claims description 25
- 238000012360 testing method Methods 0.000 claims description 19
- 239000000463 material Substances 0.000 claims description 16
- 238000004891 communication Methods 0.000 claims description 14
- 230000007797 corrosion Effects 0.000 claims description 14
- 238000005260 corrosion Methods 0.000 claims description 14
- 238000000034 method Methods 0.000 claims description 10
- 238000013461 design Methods 0.000 claims description 4
- 230000007613 environmental effect Effects 0.000 claims description 4
- 238000010926 purge Methods 0.000 claims 2
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- 230000005611 electricity Effects 0.000 abstract description 3
- 230000009467 reduction Effects 0.000 description 6
- 238000007689 inspection Methods 0.000 description 5
- 238000005452 bending Methods 0.000 description 4
- 230000008602 contraction Effects 0.000 description 4
- 150000002431 hydrogen Chemical class 0.000 description 4
- 230000001681 protective effect Effects 0.000 description 4
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- 229920002449 FKM Polymers 0.000 description 1
- CWYNVVGOOAEACU-UHFFFAOYSA-N Fe2+ Chemical compound [Fe+2] CWYNVVGOOAEACU-UHFFFAOYSA-N 0.000 description 1
- 238000006243 chemical reaction Methods 0.000 description 1
- 238000005253 cladding Methods 0.000 description 1
- 230000006835 compression Effects 0.000 description 1
- 238000007906 compression Methods 0.000 description 1
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Classifications
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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
- H01M8/00—Fuel cells; Manufacture thereof
- H01M8/24—Grouping of fuel cells, e.g. stacking of fuel cells
-
- 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
- H01M8/04—Auxiliary arrangements, e.g. for control of pressure or for circulation of fluids
- H01M8/04298—Processes for controlling fuel cells or fuel cell systems
- H01M8/04313—Processes for controlling fuel cells or fuel cell systems characterised by the detection or assessment of variables; characterised by the detection or assessment of failure or abnormal function
- H01M8/0432—Temperature; Ambient temperature
-
- 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
- H01M8/04—Auxiliary arrangements, e.g. for control of pressure or for circulation of fluids
- H01M8/04298—Processes for controlling fuel cells or fuel cell systems
- H01M8/04313—Processes for controlling fuel cells or fuel cell systems characterised by the detection or assessment of variables; characterised by the detection or assessment of failure or abnormal function
- H01M8/0438—Pressure; Ambient pressure; Flow
-
- 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
- H01M8/04—Auxiliary arrangements, e.g. for control of pressure or for circulation of fluids
- H01M8/04298—Processes for controlling fuel cells or fuel cell systems
- H01M8/04313—Processes for controlling fuel cells or fuel cell systems characterised by the detection or assessment of variables; characterised by the detection or assessment of failure or abnormal function
- H01M8/04664—Failure or abnormal function
- H01M8/04679—Failure or abnormal function of fuel cell stacks
-
- 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
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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)
Abstract
One fuel system for being used for the fuel cell of unmanned plane includes an at least fuel storage, at least a fuel channel and an at least fuel monitoring unit.The fuel storage device is set, to store the fuel needed for an electricity generation system of the fuel cell.The channel is set, the electricity generation system of the fuel pilot flow direction which is stored to the fuel cell.The fuel monitoring unit is set, to be monitored to the fuel stored by the fuel storage, by the fuel and its parameter of the fuel of the fuel channel pilot flow direction and the fuel system local environment.
Description
Technical Field
The present invention relates to a fuel cell for an unmanned aerial vehicle, and more particularly, to a fuel system for a fuel cell of an unmanned aerial vehicle and a detection method thereof.
Background
A drone refers to an unmanned aircraft managed by remote control, which includes both remote maneuvers and autonomous flying aircraft. The energy supply system is an important component of the unmanned aerial vehicle. Which is arranged to be used to provide energy to drive the drone in flight. As an energy supply system of the unmanned aerial vehicle, the unmanned aerial vehicle has various excellent performances so as to ensure good flight performance of the aircraft.
The weight of the drone affects its flight performance, so the proportion between the power that the drone energy supply system can provide and its own weight is an important parameter affecting the application of this energy supply system in the drone, which can have a very important impact on the flight performance of the aircraft.
Fuel cells are a very common type of power generation device. Since the invention of the fuel cell, the fuel cell is widely applied to various industries, and brings great convenience to human life. Different fuel cell parameters need to be configured according to different application fields and different application requirements.
The fuel system is an important component of the fuel cell and is used to provide fuel for the proper operation of the fuel cell. As an aircraft, the unmanned aerial vehicle has very strict requirements on a fuel system of a fuel cell of the unmanned aerial vehicle, so that good flight performance, long working time and good controllability of the unmanned aerial vehicle are guaranteed. However, due to the influence of various factors such as a fuel system of the fuel cell, the existing unmanned aerial vehicle has difficulty in achieving the above good performance.
The applicant of the present invention studies the unmanned aerial vehicle, the fuel cell thereof and the fuel system of the fuel cell thereof to improve the performance of the unmanned aerial vehicle.
Disclosure of Invention
An object of the present invention is to provide a fuel system for a fuel cell of an unmanned aerial vehicle and a detection method thereof, so as to improve the performance of the fuel cell and further improve the performance of the unmanned aerial vehicle.
Another object of the present invention is to provide a fuel system for a fuel cell of an unmanned aerial vehicle and a detection method thereof, which can safely, reliably and timely supply sufficient fuel, such as hydrogen, to a power generation system of the fuel cell.
Another object of the present invention is to provide a fuel system for a fuel cell of an unmanned aerial vehicle and a detection method thereof, in which the main parameters of the fuel system can be monitored in real time.
Another object of the present invention is to provide a fuel system for a fuel cell of an unmanned aerial vehicle and a detection method thereof, in which the fuel system can automatically take measures in a predetermined manner when an abnormal situation occurs.
Another object of the present invention is to provide a fuel system for a fuel cell of an unmanned aerial vehicle and a detection method thereof to provide clean fuel, such as hydrogen.
Another object of the present invention is to provide a fuel system for a fuel cell of an unmanned aerial vehicle and a detection method thereof, wherein the fuel system has a warning function.
Another object of the present invention is to provide a fuel system for a fuel cell of an unmanned aerial vehicle and a detection method thereof, wherein the fuel system can resist the influence of the motion states of vibration, inclination, acceleration, deceleration, etc. of the unmanned aerial vehicle during take-off, normal flight and landing.
Another object of the present invention is to provide a fuel system for a fuel cell of an unmanned aerial vehicle and a detection method thereof, wherein the fuel storage device of the fuel system is safe and has a long life.
Another objective of the present invention is to provide a fuel system for a fuel cell of an unmanned aerial vehicle and a detection method thereof, wherein the fuel system marks the main parameters to provide warning effect.
Another object of the present invention is to provide a fuel system for a fuel cell of an unmanned aerial vehicle and a detection method thereof, wherein the fuel system is suitable for the unmanned flight environment.
Another object of the present invention is to provide a fuel system for a fuel cell of an unmanned aerial vehicle and a detection method thereof, in which the fuel system and a connection portion between the fuel system and other systems of the fuel cell have good sealability, thereby ensuring safety.
Another object of the present invention is to provide a fuel system for a fuel cell of an unmanned aerial vehicle and a method for testing the same, in which the fuel system conforms to hydrogen characteristics and is thus suitable for supplying hydrogen feedstock.
Another object of the present invention is to provide a fuel system for fuel cell of unmanned aerial vehicle and a detection method thereof, wherein the chemical composition and structural configuration of the material selected for the connection portion of the unit device, the inner surface of the unit device directly or indirectly contacted with the fuel, the component or the sealing member can be adapted to the performance of the fuel, for example, when the fuel is hydrogen, hydrogen embrittlement, hydrogen corrosion, stress corrosion and other forms of corrosion can be avoided.
Another object of the present invention is to provide a fuel system for a fuel cell of an unmanned aerial vehicle and a method for detecting the same, in which the cabin material thereof can be moisture-proof and waterproof.
It is another object of the present invention to provide a fuel system for a fuel cell of an unmanned aerial vehicle and a method for detecting the same, wherein the cabin thereof is made of non-combustible material to prevent fire.
Another object of the present invention is to provide a fuel system for a fuel cell of an unmanned aerial vehicle and a method for inspecting the same, in which a cabin thereof should be easily installed and removed, or a cover plate thereof should be easily opened and closed, so as to facilitate inspection and maintenance of the fuel system.
Another object of the present invention is to provide a fuel system for a fuel cell of an unmanned aerial vehicle and a detection method thereof, in which the pressure of fuel can be monitored and can be fed back in real time.
Another object of the present invention is to provide a fuel system for a fuel cell of an unmanned aerial vehicle and a detection method thereof, wherein the fuel pressure, such as hydrogen pressure, which can be provided by the fuel system can be controlled to meet the demand of a stack.
Another object of the present invention is to provide a fuel system for a fuel cell of an unmanned aerial vehicle and a method for testing the same, in which the piping thereof has tightness, durability and robustness under the pressure normally used by the piping.
Another object of the present invention is to provide a fuel system for a fuel cell of an unmanned aerial vehicle and a detection method thereof, wherein the fuel system has orderly arranged pipes and accessories to avoid collision and friction with adjacent components.
Another object of the present invention is to provide a fuel system for a fuel cell of an unmanned aerial vehicle and a detection method thereof, wherein the pipelines of the fuel system include a hard pipeline and a soft pipeline, wherein for a pipe section with significant expansion and contraction caused by heat, the pipeline protection device is fully utilized to eliminate the influence of expansion and contraction caused by heat and realize the anti-seismic function.
Another object of the present invention is to provide a fuel system for fuel cell of unmanned aerial vehicle and a detection method thereof, wherein the electrical components and wiring of the fuel system can meet the requirements of safe use in terms of mechanical strength, insulation and current carrying capacity.
Another object of the present invention is to provide a fuel system for a fuel cell of an unmanned aerial vehicle and a method for detecting the same, in which the material of the fuel system electrical components can be adapted to the use environment of the fuel system, and the mechanical strength, the electrical insulation strength and the thermal insulation property of the material are good, so that the fuel system can play a role of protection even in the presence of fire and accident.
Other advantages and features of the invention will become apparent from the following description and may be realized by means of the instrumentalities and combinations particularly pointed out in the appended claims.
In accordance with the present invention, the foregoing and other objects and advantages are achieved by a fuel system for a fuel cell of a drone, comprising:
at least one fuel storage device for storing fuel required by the power generation system of the fuel cell;
at least one fuel passage for directing the fuel stored in the fuel storage device to the power generation system of the fuel cell; and
at least one fuel monitoring unit for monitoring fuel stored in the fuel storage device, fuel flowing in the fuel passage and/or fuel leaked to the environment of the fuel system.
According to some embodiments of the invention, the fuel monitoring unit comprises at least one monitoring device and at least one controller, wherein the monitoring device is arranged to monitor the fuel and its parameters in the fuel system, and wherein the controller is arranged to control the fuel and its parameters in the fuel system.
According to some embodiments of the invention, the controller comprises at least one pressure control element arranged to control the pressure of fuel exiting the fuel storage device before it enters the power generation system.
According to some embodiments of the invention, the monitoring device comprises at least two pressure sensors to monitor the fuel pressure in the fuel storage device and the fuel pressure after being controlled by the real-time pressure control assembly, respectively.
According to some embodiments of the invention, the pressure control assembly comprises at least one pressure relief valve to reduce the pressure of the fuel after it exits the fuel storage device.
According to some embodiments of the invention, the fuel monitoring unit further comprises at least one communication module, wherein the communication module is capable of transmitting data monitored by the monitoring device to the controller as a control basis for the controller.
According to some embodiments of the invention, the controller further comprises a switch control assembly, wherein the switch control assembly is configured to control whether fuel is circulated between the fuel storage device and the power generation system.
According to some embodiments of the invention, the switch control assembly comprises at least one cylinder valve disposed in the fuel storage device to control whether fuel can flow out of the fuel storage device.
According to some embodiments of the invention, the switch control assembly further comprises at least one solenoid valve, wherein the solenoid valve is disposed at a position between the pressure reducing valve and the power generation system to control whether fuel can be flowed to the power generation system.
According to some embodiments of the present invention, the pressure control assembly further comprises at least one pressure relief valve for cooperating with the pressure relief valve to reduce the fuel pressure to a predetermined pressure value.
According to some embodiments of the invention, the pressure relief valve is disposed at a position between the pressure relief valve and the solenoid valve, wherein the solenoid valve is disposed at a position between the pressure relief valve and the power generation system.
According to some embodiments of the invention, the fuel monitoring unit further comprises at least one information presentation system for presenting the parameter of the fuel and for issuing a warning signal when the parameter of the fuel reaches a predetermined value range.
According to some embodiments of the invention, the fuel passage comprises at least one soft pipe and at least one hard pipe to accommodate different pipe requirements between the fuel storage device and the power generation system, respectively.
According to some embodiments of the invention, the monitoring device further comprises at least one temperature sensor to monitor a temperature environment in which the fuel system is located.
According to some embodiments of the invention, the controller further comprises at least one temperature control device to control the temperature of the environment in which the fuel system is located.
According to some embodiments of the invention, the fuel storage device comprises at least one fuel storage tank and at least one compartment, wherein the fuel storage tank is used to store fuel, wherein the fuel storage tank is disposed within the compartment.
According to some embodiments of the invention, the fuel storage tank is a hydrogen storage bottle for storing hydrogen fuel.
According to some embodiments of the invention, the fuel storage device further comprises at least one filter, wherein the filter is disposed at the outlet of the fuel storage device to purify the fuel flowing out of the fuel storage device.
According to some embodiments of the invention, the hydrogen storage device further comprises at least one filter, wherein the filter is disposed at the outlet of the hydrogen storage cylinder to purify the hydrogen gas flowing out of the hydrogen storage cylinder.
According to some embodiments of the invention, the fuel channel and the fuel storage device are made of a material that is resistant to hydrogen embrittlement, hydrogen corrosion, and stress corrosion.
According to some embodiments of the invention, the fuel passage and the hydrogen storage cylinder are made of a material resistant to hydrogen embrittlement, hydrogen corrosion, stress corrosion.
According to some embodiments of the invention, the burst pressure of the hydrogen storage cylinder is greater than or equal to 1.5 times its operating pressure.
According to some embodiments of the invention, the burst pressure of the hydrogen storage cylinder is greater than or equal to 2 times its operating pressure.
According to some embodiments of the invention, the filter is a filter, wherein the filter is on the order of 15 μm or higher.
According to some embodiments of the invention, the design pressure of each element of the fuel storage device, the fuel passage, and the controller is greater than or equal to 1.1 times its respective operating pressure.
According to another aspect of the present invention, there is provided a method for testing a fuel system of an unmanned fuel cell, comprising the steps of:
a: setting a test environment condition;
b: detecting a starting mode and a closing mode; and
c: and detecting the stable hydrogen supply flow.
According to some embodiments of the invention, further comprising the step of:
d: detecting the hydrogen leakage rate; and
e: and detecting the vibration resistance.
According to some embodiments of the invention, further comprising the step of:
f: detecting electromagnetic compatibility; and
g: and detecting the protection grade.
According to some embodiments of the invention, further comprising the step of:
h: detection protection and alarm functions; and
i: the start-up and shut-down times are detected.
According to some embodiments of the invention, step H comprises the steps of:
h1: detecting high and low pressure protection of hydrogen;
h2: detecting alarm information; and
h3: and detecting a monitoring function.
According to some embodiments of the invention, further comprising the step of:
j: and detecting the hydrogen concentration in the cabin.
According to some embodiments of the invention, the test environmental conditions comprise:
temperature: 20 +/-10 ℃;
humidity: less than 100 percent; and
pressure: 86 to 106 kPa.
Further objects and advantages of the invention will be fully apparent from the ensuing description and drawings.
These and other objects, features and advantages of the present invention will become more fully apparent from the following detailed description, the accompanying drawings and the claims.
Drawings
Fig. 1 is a block diagram schematic diagram of a fuel system for a fuel cell of a drone in accordance with a preferred embodiment of the present invention.
Fig. 2 is a schematic structural view of the fuel system according to the above preferred embodiment of the present invention.
FIG. 3 illustrates a vibration power spectrum and acceleration spectrum applied by a vibration detection step of a fuel system detection method according to the above preferred embodiment of the present invention.
Detailed Description
The following description is presented to disclose the invention so as to enable any person skilled in the art to practice the invention. The preferred embodiments in the following description are given by way of example only, and other obvious variations will occur to those skilled in the art. The basic principles of the invention, as defined in the following description, may be applied to other embodiments, variations, modifications, equivalents, and other technical solutions without departing from the spirit and scope of the invention.
It will be understood by those skilled in the art that in the present disclosure, the terms "longitudinal," "lateral," "upper," "lower," "front," "rear," "left," "right," "vertical," "horizontal," "top," "bottom," "inner," "outer," and the like are used in an orientation or positional relationship indicated in the drawings for ease of description and simplicity of description, and do not indicate or imply that the referenced devices or components must be constructed and operated in a particular orientation and thus are not to be considered limiting.
It is understood that the terms "a" and "an" should be interpreted as meaning that a number of one element or element is one in one embodiment, while a number of other elements is one in another embodiment, and the terms "a" and "an" should not be interpreted as limiting the number.
Fig. 1-2 of the drawings disclose a fuel system of a fuel cell according to a preferred embodiment of the present invention, wherein the fuel cell is adapted to be used for a drone to provide good power to the drone and to sufficiently secure the safety of the drone.
As shown in fig. 1 of the drawings, the fuel system includes a fuel storage device 10, a fuel passage 20, and a fuel monitoring unit 30. The fuel storage device 10 is provided to store fuel required by a power generation system of the fuel cell. According to the preferred embodiment of the present invention, the fuel storage device 10 is configured to store hydrogen gas to accommodate various properties of hydrogen gas. The fuel passage 20 is provided to guide the flow of hydrogen gas stored in the fuel storage device 10 to the power generation system of the fuel cell. It is worth mentioning that the fuel channel 20 and its connections to other components of the fuel system in the power generation system of the fuel storage device 10 to the fuel cell have good gas tightness to prevent hydrogen leakage. Specifically, as shown in fig. 1 of the drawings, the fuel system further includes a plurality of sealing members to be used to enhance sealability between the respective components of the fuel system to prevent hydrogen gas leakage.
According to the preferred embodiment of the invention, the sealing element is embodied as a sealing gasket, which is made of stainless steel, non-ferrous metal, polytetrafluoroethylene or viton.
According to the preferred embodiment of the present invention, the fuel passage 20 is made of a hydrogen embrittlement resistant material. Under the usual pressures of the fuel system, the fuel passage 20 is not only leak tight, but also durable and robust, thereby extending its useful life, and thus the useful life of the fuel system.
The fuel passage 20 includes at least one soft pipe 21 and at least one hard pipe 22 to meet different requirements for directing the flow of fuel under different conditions. Some pipe sections may be subject to thermal expansion and contraction. In this case, the protection device can be arranged to eliminate the influence of expansion with heat and contraction with cold and realize the anti-seismic function. According to this preferred embodiment of the invention, the pipe, which is fixed at both ends, is provided with a suitable bend to form a curved section. Two straight pipe sections close to the bending section on two sides of the bending part of the pipeline are respectively provided with a fixed point so as to fix the pipeline. It is worth mentioning that the soft pipeline 21 is adopted to connect between the components with possible relative displacement, and the hard pipeline 22 is not used, so that the stability of the whole fuel system mechanism is guaranteed, the pipeline fracture caused by the relative displacement between the components is prevented, the fuel leakage is further prevented, and the safety is further guaranteed. The hose 21 is mounted so as to avoid friction and torsion, has a suitable bending radius, is kept at a safe distance from a harmful heat source, and takes necessary heat insulation measures. According to the preferred embodiment of the present invention, the flexible pipe 21 is fixed by using a fixing clip having elasticity, wherein the fixing point interval should not be excessively large and should be fastened before and after each bending. The connection via the hose 21 is made such that the length of the hose 21 is greater than the distance between the two parts connected by it to accommodate displacement due to external factors such as vibration. It is worth mentioning that the resonance phenomenon can be avoided in both the soft pipe 21 and the hard pipe 22. Where there are pipe sections that may be more susceptible to breakage over the entire pipe layout, these more susceptible portions are protected by a cladding component in accordance with the preferred embodiment of the present invention. It is worth mentioning that the arrangement of the covering member does not cause a malfunction.
As shown in fig. 1, the fuel system further includes a fuel monitoring unit 30 configured to monitor and control various parameters of the fuel stored in the fuel storage device 10 and the fuel of the power generation system from the fuel storage device 10 to the fuel cell. Pressure, temperature, and flow of fuel are important parameters of the fuel that can have a very significant effect on the fuel cell. The fuel monitoring unit 30 is capable of monitoring and controlling the pressure, temperature and flow of fuel.
Specifically, the fuel monitoring unit 30 includes a monitoring device 31 and a controller 34. The monitoring device 31 is arranged to monitor various parameters of the fuel. The controller 34 is arranged to control various parameters of the fuel.
As shown in fig. 1 of the drawings, the fuel monitoring unit 30 further includes a communication module 33. This communication module 33 can communicate between this monitoring devices 31 and this controller 34 to this controller 34 can regard the parameter of the fuel that this monitoring devices 31 monitored as this controller 34 to the basis that fuel parameter controlled, with guarantee this fuel system and whole fuel cell, and even this unmanned aerial vehicle's good performance.
Referring to fig. 1 of the drawings, the monitoring device 31 includes a temperature sensor 311 and at least two pressure sensors 312. According to the preferred embodiment of the present invention, the temperature sensor 311 is arranged to monitor the ambient temperature to which the fuel system is exposed. The two pressure sensors 312 are provided to monitor the pressure of the fuel at different positions, respectively.
Specifically, the controller 34 includes a pressure control assembly 342. According to the preferred embodiment of the present invention, the pressure control assembly 342 is configured to reduce the pressure of the fuel after it exits the fuel storage device 10 to accommodate the fuel pressure requirements of the power generation system of the fuel cell. According to the preferred embodiment of the present invention, two pressure sensors 312 are used to monitor the pressure of the fuel flowing out of the fuel storage device 10 and the pressure of the fuel depressurized by the pressure control assembly 342, respectively. More specifically, the pressure control assembly 342 includes at least one pressure relief valve 3421. The pressure reducing valve 3421 is provided to reduce the pressure of the fuel to a predetermined pressure value. It is worth mentioning that when one pressure reducing valve 3421 can reduce the fuel pressure to the preset pressure value, only one pressure reducing valve 3421 needs to be provided to achieve the purpose. When the fuel pressure cannot be reduced to the fuel pressure value required by the power generation system of the fuel cell by the primary pressure reduction of one pressure reduction valve 3421, another pressure reduction valve 3421 is required to provide the secondary pressure reduction. It is noted that, according to the preferred embodiment, the pressure control assembly 342 further includes a pressure relief valve 3422. The pressure relief valve 3422 is provided so as to be automatically opened when the fuel pressure cannot be reduced to the preset pressure value by the pressure reducing valve 3421 but can be reduced to a value higher than the preset pressure value, thereby releasing the fuel hydrogen gas to provide overpressure protection. It is worth mentioning that the pressure control assembly 342 may be provided with a plurality of pressure relief valves 3422 for overpressure protection at different hydrogen pressure sections. It is worth mentioning that the outlet of the pressure relief valve 3422 should be connected to one or more centralized exhaust ports through a pipeline and discharge the hydrogen gas to the outside of the robot. The diameter of the exhaust port of the pressure relief valve 3422 is not smaller than the maximum diameter of the vent line. The discharge direction should not discharge the fuel to the fuel cell chamber or the closed space, the device which is easy to generate static electricity, the exposed electric terminal, the electric switch device and the ignition source.
It should be noted that the provision of the pressure relief valve 3422 is merely an example and not a limitation of the present invention. The relief valve 3422 may not be provided if the pressure of the fuel can be reduced to the preset pressure value by the pressure reducing valve 3421. The present invention is not limited in this respect as long as the object of the present invention can be achieved.
The fuel storage device 10 includes a fuel storage tank 11. The fuel storage tank 11 is provided to store fuel in a storage space 119 thereof. According to the preferred embodiment of the present invention, the fuel storage tank 11 is embodied as a hydrogen storage bottle. The fuel storage tank 11 has an inlet 118 and an outlet 117. The inlet 118 is embodied as a fueling interface to enable the fuel system to be connected to an external hydrogen device to facilitate the filling of external hydrogen into the hydrogen storage cylinder. The fueling interface is disposed remotely from the exposed electrical terminals, the electrical switch, and the ignition source. An obvious warning sign is arranged near the fuel filling result to prevent misoperation and rotation. According to the preferred embodiment of the invention, the fuel filling interface is provided with a one-way valve to control the fuel flow direction and prevent the hydrogen backflow during hydrogenation.
Each pressure sensor 312 is embodied as a pressure sensor. As shown in fig. 2, one of the pressure sensors 312a is disposed in the fuel storage tank 11 to be used for monitoring the fuel pressure in the fuel storage tank 11. Another pressure sensor 312b is disposed behind the pressure reducing valve 3421 and the pressure relief valve 3422 to monitor the fuel pressure after being reduced and relieved.
As shown in fig. 1 of the drawings, the fuel monitoring unit 30 further includes an information presentation system 32, which is used to present the fuel parameter monitored by the monitoring device 31 and the control state of the controller. The fuel pressure monitored by the pressure sensor 312 can be presented by the information presentation system. More specifically, the information presentation system 32 includes at least one pressure presentation device 321 for presenting the fuel pressure monitored by the pressure sensor 312. The pressure sensor 312a is provided so that the pressure of hydrogen gas in the fuel storage tank 11 can be monitored in real time and then presented in real time by the pressure presentation device 321. It is worth mentioning that the pressure sensor 312a can monitor not only the fuel pressure during the use of the fuel in the fuel storage tank 11, i.e., the hydrogen pressure during the use of hydrogen gas, but also the hydrogen pressure during the filling of hydrogen gas.
As shown in fig. 1, the information presentation system 32 further includes an alert device 323 for presenting alert information. When the hydrogen pressure in the fuel storage tank 11 is higher or lower than the design value, the warning device 323 can provide a corresponding warning to indicate that the pressure in the tank is too high or too low. Similarly, when the hydrogen supply line pressure is greater than or less than the designed safety value, the warning device 323 can provide a corresponding warning to indicate that the line pressure is too high or too low.
As shown in fig. 1, the controller 34 further includes a switch control assembly 343 that is used to control the fuel flow. The switch control assembly 343 includes a cylinder valve 3431 to be used for controlling whether the fuel storage tank 11 outputs fuel. When the outlet hydrogen pressure of the fuel storage tank 11 is lower than the specified minimum pressure, it can be monitored by the monitoring device 31, and the corresponding information is transmitted to the controller 34 through the communication module 33, and is further controlled by the controller 34 to take the corresponding protective measures, such as closing the cylinder valve 3431. It is worth mentioning that the control of the fuel output of the fuel storage tank 11 by the cylinder valve 3431 is only an example and not a limitation of the present invention. According to other embodiments of the invention, it may also be controlled in other ways, for example by a solenoid valve. The present invention is not limited in this respect as long as the object of the present invention can be achieved.
As shown in fig. 1, the switch control assembly 343 further includes a solenoid valve 3432. The electromagnetic valve 3432 is disposed downstream of the pressure sensor 312b, i.e., downstream of the flow of hydrogen gas from the fuel storage tank 11 to the power generation system of the fuel cell. When the pressure sensor 312b detects that the pressure of the hydrogen gas decompressed by the decompression valve 3421 and decompressed by the decompression valve 3422 is lower than a set lowest pressure or higher than a set highest pressure, it transmits corresponding information to the controller 34 through the communication module 33, and the controller 34 can be used to control it to take protective measures, such as closing the solenoid valve 3432 of the power generation system next to the fuel cell.
The solenoid valve 3432 is provided to achieve rapid supply and shutoff of fuel hydrogen. According to the preferred embodiment of the present invention, the solenoid valve 3432 is configured to be normally closed, i.e., automatically closed when the operating power is removed, to secure the operational safety of the fuel cell.
As shown in fig. 1 of the drawings, the monitoring device 31 further includes a temperature sensor 311 for monitoring the temperature environment of the fuel system, and further transmits the monitored temperature environment information to the controller 34 through the communication module 33. According to the preferred embodiment of the present invention, the temperature sensor 311 is embodied as a temperature sensor. As shown in fig. 1, the controller 34 further includes a temperature control device 341 to control the temperature environment of the fuel system. According to the preferred embodiment of the invention, the fuel system can be suitable for the temperature environment of-20-50 ℃.
Referring to fig. 1 of the drawings, the fuel storage device 10 includes a chamber 12. The fuel storage tank 11 is disposed within the chamber 12 such that the chamber 12 provides a suitable environment for the fuel storage tank 11. More specifically, according to the preferred embodiment of the present invention, the chamber 12 is made of a waterproof, moisture-proof and non-combustible material to prevent the technical performance or use function of the individual devices or components from being affected by direct or indirect contact with water or humid gas, and to prevent fire. According to the preferred embodiment of the invention, the chamber 12 is provided with an insulating layer. The heat insulating layer is made of non-combustible material and measures for preventing the material from flying and scattering are arranged. The chamber 12 is configured for easy installation and removal or easy opening and closing of its cover to facilitate inspection and maintenance of the fuel system.
According to the preferred embodiment of the present invention, the monitoring device 31 further comprises a concentration monitoring device 313 to monitor the concentration of the fuel in the chamber 12, and transmit the concentration parameter monitored by the concentration monitoring device to the information presentation system 32 through the communication module 33. When the concentration exceeds the standard, the warning device 323 can send out a corresponding warning signal. According to the preferred embodiment of the invention, the hydrogen concentration in the chamber 12 is < 50% LFL for safety.
Those skilled in the art will appreciate that the provision of the chamber 12 is merely illustrative and not limiting of the present invention. According to other embodiments of the present invention, the chamber 12 may not be provided, and in this case, the concentration monitoring device 313 may not be provided. The concentration monitoring device 313 may also be omitted when the cabin 12 is well ventilated from the outside so that there is no risk of the concentration exceeding the standard. The present invention is not limited in this respect as long as the object of the present invention can be achieved.
It should be noted that, according to the preferred embodiment of the present invention, the communication module 33 CAN be implemented as a standard communication interface, such as CAN, RS485 or RS232, or a data interface, to receive the fuel parameter monitored by the monitoring device 31 and send a control signal to the controller, for example, to actively control the triggering of each device or component of the controller 34. The communication module 33 can also assist the controller 34 in controlling the operating state of the switch control assembly 343 based on the fuel parameter monitored by the monitoring device 31. The communication module 33 can also control the warning device 323 to send warning signals such as alarm, and transmit the signals to the remote monitoring device in a wireless manner.
As shown in fig. 1, the fuel system further includes a filter 40 to purify the fuel, thereby ensuring the purity of the fuel reaching the power generation system of the fuel cell, and further ensuring and improving the performance of the fuel cell. According to the preferred embodiment of the present invention, the filter 40 is embodied as a filter. The filter is installed at the outlet 117 of the fuel storage tank 11 to remove solid particles that may be present in the fuel hydrogen gas. Preferably, the filter is rated at not less than 15 μm. It should be understood by those skilled in the art that the filter 40 may not be provided when the fuel storage device 10 provides a fuel having a purity level that meets the requirements of the power generation system of the fuel cell. The present invention is not limited in this respect as long as the object of the present invention can be achieved.
It is worth mentioning that according to the preferred embodiment of the invention, all the pipes, valves, elements of the fuel system are designed to have a pressure at least 1.1 times their operating pressure. The burst pressure of the fuel storage tank 11 (hydrogen storage bottle) is not less than 1.5 times (working pressure is 70 MPa) or 2.0 times (working pressure is 35 MPa) of the working pressure. The design fatigue number of the fuel storage tank 11 is not less than 800. The fuel system can be used under the following environmental conditions: temperature: -20 to 50 ℃, humidity: < 100%, altitude: less than or equal to 3000 m.
The material selected for the connection points of the individual devices of the fuel system, the internal surfaces in direct or indirect contact with hydrogen, the components or the seals has the following properties:
a) necessary chemical stability under all conditions of use; various chemical reactions can not occur in normal use;
b) can adapt to the change of physical environment, meet various mechanical performance requirements and keep stable mechanical performance under the use condition;
c) the chemical composition and the structural form of the selected material can avoid hydrogen embrittlement, hydrogen corrosion, stress corrosion and other forms of corrosion;
d) the selected material meets the overall life expectancy requirements of the fuel system.
It is worth mentioning that according to the preferred embodiment of the present invention, the fuel system is started and shut down in three ways, manual, remote and automatic, to meet different requirements under different conditions, thereby fully ensuring convenience and safety of operation. The starting time and the closing time are less than or equal to 10 seconds. The fuel system should provide a stable hydrogen supply flow rate that meets 110% of the maximum power of the stack of the power generation system of the fuel cell. The hydrogen leakage per hour is less than 0.5%. The vibration resistance of the hydrogen leakage resistance test device can meet the requirement that the hydrogen leakage amount per hour is less than 0.5 percent after the vibration resistance test.
The parameters of the fuel system directly affect the performance of the fuel cell, so the detection of the fuel system is a crucial operation. A fuel system testing method according to the preferred embodiment of the present invention is further disclosed below.
The fuel system detection method comprises the following steps:
1001: preparation before testing.
Before the test, various certificates and technical documents of hydrogen cylinders, monomer equipment, pipelines and accessories of the fuel system, including all routine test records and certificates, drawing data, safety quality supervision and inspection certificates and the like are checked. After the data are complete and are checked one by one, the following steps can be carried out:
1002: and (6) appearance inspection.
The completed product was subjected to appearance inspection. And checking the connection accuracy of the gas pipeline and the electric line, and the like.
1003: and setting detection conditions.
According to this preferred embodiment of the invention, the environmental conditions of the fuel system detection method are:
temperature: 20 +/-10 ℃;
humidity: less than 100 percent;
pressure: 86 to 106 kPa.
1004: and (5) detecting the performance.
The performance detecting step further comprises the steps of:
10041: startup/shutdown mode detection.
When the manual mode is detected, the fuel system is manually started or shut down, and whether the system is normally started or shut down is checked.
When the remote control mode is detected, the fuel system is remotely started or shut down, and whether the system is normally started or shut down is checked.
When the automatic mode is detected, the fuel system is started or closed regularly, and whether the system is started or closed normally is checked.
10042: start-up/shut-down time detection.
A hydrogen flowmeter is installed at the hydrogen outlet of the fuel system to keep the hydrogen outlet of the fuel system open, and a pressure reducing valve 3421 in the fuel system is set at a pressure value at which it operates. The cylinder valve of the fuel system is opened. And sending an opening instruction to the electromagnetic valve, and recording the time length from the moment of sending the opening instruction to the moment of detecting the hydrogen flow by the flow meter to be the starting time of the fuel system. And then sending a closing instruction to the electromagnetic valve, and recording the time length from the moment of sending the closing instruction to the moment of not detecting the hydrogen flow by the flow meter as the closing time of the fuel system.
10043: and detecting the stable hydrogen supply flow.
A hydrogen flow meter is installed at the fuel system hydrogen outlet to keep the fuel system hydrogen outlet open, and a pressure reducing valve 3421 in the fuel system is set at its operating pressure value. Opening a cylinder valve and an electromagnetic valve of the fuel system, recording a hydrogen flow value every 10 seconds after hydrogen decompressed by a decompression valve 3421 arranged in the fuel system flows out of a hydrogen outlet of the fuel system for 5 seconds, and taking the average value in 2 minutes as the maximum hydrogen flow.
10044: and (5) detecting the hydrogen leakage rate.
The leakage rate of hydrogen is calculated by detecting the change in hydrogen pressure in the hydrogen line at the rear end of the pressure reducing valve 3421 before and after the experiment, by the following method:
a pressure gauge with an accuracy of 0.5% was installed at the hydrogen outlet of the fuel system, and then the hydrogen outlet of the fuel system was closed. The pressure reducing valve 3421 in the fuel system is set at a pressure value at which it operates. The cylinder valve and the electromagnetic valve of the fuel system are opened, and after the hydrogen pressure in the hydrogen pipeline at the rear end of the pressure reducing valve 3421 is stabilized for 1 minute, the pressure P measured by the pressure sensor is recorded1. The cylinder valve and the solenoid valve of the fuel system are closed, and the pressure P measured by the pressure sensor is recorded after 24 hours2. The hydrogen leakage amount qfuel per hour was calculated according to the formula (1). Due to P1And P2Generally, the pressure is only slightly higher than the atmospheric pressure, and the difference between the two is not large, so that the compression factor of hydrogen does not need to be introduced in the formula (1).
qfuel＝[(1-P2T1/P1T2)/24]*100％.........................(1)
Wherein,
p1 — pressure recorded at the beginning of the measurement;
p2 — pressure recorded at the end of measurement;
t1-ambient temperature at recording P1;
t2-record ambient temperature at P2.
10045: and detecting the vibration resistance.
The fuel system is rigidly connected to a vibration table, and the fuel system is tested according to the vibration power spectrum shape and the acceleration spectrum root mean square value of figure 3 of the attached drawing of the specification in three directions of X, Y and Z, and vibrates for 5min in each direction.
10046: and detecting the hydrogen concentration in the cabin.
The fuel system hydrogen outlet is blocked and the pressure reducing valve 3421 in the fuel system is set at its operating pressure reduction value. The cylinder valve 3431 and the solenoid valve 3432 of the fuel system were opened, and the concentration of hydrogen gas at the highest point of the chamber where the fuel system was located was measured and recorded by a hydrogen gas concentration detector for 30min, and a value was recorded every second.
The preferred embodiment of the present invention is provided with the chamber 12 so that the hydrogen concentration in the chamber can be detected by the above-described method.
In embodiments where no chamber is provided, the hydrogen concentration in the chamber may be detected by: the fuel system is placed in an unmanned aerial vehicle using the fuel system, or the fuel system is placed in a shell which can just contain the fuel system, the concentration of hydrogen at the highest position of a cabin where the fuel system is located within 30min is measured and recorded by a hydrogen concentration detector, and a numerical value is recorded every second.
10047: and detecting the electromagnetic compatibility.
The electrostatic discharge immunity test is carried out according to GB/T17626.2-2006: contact discharge with a test voltage of 6 kV; air discharge, test voltage 8 kV.
The radio frequency electromagnetic field radiation immunity test is carried out according to GB/T17626.3-2006: the test field intensity is 10V/m, and the frequency range is 80 MHz-100 MHz.
10048: and (5) detecting the protection grade.
Dust and water resistance tests were performed according to GB 4208-2008 standard clause 13.4 and clause 14.2.4, respectively. For this fuel system to be installed in the cabin or in the drone housing, this detection needs to be performed while installing this fuel system in the cabin or in the drone housing.
10049: protection and alarm function detection, further comprising the steps of:
100491: and (5) protecting and detecting the high pressure and the low pressure of the hydrogen.
And when the hydrogen pressure at the outlet of the hydrogen cylinder is lower than the specified minimum pressure, observing whether the fuel system takes corresponding protective measures (such as whether an electromagnetic valve for controlling the start and stop of the hydrogen is closed). When the pressure of the hydrogen gas after the pressure reduction valve 3421 reduces the pressure is lower than the set minimum pressure or higher than the set maximum pressure, it is observed whether the fuel system takes corresponding protective measures (e.g., whether the solenoid valve next to the stack is closed).
100492: and (5) detecting alarm information.
And observing whether the system can transmit the alarm signal to the remote monitoring equipment in a wireless mode when the hydrogen pressure is abnormal.
100493: and detecting a monitoring function.
Detecting whether the fuel system has the following monitoring function:
-telemetry: the hydrogen pressure in the hydrogen cylinder and the pressure of the decompressed hydrogen.
-remote signalling: the hydrogen pressure in the hydrogen cylinder is low, and the pressure of the decompressed hydrogen is low/high.
-remote control: the fuel system is on/off.
It will be appreciated by persons skilled in the art that the embodiments of the invention described above and shown in the drawings are given by way of example only and are not limiting of the invention. The objects of the invention have been fully and effectively accomplished.
The functional and structural principles of the present invention have been shown and described in the examples, and any variations or modifications of the embodiments of the present invention may be made without departing from the principles.
Claims (32)
1. A fuel system for unmanned aerial vehicle fuel cell, its characterized in that includes:
at least one fuel storage device for storing fuel required by the power generation system of the fuel cell;
at least one fuel passage for directing fuel stored in said fuel storage device to flow to the power generation system of the fuel cell; and
at least one fuel monitoring unit to monitor fuel stored in the fuel storage device, fuel flowing in the fuel passage, and/or fuel leaked to an environment in which the fuel system is located.
2. The fuel system of claim 1, wherein the fuel monitoring unit comprises at least one monitoring device configured to monitor fuel and its parameters in the fuel system and at least one controller configured to control fuel and its parameters in the fuel system.
3. The fuel system of claim 2, wherein the controller includes at least one pressure control assembly configured to control the pressure of fuel exiting the fuel storage device prior to entering the power generation system.
4. The fuel system of claim 3, wherein the monitoring device comprises at least two pressure sensors to monitor the fuel pressure in the fuel storage device and the fuel pressure after being controlled by the real-time pressure control assembly, respectively.
5. The fuel system of claim 4 wherein said pressure control assembly includes at least one pressure relief valve to reduce the pressure of the fuel after it exits said fuel storage device.
6. The fuel system of claim 5, wherein the fuel monitoring unit further comprises at least one communication module, wherein the communication module is capable of transmitting data monitored by the monitoring device to the controller as a control basis for the controller.
7. The fuel system of claim 6, wherein the controller further comprises a switch control assembly, wherein the switch control assembly is configured to control the flow of fuel between the fuel storage device and the power generation system.
8. The fuel system of claim 7, wherein the on-off control assembly includes at least one cylinder valve disposed in the fuel storage device to control whether fuel can flow from the fuel storage device.
9. The fuel system of claim 8, wherein the on-off control assembly further comprises at least one solenoid valve, wherein the solenoid valve is positioned at a location between the pressure relief valve and the power generation system to control whether fuel can be flowed to the power generation system.
10. The fuel system of claim 9, wherein the pressure control assembly further comprises at least one pressure relief valve for cooperating with the pressure relief valve to reduce the fuel pressure to a predetermined pressure value.
11. The fuel system according to claim 10, wherein the pressure relief valve is provided at a position between the pressure relief valve and the solenoid valve, wherein the solenoid valve is provided at a position between the pressure relief valve and the power generation system.
12. The fuel system of claim 11, wherein the fuel monitoring unit further comprises at least one information presentation system to present the fuel parameter and to issue a warning signal when the fuel parameter reaches a predetermined range of values.
13. The fuel system of claim 12, wherein the fuel passage includes at least one soft pipe and at least one hard pipe to accommodate different pipe requirements between the fuel storage device and the power generation system, respectively.
14. The fuel system of claim 13, wherein the monitoring device further comprises at least one temperature sensor to monitor a temperature environment in which the fuel system is located.
15. The fuel system of claim 14, wherein the controller further comprises at least one temperature control device to control the temperature of the environment in which the fuel system is located.
16. The fuel system of any one of claims 1 to 15, wherein the fuel storage means comprises at least one fuel storage tank and at least one compartment, wherein the fuel storage tank is used to store fuel, wherein the fuel storage tank is disposed within the compartment.
17. The fuel system of claim 16, wherein the fuel storage tank is a hydrogen storage bottle for storing hydrogen fuel.
18. The fuel system of any one of claims 1 to 15, further comprising at least one filter, wherein the filter is disposed at an outlet of the fuel storage device to purge fuel flowing from the fuel storage device.
19. The fuel system of claim 17, further comprising at least one filter, wherein the filter is disposed at an outlet of the hydrogen storage cylinder to purge hydrogen gas flowing out of the hydrogen storage cylinder.
20. The fuel system of any one of claims 1 to 15, wherein the fuel channels and the fuel storage device are made of a material resistant to hydrogen embrittlement, hydrogen corrosion, stress corrosion.
21. The fuel system of claim 17, wherein the fuel passage and the hydrogen storage cylinder are made of a material resistant to hydrogen embrittlement, hydrogen corrosion, and stress corrosion.
22. The fuel system of claim 17, wherein the burst pressure of the hydrogen storage cylinder is greater than or equal to 1.5 times its operating pressure.
23. The fuel system of claim 17, wherein the burst pressure of the hydrogen storage cylinder is greater than or equal to 2 times its operating pressure.
24. The fuel system of claim 19, wherein the filter is a filter, wherein the filter is above or equal to a 15 μ ι η rating.
25. The fuel system of any one of claims 2 to 15, wherein the design pressure of each element of the fuel storage device, the fuel passage and the controller is greater than or equal to 1.1 times its respective operating pressure.
26. A method for testing a fuel system of an unmanned fuel cell, comprising the steps of:
a: setting a test environment condition;
b: detecting a starting mode and a closing mode; and
c: and detecting the stable hydrogen supply flow.
27. The detection method of claim 26, further comprising the steps of:
d: detecting the hydrogen leakage rate; and
e: and detecting the vibration resistance.
28. The detection method of claim 27, further comprising the steps of:
f: detecting electromagnetic compatibility; and
g: and detecting the protection grade.
29. The detection method of claim 28, further comprising the steps of:
h: detection protection and alarm functions; and
i: the start-up and shut-down times are detected.
30. The detection method according to claim 29, wherein step H comprises the steps of:
h1: detecting high and low pressure protection of hydrogen;
h2: detecting alarm information; and
h3: and detecting a monitoring function.
31. The detection method of claim 30, further comprising the steps of:
j: and detecting the hydrogen concentration in the cabin.
32. A method of testing as claimed in any one of claims 26 to 30 wherein the test environmental conditions include:
temperature: 20 +/-10 ℃;
humidity: less than 100 percent; and
pressure: 86 to 106 kPa.
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| CN201710090811.9A CN108470928A (en) | 2017-02-20 | 2017-02-20 | Fuel system and its detection method for unmanned plane fuel cell |
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Application publication date: 20180831 |