Unmanned aerial vehicle hydrogen fuel cell and hydrogen storage device

Abstract

The invention discloses an unmanned aerial vehicle hydrogen fuel cell and a hydrogen storage device, and relates to the technical field of cells. The unmanned aerial vehicle hydrogen fuel cell comprises a hydrogen storage device, a pressure reducing valve, an ejector, a buffer tank, a safety valve, a fuel cell stack, a gas-liquid separator and an exhaust valve, an inlet of the ejector comprises a primary inflow port and a secondary inflow port, and the hydrogen storage device, the pressure reducing valve and the primary inflow port are sequentially communicated; an outlet of the ejector, the buffer tank and an anode inlet of the fuel cell stack are sequentially communicated, the safety valve is communicated with the buffer tank, an anode outlet of the fuel cell stack, the gas-liquid separator and the exhaust valve are sequentially communicated, and the secondary flow inlet is connected between the gas-liquid separator and the exhaust valve. According to the unmanned aerial vehicle hydrogen fuel cell and the hydrogen storage device disclosed by the invention, a part of hydrogen which does not participate in reaction can be recycled, the utilization rate of hydrogen is improved, and the cruising ability of the unmanned aerial vehicle can be improved under the condition that the hydrogen fuel is limited.

Description

Technical Field

[0001] The present invention belongs to the technical field of batteries, and in particular relates to a hydrogen fuel cell and a hydrogen storage device for an unmanned aerial vehicle. Background Art

[0002] As one of the most anticipated new energy technologies in the 21st century, hydrogen fuel cells have shown great potential in the field of drones. Hydrogen fuel cell drones have become an ideal choice for industrial drone applications due to their high energy density and zero emissions. However, due to the compact structure of drones, the hydrogen fuel in drone hydrogen fuel cells is limited, resulting in limited actual endurance of drones.

[0003] Therefore, how to provide an effective solution to improve the endurance of UAVs when hydrogen fuel is limited has become a difficult problem to be solved urgently in the existing technology. Summary of the invention

[0004] The purpose of the present invention is to provide a hydrogen fuel cell and a hydrogen storage device for an unmanned aerial vehicle to solve the above-mentioned problems existing in the prior art.

[0005] In order to achieve the above object, the present invention adopts the following technical solutions:

[0006] In the first aspect, the present invention provides a hydrogen fuel cell for an unmanned aerial vehicle, comprising a hydrogen storage device, a pressure reducing valve, an ejector, a buffer tank, a safety valve, a fuel cell stack, a gas-liquid separator and an exhaust valve, wherein the inlet of the ejector comprises a primary flow inlet and a secondary flow inlet, the hydrogen storage device, the pressure reducing valve and the primary flow inlet are connected in sequence, the outlet of the ejector, the buffer tank and the anode inlet of the fuel cell stack are connected in sequence, the safety valve is connected to the buffer tank, the anode outlet of the fuel cell stack, the gas-liquid separator and the exhaust valve are connected in sequence, and the secondary flow inlet is connected between the gas-liquid separator and the exhaust valve.

[0007] Based on the above disclosed content, the present invention is provided with a hydrogen storage device, a pressure reducing valve, an ejector, a buffer tank, a safety valve, a fuel cell stack, a gas-liquid separator and an exhaust valve, the inlet of the ejector includes a primary flow inlet and a secondary flow inlet, the hydrogen storage device, the pressure reducing valve and the primary flow inlet are connected in sequence, the outlet of the ejector, the buffer tank and the anode inlet of the fuel cell stack are connected in sequence, the safety valve is connected to the buffer tank, the anode outlet of the fuel cell stack, the gas-liquid separator and the exhaust valve are connected in sequence, and the secondary flow inlet is connected between the gas-liquid separator and the exhaust valve. In this way, the high-pressure hydrogen entering the primary flow inlet will be ejected at a higher speed and form a low-pressure area, thereby sucking in a part of the hydrogen that does not participate in the reaction after entering the fuel cell stack, and mixing it with the high-pressure hydrogen to form hydrogen that meets the pressure requirement of the anode inlet of the fuel cell stack in the buffer tank, and then enters the anode of the fuel cell stack to react, so that a part of the hydrogen that does not participate in the reaction can be recycled and reused, the utilization rate of hydrogen can be improved, and the endurance of the drone can be improved when the hydrogen fuel is limited.

[0008] In a possible design, the drone hydrogen fuel cell further includes a controller, a first pressure sensor and a second pressure sensor, wherein the controller is electrically connected to the pressure reducing valve, the exhaust valve, the first pressure sensor and the second pressure sensor, respectively, the first pressure sensor is arranged between the pressure reducing valve and the primary inlet, and the second pressure sensor is arranged between the gas-liquid separator and the secondary inlet;

[0009] The first pressure sensor is used to detect the pressure of the gas entering the primary flow inlet;

[0010] The second pressure sensor is used to detect the pressure of the gas entering the secondary flow inlet;

[0011] The controller is used for adjusting the opening of the pressure reducing valve to make the gas pressure of the primary inlet within the first preset pressure range when the gas pressure of the primary inlet exceeds the first preset pressure range; and

[0012] When the gas pressure of the primary inlet is within a first preset pressure range and the gas pressure of the secondary inlet exceeds a second preset pressure range, the opening of the exhaust valve is adjusted to make the gas pressure of the secondary inlet within the second preset pressure range.

[0013] In one possible design, the drone hydrogen fuel cell further includes a third pressure sensor, the third pressure sensor is electrically connected to the controller, and the third pressure sensor is disposed between the buffer tank and the anode inlet of the fuel cell stack;

[0014] The third pressure sensor is used to detect the gas pressure entering the anode inlet of the fuel cell stack;

[0015] The controller is further used to adjust the opening of the safety valve when the gas pressure of the primary inlet is within a first preset pressure range, the gas pressure of the secondary inlet is within a second preset pressure range, and the gas pressure of the anode inlet of the fuel cell stack exceeds a third preset pressure range, so that the gas pressure of the anode inlet of the fuel cell stack is within the third preset pressure range; or

[0016] When the gas pressure at the primary inlet is within the first preset pressure range, the gas pressure at the secondary inlet is within the second preset pressure range, and the gas pressure at the anode inlet of the fuel cell stack exceeds the third preset pressure range, the opening of the pressure reducing valve and / or the exhaust valve is adjusted so that the gas pressure at the primary inlet is within the first preset pressure range, the gas pressure at the secondary inlet is within the second preset pressure range, and the gas pressure at the anode inlet of the fuel cell stack is within the third preset pressure range.

[0017] In a possible design, the ejector includes a nozzle, a suction chamber, a mixing chamber and a diffusion chamber, the nozzle, the suction chamber, the mixing chamber and the diffusion chamber are connected in sequence, the inlet of the nozzle forms the primary flow inlet, the side wall of the suction chamber is provided with the secondary flow inlet, and the inner diameter of the diffusion chamber gradually increases along the direction from the suction chamber to the mixing chamber.

[0018] In a possible design, the length of the diffusion chamber is greater than the length of the mixing chamber.

[0019] In a possible design, the length ratio of the diffusion chamber to the mixing chamber is 4:1.

[0020] In one possible design, the drone hydrogen fuel cell also includes a radiator, which is disposed on opposite sides of the fuel cell stack.

[0021] In a second aspect, the present invention discloses a hydrogen storage device, which is applied to the unmanned aerial vehicle hydrogen fuel cell described in the first aspect or any possible design of the first aspect, the hydrogen storage device includes a hydrogen storage tank and a protective tank, the protective tank is outermost of the hydrogen storage tank, and a closed space is formed between the protective tank and the hydrogen storage tank, the pressure in the closed space is greater than the atmospheric pressure, and the pressure in the closed space is less than the pressure in the hydrogen storage tank.

[0022] In a possible design, the enclosed space is filled with nitrogen or an inert gas.

[0023] In a possible design, the protective tank is a multi-layer structure.

[0024] Beneficial effects:

[0025] The UAV hydrogen fuel cell and hydrogen storage device provided by the present invention can recycle a portion of the hydrogen that does not participate in the reaction, thereby improving the utilization rate of hydrogen. When hydrogen fuel is limited, the endurance of the UAV can be improved, thereby facilitating practical application and promotion. BRIEF DESCRIPTION OF THE DRAWINGS

[0026] Figure 1 A schematic diagram of the structure of a hydrogen fuel cell for a drone provided in an embodiment of the present application;

[0027] Figure 2 A schematic diagram of the structure of the ejector provided in the embodiment of the present application;

[0028] Figure 3 A circuit block diagram of a hydrogen fuel cell for a drone provided in an embodiment of the present application.

[0029] Reference numerals:

[0030] 11-hydrogen storage device; 12-pressure reducing valve; 13-ejector; 131-nozzle; 132-intake chamber; 133-mixing chamber; 134-diffusion chamber; 14-buffer tank; 15-safety valve; 16-fuel cell stack; 17-gas-liquid separator; 18-exhaust valve; 19-controller; 20-first pressure sensor; 21-second pressure sensor; 22-third pressure sensor. DETAILED DESCRIPTION

[0031] In order to more clearly illustrate the technical solutions in the embodiments of the present invention or the prior art, the present invention will be briefly introduced below in combination with the drawings and the description of the embodiments or the prior art. Obviously, the following description of the structure of the drawings is only some embodiments of the present invention. For ordinary technicians in this field, other drawings can be obtained based on these drawings without creative work. It should be noted that the description of these embodiments is used to help understand the present invention, but does not constitute a limitation of the present invention.

[0032] It should be understood that although the terms first, second, etc. may be used herein to describe various units, these units should not be limited by these terms. These terms are only used to distinguish one unit from another unit. For example, a first unit can be referred to as a second unit, and similarly, a second unit can be referred to as a first unit without departing from the scope of the exemplary embodiments of the present invention.

[0033] It should be understood that the term "and / or" that may appear in this article is merely a description of the association relationship between associated objects, indicating that three relationships may exist. For example, A and / or B can represent three situations: A exists alone, B exists alone, and A and B exist at the same time. The term " / and" that may appear in this article describes another type of association object relationship, indicating that two relationships may exist. For example, A / and B can represent two situations: A exists alone, and A and B exist alone. In addition, the character " / " that may appear in this article generally indicates that the previous and next associated objects are in an "or" relationship.

[0034] like Figure 1 As shown, the first aspect of the embodiment of the present application provides a UAV hydrogen fuel cell for powering the UAV, the UAV hydrogen fuel cell includes a hydrogen storage device 11, a pressure reducing valve 12, an ejector 13, a buffer tank 14, a safety valve 15, a fuel cell stack 16, a gas-liquid separator 17 and an exhaust valve 18, the inlet of the ejector 13 includes a primary flow inlet and a secondary flow inlet, the hydrogen storage device 11, the pressure reducing valve 12 and the primary flow inlet are connected in sequence, the outlet of the ejector 13, the buffer tank 14 and the anode inlet of the fuel cell stack 16 are connected in sequence, the safety valve 15 is connected to the buffer tank 14, the anode outlet of the fuel cell stack 16, the gas-liquid separator 17 and the exhaust valve 18 are connected in sequence, and the secondary flow inlet is connected between the gas-liquid separator 17 and the exhaust valve 18.

[0035] The hydrogen storage device 11 is used to store liquid hydrogen. After part of the liquid hydrogen in the hydrogen storage device 11 is gasified, it enters the primary inlet of the ejector 13 through the pressure reducing valve 12. Based on Bernoulli's principle, the high-pressure hydrogen entering the primary inlet will be ejected at a higher speed to form a low-pressure area, and a part of the hydrogen that does not participate in the reaction after being discharged from the anode outlet of the fuel cell stack 16 and separated by the gas-liquid separator 17 will be absorbed, and after being mixed in the ejector 13, it will enter the buffer tank 14, and form hydrogen in the buffer tank 14 that meets the anode inlet pressure requirement of the fuel cell stack 16. If the gas pressure in the buffer tank 14 is too high, it can be discharged through the safety Valve 15 releases a part of hydrogen, so that the hydrogen in buffer tank 14 meets the pressure requirement of the anode inlet of fuel cell stack 16. After hydrogen enters the anode of fuel cell stack 16, it reacts with oxygen entering from the cathode of fuel cell stack 16 in fuel cell stack 16 and generates electricity. Water generated by the reaction in fuel cell stack 16 and a part of hydrogen that does not participate in the reaction enter gas-liquid separator 17 through the anode outlet of fuel cell stack 16 for gas-liquid separation. A part of the separated hydrogen is sucked into ejector 13 and reused, and a part of the hydrogen that is not sucked into ejector 13 is discharged through exhaust valve 18. In this way, a part of the hydrogen that does not participate in the reaction can be recycled and reused, which improves the utilization rate of hydrogen and can improve the endurance of the drone when hydrogen fuel is limited.

[0036] The ejector 13 is used to absorb a portion of the hydrogen gas discharged from the anode outlet of the fuel cell stack 16 and not participating in the reaction based on Bernoulli's principle, so as to recycle and reuse the hydrogen gas. Figure 2 The ejector 13 includes a nozzle 131, an inhalation chamber 132, a mixing chamber 133 and a diffusion chamber 134, and the nozzle 131, the inhalation chamber 132, the mixing chamber 133 and the diffusion chamber 134 are connected in sequence. Among them, the inlet of the nozzle 131 forms the primary inlet, and the inner diameter of the primary inlet gradually decreases from the mixing chamber 133 to the diffusion chamber 134, that is, the cross-section of the nozzle 131 is trapezoidal, and the side wall of the inhalation chamber 132 is provided with the secondary inlet. The inner diameter of the mixing chamber 133 remains unchanged, while the inner diameter of the diffusion chamber 134 gradually increases from the inhalation chamber 132 to the mixing chamber 133. The mixing chamber 133 is used to mix the gas entering from the primary inlet and the secondary inlet. The larger length of the mixing chamber 133 can ensure that the gas entering from the primary inlet and the secondary inlet is fully mixed. Therefore, in the embodiment of the present application, the length of the diffusion chamber 134 is greater than the length of the mixing chamber 133.

[0037] The length ratio of the diffusion chamber 134 to the mixing chamber 114 may be, but is not limited to, 2:1, 4:1 or 5:1, etc. In the embodiment of the present application, the length ratio of the diffusion chamber 134 to the mixing chamber 114 is 4:1.

[0038] In addition, in order to ensure the heat dissipation of the hydrogen fuel cell of the drone, radiators can be arranged on opposite sides of the fuel cell stack 16 to enhance the heat dissipation effect.

[0039] In order to ensure good ejection performance, the gas pressure of the primary inlet and the gas pressure of the secondary inlet need to be maintained within a pressure range of one degree, so that the ejector 13 has good ejection performance, that is, the ejector 13 has a high ejection ratio. Therefore, the gas pressure ranges of the primary inlet and the secondary inlet when the ejector 13 has good ejection performance can be determined in advance through testing. In the embodiment of the present application, the gas pressure range of the primary inlet when the ejector 13 has good ejection performance is referred to as the first preset pressure range, and the gas pressure range of the secondary inlet when the ejector 13 has good ejection performance is referred to as the second preset pressure range.

[0040] Please refer to Figure 3 The UAV hydrogen fuel cell is also provided with a controller 19, a first pressure sensor 20 and a second pressure sensor 21. The controller 19 is electrically connected to the pressure reducing valve 12, the exhaust valve 18, the first pressure sensor 20 and the second pressure sensor 21 respectively. The first pressure sensor 20 is arranged between the pressure reducing valve 12 and the primary inlet, and the second pressure sensor 21 is arranged between the gas-liquid separator 17 and the secondary inlet.

[0041] Among them, the first pressure sensor 20 is used to detect the gas pressure entering the primary inlet, the second pressure sensor 21 is used to detect the gas pressure entering the secondary inlet, and the controller 19 is used to adjust the opening of the pressure reducing valve 12 so that the gas pressure of the primary inlet is within the first preset pressure range when the gas pressure of the primary inlet exceeds the first preset pressure range, and to adjust the opening of the exhaust valve 18 so that the gas pressure of the secondary inlet is within the second preset pressure range when the gas pressure of the primary inlet is within the first preset pressure range and the gas pressure of the secondary inlet exceeds the second preset pressure range.

[0042] By setting up a controller 19, a first pressure sensor 20 and a second pressure sensor 21, the gas pressure entering the primary flow inlet and the gas pressure entering the secondary flow inlet can be detected in real time, and the gas pressure at the primary flow inlet is always within the first preset pressure range, and the gas pressure at the secondary flow inlet is always within the second preset pressure range, so that the ejector 13 can achieve good ejection performance, improve the recycling rate of hydrogen, and further improve the endurance of the UAV.

[0043] See also Figure 3 In one or more embodiments, the UAV hydrogen fuel cell also includes a third pressure sensor 22, which is electrically connected to the controller 19 and is disposed between the buffer tank 14 and the anode inlet of the fuel cell stack 16.

[0044] The third pressure sensor 22 is used to detect the pressure of the gas entering the anode inlet of the fuel cell stack 16 .

[0045] The controller 19 is also used to adjust the opening of the safety valve 15 so that the gas pressure at the anode inlet of the fuel cell stack 16 is within the third preset pressure range when the gas pressure at the primary inlet is within the first preset pressure range, the gas pressure at the secondary inlet is within the second preset pressure range, and the gas pressure at the anode inlet of the fuel cell stack 16 exceeds the third preset pressure range. Or when the gas pressure at the primary inlet is within the first preset pressure range, the gas pressure at the secondary inlet is within the second preset pressure range, and the gas pressure at the anode inlet of the fuel cell stack 16 exceeds the third preset pressure range, adjust the opening of the pressure reducing valve 12 and / or the exhaust valve 18 so that the gas pressure at the primary inlet is within the first preset pressure range and the gas pressure at the secondary inlet is within the second preset pressure range, and the gas pressure at the anode inlet of the fuel cell stack 16 is within the third preset pressure range.

[0046] Among them, the third preset pressure range is the required pressure range of the anode inlet of the fuel cell stack 16. The opening of the safety valve 15 is adjusted so that the gas pressure at the anode inlet of the fuel cell stack 16 is within the third preset pressure range, mainly for the situation where the pressure in the buffer tank 14 is too high. The opening of the pressure reducing valve 12 and / or the exhaust valve 18 is adjusted mainly for the situation where the pressure in the buffer tank 14 is too high or too low. On the premise that the gas pressure at the primary inlet is within the first preset pressure range and the gas pressure at the secondary inlet is within the second preset pressure range, the gas pressure at the primary inlet and / or the gas pressure at the secondary inlet are appropriately increased, thereby increasing the pressure in the buffer tank 14 so that the pressure in the buffer tank 14 meets the pressure requirement of the anode inlet of the fuel cell stack 16.

[0047] By providing the third pressure sensor 22, it can be ensured that the hydrogen in the buffer tank 14 meets the pressure requirement of the anode inlet of the fuel cell stack 16, thereby ensuring the normal power supply of the hydrogen fuel cell of the drone.

[0048] In summary, the unmanned aerial vehicle hydrogen fuel cell provided by the present invention is provided with a hydrogen storage device, a pressure reducing valve, an ejector, a buffer tank, a safety valve, a fuel cell stack, a gas-liquid separator and an exhaust valve, the inlet of the ejector includes a primary flow inlet and a secondary flow inlet, the hydrogen storage device, the pressure reducing valve and the primary flow inlet are connected in sequence, the outlet of the ejector, the buffer tank and the anode inlet of the fuel cell stack are connected in sequence, the safety valve is connected to the buffer tank, the anode outlet of the fuel cell stack, the gas-liquid separator and the exhaust valve are connected in sequence, and the secondary flow inlet is connected between the gas-liquid separator and the exhaust valve. In this way, the high-pressure hydrogen entering the primary flow inlet will be ejected at a higher speed and form a low-pressure area, thereby inhaling a part of the hydrogen that does not participate in the reaction after entering the fuel cell stack, and mixing it with the high-pressure hydrogen to form hydrogen that meets the pressure requirement of the anode inlet of the fuel cell stack in the buffer tank, and then enter the anode of the fuel cell stack to react, so that a part of the hydrogen that does not participate in the reaction can be recycled and reused, the utilization rate of hydrogen can be improved, and the endurance of the unmanned aerial vehicle can be improved when the hydrogen fuel is limited. By setting up a controller, a first pressure sensor and a second pressure sensor, the gas pressure entering the primary inlet and the gas pressure entering the secondary inlet can be detected in real time, and the gas pressure of the primary inlet is always within the first preset pressure range, and the gas pressure of the secondary inlet is always within the second preset pressure range, so that the ejector can achieve good ejection performance, improve the recycling rate of hydrogen, and further improve the endurance of the drone. By setting up a third pressure sensor, it can be ensured that the hydrogen in the buffer tank meets the pressure requirements of the anode inlet of the fuel cell stack, ensuring the normal power supply of the drone hydrogen fuel cell.

[0049] A second aspect of an embodiment of the present application provides a hydrogen storage device, which is applied to the drone hydrogen fuel cell described in the first aspect. The hydrogen storage device includes a hydrogen storage tank and a protective tank. The protective tank is disposed outside the hydrogen storage tank, and the protective tank and the hydrogen storage tank form a closed space. The pressure in the closed space is greater than the atmospheric pressure, and the pressure in the closed space is less than the pressure in the hydrogen storage tank.

[0050] By setting up a hydrogen storage tank and a protection tank, and the pressure of the enclosed space formed between the protection tank and the hydrogen storage tank is greater than the atmospheric pressure and less than the pressure inside the hydrogen storage tank, it can play a role in balancing the pressure inside and outside the hydrogen storage tank to a certain extent, avoiding the rupture of the hydrogen storage tank due to excessive pressure difference inside and outside the hydrogen storage tank, and then causing hydrogen fuel leakage.

[0051] In a possible design, the enclosed space is filled with nitrogen or an inert gas.

[0052] In a possible design, the protective tank is a multi-layer structure.

[0053] It should be understood that certain details are provided in the following description to facilitate a complete understanding of the example embodiments. However, it should be understood by those of ordinary skill in the art that the example embodiments can be implemented without these certain details. For example, the system can be shown in a block diagram to avoid obscuring the example with unnecessary details. In other examples, well-known processes, structures, and techniques may not be shown in unnecessary detail to avoid obscuring the example embodiments.

[0054] Finally, it should be noted that the above description is only a preferred embodiment of the present invention and is not intended to limit the protection scope of the present invention. Any modification, equivalent replacement, improvement, etc. made within the spirit and principle of the present invention shall be included in the protection scope of the present invention.

Claims

1. A hydrogen fuel cell for an unmanned aerial vehicle, characterized in that: It includes a hydrogen storage device, a pressure reducing valve, an ejector, a buffer tank, a safety valve, a fuel cell stack, a gas-liquid separator and an exhaust valve, the inlet of the ejector includes a primary flow inlet and a secondary flow inlet, the hydrogen storage device, the pressure reducing valve and the primary flow inlet are connected in sequence, the outlet of the ejector, the buffer tank and the anode inlet of the fuel cell stack are connected in sequence, the safety valve is connected to the buffer tank, the anode outlet of the fuel cell stack, the gas-liquid separator and the exhaust valve are connected in sequence, and the secondary flow inlet is connected between the gas-liquid separator and the exhaust valve.

2. The hydrogen fuel cell for drone according to claim 1, characterized in that: It also includes a controller, a first pressure sensor and a second pressure sensor, wherein the controller is electrically connected to the pressure reducing valve, the exhaust valve, the first pressure sensor and the second pressure sensor, respectively, the first pressure sensor is arranged between the pressure reducing valve and the primary inlet, and the second pressure sensor is arranged between the gas-liquid separator and the secondary inlet; The first pressure sensor is used to detect the pressure of the gas entering the primary flow inlet; The second pressure sensor is used to detect the pressure of the gas entering the secondary flow inlet; The controller is used to adjust the opening of the pressure reducing valve when the gas pressure of the primary inlet exceeds a first preset pressure range so that the gas pressure of the primary inlet is within the first preset pressure range; as well as When the gas pressure of the primary inlet is within a first preset pressure range and the gas pressure of the secondary inlet exceeds a second preset pressure range, the opening of the exhaust valve is adjusted to make the gas pressure of the secondary inlet within the second preset pressure range.

3. The hydrogen fuel cell for drone according to claim 2, characterized in that: Also includes a third pressure sensor, the third pressure sensor is electrically connected to the controller, and the third pressure sensor is arranged between the buffer tank and the anode inlet of the fuel cell stack; The third pressure sensor is used to detect the gas pressure entering the anode inlet of the fuel cell stack; The controller is further configured to adjust the opening of the safety valve when the gas pressure at the primary inlet is within a first preset pressure range, the gas pressure at the secondary inlet is within a second preset pressure range, and the gas pressure at the anode inlet of the fuel cell stack exceeds a third preset pressure range, so that the gas pressure at the anode inlet of the fuel cell stack is within the third preset pressure range; or When the gas pressure at the primary inlet is within the first preset pressure range, the gas pressure at the secondary inlet is within the second preset pressure range, and the gas pressure at the anode inlet of the fuel cell stack exceeds the third preset pressure range, the opening of the pressure reducing valve and / or the exhaust valve is adjusted so that the gas pressure at the primary inlet is within the first preset pressure range, the gas pressure at the secondary inlet is within the second preset pressure range, and the gas pressure at the anode inlet of the fuel cell stack is within the third preset pressure range.

4. The hydrogen fuel cell for drone according to claim 1, characterized in that: The ejector includes a nozzle, a suction chamber, a mixing chamber and a diffusion chamber. The nozzle, the suction chamber, the mixing chamber and the diffusion chamber are connected in sequence. The inlet of the nozzle forms the primary flow inlet. The side wall of the suction chamber is provided with the secondary flow inlet. The inner diameter of the diffusion chamber gradually increases along the direction from the suction chamber to the mixing chamber.

5. The hydrogen fuel cell for drone according to claim 4, characterized in that: The length of the diffusion chamber is greater than the length of the mixing chamber.

6. The hydrogen fuel cell for drone according to claim 1, characterized in that: The length ratio of the diffusion chamber to the mixing chamber is 4:

1.

7. The hydrogen fuel cell for drone according to claim 1, characterized in that: A radiator is also included, and the radiator is arranged on two opposite sides of the fuel cell stack.

8. A hydrogen storage device, applied to the hydrogen fuel cell of the drone according to any one of claims 1 to 7, characterized in that: It includes a hydrogen storage tank and a protection tank, wherein the protection tank is placed outside the hydrogen storage tank, and a closed space is formed between the protection tank and the hydrogen storage tank, the pressure in the closed space is greater than the atmospheric pressure, and the pressure in the closed space is less than the pressure in the hydrogen storage tank.

9. The hydrogen storage device according to claim 8, characterized in that: The enclosed space is filled with nitrogen or an inert gas.

10. The hydrogen storage device according to claim 8, characterized in that: The protection tank is a multi-layer structure.

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