Fuel cell structure for hovercar

Abstract

The utility model provides a fuel cell structure for an aerocar, which relates to the technical field of aerocar fuel cells and comprises a U-shaped conductive plate, the outer wall of the U-shaped conductive plate is subjected to conductive anti-corrosion treatment and is in contact with a membrane electrode, a radiating fin and a sealing gasket are integrated on the inner wall of the U-shaped conductive plate, and the U-shaped conductive plate is packaged to form a bipolar plate assembly; a plurality of bipolar plate assemblies and a membrane electrode are overlapped to form an electric pile, the electric pile is covered with a wind scooper and is in sealed connection with a cooling fan to form a forced convection heat dissipation channel, and cooling air is filtered by filter cotton at a negative pressure opening of the electric pile and then is subjected to closed-loop circulation heat dissipation. A shock pad is arranged at the bottom of the galvanic pile and connected with a hovercar body through a system shock absorption support, a hydrogen supply system is separated from an electric appliance chamber through a separation plate, and a main gas storage tank circulates to an anode flow field after the flow is adjusted through a proportional valve; the air supply system supplies air to the cathode flow field through an air compressor and a humidifier. The utility model has the advantages of compact structure, high heat dissipation efficiency, strong shock resistance, low maintenance cost and the like, and is suitable for the field of eVTOL hovercars.

Description

Technical Field

[0001] This utility model relates to the field of fuel cell technology for flying cars, and more particularly to a fuel cell structure for flying cars. Background Technology

[0002] Flying cars, as the core carrier of future three-dimensional transportation systems, need to possess characteristics such as vertical takeoff and landing, long-endurance flight, and efficient energy utilization. Existing power systems mostly employ pure lithium batteries or traditional fuel cells, but these have significant bottlenecks: lithium batteries have low energy density and long charging times, making them unsuitable for long-endurance flight; while traditional hydrogen fuel cells, with their liquid cooling systems requiring complex piping, pumps, and heat dissipation components, are bulky and heavy, making them unsuitable for the compact space of flying cars. Furthermore, while conventional air-cooled hydrogen fuel cells simplify the heat dissipation structure, their membrane electrode assemblies are directly exposed to the environment, making them susceptible to temperature and humidity fluctuations, leading to unstable output performance. Uneven heat dissipation can also cause localized overheating, reducing battery life.

[0003] Among existing technologies, the contradiction between liquid cooling and air cooling solutions is particularly prominent. Although liquid-cooled fuel cell stacks have higher heat dissipation efficiency, their integration complexity and weight significantly increase the design burden of flying cars. While air-cooled fuel cell stacks have a simple structure, their open design results in poor environmental adaptability, failing to meet the high-altitude and variable operating conditions required by flying cars. At the same time, flying cars have stringent requirements for lightweight, modular layout, and vibration resistance of the power system. Traditional fuel cell systems, due to their rigid installation and distributed gas supply / cooling design, cannot effectively utilize space such as wings, and flight vibrations can easily cause component loosening or leakage risks.

[0004] Therefore, there is an urgent need for a hydrogen fuel cell that combines efficient heat dissipation, lightweight design, and shock resistance to break through the technological bottleneck of flying cars and achieve long-duration, highly reliable vertical take-off and landing and flight. Utility Model Content

[0005] To address the aforementioned technical issues, a fuel cell structure for flying cars is provided, which achieves efficient thermal management and long-endurance flight through a U-shaped bipolar plate integrated design and modular distributed layout.

[0006] To achieve the above objectives, this utility model provides a fuel cell structure for flying cars, comprising:

[0007] The closed gas-cooled fuel cell stack includes a bipolar plate assembly, which is formed by bending a single metal plate into a U-shaped conductive plate. Its outer wall is treated with conductive and anti-corrosion properties and is in contact with the membrane electrode. The inner wall holds and fixes the heat sink and sealing gasket. The U-shaped opening is encapsulated to form an integrated structure.

[0008] The air guide shroud covers the outside of the fuel cell stack and is connected to the fuel cell stack flow field to uniformly distribute the cooling air pressure.

[0009] The cooling fan is sealed to the air guide shroud to form a forced convection heat dissipation channel;

[0010] The fuel cell stack vibration damping pad is installed at the bottom of the fuel cell stack and connected to the flying car body through the system vibration damping bracket to absorb flight vibrations;

[0011] The air supply system includes an air filter, a compressor, and a humidifier connected in sequence, and is connected to the cathode flow field of the fuel cell stack through a pipeline;

[0012] The hydrogen supply system includes a hydrogen storage tank, a hydrogen circulation pump, and a shut-off valve. It is separated from the electrical room by an isolation plate, and the hydrogen is circulated through pipelines to the anode flow field of the fuel cell stack.

[0013] Furthermore, the U-shaped conductive plate of the bipolar plate assembly integrates positioning latches, positioning holes, hydrogen holes, air holes, and cathode and anode flow fields, which are symmetrically distributed.

[0014] Furthermore, a filter cotton with a negative pressure port is provided between the air guide shroud and the cooling fan. The cooling air passes through the filter cotton, the flow field of the fuel cell stack, and the inner cavity of the air guide shroud in sequence to form a closed-loop heat dissipation path.

[0015] Furthermore, a hydrogen storage chamber isolation plate is provided between the main storage tank and the distributed hydrogen storage tank of the hydrogen supply system. After the hydrogen flow rate is adjusted by the proportional valve, it is circulated to the fuel cell stack by the hydrogen circulation pump. The tail valve is used to discharge hydrogen containing impurities.

[0016] Furthermore, the fuel cell stack adopts a modular distributed layout, is installed inside the double-layer fixed wing of the flying car, and is connected to the airframe through a system shock-absorbing bracket.

[0017] Furthermore, the double-layer fixed wing integrates a gas-cooled fuel cell stack assembly, a lithium battery pack, and a hydrogen storage tank. The internal cavity of the wing is connected to the external environment through a heat dissipation plate in the electrical compartment, and a hydrogen refueling port is provided on the leading edge of the wing to connect with the main storage tank.

[0018] This invention also provides a flying car, including a fuel cell structure.

[0019] By adopting the above technical solution, this utility model has the following advantages compared with the prior art:

[0020] 1. This utility model provides a fuel cell structure for flying cars. By bending a single metal plate into a U-shaped conductive plate and integrating heat sinks and sealing gaskets, the contact surfaces of the bipolar plates are reduced from four to two, effectively reducing contact resistance and internal losses. The outer wall is treated with conductive and corrosion-resistant material to ensure stable contact with the membrane electrode assembly (MEA), while the inner wall clamps and fixes the heat sinks to form a uniform heat dissipation path. This design not only simplifies the assembly process but also improves the stack output efficiency and extends the service life of the bipolar plates and the overall stack.

[0021] 2. This utility model provides a fuel cell structure for flying cars. By modularly distributing the enclosed gas-cooled fuel cell stack assembly, hydrogen supply system, and lithium battery pack inside the double-layer fixed wing or below the cockpit, it makes full use of the compact space of the flying car and improves the structural integration. The modular design supports distributed or centralized installation, flexibly adjusts weight distribution, avoids local overload, and enhances flight stability. The wing's internal cavity and heat dissipation perforated plates work together to further optimize both efficient heat dissipation and space utilization. Attached Figure Description

[0022] To more clearly illustrate the technical solutions in the embodiments of this utility model or the prior art, the drawings used in the description of the embodiments or the prior art will be briefly introduced below. Obviously, the drawings described below are some embodiments of this utility model. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort.

[0023] Figure 1 This is a schematic diagram of a closed gas-cooled fuel cell stack assembly structure for a flying car according to the present invention.

[0024] Figure 2 This is a schematic diagram of the bipolar plate assembly structure of a fuel cell stack for flying cars according to the present invention.

[0025] Figure 3 This is a schematic diagram of a single fuel cell structure for a flying car according to the present invention.

[0026] Figure 4 This is a schematic diagram of the bottom structure of a fuel cell unit for flying cars according to the present invention;

[0027] Figure 5 This is a schematic diagram of a hydrogen fuel cell structure with small unit distributed installation for a flying car, as described in this utility model.

[0028] Figure 6 This is a side view of a hydrogen fuel cell structure with small unit distribution for use in flying cars, as described in this utility model.

[0029] Figure 7 This is a schematic diagram of the bottom structure of a hydrogen fuel cell with small unit distribution for use in a flying car, as described in this utility model.

[0030] Figure 8 This is a top view of a fuel cell structure for a flying car as described in this utility model, installed on the flying car.

[0031] Figure 9 This is a side view of a fuel cell structure for a flying car, as described in this utility model, installed on a flying car.

[0032] In the diagram: 1. Enclosed gas-cooled fuel cell stack; 2. Air duct; 3. Cooling fan; 4. Humidifier; 5. Air filter; 6. Compressor; 7. Fuel cell stack vibration damping pad; 8. Fuel cell stack negative pressure port filter cotton; 9. Fuel cell stack support; 10. Fuel cell stack hydrogen outlet pipe; 11. Fuel cell stack hydrogen outlet connector; 12. Fuel cell stack air inlet connector; 13. Fuel cell stack hydrogen inlet connector; 14. Fuel cell stack air outlet connector; 15. Electrical compartment isolation plate; 16. DC-DC electronic control system; 17. DC-DC module; 18. Electrical compartment 19. Heat dissipation perforated plate; 20. System vibration damping bracket; 21. Hydrogen storage chamber isolation plate; 22. Distributed hydrogen storage tank; 23. System lifting point; 24. Hydrogen filling port; 25. Lithium battery pack; 26. Mounting bracket; 27. Communication and power connector; 28. Muffler; 29. ​​Throttle valve; 30. Double-layer fixed wing; 31. Tail exhaust valve; 32. Shut-off valve; 33. Positioning latch; 34. Positioning hole; 35. Hydrogen port; 36. Air port; 37. Cathode flow field; 38. Anode flow field; 39. Main storage tank. Detailed Implementation

[0033] It should be noted that, where there is no conflict, the embodiments and features in the embodiments of this utility model can be combined with each other. The present utility model will now be described in detail with reference to the accompanying drawings and embodiments.

[0034] To make the objectives, technical solutions, and advantages of the embodiments of this utility model clearer, the technical solutions of the embodiments of this utility model will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of this utility model, and not all embodiments. The following description of at least one exemplary embodiment is merely illustrative and is in no way intended to limit this utility model or its application or use. Based on the embodiments of this utility model, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of this utility model.

[0035] It should be noted that the terminology used herein is for the purpose of describing particular embodiments only and is not intended to limit the exemplary embodiments according to the present invention. As used herein, the singular form is intended to include the plural form as well, unless the context clearly indicates otherwise. Furthermore, it should be understood that when the terms "comprising" and / or "including" are used in this specification, they indicate the presence of features, steps, operations, devices, components, and / or combinations thereof.

[0036] Unless otherwise specifically stated, the relative arrangement, numerical expressions, and values ​​of the components and steps described in these embodiments do not limit the scope of this invention. It should also be understood that, for ease of description, the dimensions of the various parts shown in the drawings are not drawn to actual scale. Techniques, methods, and devices known to those skilled in the art may not be discussed in detail, but where appropriate, such techniques, methods, and devices should be considered part of the specification. In all examples shown and discussed herein, any specific values ​​should be interpreted as merely exemplary and not as limitations. Therefore, other examples of exemplary embodiments may have different values. It should be noted that similar reference numerals and letters in the following drawings denote similar items; therefore, once an item is defined in one drawing, it need not be further discussed in subsequent drawings.

[0037] In the description of this utility model, it should be understood that the orientation or positional relationship indicated by directional terms such as "front, back, up, down, left, right", "horizontal, vertical, horizontal" and "top, bottom" is usually based on the orientation or positional relationship shown in the accompanying drawings, and is only for the convenience of describing this utility model and simplifying the description. Unless otherwise stated, these directional terms do not indicate or imply that the device or element referred to must have a specific orientation or be constructed and operated in a specific orientation, and therefore should not be construed as a limitation on the scope of protection of this utility model. The directional terms "inner" and "outer" refer to the inner and outer contours relative to the outline of each component itself.

[0038] For ease of description, spatial relative terms such as "above," "over," "on the upper surface of," "above," etc., are used herein to describe the spatial positional relationship of a device or feature as shown in the figures to other devices or features. It should be understood that spatial relative terms are intended to encompass different orientations in use or operation besides the orientation of the device as described in the figures. For example, if the device in the figures is inverted, a device described as "above" or "above" other devices or structures would subsequently be positioned as "below" or "under" other devices or structures. Thus, the exemplary term "above" can include both "above" and "below." The device may also be positioned in other different ways (rotated 90 degrees or in other orientations), and the spatial relative descriptions used herein will be interpreted accordingly.

[0039] Furthermore, it should be noted that the use of terms such as "first" and "second" to define components is merely for the purpose of distinguishing the corresponding components. Unless otherwise stated, the above terms have no special meaning and therefore cannot be construed as limiting the scope of protection of this utility model.

[0040] like Figures 1 to 9 As shown, this utility model provides a fuel cell structure for flying cars, including: a closed gas-cooled stack 1 including a bipolar plate assembly, which is formed by integrally bending a single metal plate into a U-shaped conductive plate. Its outer wall is treated with conductive and anti-corrosion treatment and is in contact with the membrane electrode. The inner wall holds and fixes heat sinks and sealing gaskets. The U-shaped opening is encapsulated to form an integrated structure.

[0041] The air guide shroud 2 covers the outside of the fuel cell stack 1 and is connected to the fuel cell stack flow field to uniformly distribute the cooling air pressure;

[0042] Cooling fan 3 is sealed to air guide shroud 2 to form a forced convection heat dissipation channel;

[0043] The fuel cell stack vibration damping pad 7 is located at the bottom of the fuel cell stack 1 and connected to the flying car body through the system vibration damping bracket 19, and is used to absorb flight vibrations;

[0044] The air supply system includes an air filter 5, a compressor 6, and a humidifier 4 connected in sequence, and is connected to the cathode flow field 36 of the fuel cell stack 1 through a pipe.

[0045] The hydrogen supply system includes a hydrogen storage tank, a hydrogen circulation pump and a shut-off valve 31. It is separated from the electrical room by an isolation plate. The hydrogen is circulated through pipelines to the anode flow field 37 of the fuel cell stack 1.

[0046] Furthermore, a single metal plate is selected and a U-shaped conductive plate is made through an integrated bending process. The outer wall is treated with conductive and anti-corrosion coating to ensure the conductivity and corrosion resistance of the contact surface with the membrane electrode. Heat sinks and sealing gaskets are fixed on the inner wall of the U-shaped conductive plate and precisely aligned with the positioning lock 32 and positioning hole 33. The cathode flow field 36 and anode flow field 37 are symmetrically distributed on both sides of the U-shaped plate, and hydrogen holes 34 and air holes 35 are integrated to seal the U-shaped opening, forming an integrated bipolar plate assembly. Multiple bipolar plate assemblies are staggered with the membrane electrode and assembled into a closed gas-cooled fuel cell stack 1 through the fuel cell stack support 9.

[0047] The air guide shroud 2 covers the outside of the fuel cell stack 1, ensuring that it is in communication with the flow field of the fuel cell stack. The inner cavity of the air guide shroud 2 is designed as a gradually narrowing flow channel to evenly distribute the cooling air pressure. A filter cotton 8 for the fuel cell stack negative pressure port is installed between the air guide shroud 2 and the cooling fan 3 to filter impurities in the cooling air. The cooling fan 3 is sealed to the air guide shroud 2 to form a forced convection heat dissipation channel, which dissipates the heat of the fuel cell stack 1 through a closed loop path.

[0048] A shock-absorbing pad 7 is installed at the bottom of the fuel cell stack 1 and fixed to the flying car body by bolts through the system shock-absorbing bracket 19 to absorb the vertical and horizontal vibrations generated during flight.

[0049] Air filter 5, compressor 6, and humidifier 4 are connected in sequence through pipes. After being filtered, the air enters the compressor 6 for pressurization through the fuel cell stack air inlet connector 12, and then the humidity is adjusted by the humidifier 4. Finally, the air is delivered to the fuel cell stack cathode flow field 36 through the fuel cell stack air outlet connector 14 to participate in the reaction. The air achieves flow control and noise suppression through the throttle valve 28 and the muffler 27.

[0050] The hydrogen storage tank is connected to the hydrogen inlet connector 13 and the hydrogen outlet pipe 10 of the fuel cell stack via a hydrogen circulation pump and a shut-off valve 31. After the hydrogen flow rate is regulated by a proportional valve, it circulates to the anode flow field 37 of the fuel cell stack through the hydrogen outlet connector 11. The tail valve 30 is used to discharge residual hydrogen containing impurities. The hydrogen system is physically separated from the electrical room by an isolation plate to prevent leakage risks.

[0051] Furthermore, the U-shaped conductive plate of the bipolar plate assembly integrates a positioning latch 32, a positioning hole 33, a hydrogen gas hole 34, an air hole 35, and a cathode flow field 36 and an anode flow field 37. The cathode flow field 36 and the anode flow field 37 are symmetrically distributed and adopt a parallel flow channel design to ensure uniform distribution of the reaction gas. The positioning latch 32 fixes adjacent bipolar plates by snap-fitting, realizing precise alignment between the stack layers and reducing assembly errors.

[0052] Furthermore, the bottom of the fuel cell stack 1 is provided with a communication and power connector 26, which converts the electrical energy generated by the fuel cell stack 1 into a voltage suitable for use by the flying car through the DC-DC power regulator system 16 and the DC-DC module 17, and then transmits it to each power component through the communication and power connector 26.

[0053] Furthermore, a negative pressure port filter cotton 8 is provided between the air guide shroud 2 and the cooling fan 3. The cooling air passes through the filter cotton, the fuel cell flow field and the inner cavity of the air guide shroud 2 in sequence to form a closed-loop heat dissipation path, avoid interference from the external environment temperature and humidity, and improve heat dissipation stability.

[0054] Furthermore, a hydrogen storage chamber isolation plate 20 is provided between the main storage tank 38 and the distributed hydrogen storage tank 21 of the hydrogen supply system. After the hydrogen flow rate is adjusted by the proportional valve, it is circulated to the fuel cell stack 1 by the hydrogen circulation pump. The tail valve 30 is used to discharge hydrogen containing impurities to maintain the purity of hydrogen.

[0055] Furthermore, the fuel cell stack 1 adopts a modular distributed layout, divided into multiple independent units, which are installed in the double-layer fixed wing 29 of the flying car and connected to the fuselage through the system shock absorption bracket 19 and the mounting bracket 25. The internal space of the wing is used to optimize the weight distribution. Furthermore, due to the existence of the system lifting point 22, the fuel cell module can be flexibly fixed in different parts of the flying car, optimizing the space utilization rate, while adjusting the overall weight distribution to balance flight stability.

[0056] Furthermore, the modular space inside the wing is equipped with an electrical compartment isolation panel 15, which physically isolates the fuel cell control system, DC-DC electronic speed control system 16, and communication cables from the hydrogen fuel assembly, thereby improving safety.

[0057] Furthermore, the double-layer fixed wing 29 integrates a gas-cooled fuel cell stack assembly, a lithium battery pack 24, and a hydrogen storage tank. The internal cavity of the wing is connected to the external environment through the heat dissipation plate 18 of the electrical compartment, and the leading edge of the wing is provided with a hydrogen filling port 23 connected to the main storage tank 38.

[0058] Furthermore, the flying car integrates the aforementioned closed-loop gas-cooled fuel cell stack system, combined with a dual-layer fixed wing structure 29, to achieve switching between vertical take-off and landing and level flight cruise modes. The power system is coupled to the lithium battery pack 24 through a DC-DC electronic speed controller module, with the fuel cell providing continuous power and the lithium battery assisting in transient high power demands.

[0059] Finally, it should be noted that the above embodiments are only used to illustrate the technical solutions of this utility model, and are not intended to limit it. Although this utility model has been described in detail with reference to the foregoing embodiments, those skilled in the art should understand that modifications can still be made to the technical solutions described in the foregoing embodiments, or equivalent substitutions can be made to some or all of the technical features therein. Such modifications or substitutions do not cause the essence of the corresponding technical solutions to deviate from the scope of the technical solutions of the embodiments of this utility model.

Claims

1. A fuel cell structure for a flying car, characterized in that, include: The closed gas-cooled fuel cell stack includes a bipolar plate assembly, which is formed by bending a single metal plate into a U-shaped conductive plate. Its outer wall is treated with conductive and anti-corrosion properties and is in contact with the membrane electrode. The inner wall holds and fixes the heat sink and sealing gasket. The U-shaped opening is encapsulated to form an integrated structure. The air guide shroud covers the outside of the enclosed gas-cooled fuel cell stack and is connected to the stack's flow field, used to evenly distribute the cooling air pressure. The cooling fan is sealed to the air guide shroud to form a forced convection heat dissipation channel; The fuel cell stack vibration damping pad is installed at the bottom of the enclosed gas-cooled fuel cell stack and connected to the flying car body through the system vibration damping bracket to absorb flight vibrations. The air supply system includes an air filter, a compressor, and a humidifier connected in sequence, and is connected to the cathode flow field of the closed gas-cooled fuel cell stack through a pipeline; The hydrogen supply system includes a hydrogen storage tank, a hydrogen circulation pump, and a shut-off valve. It is separated from the electrical room by an isolation plate. The hydrogen is circulated through pipelines to the anode flow field of the closed gas-cooled fuel cell stack.

2. The fuel cell structure for a flying car according to claim 1, characterized in that, The bipolar plate assembly integrates a positioning latch, positioning hole, hydrogen hole, air hole, and cathode and anode flow fields within its U-shaped conductive plate, which are symmetrically distributed.

3. The fuel cell structure for a flying car according to claim 1, characterized in that, A filter cotton with a negative pressure port is provided between the air guide shroud and the cooling fan. Cooling air passes through the filter cotton, the fuel cell flow field and the inner cavity of the air guide shroud in sequence to form a closed-loop heat dissipation path.

4. A fuel cell structure for a flying car according to claim 1, characterized in that, The main storage tank and the distributed hydrogen storage tanks of the hydrogen supply system are separated by a hydrogen storage chamber isolation plate. After the hydrogen flow rate is adjusted by a proportional valve, it is circulated to the closed gas-cooled fuel cell stack by a hydrogen circulation pump. The tail valve is used to discharge hydrogen containing impurities.

5. A fuel cell structure for a flying car according to claim 1, characterized in that, The enclosed gas-cooled fuel cell stack adopts a modular distributed layout, is installed in the double-layer fixed wing of the flying car, and is connected to the airframe through a system shock-absorbing bracket.

6. A fuel cell structure for a flying car according to claim 5, characterized in that, The double-layer fixed wing integrates a closed gas-cooled fuel cell stack assembly, a lithium battery pack, and a hydrogen storage tank. The internal cavity of the wing is connected to the external environment through a heat dissipation plate in the electrical compartment, and a hydrogen refueling port is provided on the leading edge of the wing to connect to the main storage tank.

7. A flying car, characterized in that, Includes the fuel cell structure as described in any one of claims 1 to 6.

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