Fuel cell engine of unmanned aerial vehicle

Abstract

The utility model discloses a fuel cell engine of an unmanned aerial vehicle. The fuel cell engine comprises a frame, and a plurality of air-cooled galvanic pile modules, a plurality of fans, an electric control module, a hydrogen bottle and a battery pack which are connected with one another, a plurality of placing areas, a plurality of windward channels and a storage area which are communicated with one another are arranged in the frame; the windward channels are located among the multiple placement areas, and the storage areas are located among the multiple windward channels; the windward channel is used for providing natural wind to cool the air-cooled galvanic pile module, the electric control module, the hydrogen bottle and the battery pack; the air-cooled electric pile module is positioned in the placement area; the fan is mounted on one side, far away from the windward channel, of the air-cooled galvanic pile module; the electric control module is located in the storage area; and the hydrogen bottle and the battery pack are arranged on the frame. According to the utility model, natural wind can be provided for an electric pile, heat can be dissipated for other modules, and a fuel cell system is helped to work more stably.

Description

Technical Field

[0001] The utility model relates to the technical field of unmanned aerial vehicle fuel cells, in particular to a fuel cell engine for an unmanned aerial vehicle. Background Art

[0002] For proton exchange membrane fuel cells, the temperature and humidity of the membrane electrode are key factors affecting output performance. Liquid-cooled fuel cells can easily control the temperature and humidity of the stack through peripheral equipment, but it is relatively difficult to control the temperature and humidity of air-cooled fuel cells because the temperature and humidity are coupled together and difficult to control separately. Especially for open air-cooled stacks, when the output power of the stack is low, the temperature rises slowly. When the output power of the stack is high, it is necessary to rely on the fan to inhale a large amount of air for convection heat dissipation. When running at high power, if the fan air volume is too large, the temperature can be controlled, but it is easy to dry the membrane electrode; when running at low power, if the fan is turned on low, the water vapor cannot be discharged, and if the fan is turned on high, the temperature of the stack will drop again. Although the closed air-cooled stack can solve the above problems, it lacks advantages in power density ratio and equipment complexity compared with the open air-cooled stack. The air-cooled stack is equipped with a fan to provide the necessary air for the normal operation of the stack cathode. The fan is an energy-consuming component. Although a large number of fans will facilitate the temperature and humidity control of the stack, it will also reduce the electric power provided by the fuel cell for the drone.

[0003] Therefore, it is urgent to propose a UAV fuel cell engine to solve the above problems. Utility Model Content

[0004] The purpose of the utility model is to provide a UAV fuel cell engine, which can provide natural wind for the fuel cell stack and dissipate heat for other modules, so as to help the fuel cell system work more stably.

[0005] In order to solve the above technical problems, the utility model provides a UAV fuel cell engine, including a frame and a plurality of air-cooled stack modules connected thereto, a plurality of fans, an electronic control module, a hydrogen bottle and a battery pack;

[0006] The frame is provided with multiple interconnected placement areas, multiple windward channels and storage areas; the windward channel is located between the multiple placement areas, and the storage area is located between the multiple windward channels; the windward channel is used to provide natural wind to dissipate heat for the air-cooled fuel cell module, the electronic control module, the hydrogen bottle and the battery pack; the air-cooled fuel cell module is located in the placement area; the fan is installed on the side of the air-cooled fuel cell module away from the windward channel; the electronic control module is located in the storage area; the hydrogen bottle and the battery pack are both installed on the frame.

[0007] Furthermore, the plurality of windward channels are symmetrically arranged.

[0008] Furthermore, the frame includes a bottom and a top; the hydrogen bottle is installed at the bottom of the frame; and the battery pack is installed at the top of the frame.

[0009] Furthermore, blocks are provided at the four corners on the top of the frame for positioning the battery pack.

[0010] Furthermore, the placement area includes a group of relatively arranged openings; one of the openings is connected to one of the windward channels, and the fan is installed on the air-cooled fuel cell stack module through another opening.

[0011] Furthermore, the electronic control module includes a fuel cell control module and a power supply control module which are connected to each other.

[0012] Furthermore, the battery pack includes a connected battery stack inspection system, a battery management system, a lithium battery and a wiring harness.

[0013] Furthermore, the material of the frame includes at least one of carbon fiber, aluminum alloy and titanium alloy.

[0014] Furthermore, the air-cooled fuel cell stack module includes a closed air-cooled fuel cell stack module and an open air-cooled fuel cell stack module.

[0015] Furthermore, the hydrogen bottle includes a high-pressure hydrogen bottle or a liquid hydrogen bottle.

[0016] Through the above technical solution, the utility model has the following beneficial effects:

[0017] Through the arrangement of a frame and multiple connected air-cooled stack modules, multiple fans, electric control modules, hydrogen bottles and battery packs; and multiple placement areas, multiple windward channels and storage areas are connected in the frame; the windward channels are located between the multiple placement areas, and the storage areas are located between the multiple windward channels; the windward channels are used to provide natural wind to dissipate heat for the air-cooled stack modules, electric control modules, hydrogen bottles and battery packs; the air-cooled stack modules are located in the placement areas; the fans are installed on the side of the air-cooled stack modules away from the windward channels; the electric control modules are located in the storage areas; the hydrogen bottles and battery packs are both installed on the frame. The utility model can be beneficial for providing natural wind for the stack, and can dissipate heat for other modules, helping the fuel cell system to work more stably. BRIEF DESCRIPTION OF THE DRAWINGS

[0018] Figure 1 This is a schematic diagram of the overall structure of a fuel cell engine for a drone in one embodiment of the utility model;

[0019] Figure 2 This is an exploded view of a UAV fuel cell engine in one embodiment of the utility model.

[0020] In the figure, 1. frame; 11. placement area; 12. windward channel; 13. storage area; 14. block; 2. air-cooled stack module; 3. fan; 4. electronic control module; 5. hydrogen bottle; 6. battery pack. DETAILED DESCRIPTION

[0021] The following is a more detailed description of a UAV fuel cell engine of the utility model in conjunction with the accompanying drawings, which shows a preferred embodiment of the utility model. It should be understood that those skilled in the art can modify the utility model described herein and still achieve the beneficial effects of the utility model. Therefore, the following description should be understood as being widely known to those skilled in the art and not as a limitation to the utility model.

[0022] The present invention is described in more detail in the following paragraphs by way of example with reference to the accompanying drawings. The advantages and features of the present invention will become more apparent from the following description. It should be noted that the accompanying drawings are in very simplified form and in non-precise proportions, and are only used to conveniently and clearly assist in explaining the purpose of the embodiments of the present invention.

[0023] like Figure 1-2 As shown, an embodiment of the utility model proposes a UAV fuel cell engine, including a frame 1 and a plurality of air-cooled stack modules 2, a plurality of fans 3, an electronic control module 4, a hydrogen bottle 5 and a battery pack 6 connected thereto.

[0024] Specifically, the frame 1 has a plurality of interconnected placement areas 11, a plurality of windward channels 12 and a storage area 13; the windward channel 12 is located between the plurality of placement areas 11, and the storage area 13 is located between the plurality of windward channels 12; the windward channel 12 is used to provide natural wind to dissipate heat for the air-cooled fuel cell module 2, the electronic control module 4, the hydrogen bottle 5 and the battery pack 6; the air-cooled fuel cell module 2 is located in the placement area 11; the fan 3 is installed on the side of the air-cooled fuel cell module 2 away from the windward channel 12; the electronic control module 4 is located in the storage area 13; the hydrogen bottle 5 and the battery pack 6 are both installed on the frame 1.

[0025] Preferably, the plurality of windward channels 12 are symmetrically arranged. The symmetrical arrangement of the windward channels 12 can balance the center of gravity of the drone during flight, improve flight stability and maneuverability, and evenly distribute cooling air to each air-cooled stack module 2, thereby improving heat dissipation efficiency and avoiding performance degradation or damage caused by uneven heat dissipation.

[0026] Those skilled in the art will appreciate that the plurality of windward channels 12 may also be arranged asymmetrically, and may be arranged according to actual needs.

[0027] In a specific example, two windward channels 12 are left on the frame 1. During the flight of the drone, high-speed airflow passes through the windward channels 12, generating negative pressure on the inner side of the air-cooled stack module 2. The fan 3 on the outer side of the air-cooled stack module 2 can set the speed of the fan 3 according to the negative pressure, stack temperature, membrane humidity, and air temperature and humidity detection data. Compared with traditional technology, the natural wind generated by the flight of the aircraft is sucked into the air-cooled stack module 2, which can reduce the operating burden of the fan 3 and create favorable conditions for the precise control of the temperature and humidity of the air-cooled stack module 2. Among them, the windward channel 12 can also achieve the effect of cooling other modules.

[0028] In a specific example, for example, the windward channel 12 and the air-cooled stack module 2 are both set to two, and the cross-sectional shape and size of the two windward channels 12 can be selected and set according to actual needs. In addition, the two windward channels 12 on the left and right can also be asymmetric, and the specific arrangement is determined by the maximum air intake speed, air intake flow rate and weight distribution required by the left and right air-cooled stack modules 2.

[0029] Among them, the frame 1 can arrange two air-cooled stack modules 2 on the left and right, and the structure is compact. The models or types of the two air-cooled stack modules 2 can be set according to actual needs. If their weights or center of gravity positions are inconsistent, it is necessary to consider making the center of gravity of the entire system meet the design requirements of the drone during setting.

[0030] In a specific embodiment, different types of air-cooled stack modules 2 can be configured according to the application environment. For high-altitude application environments, it is recommended to arrange a closed air-cooled stack module; the air-cooled stack module 2 has a fan 3 arranged outward on one side, which is used to draw air into the entire system. When the water content of the membrane electrode is too low, it can also rotate in the opposite direction to prevent the inflow of natural wind.

[0031] In one embodiment, the frame 1 includes a bottom and a top; the hydrogen bottle 5 is installed at the bottom of the frame 1; and the battery pack 6 is installed at the top of the frame 1. The installation position of the hydrogen bottle 5 can be the bottom or the top, which can be set according to actual conditions.

[0032] The hydrogen bottle 5 includes a high-pressure hydrogen bottle or a liquid hydrogen bottle. Those skilled in the art will appreciate that the hydrogen bottle 5 may be a desired type of hydrogen bottle according to actual conditions, that is, it may include other types of hydrogen bottles in addition to the high-pressure hydrogen bottle or liquid hydrogen bottle in this embodiment.

[0033] Preferably, blocks 14 are provided at the four corners on the top of the frame 1 for positioning the battery pack 6 to improve safety.

[0034] In this embodiment, the placement area 11 includes a group of relatively arranged through openings; one of the through openings is connected to one of the windward channels 12, and the fan 3 is installed on the air-cooled stack module 2 through another through opening. The fan 3 directly forces air cooling on the air-cooled stack module 2 through the through opening, which can significantly improve the heat dissipation efficiency, especially under high temperature or high load working conditions, which helps to keep the stack temperature within a reasonable range and prevent overheating. The position and direction of the fan 3 can be optimized according to the setting of the through opening to achieve the best airflow dynamics effect, reduce airflow resistance, and improve the efficiency of the fan 3.

[0035] The fan 3 is located outside the frame 1 .

[0036] In this embodiment, the electric control module 4 includes a fuel cell control module and a power control module connected to each other. The fuel cell control module and the power control module can be arranged between the two windward channels 12, and the module side faces and the airflow in the windward channel 12 perform efficient convection heat exchange, thereby ensuring the stable operation of the electrical module.

[0037] In one embodiment, the battery pack 6 includes a battery stack inspection system, a battery management system, a lithium battery and a wiring harness that are connected to each other.

[0038] Preferably, the material of the frame 1 includes at least one of carbon fiber, aluminum alloy and titanium alloy, which can effectively reduce the weight of the drone and improve the load capacity and endurance of the drone. It is known to those skilled in the art that the material of the frame 1 can also include other materials while achieving the same effect, and can be set according to actual needs.

[0039] In this embodiment, the air-cooled stack module 2 includes a closed air-cooled stack module and an open air-cooled stack module. The type of the air-cooled stack module 2 can be selected according to actual needs.

[0040] In this embodiment, during the flight of the aircraft, a large amount of air will pass through the windward channel 12, generating negative pressure on the side of the windward channel 12, and the side of the windward channel 12 is connected to the inner side of the air-cooled stack module 2. The negative pressure helps the natural wind to flow into the cathode flow channel of the air-cooled stack module 2 through the fan 3 on the outside of the air-cooled stack module 2, providing the air-cooled stack module 2 with a large amount of additional air generated by the windward channel 12, increasing the temperature and humidity adjustable space of the air-cooled stack module 2. This device introduces the concept of the windward channel 12 in the UAV fuel cell power system. The windward channel 12 not only brings additional natural wind to the stack, but also cools down other modules, thereby helping the fuel cell system to work more stably.

[0041] In summary, the UAV fuel cell engine proposed in the utility model has the following advantages:

[0042] Through the arrangement of a frame and multiple connected air-cooled stack modules, multiple fans, electric control modules, hydrogen bottles and battery packs; and multiple placement areas, multiple windward channels and storage areas are connected in the frame; the windward channels are located between the multiple placement areas, and the storage areas are located between the multiple windward channels; the windward channels are used to provide natural wind to dissipate heat for the air-cooled stack modules, electric control modules, hydrogen bottles and battery packs; the air-cooled stack modules are located in the placement areas; the fans are installed on the side of the air-cooled stack modules away from the windward channels; the electric control modules are located in the storage areas; the hydrogen bottles and battery packs are both installed on the frame. The utility model can be beneficial for providing natural wind for the stack, and can dissipate heat for other modules, helping the fuel cell system to work more stably.

[0043] Obviously, those skilled in the art can make various changes and modifications to the present invention without departing from the spirit and scope of the present invention. Thus, if these modifications and variations of the present invention fall within the scope of the claims of the present invention and their equivalents, the present invention is also intended to include these modifications and variations.

Claims

1. A fuel cell engine for an unmanned aerial vehicle, characterized in that: It includes a frame and multiple connected air-cooled fuel cell modules, multiple fans, an electronic control module, a hydrogen bottle and a battery pack; The frame is provided with multiple interconnected placement areas, multiple windward channels and storage areas; the windward channel is located between the multiple placement areas, and the storage area is located between the multiple windward channels; the windward channel is used to provide natural wind to dissipate heat for the air-cooled fuel cell module, the electronic control module, the hydrogen bottle and the battery pack; the air-cooled fuel cell module is located in the placement area; the fan is installed on the side of the air-cooled fuel cell module away from the windward channel; the electronic control module is located in the storage area; the hydrogen bottle and the battery pack are both installed on the frame.

2. The UAV fuel cell engine according to claim 1, characterized in that: The plurality of windward channels are symmetrically arranged.

3. The UAV fuel cell engine according to claim 1, characterized in that: The frame includes a bottom and a top; the hydrogen bottle is installed at the bottom of the frame; and the battery pack is installed at the top of the frame.

4. The UAV fuel cell engine according to claim 3, characterized in that: Stoppers are provided at the four corners on the top of the frame for positioning the battery pack.

5. The UAV fuel cell engine according to claim 1, characterized in that: The placement area includes a group of relatively arranged through-holes; one of the through-holes is connected to one of the windward channels, and the fan is installed on the air-cooled stack module through another through-hole.

6. The UAV fuel cell engine according to claim 1, characterized in that: The electric control module includes a fuel cell control module and a power control module which are connected to each other.

7. The UAV fuel cell engine according to claim 1, characterized in that: The battery pack includes a battery stack inspection system, a battery management system, a lithium battery and a wiring harness that are connected to each other.

8. The UAV fuel cell engine according to claim 1, characterized in that: The material of the frame includes at least one of carbon fiber, aluminum alloy and titanium alloy.

9. The UAV fuel cell engine according to claim 1, characterized in that: The air-cooled fuel cell stack module includes a closed air-cooled fuel cell stack module and an open air-cooled fuel cell stack module.

10. The UAV fuel cell engine according to claim 1, characterized in that: The hydrogen bottle includes a high-pressure hydrogen bottle or a liquid hydrogen bottle.

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