Hydrogen fuel cell unmanned aerial vehicle for power field

Abstract

The hydrogen fuel cell unmanned aerial vehicle comprises a vehicle body and a high-pressure air inlet end, and the vehicle body is provided with a high-pressure area around the vehicle body in the flying process; the air inlet end is used for entering air, the air inlet end is communicated with the fuel cell in an air path mode, the air inlet end is located in a high-pressure area, and the air is sucked and squeezed into the air inlet end in a high-pressure state. According to the invention, the high-pressure air inlet end is arranged below the paddle of the unmanned aerial vehicle, so that when the paddle of the unmanned aerial vehicle works, the high-pressure area below can ensure that enough air enters the high-pressure air inlet end, and air is stably supplied to the fuel cell through the air inlet end, so that the unmanned aerial vehicle adapts to the working environment of air areas such as high altitude or high altitude.

Description

Technical Field

[0001] This invention relates to aerial work equipment, and more specifically to a hydrogen fuel cell drone for the power industry. Background Technology

[0002] Compared to traditional drones equipped with fixed energy storage batteries, drones equipped with hydrogen fuel cells are better suited for longer flight times, making them more suitable for special operations. However, in current technology, hydrogen fuel cell drones used for power equipment installation and inspection, especially those operating at high altitudes and at high altitudes, suffer from low oxygen supply due to the thin air, resulting in slower internal reactions and a lower energy supply rate. Therefore, further technological improvements are needed for drones operating in such environments. Summary of the Invention

[0003] The purpose of this section is to outline some aspects of embodiments of the present invention and to briefly describe some preferred embodiments. Simplifications or omissions may be made in this section, as well as in the abstract and title of this application, to avoid obscuring the purpose of these documents; however, such simplifications or omissions should not be construed as limiting the scope of the invention.

[0004] To address the technical problems reflected in the background section, the present invention provides the following technical solution: A hydrogen fuel cell drone for the power sector includes a body, and a high-pressure air intake end and a low-pressure air intake end for air intake, wherein: The aircraft has a high-pressure zone around itself during flight; The high-pressure air inlet is used to introduce air and is configured to be connected to the fuel cell via an air passage. The high-pressure air inlet is located in the high-pressure zone, and air is drawn into the high-pressure air inlet under high pressure. The low-pressure intake end is not located in the high-pressure area and works alternately with the high-pressure intake end.

[0005] As a preferred technical solution for hydrogen fuel cell drones used in the power sector, the high-pressure air intake is located below the propeller blades of the fuselage.

[0006] As a preferred technical solution for hydrogen fuel cell drones used in the power sector, the low-pressure air inlet is located in the atmospheric pressure region and is configured to work alternately with the high-pressure air inlet.

[0007] As a preferred technical solution for hydrogen fuel cell drones used in the power sector, both the high-pressure air inlet and the low-pressure air inlet are configured to be openable or closed.

[0008] As a preferred technical solution for hydrogen fuel cell drones in the power field, it also includes a transition cavity. The high-pressure air inlet is connected to the fuel cell gas path through the transition cavity, and the low-pressure air inlet is disposed on the transition cavity. The transition cavity keeps the low-pressure air inlet closed under high pressure.

[0009] As a preferred technical solution for hydrogen fuel cell drones used in the power sector, a sealing component is movably disposed on the transition cavity, and the sealing component moves to keep the low-pressure air inlet closed under the impact of airflow.

[0010] As a preferred technical solution for hydrogen fuel cell drones used in the power field, the high-pressure air inlet includes a gas storage hood fixedly configured below the propeller blades. The gas storage hood has a pressure relief port through which airflow passes longitudinally, and also includes a shielding component configured to either block or release the pressure relief port. A connecting pipe is configured between the inner side of the gas storage hood and the transition cavity.

[0011] As a preferred technical solution for hydrogen fuel cell drones used in the power sector, the diameter of the channel inside the gas storage hood gradually decreases from top to bottom, and the pressure relief port is located at the bottom of the gas storage hood.

[0012] As a preferred technical solution for hydrogen fuel cell drones used in the power sector, a magnetic action part is fixedly provided inside the gas storage cover, and the shielding component is configured to be elastically away from the pressure relief port and is equipped with a permanent magnet.

[0013] As a preferred technical solution for hydrogen fuel cell drones used in the power field, a guide rod is fixedly installed inside the gas storage hood, and the shielding component slides in cooperation with the guide rod. When the shielding component slides down to the lowest point, it abuts against the inner wall of the gas storage hood to cover the pressure relief port.

[0014] The hydrogen fuel cell drone for the power sector provided by this invention has the following beneficial effects: (1) The present invention provides a high-pressure air intake end below the rotor blades of the UAV, so that when the UAV rotor blades are working, the high-pressure area below can ensure that enough air enters the high-pressure air intake end, thereby providing stable air supply to the fuel cell through the high-pressure air intake end, so as to adapt to the working environment of high-altitude or high-air areas.

[0015] (2) By combining the high-pressure air intake end and the low-pressure air intake end, the present invention can select the appropriate air intake method according to the different air concentrations in the environment where the UAV is located, so that the impact of the high-pressure air intake end on the flight of the aircraft can be reduced when necessary. Attached Figure Description

[0016] To more clearly illustrate the technical solutions of the embodiments of the present invention, the drawings used in the description of the embodiments will be briefly introduced below. Obviously, the drawings described below are only some embodiments of the present invention. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort. Wherein: Figure 1 This is a perspective view of the drone described in an embodiment of the present invention.

[0017] Figure 2 for Figure 1 Top view of the structure shown.

[0018] Figure 3 This is a schematic diagram of the high-pressure air intake end in an embodiment of the present invention.

[0019] Figure 4 This is a schematic diagram of the structure of the magnetic action part in an embodiment of the present invention.

[0020] Figure 5 This is a schematic diagram of the transition cavity described in an embodiment of the present invention.

[0021] Figure 6 for Figure 5 A diagram showing the internal structure.

[0022] Figure 7 for Figure 6 Another perspective view of the structure shown.

[0023] Figure label: 1. Gas reservoir cover; 2. Pressure relief port; 3. Pad block; 4. Guide rod; 5. Excitation coil; 6. Shielding component; 7. Exchange box; 8. Air inlet; 9. Air outlet; 10. Low-pressure air inlet end; 11. Sealing component. Detailed Implementation

[0024] To make the above-mentioned objects, features and advantages of the present invention more apparent and understandable, the specific embodiments of the present invention will be described in detail below with reference to the accompanying drawings.

[0025] Many specific details are set forth in the following description in order to provide a full understanding of the invention. However, the invention may also be practiced in other ways different from those described herein, and those skilled in the art can make similar extensions without departing from the spirit of the invention. Therefore, the invention is not limited to the specific embodiments disclosed below.

[0026] Secondly, the term "one embodiment" or "embodiment" as used herein refers to a specific feature, structure, or characteristic that may be included in at least one implementation of the present invention. The phrase "in one embodiment" appearing in different places in this specification does not necessarily refer to the same embodiment, nor is it a single or selective embodiment that is mutually exclusive with other embodiments.

[0027] Secondly, the present invention is described in detail with reference to the schematic diagrams. When detailing the embodiments of the present invention, for ease of explanation, the cross-sectional views illustrating the device structure may be partially enlarged, not according to the usual scale. Furthermore, the schematic diagrams are merely examples and should not limit the scope of protection of the present invention. In addition, actual fabrication should include three-dimensional spatial dimensions of length, width, and depth.

[0028] Example: Reference Figure 1 and Figure 2 The present invention provides a hydrogen fuel cell drone for the power field, including the drone body (hereinafter referred to as the body), and the body is equipped with a hydrogen fuel cell and a hydrogen storage tank in accordance with the prior art. Furthermore, at least several propeller blades on the fuselage are equipped with high-pressure air intakes below them. Regarding their structure, specifically, as follows... Figures 1 to 3 As shown, the high-pressure air intake includes an air storage hood 1 fixedly installed at the bottom of the propeller motor. The air storage hood 1 is conical with an open pressure relief port 2 at the bottom. The conical structure causes the internal channel of the air storage hood 1 to gradually narrow from top to bottom in the longitudinal direction, so that the air pressed down by the propeller can be gradually compressed after entering the air storage hood 1, thereby increasing the pressure. A pad 3 and a guide rod 4 are fixedly installed at the bottom of the propeller motor. An excitation coil 5 is installed inside the pad 3. A blocking member 6 is slidably installed on the guide rod 4. The blocking member 6 has a circular structure and is equipped with a permanent magnet. A spring is connected between the blocking member 6 and the pad 3. By the elastic force of the spring, the blocking member 6 is kept away from the pressure relief port 2 in the normal state, so that the pressure relief port 2 is in the normally open state. When the blocking member 6 slides down to the bottom, it abuts against the inner wall of the air storage hood 1, thereby sealing the pressure relief port 2. Furthermore, the present invention also includes an exchange box 7, the interior of which is the aforementioned transition cavity. Specifically, the exchange box 7 has an air inlet 8 and an air outlet 9. The air inlet 8 is used to connect to the inside of multiple gas storage hoods 1 through a pipeline. The pipeline can be hidden inside the support arm of the machine body to prevent dragging and affecting the appearance. The air outlet 9 is used to connect to the gas supply end of the hydrogen fuel cell. In addition, the exchange box 7 is also equipped with a low-pressure air inlet 10. The low-pressure air inlet 10 is an open structure. A sealing member 11 is movably disposed inside the exchange box 7. The sealing member 11 is a thin sheet structure and is movably disposed near the low-pressure air inlet 10. When there is a certain gas pressure in the transition cavity, it will squeeze the sealing member 11 to the low-pressure air inlet 10, thereby keeping the low-pressure air inlet 10 closed. In summary, when the machine operates under normal pressure, the excitation coil 5 is not activated, and the pressure relief port 2 remains open. The air swept by the blades can pass through the pressure relief port 2 normally when passing through the gas storage hood 1, thereby reducing the impact on the lift of the machine. When the fuel cell is operating normally, air is supplied through the low-pressure intake end 10, and the section of the intake port 8 connected to the gas storage hood 1 can also assist in supplying air. When the machine operates in an environment with high altitude or low air concentration, the excitation coil 5 is activated, and a repulsive effect is formed between it and the shielding component 6, causing the shielding component 6 to be pushed to block the pressure relief port 2. At this time, the air pressed down by the blades gathers inside the gas storage hood 1 and forms a certain pressure, which is then squeezed into the fuel cell through the pipeline and transition chamber to ensure sufficient oxygen supply to the fuel cell. During this process, when the pressurized airflow passes through the transition chamber, the pressure will squeeze the sealing component 11, thereby keeping the low-pressure intake end 10 closed to prevent the pressed airflow from escaping. Compared to existing technologies, this invention utilizes the high-pressure zone formed below the blades during operation to pressurize the fuel cell's air intake, thereby ensuring the air intake requirements of the battery when operating in a low-pressure environment, thus guaranteeing the power supply rate and enabling the unit to operate stably even at high altitudes.

[0029] It should be understood that numerous specific implementation decisions can be made during the development of any practical implementation, such as in any engineering or design project. Such development efforts may be complex and time-consuming, but for those skilled in the art who benefit from this disclosure, the development effort will be a routine work of design, manufacturing, and production without requiring much experimentation.

[0030] It should be noted that the above embodiments are only used to illustrate the technical solutions of the present invention and are not intended to limit it. Although the present invention has been described in detail with reference to preferred embodiments, those skilled in the art should understand that modifications or equivalent substitutions can be made to the technical solutions of the present invention without departing from the spirit and scope of the technical solutions of the present invention, and all such modifications or substitutions should be covered within the scope of the claims of the present invention.

Claims

1. A hydrogen fuel cell drone for the power sector, characterized in that: This includes the air intake body, and the high-pressure intake end and low-pressure intake end for air intake, wherein: The aircraft has a high-pressure zone around itself during flight; The high-pressure air inlet is used to introduce air and is configured to be connected to the fuel cell via an air passage. The high-pressure air inlet is located in the high-pressure zone, and air is drawn into the high-pressure air inlet under high pressure. The low-pressure intake end is not located in the high-pressure area and works alternately with the high-pressure intake end.

2. The hydrogen fuel cell drone for the power sector according to claim 1, characterized in that: The high-pressure air intake is located below the propeller blades of the engine body.

3. The hydrogen fuel cell drone for the power sector according to claim 1, characterized in that: The low-pressure intake end is located in the atmospheric pressure region and is configured to alternately supply gas to the fuel cell with the high-pressure intake end.

4. The hydrogen fuel cell drone for the power sector according to claim 3, characterized in that: Both the high-pressure air inlet and the low-pressure air inlet are configured to be openable or closed.

5. The hydrogen fuel cell drone for the power sector according to claim 4, characterized in that: It also includes a transition cavity, through which the high-pressure air inlet is connected to the fuel cell gas path, and the low-pressure air inlet is disposed on the transition cavity. The transition cavity keeps the low-pressure air inlet closed under high pressure.

6. The hydrogen fuel cell drone for the power sector according to claim 5, characterized in that: A sealing element is movably disposed on the transition cavity, and the sealing element moves to keep the low-pressure air inlet closed under the impact of airflow.

7. The hydrogen fuel cell drone for the power sector according to claim 5, characterized in that: The high-pressure air inlet includes an air storage shroud fixedly disposed below the blade. The air storage shroud has a pressure relief port through which airflow passes longitudinally. It also includes a shielding component configured to either block or release the pressure relief port. A connecting pipe is disposed between the inner side of the air storage shroud and the transition cavity.

8. The hydrogen fuel cell drone for the power sector according to claim 7, characterized in that: The diameter of the channel inside the gas storage hood gradually decreases from top to bottom, and the pressure relief port is located at the bottom of the gas storage hood.

9. The hydrogen fuel cell drone for the power sector according to claim 8, characterized in that: A magnetic actuating part is fixedly installed on the inner side of the gas storage hood, and the shielding part is configured to be elastically away from the pressure relief port and is equipped with a permanent magnet.

10. The hydrogen fuel cell drone for the power sector according to claim 9, characterized in that: A guide rod is fixedly installed inside the gas storage hood. The shielding component slides in cooperation with the guide rod. When the shielding component slides down to its lowest point, it abuts against the inner wall of the gas storage hood to cover the pressure relief port.

Images