Hydrogen-powered fiber unmanned aerial vehicle

Abstract

This utility model discloses a hydrogen-powered fiber optic unmanned aerial vehicle (UAV), relating to the technical field of UAVs. It includes a main body of the aircraft with a support platform at its bottom; a fiber optic laying mechanism fixed below the support platform; a hydrogen fuel cell system installed on the support platform, including a hydrogen input end and a power output end, the power output end being connected to the power system of the main body of the aircraft; a hybrid cable including an optical fiber and a hydrogen pipe, the two ends of the optical fiber being connected to the main body of the aircraft and a ground control station respectively, and the hydrogen pipe forming a sealed hydrogen transmission channel; a hydrogen source, the two ends of the hydrogen pipe being connected to a hydrogen source and a hydrogen fuel cell system respectively, the hydrogen source supplying hydrogen to the hydrogen input end of the hydrogen fuel cell system through the hydrogen pipe. This utility model supplies hydrogen to the hydrogen fuel cell system through the hydrogen source and hydrogen pipe, achieving uninterrupted hydrogen supply and greatly improving the endurance of the main body of the aircraft. The hollow optical fiber enables high-speed and stable communication for the UAV.

Description

Technical Field

[0001] This utility model relates to the technical field of fiber optic drones, specifically to fiber optic drones powered by hydrogen fuel cells. Background Technology

[0002] Currently, most tethered drones use cable power supply. For example, Chinese invention patent CN115583360A discloses a tethered drone power supply system, including: a power supply, a bidirectional DC-DC converter, a connecting cable, and an onboard power supply; the power supply is electrically connected to the bidirectional DC-DC converter via the connecting cable, enabling bidirectional power supply to the tethered drone. This type of cable-powered tethered drone achieves long endurance, but the drawback is that the cable is relatively heavy, limiting flight altitude and maneuverability.

[0003] Besides tethered drones, most drones carry energy storage batteries, or hydrogen fuel cells and hydrogen storage tanks. The drawbacks of these drones are that the batteries are heavy, energy consumption is high, and they lack long-endurance capabilities. For example, Chinese utility model patent CN222040777U discloses a hydrogen fuel cell drone, including a drone body, a drone support, a carrier, and a hydrogen fuel cell system. The drone body is located on top of the drone support, the hydrogen fuel cell system is fixedly mounted on the carrier, and the carrier is fixedly mounted on the drone support. The drone is powered by electricity generated by the hydrogen fuel cell system. Hydrogen is supplied to the fuel cell stack through a hydrogen tank. Once the hydrogen in the tank is depleted, the drone needs to land to refuel.

[0004] To avoid interference from external electromagnetic signals, fiber-optic guided drones have been developed. Unlike drones controlled by electromagnetic signals, fiber-optic drones receive commands and transmit data via optical fibers trailing behind them. Because optical signals propagate within the fiber, they are largely unaffected by other external electromagnetic signals. As long as the fiber remains undamaged, the pilot and the drone can engage in safe, stable, and covert information and data exchange. These fiber-optic drones still require either a battery or a power cable for energy storage.

[0005] Therefore, in order to enable drones to achieve long-endurance flight, it is also necessary to solve the problem of long-term power supply for drones. Summary of the Invention

[0006] Therefore, it is necessary to provide a hydrogen-powered fiber optic drone to address the technical problem that drones have low battery capacity, high weight, and short flight time.

[0007] To achieve the above objectives, this utility model provides the following technical solution:

[0008] Hydrogen-powered fiber optic drones, including:

[0009] The main body of the aircraft has a support platform at its bottom;

[0010] The fiber optic laying mechanism is fixed below the support platform and has a built-in fiber optic reel.

[0011] The hydrogen fuel cell system, installed on the carrier platform, includes a hydrogen input end and an electric output end, with the electric output end connected to the power system of the main body of the aircraft;

[0012] The hybrid cable includes an optical fiber and a hydrogen tube, with the two ends of the optical fiber connected to the main body of the aircraft and the ground control station, respectively, and the hydrogen tube forming a sealed hydrogen transmission channel.

[0013] The hydrogen source is connected to both ends of the hydrogen pipe, which are connected to the hydrogen source and the hydrogen fuel cell system respectively. The hydrogen source inputs hydrogen to the hydrogen input terminal of the hydrogen fuel cell system through the hydrogen pipe.

[0014] Preferably, the hydrogen fuel cell system includes:

[0015] The hydrogen fuel cell stack has its anode inlet constituting the hydrogen input terminal;

[0016] The DC / DC converter is connected to the power output terminal of the hydrogen fuel cell stack.

[0017] The battery is the power system that connects the output of the DC / DC converter to the main body of the aircraft.

[0018] The system controller is connected to the hydrogen fuel cell stack, DC / DC converter, and battery.

[0019] Preferably, the hydrogen source is connected to one end of the hydrogen pipe via a first connector, and the hydrogen fuel cell stack is connected to the other end of the hydrogen pipe via a second connector.

[0020] Preferably, both the first connector and the second connector are metal microtube sealed joints, comprising:

[0021] The gas delivery tube has one end connected to the output end of the hydrogen source;

[0022] A sealing ring is nested inside the other end of the air duct;

[0023] A quick-connect mechanism is connected to the other end of the gas delivery tube, and the hydrogen tube is detachably inserted into the quick-connect mechanism.

[0024] Preferably, the hydrogen source is a high-pressure hydrogen storage device or a solid-state hydrogen storage device, and the output end of the hydrogen source is equipped with a pressure reducing valve and an electromagnetic safety shut-off valve, wherein the electromagnetic safety shut-off valve is connected to the system controller.

[0025] Preferred options also include:

[0026] The flight controller, installed on the main body of the aircraft, is used to receive flight control commands from the ground control station and to control the flight of the main body of the aircraft.

[0027] Preferably, the hydrogen tube is a hollow optical fiber.

[0028] Compared with related technologies, the hydrogen-powered fiber optic UAV provided by this utility model has the following beneficial effects:

[0029] 1. This utility model supplies hydrogen to the hydrogen fuel cell system through a hydrogen source and hydrogen pipe, achieving uninterrupted hydrogen supply and greatly improving the flight time of the main body of the aircraft.

[0030] 2. The hollow optical fiber of this invention enables high-speed and stable communication for UAVs. The optical fiber is very light in weight and has little impact on the flight altitude and maneuverability of the aircraft. Attached Figure Description

[0031] Figure 1 A schematic diagram of the structure of a hydrogen-powered fiber optic drone;

[0032] Figure 2 Three-dimensional for the main body of the aircraft Figure 1 ;

[0033] Figure 3 Three-dimensional for the main body of the aircraft Figure 2 ;

[0034] Figure 4 This is a cross-sectional view of the hydrogen pipeline;

[0035] Figure 5 This is a three-dimensional view of the first connector and the second connector.

[0036] Reference numerals: 1. Aircraft body; 11. Aircraft support frame; 2. Support platform; 3. Fiber optic cable laying mechanism; 4. Hydrogen fuel cell system; 41. Hydrogen fuel cell stack; 42. Battery; 5. Hybrid cable; 51. Fiber optic cable; 52. Hydrogen pipe; 521. Hydrogen transmission channel; 6. Hydrogen source; 7. First connector; 8. Second connector; 81. Gas duct; 82. Quick-connect mechanism; 9. Ground control station. Detailed Implementation

[0037] To make the objectives, technical solutions, and advantages of this utility model clearer, the present utility model will be further described in detail below with reference to the accompanying drawings and embodiments.

[0038] It should be noted that in the description of this utility model, terms such as "upper," "lower," "left," and "right," which indicate direction or positional relationship, are based on the direction or positional relationship shown in the accompanying drawings. This is merely for ease of description and does not indicate or imply that the device or element must have a specific orientation, or be constructed and operated in a specific orientation. Therefore, it should not be construed as a limitation of this utility model.

[0039] Furthermore, it should be noted that, in the description of this utility model, unless otherwise explicitly specified and limited, the terms "installation," "connection," and "joining" should be interpreted broadly. For example, they can refer to a fixed connection, a detachable connection, or an integral connection; they can refer to a direct connection or an indirect connection through an intermediate medium. Those skilled in the art can understand the specific meaning of the above terms in this utility model according to the specific circumstances. Example

[0040] Please see Figures 1 to 5 As shown, the hydrogen-powered fiber optic drone provided in this embodiment of the present invention includes an aircraft body 1, a fiber optic laying mechanism 3, a hydrogen fuel cell system 4, a hybrid cable 5, and a hydrogen source 6. Specifically, the aircraft body 1 is located at the upper end of the aircraft support 11, and a support platform 2 is provided at the bottom of the aircraft body 1. The fiber optic laying mechanism 3 is fixed below the support platform 2, and contains a fiber optic reel (not shown in the figure) for winding and unwinding the hybrid cable 5.

[0041] The hydrogen fuel cell system 4 serves as the power supply system for the main body of the aircraft 1 and is installed on the support platform 2. The hydrogen fuel cell system 4 includes a hydrogen input end and a power output end. The hydrogen input end of the hydrogen fuel cell system 4 is used to input hydrogen into the hydrogen fuel cell system 4 and generate electricity using hydrogen. The power output end of the hydrogen fuel cell system 4 is connected to the power system of the main body of the aircraft 1 and is used to supply power to the power system of the main body of the aircraft 1.

[0042] The hybrid cable 5 includes an optical fiber 51 and a hydrogen conduit 52. The hybrid cable 5 is coiled within the optical fiber laying mechanism 3, which has an opening for the hybrid cable 5 to extend outwards. The optical fiber laying mechanism 3 is a mature product and will not be described in detail here. The hydrogen conduit 52 forms a sealed hydrogen transmission channel for continuously supplying hydrogen to the hydrogen fuel cell system 4.

[0043] The hydrogen source 6 is located on the ground and stores hydrogen gas inside. The two ends of the hydrogen pipe 52 are connected to the hydrogen source 6 and the hydrogen fuel cell system 4, respectively. The hydrogen source 6 inputs hydrogen gas to the hydrogen input terminal of the hydrogen fuel cell system 4 through the hydrogen pipe 52.

[0044] In this embodiment, the hydrogen source 6 is connected to one end of the hydrogen pipe 52 via the first connector 7, allowing hydrogen to be input into the hydrogen pipe 52. The hydrogen fuel cell system 4 is connected to the other end of the hydrogen pipe 52 via the second connector 8, allowing hydrogen to be input into the hydrogen fuel cell system 4 via the hydrogen pipe 52. The optical fiber 51 is used to transmit optical signals, while the hydrogen pipe 52 is used for hydrogen delivery.

[0045] In this embodiment, the hydrogen fuel cell system 4 includes a hydrogen fuel cell stack 41, a DC / DC converter (not shown in the figure), a battery 42, and a system controller (not shown in the figure). The hydrogen fuel cell stack 41 is an air-cooled stack, and its anode inlet constitutes the hydrogen input terminal and is connected to the hydrogen pipe 52 through the second connector 8.

[0046] In this embodiment, the input terminal of the DC / DC converter is connected to the power output terminal of the hydrogen fuel cell stack 41 via a low-voltage wiring harness. The output terminal of the DC / DC converter is connected to the high-voltage DC bus. The positive and negative terminals of the battery 42 are connected to the high-voltage DC bus via contactors, so that the electrical energy generated by the hydrogen fuel cell stack 41 is input into the battery 42 for storage. The output terminal of the battery 42 is connected to the power system of the aircraft body 1 to supply power to the power system. The hydrogen fuel cell stack 41, the DC / DC converter, and the battery 42 are all connected to the system controller to monitor and adjust the hydrogen flow rate, the output power of the battery 42, and the communication status of the fiber optic 51 in real time.

[0047] In this embodiment, both the first connector 7 and the second connector 8 are metal microtube sealed connectors. The metal microtube sealed connector includes a gas guide tube 81, a sealing ring (not shown in the figure), and a quick-connect / remove mechanism 82. The gas guide tube 81 is a hollow cylindrical tube made of 316L stainless steel. One end of the gas guide tube 81 is connected to the output end of the hydrogen source 6, and the other end of the gas guide tube 81 has a sealing ring nested inside. The outer wall of the sealing ring is laser-welded to the inner wall of the gas guide tube 81. A 20μm thick carbon nanotube coating is deposited on the surface of the sealing ring to prevent hydrogen permeation. The quick-connect / remove mechanism 82 is connected to the other end of the gas guide tube 81, and the hydrogen tube 52 is detachably inserted into the quick-connect / remove mechanism 82. The quick-connect / remove mechanism 82 is a mature product and will not be described in detail here.

[0048] In this embodiment, the hydrogen source 6 is a high-pressure hydrogen storage device or a solid-state hydrogen storage device with a pressure of 35 MPa or above. The output end of the hydrogen source 6 is equipped with a pressure reducing valve and an electromagnetic safety shut-off valve. The pressure reducing valve reduces the hydrogen output pressure to 0.1-0.5 MPa. The electromagnetic safety shut-off valve is connected to the system controller and can respond to the control commands of the system controller.

[0049] In this embodiment, it also includes: a flight controller (not shown in the figure), a ground control station 9 that generates flight control commands, the flight controller being installed inside the aircraft body 1, used to receive flight control commands issued by the ground control station 9, demodulate optical signals to execute control commands, perform flight control on the aircraft body 1, and transmit flight status data back.

[0050] In this embodiment, the hydrogen tube 52 is a hollow optical fiber with a continuous cavity along its central axis. The cavity forms a sealed hydrogen transmission channel, and the hollow optical fiber has the advantage of being lightweight.

[0051] It should be noted that, in this document, the terms “comprising,” “including,” or any other variations thereof are intended to cover non-exclusive inclusion, such that a process, method, article, or apparatus that comprises a list of elements includes not only those elements but also other elements not expressly listed, or elements inherent to such process, method, article, or apparatus.

[0052] Although embodiments of the present invention have been shown and described, it will be understood by those skilled in the art that various changes, modifications, substitutions and alterations can be made to these embodiments without departing from the principles and spirit of the present invention, the scope of which is defined by the appended claims and their equivalents.

Claims

1. A hydrogen powered fiber drone, characterized by, include: The main body of the aircraft (1) has a support platform (2) at its bottom; The fiber optic laying mechanism (3) is fixed below the support platform (2) and has a built-in fiber optic reel; The hydrogen fuel cell system (4) is installed on the carrier platform (2) and includes a hydrogen input end and an electric output end. The electric output end is connected to the power system of the aircraft body (1). The hybrid cable (5) includes an optical fiber (51) and a hydrogen tube (52). The two ends of the optical fiber (51) are connected to the main body of the aircraft (1) and the ground control station (9) respectively. The hydrogen tube (52) forms a sealed hydrogen transmission channel. The hydrogen source (6) and the two ends of the hydrogen pipe (52) are respectively connected to the hydrogen source (6) and the hydrogen fuel cell system (4). The hydrogen source (6) inputs hydrogen into the hydrogen input end of the hydrogen fuel cell system (4) through the hydrogen pipe (52).

2. The hydrogen powered fiber drone of claim 1, wherein: The hydrogen fuel cell system (4) includes: The hydrogen fuel cell stack (41) has its anode inlet constituting the hydrogen input terminal; The DC / DC converter is connected to the power output terminal of the hydrogen fuel cell stack (41) at its input terminal. Battery (42), a power system connected to the output of DC / DC converter and the main body of the aircraft (1); The system controller is connected to the hydrogen fuel cell stack (41), DC / DC converter, and battery (42).

3. The hydrogen-powered fiber optic UAV according to claim 2, characterized in that: The hydrogen source is connected to one end of the hydrogen pipe (52) via a first connector (7), and the hydrogen fuel cell stack (41) is connected to the other end of the hydrogen pipe (52) via a second connector (8).

4. The hydrogen powered fiber drone of claim 3, wherein: Both the first connector (7) and the second connector (8) are metal microtube sealing joints, including: A gas delivery tube (81) is used to connect one end to the output end of a hydrogen source (6); A sealing ring is nested inside the other end of the air duct (81); The quick-connect mechanism (82) is connected to the other end of the gas guide tube (81), and one end of the hydrogen tube (52) is detachably inserted into the quick-connect mechanism (82).

5. The hydrogen powered fiber drone of claim 2, wherein: The hydrogen source (6) is a high-pressure hydrogen storage device or a solid hydrogen storage device. The output end of the hydrogen source (6) is equipped with a pressure reducing valve and an electromagnetic safety shut-off valve. The electromagnetic safety shut-off valve is connected to the system controller.

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