Hydrogen supply system for hydrogen fuel cell of unmanned aerial vehicle

Abstract

The invention provides a hydrogen supply system for a hydrogen fuel cell of an unmanned aerial vehicle, the hydrogen supply system comprises a hydrogen cylinder and a bottle opening valve connected to one end of the hydrogen cylinder, the bottle opening valve comprises a stop valve, a two-stage pressure reducing valve mechanism, an adding and discharging mechanism, a temperature sensing pressure relief mechanism and a pressure sensing mechanism, and the other end of the IV type hydrogen cylinder is provided with a pressure sensing pressure relief mechanism. The stop valve is connected between the IV-type hydrogen cylinder and the two-stage pressure reducing valve mechanism and is used for stopping communication with the downstream when the IV-type hydrogen cylinder is inflated; the stop valve, the two-stage pressure reducing valve mechanism, the adding and discharging mechanism, the TPRD temperature sensing pressure relief mechanism and the pressure sensing mechanism are integrated through the bottleneck valve, so that the sealing performance and safety of the system are guaranteed; double overpressure protection mechanisms of the TPRD temperature sensing pressure relief mechanism and the pressure sensing pressure relief mechanism are adopted, so that the safety and reliability of the system are further improved; and the design of high integration, high light weight and double safety mechanisms is adopted, so that the device has higher market competitiveness in use.

Description

Technical Field

[0001] This invention relates to the field of power system technology for low-altitude economic unmanned aerial vehicles (UAVs), and in particular to a hydrogen supply system for a hydrogen fuel cell for UAVs. Background Technology

[0002] In recent years, drone technology has developed rapidly and has been widely used in many fields such as military reconnaissance, logistics transportation, geographic surveying, agricultural asset preservation, and power line inspection. However, endurance has always been a key factor restricting the further expansion of drone applications.

[0003] Traditional battery technology suffers from low energy density and long charging times, making it difficult to meet the demands of extended flight. Against this backdrop, hydrogen fuel cells have attracted significant attention as a novel energy solution. Their advantages, including high energy density, rapid charging, and zero emissions, offer a new direction for drone endurance. The drone hydrogen supply system project has emerged to address this need, aiming to develop a reliable and efficient hydrogen supply system, enabling the drone industry to overcome endurance bottlenecks and unlock broader application prospects.

[0004] The market demand for drone-based hydrogen supply systems is experiencing unprecedented growth, driven by multiple factors including technological advancements, market demand, and relevant policies. In the future, as the industry chain matures and the demand for industrial-grade applications increases, drone-based hydrogen supply systems will see widespread development. Summary of the Invention

[0005] In view of this, the present invention proposes a hydrogen supply system for unmanned aerial vehicles (UAVs) using hydrogen fuel cells, which solves the problems of low energy density and long charging time of existing UAV batteries. The specific technical solution is as follows:

[0006] A hydrogen supply system for a drone hydrogen fuel cell includes a hydrogen cylinder and a cylinder valve connected to one end of the type IV hydrogen cylinder. The cylinder valve includes a shut-off valve, a two-stage pressure reducing valve mechanism, a filling and discharging mechanism, a temperature-sensing pressure relief mechanism, and a pressure sensing mechanism. The other end of the type IV hydrogen cylinder is provided with a pressure-sensing pressure relief mechanism. The shut-off valve is connected between the type IV hydrogen cylinder and the two-stage pressure reducing valve mechanism, and its function is to cut off the connection with the downstream when the type IV hydrogen cylinder is filled with gas.

[0007] The discharge mechanism is connected between the Type IV hydrogen cylinder and the shut-off valve. The temperature-sensing pressure relief mechanism is connected to the Type IV hydrogen cylinder through the internal channel of the cylinder valve to discharge the high-pressure gas from the Type IV hydrogen cylinder and prevent the Type IV hydrogen cylinder from exploding.

[0008] The pressure sensing mechanism is connected to the Type IV hydrogen cylinder through the internal channel of the valve block to monitor the gas pressure inside the hydrogen cylinder.

[0009] The dual-stage pressure reducing valve mechanism is connected between the Type IV hydrogen cylinder and the UAV hydrogen fuel cell reactor, which reduces the pressure of the high-pressure gas in the cylinder and outputs it stably to the UAV hydrogen fuel cell reactor.

[0010] The pressure-sensing and pressure-relieving mechanism is installed at the bottom of the Type IV hydrogen cylinder. When the system is in a high-temperature environment, the overpressure relief mechanism can open automatically to release the high-pressure gas from the cylinder and prevent the Type IV hydrogen cylinder from exploding.

[0011] Furthermore, a filter device is provided at the bottom of the bottle valve.

[0012] The above technical solution has the following beneficial effects:

[0013] The shut-off valve, two-stage pressure reducing valve mechanism, venting mechanism, TPRD temperature-sensing pressure relief mechanism, and pressure sensing mechanism in this invention are integrated through the bottle neck valve to ensure the system's sealing and safety. The Type IV hydrogen cylinder uses a plastic inner liner and carbon fiber winding (T800), which has significant advantages such as light weight, short production cycle, and low cost. This invention adopts a dual overpressure protection mechanism of TPRD temperature-sensing pressure relief mechanism and pressure-sensing pressure relief mechanism, further improving the system's safety and reliability. The design with high integration, high lightweight, and dual safety mechanisms makes it highly competitive in the market. Attached Figure Description

[0014] Figure 1 This is a schematic diagram of a hydrogen supply system for a hydrogen fuel cell in an unmanned aerial vehicle (UAV) according to the present invention.

[0015] Figure 2 This is a schematic diagram of the structure of a hydrogen supply system for a hydrogen fuel cell in an unmanned aerial vehicle (UAV) according to the present invention.

[0016] Figure 3 This is a schematic diagram of the structure of a bottle valve for a hydrogen supply system for a hydrogen fuel cell in an unmanned aerial vehicle (UAV) according to the present invention.

[0017] Figure 4 This is a schematic cross-sectional view of the bottle neck valve of a hydrogen supply system for a hydrogen fuel cell in an unmanned aerial vehicle (UAV) according to the present invention. Figure 1 ;

[0018] Figure 5 This is a schematic cross-sectional view of the bottle neck valve of a hydrogen supply system for a hydrogen fuel cell in an unmanned aerial vehicle (UAV) according to the present invention. Figure 2 ;

[0019] Figure 6 This is a schematic diagram of the force analysis of a hydrogen supply system for a drone hydrogen fuel cell according to the present invention. Figure 1 ;

[0020] Figure 7 This is a schematic diagram of the force analysis of a hydrogen supply system for a drone hydrogen fuel cell according to the present invention. Figure 2 ;

[0021] In the diagram: 1-Hydrogen cylinder; 2-Supply and exhaust mechanism; 3-Two-stage pressure reducing valve mechanism; 4-Pressure sensing mechanism; 5-Stop valve; 6-Temperature-sensing pressure relief mechanism; 7-Pressure-sensing pressure relief mechanism; 8-Filter device; 9-Bottle neck valve. Detailed Implementation

[0022] The technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of the present invention, and not all embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of the present invention.

[0023] See Figure 1-5 The hydrogen supply system for a drone hydrogen fuel cell shown includes a type IV hydrogen cylinder 1 and a cylinder valve 9 connected to one end of the type IV hydrogen cylinder 1. The cylinder valve 9 includes a shut-off valve 5, a two-stage pressure reducing valve mechanism, a filling and discharging mechanism 2, a temperature-sensing pressure relief mechanism 6, and a pressure sensing mechanism 4. The other end of the type IV hydrogen cylinder 1 is provided with a pressure-sensing pressure relief mechanism 7. The shut-off valve 5 is connected between the type IV hydrogen cylinder 1 and the two-stage pressure reducing valve mechanism, and its function is to cut off the connection with the downstream when the type IV hydrogen cylinder 1 is filled with gas.

[0024] The shut-off valve 5, the two-stage pressure reducing valve mechanism, the filling and discharging mechanism 2, the TPRD temperature-sensing pressure relief mechanism 6, and the pressure sensing mechanism 4 are connected via the bottle neck valve 9. The pressure-sensing pressure relief mechanism 7 is installed at the bottom of the type IV hydrogen cylinder 1. The shut-off valve 5 is connected between the type IV hydrogen cylinder 1 and the two-stage pressure reducing valve mechanism, and its function is to cut off the connection with the downstream when the type IV hydrogen cylinder 1 is being filled with gas;

[0025] The filling and discharging mechanism 2 is connected between the type IV hydrogen cylinder 1 and the shut-off valve 5, and its function is to fill the type IV hydrogen cylinder 1 with gas; the TPRD temperature-sensing pressure relief mechanism 6 is connected to the type IV hydrogen cylinder 1 through the internal channel of the valve block, and its function is to open the relief mechanism when the system is in a high temperature environment (10±5℃) to discharge the high pressure gas in the cylinder and prevent the type IV hydrogen cylinder 1 from exploding; the bottom of the cylinder valve 9 is equipped with a filter device 8.

[0026] The pressure sensing mechanism 4 is connected to the Type IV hydrogen cylinder 1 through the internal channel of the bottle valve 9, and its function is to monitor the gas pressure inside the Type IV hydrogen cylinder 1; the two-stage pressure reducing valve mechanism is connected between the Type IV hydrogen cylinder 1 and the UAV hydrogen fuel cell reactor, and its function is to reduce the pressure of the high-pressure gas in the cylinder and output it stably to the UAV hydrogen fuel cell reactor.

[0027] The pressure-sensing pressure relief mechanism 7 is installed at the bottom of the Type IV hydrogen cylinder 1. Its function is to automatically open the overpressure relief mechanism when the system is in a high-temperature environment to release the high-pressure gas in the cylinder and prevent the Type IV hydrogen cylinder 1 from exploding. The filling and releasing mechanism 2 is connected between the Type IV hydrogen cylinder 1 and the shut-off valve 5. Its function is to fill the Type IV hydrogen cylinder 1 with gas.

[0028] The TPRD temperature-sensing pressure relief mechanism 6 is connected to the Type IV hydrogen cylinder 1 through the internal channel of the valve block (cylinder valve 9). Its function is to open the relief mechanism when the system is in a high-temperature environment (10±5℃) to release the high-pressure gas in the cylinder and prevent the Type IV hydrogen cylinder 1 from exploding. The pressure sensing mechanism 4 is connected to the Type IV hydrogen cylinder 1 through the internal channel of the valve block. Its function is to monitor the gas pressure inside the Type IV hydrogen cylinder 1.

[0029] The dual-stage pressure reducing valve mechanism 3 is connected between the Type IV hydrogen cylinder 1 and the UAV hydrogen fuel cell reactor. Its function is to reduce the pressure of the high-pressure gas in the cylinder and output it stably to the UAV hydrogen fuel cell reactor. The pressure-sensing pressure relief mechanism 7 is installed at the bottom of the Type IV hydrogen cylinder 1. Its function is that when the system is in a high-temperature environment, the overpressure relief mechanism can open automatically to discharge the high-pressure gas in the cylinder to prevent the Type IV hydrogen cylinder 1 from exploding.

[0030] Storage method: Hydrogen is compressed to a high pressure, typically between 35 MPa and 70 MPa, and stored in high-strength carbon fiber or aluminum alloy wound cylinders. This method has advantages such as high hydrogen storage density and fast filling and discharging speed, and can meet the hydrogen requirements of drone operations.

[0031] Refueling method: The hydrogen refueling station connects to the refueling / discharging mechanism 2 on the hydrogen supply system via a special tool. High-pressure hydrogen then opens the one-way valve, initiating the refueling of hydrogen into the Type IV hydrogen cylinder 1. The entire refueling process is monitored by the pressure sensor 4 to determine if the cylinder is full. Once full, the special tool separates from the refueling / discharging mechanism 2, and the one-way valve automatically seals the pipeline.

[0032] Safety relief methods: The pressure relief mechanism 7 is located at the bottom of the gas cylinder, and the temperature relief mechanism 6 is located at the valve block of the cylinder valve 9.

[0033] When the system is in an abnormal operating environment, the pressure inside the gas cylinder will increase with the rise in temperature. When the pressure rises to the designed safe value, the pressure-sensitive diaphragm in the pressure-sensing relief mechanism 7 will rupture, releasing the high-pressure gas from the cylinder. When the system is in the set maximum operating temperature environment, the temperature-sensing element (glass bulb) in the temperature-sensing pressure relief mechanism 6 will automatically rupture, and the high-pressure gas will push open the piston in the relief mechanism, achieving automatic pressure relief. Both the pressure-sensing relief mechanism 7 and the temperature-sensing pressure relief mechanism 6 are used to protect the safety of the drone.

[0034] Two-stage pressure reduction: The working principle of a pressure reducing valve is mainly based on the throttling principle in fluid mechanics. It changes the flow velocity and kinetic energy of the fluid by altering the throttling area, thus creating different pressure losses and achieving pressure reduction. Simultaneously, the pressure reducing valve relies on the regulation of the control and adjustment system to balance the fluctuations in the downstream pressure with the spring force, thereby maintaining a constant downstream pressure within a certain error range.

[0035] See Figures 6-7 As shown, the pressure reducing mechanism adopts a two-stage series structure. The first-stage pressure reducing valve uses a forward non-unloading pressure reducing valve, and the second-stage valve uses a reverse non-unloading pressure reducing valve. Under the condition of no gas supply, it can be seen from the structural diagram of the first-stage pressure reducing valve and the force diagram of the first-stage valve that F1=0, F3=0, F4=0. Under the action of the spring force F2, the first-stage pressure reducing valve is in the normally open state. From the structural diagram of the second-stage pressure reducing valve and the force diagram of the second-stage valve, it can be seen that F4=0, F6=0, F7>F5 (the design value of the spring force). Under the action of the spring force F7>F5, the second-stage pressure reducing valve is in the normally open state.

[0036] When gas is supplied to the inlet of the primary pressure reducing valve and output from the outlet, the outlet pressure exerts a closing force on the valve core. When the outlet pressure reaches 1.2–1.5 MPa, the force on the primary valve is F1+F2+F3≤F4, and the primary valve closes, preventing downstream flow. When the output pressure falls below the locking value, the force on the primary valve is F1+F2>F4+F3, and the primary valve automatically opens under spring action. The force analysis is as follows: Figure 6 .

[0037] F1—Primary inlet high-pressure gas pressure;

[0038] F2—First-stage adjustable spring force;

[0039] F3—Frictional force during the movement of the primary valve;

[0040] F4—Secondary pressure reduction inlet gas pressure;

[0041] When gas is supplied to the inlet of the secondary pressure reducing valve and output from the outlet, the outlet pressure exerts a force on the diaphragm of the secondary pressure reducing valve. This reduces the force exerted by the diaphragm on the valve core. When the secondary output pressure reaches the set locking pressure (adjustable), and F4+F5+F6≥F7, the secondary valve closes, preventing pressure output downstream. The force analysis is as follows: Figure 7 .

[0042] F4—Secondary pressure reduction inlet gas pressure;

[0043] F5—Reset spring force;

[0044] F6—Secondary pressure reduction outlet gas pressure;

[0045] F7—Adjusting spring force;

[0046] Supply System: When the drone is operating, the high-pressure hydrogen in the cylinder is reduced to the operating pressure required by the fuel cell, typically around 0.1 MPa to 0.5 MPa, by a pressure reducing device at the cylinder opening. It is then delivered to the fuel cell through pipelines. Simultaneously, the system is equipped with a flow control device to precisely adjust the hydrogen supply flow rate according to the fuel cell's load requirements.

[0047] The basic principles and main features of the present invention have been described above. Those skilled in the art should understand that the present invention is not limited to the above embodiments. The embodiments and descriptions in the specification are only illustrative of the principles of the present invention. Various changes and modifications can be made to the present invention without departing from the spirit and scope of the present invention. All such changes and modifications fall within the scope of the present invention as claimed. The scope of protection of the invention is defined by the appended claims and their equivalents.

Claims

1. A hydrogen supply system for a hydrogen fuel cell of a drone, characterized by, The application relates to a type IV hydrogen cylinder and a bottle mouth valve connected to one end of the type IV hydrogen cylinder, wherein the bottle mouth valve comprises a stop valve, a two-stage pressure reducing mechanism, a filling and discharging mechanism, a temperature and pressure relief mechanism and a pressure sensing mechanism; the other end of the type IV hydrogen cylinder is provided with a pressure sensing pressure relief mechanism; the stop valve is connected between the type IV hydrogen cylinder and the two-stage pressure reducing mechanism, and the stop valve is used to cut off the communication between the type IV hydrogen cylinder and the downstream when the type IV hydrogen cylinder is filled with gas; the filling and discharging mechanism is connected between the type IV hydrogen cylinder and the stop valve; the temperature and pressure relief mechanism is communicated with the type IV hydrogen cylinder through an internal channel of the bottle mouth valve, and high-pressure gas in the type IV hydrogen cylinder is discharged to avoid explosion of the type IV hydrogen cylinder; the pressure sensing mechanism is communicated with the type IV hydrogen cylinder through an internal channel of the valve block, and the pressure sensing mechanism is used to monitor the gas pressure in the type IV hydrogen cylinder; the two-stage pressure reducing mechanism is connected between the type IV hydrogen cylinder and a hydrogen fuel cell reactor of an unmanned aerial vehicle, and the two-stage pressure reducing mechanism is used to reduce the high-pressure gas in the cylinder and stably output the high-pressure gas to the hydrogen fuel cell reactor of the unmanned aerial vehicle; the pressure sensing pressure relief mechanism is installed at the bottom of the type IV hydrogen cylinder, and when the system is in a high-temperature environment, the overpressure relief mechanism can be automatically opened to discharge the high-pressure gas in the cylinder and avoid explosion of the type IV hydrogen cylinder.

2. The hydrogen supply system for hydrogen fuel cells of unmanned aerial vehicles according to claim 1, characterized in that, The bottom of the bottle mouth valve is provided with a filtering device. 3.The hydrogen supply system for hydrogen fuel cells of unmanned aerial vehicles according to claim 1, characterized in that, The two-stage pressure reducing mechanism adopts a two-stage series structure, a first-stage pressure reducing mechanism adopts a forward non-unloading pressure reducing valve, and a second-stage pressure reducing mechanism adopts a reverse non-unloading pressure reducing valve.

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