An unmanned aerial vehicle deicing thermal management system and method based on hydrogen fuel cell power system waste heat utilization

Abstract

The application relates to an unmanned aerial vehicle deicing thermal management system and method based on hydrogen fuel cell power system waste heat utilization, relates to the field of unmanned aerial vehicle thermal management, and solves the problem that the icing of the front edge of a wing, a propeller and other windward surfaces of an existing unmanned aerial vehicle leads to the decline of the flight performance and aerodynamic performance of the unmanned aerial vehicle when the unmanned aerial vehicle flies in the icing weather environment at a high altitude. The method comprises a hydrogen storage tank, a hydrogen preheater, an air heat exchanger, a fuel cell, a phase change heat accumulator, a cooling liquid circulating pump and a deicing module. The hydrogen storage tank, the hydrogen preheater and the anode of the fuel cell are sequentially communicated; the air heat exchanger and a compressor are communicated with the cathode of the fuel cell; the fuel cell, the phase change heat accumulator and the deicing system are communicated; an electric control unit is electrically connected with an icing detector, an electric three-way regulating valve and the fuel cell; the application utilizes the waste heat of the fuel cell to deice the body and the propeller, realizes the cascade utilization of heat flow in series, realizes the efficient utilization of energy, guarantees the flight safety of the unmanned aerial vehicle and prolongs the endurance time of the unmanned aerial vehicle.

Description

Technical Field

[0001] This invention relates to the field of drone thermal management and de-icing technology, specifically to a drone de-icing thermal management system and method based on the utilization of waste heat from a hydrogen fuel cell power system. Background Technology

[0002] As the application scenarios of drones continue to expand, they have been widely extended to fields such as civilian security, power line inspection, agricultural and forestry plant protection, and logistics delivery in remote areas. With the surge in demand for long-endurance missions, drones often need to perform all-weather operations under complex weather conditions. However, the high-altitude environment often contains a large number of supercooled water droplets. When aircraft pass through such icing weather conditions, frost can easily accumulate on the windward side of the wings, leading to icing.

[0003] The dangers of icing on aircraft surfaces are far-reaching. Icing not only severely alters the aerodynamic shape of the wing leading edge, causing a sharp drop in lift and a significant increase in drag, but can also induce a critical stall. Furthermore, detached ice fragments can strike the fragile fuselage skin or be sucked into the air intake or propeller, causing fatal mechanical damage.

[0004] High-altitude long-endurance (HAL) UAVs place stringent demands on the energy density and range of their power systems. Traditional lithium-ion battery power systems, limited by energy density bottlenecks, struggle to meet the demands of high-altitude, long-endurance operation. Hydrogen fuel cell power systems, with their advantages of high energy density (tens of times that of lithium-ion batteries), zero emissions, low noise, and high efficiency, have become an important development direction for HAL UAVs. However, hydrogen fuel cells generate significant waste heat during operation, and traditional solutions often dissipate this heat directly into the atmosphere through radiators, resulting in substantial energy waste. If this heat could be effectively recovered and used for UAV de-icing, the icing problem could be solved without consuming additional electrical energy.

[0005] Currently, active de-icing methods for aircraft include mechanical de-icing, liquid de-icing, and thermal de-icing. While these technologies are effective, they all increase the weight of the structure, control system, and energy payload, which is very disadvantageous for high-altitude UAVs that aim for long endurance and long-distance flight.

[0006] Therefore, it is necessary to develop a low-energy-consumption, high-efficiency drone de-icing thermal management system to coordinate the management of usable waste heat in the hydrogen fuel cell power system. While ensuring the normal operation of the fuel cell and the drone power system, this system can achieve efficient de-icing of the airframe and propellers, thereby improving the energy efficiency, endurance, and flight safety of the drone. Summary of the Invention

[0007] This invention addresses the technical problem in existing technologies where icing on the leading edges of wings and propellers of unmanned aerial vehicles (UAVs) during high-altitude icing weather conditions leads to a decrease in flight and aerodynamic performance. To this end, this invention proposes a UAV de-icing thermal management system and method based on the utilization of waste heat from a hydrogen fuel cell power system. The invention achieves the above-mentioned technical problems through the following technical solution: Option 1: This invention proposes a de-icing thermal management system for unmanned aerial vehicles (UAVs) based on the utilization of waste heat from a hydrogen fuel cell power system. The system includes a hydrogen storage tank, a hydrogen preheater, an air heat exchanger, a compressor, a fuel cell, a phase change heat storage coolant circulation pump, and a de-icing module. The hydrogen storage tank, the cold side of the hydrogen preheater, and the anode of the fuel cell are connected in sequence; the cold side of the air heat exchanger is connected to the compressor and the cathode of the fuel cell; the fuel cell, the phase change heat storage device, the coolant circulation pump, and the de-icing module are connected in sequence; the hot side channels of the hydrogen preheater, the air heat exchanger, and the coolant circulation pump are connected in sequence.

[0008] Furthermore, the de-icing module includes an electronic control unit, an electrically adjustable three-way valve, a heat pipe, a UAV body, propeller blades, and an icing detector; the heat pipe is arranged on the inner surface of the wing skin and propeller blades of the UAV body, the inlet of the heat pipe is connected to the first outlet of the electrically adjustable three-way valve, and the outlet is connected to the hot side inlet of the coolant circulation pump.

[0009] Furthermore, the electric three-way regulating valve is provided with an inlet and a first outlet and a second outlet. The inlet is connected to the hot side outlet of the phase change heat storage device; the second outlet is connected to the hot side inlet of the hydrogen preheater.

[0010] Furthermore, the electronic control unit is electrically connected to the icing detector, the electric three-way regulating valve, and the fuel cell; when the icing detector does not detect an icing signal, the electronic control unit controls the first outlet of the electric three-way regulating valve to maintain a preset small opening.

[0011] Furthermore, when the icing detector detects an icing signal, the electronic control unit increases the opening of the first outlet of the electric three-way regulating valve, so that the high-temperature coolant preferentially enters the heat pipe to de-ice the wing skin and blades; at the same time, the electronic control unit sends a power limiting command to the fuel cell to temporarily reduce the output power of the fuel cell; the phase change heat storage device (6) is connected to the electric three-way regulating valve.

[0012] Furthermore, the hot-side channels of the hydrogen preheater and the air heat exchanger are connected in series, so that the coolant flowing out of the phase change heat storage device first preheats the hydrogen through the hot side of the hydrogen preheater, then preheats the air through the hot side of the air heat exchanger, and finally, after merging with the return coolant from the heat pipe, it is pumped back to the fuel cell by the coolant circulation pump, thus realizing the stepwise heat release of hydrogen in the high-temperature section and air in the low-temperature section.

[0013] Furthermore, the heat pipe is embedded inside the wing skin and blades of the fuselage to avoid altering the external aerodynamic profile of the fuselage and blades.

[0014] Furthermore, the coolant circulation pump is installed on the return pipeline between the second outlet of the electric three-way regulating valve and the hot side inlet of the hydrogen preheater, and is used to drive the coolant to circulate between the fuel cell, the phase change heat storage device, the de-icing system and the stepped flow path.

[0015] Furthermore, the fuel cell is a proton exchange membrane fuel cell.

[0016] Option 2: A method for de-icing thermal management of unmanned aerial vehicles (UAVs) based on waste heat utilization from a hydrogen fuel cell power system. The method is implemented based on the system described in Option 1 and includes the following steps: Step 1: The electronic control unit receives the icing signal from the icing detector in real time, and adjusts the opening of the electric three-way regulating valve according to the icing signal to control the distribution ratio of high-temperature coolant between the de-icing system and the series stepped flow path of the hydrogen preheater and air heat exchanger. Step 2: When no icing signal is received, the first outlet of the electric three-way regulating valve is kept at a preset small opening, and the second outlet is kept at a large opening, so that a small amount of coolant continuously enters the wing skin and blade heat pipes to maintain the anti-icing temperature. At the same time, most of the coolant flows through the hot side channels of the hydrogen preheater and air heat exchanger to complete the cascade heat release and then flows back to the fuel cell.

[0017] The advantages of this invention are: The UAV de-icing thermal management system and method based on waste heat utilization of hydrogen fuel cell power systems, as described in this invention, directly utilizes the waste heat generated by the operation of the fuel cell for de-icing and anti-icing of the UAV body and propellers, replacing traditional electric heating de-icing, saving a significant amount of electrical energy consumption, and significantly improving the UAV's endurance and energy utilization efficiency. The coolant described in this invention adopts a series stepped flow path, flowing sequentially through the hydrogen heat exchange unit and the air heat exchange unit, achieving step-by-step utilization of "heating hydrogen in the high-temperature section and preheating air in the low-temperature section," resulting in uniform heat exchange temperature difference and high energy efficiency. High utilization rate; the de-icing branch and the gas preheating branch are separated and do not interfere with each other. Under non-icing conditions, a small flow of heat is continuously supplied to the fuselage and propellers to maintain anti-icing status, eliminating the icing formation window. When icing occurs, the heat flow is rapidly increased for de-icing. With the help of the thermal buffer of the phase change heat storage device and the power coordinated control of the electronic control unit, the intake preheating during the peak de-icing period is still maintained within an acceptable range, ensuring the normal operation of the fuel cell. At the same time, the heat conduction pipe channels built into the fuselage and propellers do not change the external aerodynamic profile and do not affect the normal operation and flight performance of the UAV. This invention can comprehensively utilize the waste heat of the fuel cell for de-icing of the fuselage and propellers, and the heat flow is used in series in a cascade manner, achieving efficient energy utilization, reducing energy waste, ensuring the flight safety of the UAV, and extending the endurance of the UAV.

[0018] This invention is also applicable to a thermal management system that utilizes the waste heat generated during the operation of a hydrogen fuel cell to de-ice the leading edge of the wing and the propeller blades of a high-altitude drone. This invention is particularly suitable for applications such as high-altitude long-endurance flight. Attached Figure Description

[0019] Figure 1 This is a schematic diagram of the drone de-icing thermal management system based on waste heat utilization of hydrogen fuel cell power system as described in Implementation Method 1.

[0020] Figure 2 This is a schematic diagram of the arrangement of the heat pipes on the wing of the UAV as described in Embodiment 1.

[0021] Figure 3 This is a schematic diagram of the arrangement of the heat pipes on the propeller blades of the UAV as described in Embodiment 1.

[0022] The components include: hydrogen storage tank 1, hydrogen preheater 2, air heat exchanger 3, compressor 4, fuel cell 5, phase change heat storage device 6, electronic control unit 7, electric regulating three-way valve 8, heat pipe 9, UAV body 10, propeller blades 11, coolant circulation pump 12, and icing detector 13. Detailed Implementation

[0023] To make the objectives, technical solutions, and advantages of the embodiments of this application clearer, the technical solutions of the embodiments of this application will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only a part of the embodiments of this application, and not all of them.

[0024] Implementation Method 1, see Figures 1 to 3 This embodiment describes a de-icing thermal management system for unmanned aerial vehicles (UAVs) based on the utilization of waste heat from a hydrogen fuel cell power system. The system includes a hydrogen storage tank 1, a hydrogen preheater 2, an air heat exchanger 3, a compressor 4, a fuel cell 5, a phase change heat storage device 6, an electronic control unit 7, an electrically adjustable three-way valve 8, a heat pipe 9, a UAV body 10, propellers 11, a coolant circulation pump 12, and an icing detector 13.

[0025] The hydrogen storage tank 1, hydrogen preheater 2, and the anode of fuel cell 5 are connected in sequence; the hydrogen preheater 2 is connected to the compressor 4 and the cathode of fuel cell 5; the de-icing module includes an electric three-way regulating valve 8, an icing detector 13, an electronic control unit 7, a heat pipe 9, a drone body 10, and a propeller 11; the fuel cell 5 is connected to the phase change heat storage device 6 and the de-icing module; the second outlet of the electric three-way regulating valve 8 forms a cascade flow path with the heat measurement channel of the hydrogen preheater 2 and the air heat exchanger 3; the electronic control unit 7 is electrically connected to the icing detector 13, the electric three-way regulating valve 8, and the fuel cell 5, and is used to adjust the opening of the electric three-way regulating valve according to the icing signal.

[0026] Hydrogen from storage tank 1 enters hydrogen preheater 2 and is heated to a temperature suitable for the anode inlet of the fuel cell by high-temperature coolant before entering the anode. At the same time, high-altitude air is preheated by coolant on the cold side of air preheater, and then pressurized by compressor 4 before entering the cathode of fuel cell 5. Hydrogen and oxygen react to generate electricity, and the waste heat generated is carried away by coolant.

[0027] The high-temperature coolant exiting fuel cell 5 first enters phase change heat storage tank 6, where the phase change material absorbs heat and buffers the flow, stabilizing the outlet coolant temperature before flowing into the electric three-way regulating valve. The electronic control unit 7 adjusts the valve opening based on the icing detector signal.

[0028] When there is no icing signal, the first outlet of the electric three-way regulating valve 8 remains slightly open, allowing a small amount of high-temperature coolant to flow to the heat pipes of the fuselage and propellers, maintaining the surface temperature of the fuselage skin and propellers slightly above the freezing point, thus achieving normalized anti-icing. At the same time, the second outlet remains relatively open, allowing most of the coolant to flow sequentially through the hot side of the hydrogen preheater and the hot side of the air preheater, releasing heat step by step and gradually reducing the temperature. Finally, the coolant is combined with the return coolant from the heat pipes and pumped back to the fuel cell by the coolant circulation pump, completing the cycle.

[0029] When the icing detector detects an icing signal, the electronic control unit immediately increases the opening of the first outlet, prioritizing the flow of most of the high-temperature coolant to the engine block and propeller heat pipes, causing the surfaces of the engine block and propellers to rapidly heat up and melt the ice. Simultaneously, it sends a power limiting command to the fuel cell controller, temporarily reducing the battery power to compensate for the decreased intake preheating caused by the reduced flow in the series preheating path. At this time, the phase change thermal storage device releases stored heat to compensate for the heat deficit. After the icing disappears, the low-flow anti-icing and preheating distribution resumes.

[0030] This embodiment stores the waste heat generated by the fuel cell during operation through a phase change heat storage device, and then delivers it to the wings and blades as needed through heat pipes to complete de-icing. At the same time, the excess heat is used for hydrogen heating and air heating, organically coupling the cascade utilization of fuel cell waste heat, intake preheating and de-icing of the airframe, and can intelligently adjust the heat distribution according to the icing state, which is especially suitable for high-altitude long-endurance fuel cell UAVs.

[0031] Those skilled in the art will understand that the above description is merely a preferred embodiment of the present invention, and the features described in the various embodiments and / or claims of this disclosure can be combined or combined in various ways, even if such combinations or combinations are not explicitly described in this disclosure. This is not intended to limit the present invention. Although the present invention has been described in detail with reference to the foregoing embodiments, those skilled in the art can still modify the technical solutions described in the foregoing embodiments or make equivalent substitutions for some of the technical features. Any modifications, equivalent substitutions, improvements, etc., made within the spirit and principles of the present invention should be included within the protection scope of the present invention.

[0032] Although preferred embodiments of the invention have been described, those skilled in the art, upon learning the basic inventive concept, can make other changes and modifications to these embodiments. Therefore, the appended claims are intended to be interpreted as including both the preferred embodiments and all changes and modifications falling within the scope of the invention. Clearly, those skilled in the art can make various alterations and modifications to the invention without departing from its spirit and scope. Thus, if these modifications and modifications of the invention fall within the scope of the claims and their equivalents, the invention is also intended to include these modifications and modifications.

Claims

1. A de-icing thermal management system for unmanned aerial vehicles (UAVs) based on waste heat utilization from a hydrogen fuel cell power system, characterized in that, The system includes a hydrogen storage tank (1), a hydrogen preheater (2), an air heat exchanger (3), a compressor (4), a fuel cell (5), a phase change heat storage device (6), a coolant circulation pump (12), and a de-icing module; The cold side of the hydrogen storage tank (1), the hydrogen preheater (2), and the anode of the fuel cell (5) are connected in sequence; the cold side of the air heat exchanger (3) is connected to the compressor (4) and the cathode of the fuel cell (5); the fuel cell (5), the phase change heat storage device (6), the coolant circulation pump (12), and the de-icing module are connected in sequence; the hot side channels of the hydrogen preheater (2), the air heat exchanger (3), and the coolant circulation pump (12) are connected in sequence.

2. The UAV de-icing thermal management system based on waste heat utilization of hydrogen fuel cell power system according to claim 1, characterized in that, The de-icing module includes an electronic control unit (7), an electric regulating three-way valve (8), a heat pipe (9), a UAV body (10), a propeller (11), and an icing detector (13). The heat pipe (9) is arranged on the inner surface of the wing skin and the propeller (11) of the UAV body (10). The inlet of the heat pipe (9) is connected to the first outlet of the electric regulating three-way valve (8), and the outlet is connected to the hot side inlet of the coolant circulation pump (12).

3. The UAV de-icing thermal management system based on waste heat utilization of hydrogen fuel cell power system according to claim 2, characterized in that, The electric three-way regulating valve (8) has an inlet and a first outlet and a second outlet. The inlet is connected to the hot side outlet of the phase change heat storage device (6); the second outlet is connected to the hot side inlet of the hydrogen preheater (2).

4. The UAV de-icing thermal management system based on waste heat utilization of hydrogen fuel cell power system according to claim 2, characterized in that, The electronic control unit (7) is electrically connected to the icing detector (13), the electric three-way regulating valve (8), and the fuel cell (5). When the icing detector (13) does not detect an icing signal, the electronic control unit (7) controls the first outlet of the electric three-way regulating valve (8) to maintain a preset small opening.

5. The UAV de-icing thermal management system based on waste heat utilization of hydrogen fuel cell power system according to claim 2, characterized in that, When the icing detector (13) detects an icing signal, the electronic control unit (7) increases the opening of the first outlet of the electric three-way regulating valve (8) so that the high-temperature coolant can preferentially enter the heat pipe (9) to de-ice the wing skin and blades (11); at the same time, the electronic control unit (7) sends a power limiting command to the fuel cell (5) to temporarily reduce the output power of the fuel cell (5), and the phase change heat storage device (6) is connected to the electric three-way regulating valve (8).

6. The UAV de-icing thermal management system based on waste heat utilization of hydrogen fuel cell power system according to claim 1, characterized in that, The hot-side channels of the hydrogen preheater (2) and the air heat exchanger (3) are connected in series, so that the coolant flowing out of the phase change heat storage device (6) first preheats the hydrogen through the hot side of the hydrogen preheater (2), then preheats the air through the hot side of the air heat exchanger (3), and finally merges with the return coolant of the heat pipe (9) and is sent back to the fuel cell (5) by the coolant circulation pump (12).

7. The UAV de-icing thermal management system based on waste heat utilization of hydrogen fuel cell power system according to claim 2, characterized in that, The heat pipe (9) is embedded inside the wing skin and blade (11) of the fuselage (10) to avoid changing the external aerodynamic profile of the fuselage (10) and blade (11).

8. The UAV de-icing thermal management system based on waste heat utilization of hydrogen fuel cell power system according to claim 2, characterized in that, The coolant circulation pump (12) is located on the return pipeline between the second outlet of the electric three-way regulating valve (8) and the hot side inlet of the hydrogen preheater (2), and is used to drive the coolant to circulate between the fuel cell (5), the phase change heat storage device (6), the de-icing system and the stepped flow path.

9. The UAV de-icing thermal management system based on waste heat utilization of hydrogen fuel cell power system according to claim 1, characterized in that, The fuel cell (5) is a proton exchange membrane fuel cell.

10. A method for de-icing thermal management of unmanned aerial vehicles (UAVs) based on waste heat utilization of a hydrogen fuel cell power system, the method being implemented based on the system described in any one of claims 1-9, characterized in that, The method includes the following steps: Step 1: The electronic control unit (7) receives the icing signal from the icing detector (13) in real time, and adjusts the opening of the electric three-way regulating valve (8) according to the icing signal to control the distribution ratio of high temperature coolant between the de-icing system and the series stepped flow path of the hydrogen preheater (2) and air heat exchanger (3). Step 2: When no icing signal is received, the first outlet of the electric three-way regulating valve (8) is kept at a preset small opening, and the second outlet is kept at a large opening, so that a small amount of coolant continuously enters the heat pipe (9) of the wing skin and blade (11) to maintain the anti-icing temperature. At the same time, most of the coolant flows through the hot side channel of the hydrogen preheater (2) and the air heat exchanger (3) in sequence to complete the stepped heat release and then flows back to the fuel cell (5).

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