Super-long endurance unmanned aerial vehicle power system based on reversible electrochemical circulation

Abstract

The invention discloses an ultra-long endurance unmanned aerial vehicle power system based on reversible electrochemical circulation, and belongs to the field of aviation power. A front double-engine power system is adopted and located on the front sides of machine bodies on the two sides. The solar cell panel is provided with a single maximum power point tracker MPPT, and the proton exchange membrane hydrogen fuel cells / electrolytic cells are arranged on the machine body on the two sides. The characteristics that solar energy and hydrogen energy are clean and free of pollution are utilized, when illumination exists, a solar cell panel generates electricity to drive a motor, the motor drives a propeller to generate thrust, and an electrolytic bath utilizes electric energy generated by the solar cell panel to electrolyze water to produce hydrogen; in the absence of illumination, the stored hydrogen energy is utilized to generate power in the fuel cell to drive the motor, so that the propeller is driven to generate thrust, and meanwhile, generated water is collected. The defects of intermittency and volatility of solar power generation are overcome by utilizing the electrolytic tank to electrolyze water to store hydrogen, and meanwhile, the problem that a water electrolysis hydrogen production technology needs high energy input is solved by utilizing inexhaustible solar energy.

Description

Technical Field

[0001] The present invention belongs to the field of aero-engines, and particularly relates to a power system for an ultra-long-endurance unmanned aerial vehicle based on a reversible electrochemical cycle. Background Art

[0002] The demand for clean energy in China's aviation industry is becoming increasingly urgent. Therefore, aero-engines utilizing solar energy and hydrogen energy have emerged. Aero-engines using solar energy and hydrogen energy have a wide range of energy sources, are clean and pollution-free, and theoretically can even meet the standard of zero carbon emissions. However, solar energy power generation is intermittent and volatile, making it difficult to provide a continuous and stable power supply for the load. Therefore, solar energy is used to electrolyze water to produce hydrogen, and the hydrogen is stored in a hydrogen storage tank so that when solar energy is in short supply, the aircraft still has other energy supply methods. Moreover, the electrolytic water hydrogen production technology requires a high energy input, and the energy consumption is closely related to the electricity cost. Using solar power generation to produce hydrogen can avoid such problems.

[0003] Traditional solar and hydrogen hybrid aircraft only use solar cells, hydrogen fuel cells, and an electrolyzer convertible structure to directly provide energy for the aircraft, without using solar energy to electrolyze water to produce hydrogen and storing the hydrogen in a hydrogen tank for use by the fuel cell. Summary of the Invention

[0004] In view of this, in order to solve the technical problems mentioned in the above background art, the present invention proposes a power system for an ultra-long-endurance unmanned aerial vehicle based on a reversible electrochemical cycle. The present invention uses a solar cell to generate electricity and electrolyze water to produce hydrogen when there is sunlight, and when there is no sunlight, the hydrogen fuel cell and the electrolyzer convertible structure use hydrogen and oxygen to generate electricity to provide a power source.

[0005] To achieve the above object, the present invention adopts the following technical solutions: A power system for an ultra-long-endurance unmanned aerial vehicle based on a reversible electrochemical cycle, comprising two power systems, a cabin, two fuselages, and two wings. Two fuselages are symmetrically installed on both sides of the cabin, wings are installed on the outer sides of each fuselage, a power system is installed in front of each fuselage, the fuselage is divided into a front fuselage and a rear fuselage, and an energy supply system is installed in the front fuselage;

[0006] The energy supply system includes a lithium battery, a compressor, a hydrogen fuel cell and an electrolyzer convertible structure, an energy management system, an exhaust hole, a hydrogen tank and a water storage tank. The compressor, the hydrogen fuel cell and the electrolyzer convertible structure, and the hydrogen tank are connected in sequence. An exhaust hole is provided on the front fuselage. The hydrogen fuel cell and the electrolyzer convertible structure can be converted into a hydrogen fuel cell and an electrolyzer according to the presence or absence of light. The energy management system is connected to the hydrogen tank and the compressor to control the power of the hydrogen fuel cell. When there is light, the hydrogen fuel cell and the electrolyzer convertible structure act as an electrolyzer to electrolyze water to produce hydrogen. When there is no light, the hydrogen fuel cell and the electrolyzer convertible structure are converted into a hydrogen fuel cell for power generation. The water storage tank is connected to the hydrogen fuel cell;

[0007] The hydrogen fuel cell and the electrolyzer convertible structure uses a proton exchange membrane as the core component, and is assembled in the order of the positive electrode of the hydrogen fuel cell or the cathode plate of the electrolyzer, the positive electrode of the hydrogen fuel cell or the cathode flow channel of the electrolyzer, the positive electrode of the hydrogen fuel cell or the cathode diffusion layer of the electrolyzer, the positive electrode of the hydrogen fuel cell or the cathode catalyst layer of the electrolyzer, the proton exchange membrane, the negative electrode of the hydrogen fuel cell or the anode catalyst of the electrolyzer, the negative electrode of the hydrogen fuel cell or the anode diffusion layer of the electrolyzer, the negative electrode of the hydrogen fuel cell or the anode flow channel of the electrolyzer, and the positive electrode of the hydrogen fuel cell or the anode plate of the electrolyzer;

[0008] A solar panel and an MPPT controller are installed on the wing. The MPPT controller, the hydrogen fuel cell and the electrolyzer convertible structure are respectively connected to the power system. When there is light, the MPPT controller controls the solar panel to the maximum power, and while delivering energy to the power system, it also delivers energy to the electrolyzer to electrolyze water into hydrogen and oxygen so that hydrogen can be used as fuel when there is no light.

[0009] Furthermore, when there is no light, air enters from the air inlet, is compressed by the compressor and then sent to the anode of the hydrogen fuel cell in the hydrogen fuel cell and the electrolyzer convertible structure. The hydrogen tank pumps hydrogen to the cathode of the hydrogen fuel cell, and the hydrogen fuel cell reacts to generate electrical energy to supply the airborne equipment and the power system.

[0010] Furthermore, when there is light, the hydrogen fuel cell and the electrolyzer convertible structure are converted into an electrolyzer. The solar panel generates electrical energy through light and delivers it to the electrolyzer. The water in the water storage tank is electrolyzed in the electrolyzer to produce hydrogen and oxygen. The oxygen is delivered to the atmosphere through the anode of the electrolyzer through the exhaust hole, and the hydrogen is delivered to the hydrogen storage tank through the cathode of the electrolyzer.

[0011] Furthermore, the power system includes a propeller and a motor. When there is light, the solar panel generates electrical energy and delivers it to the motor, thereby driving the propeller to generate thrust.

[0012] Furthermore, when there is no light, the hydrogen fuel cell generates electrical energy and delivers it to the motor, thereby driving the propeller to generate thrust.

[0013] Furthermore, when there is light, the solar panels generate electrical energy and transmit it to the lithium battery for charging.

[0014] Furthermore, the solar panels are distributedly laid on both wingtips, and each solar panel assembly is equipped with a single maximum power point tracker (MPPT) to ensure that the system can output the maximum power.

[0015] Furthermore, the energy management system controls the degree of the electrochemical reaction in the hydrogen fuel cell by controlling the intake of air and hydrogen entering the hydrogen fuel cell.

[0016] Furthermore, the rear fuselage is used to control and trim the flight of the aircraft in a three-dimensional plane, including a horizontal tail, an elevator, a vertical tail, and a rudder. The horizontal tail ensures the horizontal stability of the aircraft; the elevator is used to control the pitching motion of the aircraft; the vertical tail ensures the lateral dynamic stability of the aircraft; and the rudder performs yaw operations on the aircraft.

[0017] Furthermore, the wing also includes a leading-edge slat, spoiler, outboard aileron, and inboard aileron. When the leading-edge slat is extended, it can increase the critical angle of attack of the aircraft; the spoiler can reduce the lift of the wing; and the outboard aileron and inboard aileron are used to control the rolling motion of the aircraft about the longitudinal axis.

[0018] Compared with the prior art, the beneficial effects of the ultra-long-endurance UAV power system based on reversible electrochemical cycles of the present invention are as follows:

[0019] (1) A solar and hydrogen hybrid aircraft disclosed by the present invention utilizes an electrolyzer to electrolyze water for hydrogen storage to make up for the intermittency and volatility of solar power generation, while using the "inexhaustible" solar energy to solve the problem that the electrolytic water hydrogen production technology requires a relatively high energy input.

[0020] (2) Since the proton exchange membrane electrolyzer and the proton exchange membrane fuel cell of a solar and hydrogen hybrid aircraft disclosed by the present invention have a similar structure, both are basically composed of a plate electrode, a flow channel, a diffusion layer (transport layer), a catalytic layer, and a proton exchange membrane, and the reactions are inverse reactions of each other, a convertible structure of the hydrogen fuel cell and the electrolyzer of the aircraft is assembled.

[0021] (3) For a solar and hydrogen hybrid aircraft disclosed by the present invention, the lithium battery is charged by the solar panels when there is light, and is used to solve the problem that the output power response of the hydrogen fuel cell is relatively slow when there is no light.

[0022] (4) A solar and hydrogen hybrid aircraft disclosed by the present invention, in which a hydrogen fuel cell and an electrolyzer convertible structure are placed in an air flow channel between an air inlet and an air outlet. While using a compressor air inlet to inhale oxygen for reaction in the hydrogen fuel cell and the electrolyzer convertible structure, heat dissipation and thermal management of the hydrogen fuel cell and the electrolyzer convertible structure are achieved.

[0023] (5) A solar and hydrogen hybrid aircraft disclosed by the present invention, in which solar panels are arranged in a distributed manner on the wings, and each group of solar panels is equipped with an independent maximum power point tracker (MPPT), enabling each group of solar panels to operate at the optimal power point and reasonably distribute energy. BRIEF DESCRIPTION OF THE DRAWINGS

[0024] The drawings forming a part of the present invention are used to provide a further understanding of the present invention. The schematic embodiments and descriptions thereof of the present invention are used to explain the present invention and do not constitute an improper limitation to the present invention. In the drawings:

[0025] Figure 1 is a top view of a solar and hydrogen hybrid aircraft described in the present invention;

[0026] Figure 2 is a side view of the fuselage of a solar and hydrogen hybrid aircraft described in the present invention;

[0027] Figure 3 is an internal structure diagram of the hydrogen fuel cell and the electrolyzer convertible structure described in the present invention

[0028] In the figure: 1 - power system; 11 - propeller; 12 - motor; 2 - energy supply system; 21 - compressor; 22 - convertible structure of hydrogen fuel cell and electrolyzer; 221 - negative electrode of the hydrogen fuel cell or anode of the electrolyzer of the convertible structure of hydrogen fuel cell and electrolyzer; 222 - positive electrode of the fuel cell or cathode of the electrolyzer of the convertible structure of hydrogen fuel cell and electrolyzer; 2221 - positive electrode plate of hydrogen fuel cell or cathode of electrolyzer; 2222 - flow channel of positive electrode of hydrogen fuel cell or cathode of electrolyzer; 2223 - diffusion layer of positive electrode of hydrogen fuel cell or cathode of electrolyzer; 2224 - catalytic layer of positive electrode of hydrogen fuel cell or cathode of electrolyzer; 2215 - proton exchange membrane; 2214 - catalyst of negative electrode of hydrogen fuel cell or anode of electrolyzer; 2213 - diffusion layer of negative electrode of hydrogen fuel cell or anode of electrolyzer; 2212 - flow channel of negative electrode of hydrogen fuel cell or anode of electrolyzer; 2211 - negative electrode plate of hydrogen fuel cell or anode of electrolyzer; 23 - energy management system; 24 - exhaust hole; 25 - hydrogen tank; 26 - water storage tank; 27 - lithium battery; 3 - cabin; 4 - rear fuselage; 41 - horizontal tail; 42 - elevator; 43 - vertical tail; 44 - rudder; 5 - wing; 51 - leading edge slat; 52 - solar panel; 521 - MPPT controller; 53 - spoiler; 54 - outboard aileron; 55 - inboard aileron. Detailed implementation mode

[0029] The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings in the embodiments of the present invention. It should be noted that, without conflict, the embodiments and features in the embodiments of the present invention may be combined with each other. The described embodiments are only a part of the embodiments of the present invention, rather than all the embodiments.

[0030] See Figures 1-3 Describing this embodiment, a power system for an ultra-long-endurance unmanned aerial vehicle based on a reversible electrochemical cycle includes two power systems 1, a cabin 3, two fuselages, and two wings 5. Two fuselages are symmetrically installed on both sides of the cabin 3. Wings 5 are installed on the outer sides of each fuselage. A power system 1 is installed in front of each fuselage. The fuselage is divided into a front fuselage and a rear fuselage. An energy supply system 2 is installed in the front fuselage.

[0031] The energy supply system 2 includes a lithium battery 27, a compressor 21, a hydrogen fuel cell and an electrolyzer convertible structure 22, an energy management system 23, an exhaust hole 24, a hydrogen tank 25 and a water storage tank 26. The compressor 21, the hydrogen fuel cell and the electrolyzer convertible structure 22, and the hydrogen tank 25 are connected in sequence. The exhaust hole 24 is provided on the front fuselage. The hydrogen fuel cell and the electrolyzer convertible structure 22 can be converted into a hydrogen fuel cell and an electrolyzer according to the presence or absence of light. The energy management system 23 is connected to the hydrogen tank 25 and the compressor 21 to control the power of the hydrogen fuel cell. When there is light, the hydrogen fuel cell and the electrolyzer convertible structure 22 act as an electrolyzer to electrolyze water to produce hydrogen. When there is no light, the hydrogen fuel cell and the electrolyzer convertible structure 22 are converted into a hydrogen fuel cell for power generation. The water storage tank 26 is connected to the hydrogen fuel cell;

[0032] The hydrogen fuel cell and the electrolyzer convertible structure 22 uses a proton exchange membrane as a core component and is assembled in the order of the positive electrode of the hydrogen fuel cell or the cathode plate 2221 of the electrolyzer, the positive electrode of the hydrogen fuel cell or the cathode flow channel 2222 of the electrolyzer, the positive electrode of the hydrogen fuel cell or the cathode diffusion layer 2223 of the electrolyzer, the positive electrode of the hydrogen fuel cell or the cathode catalytic layer 2224 of the electrolyzer, the proton exchange membrane 2215, the negative electrode of the hydrogen fuel cell or the anode catalyst 2214 of the electrolyzer, the negative electrode of the hydrogen fuel cell or the anode diffusion layer 2213 of the electrolyzer, the negative electrode of the hydrogen fuel cell or the anode flow channel 2212 of the electrolyzer, and the positive electrode of the hydrogen fuel cell or the anode plate 2211 of the electrolyzer;

[0033] A solar panel 52 and an MPPT controller 521 are installed on the wing 5. The MPPT controller 521 and the hydrogen fuel cell and the electrolyzer convertible structure 22 are respectively connected to the power system 1. When there is light, the MPPT controller 521 controls the solar panel 52 to the maximum power. While delivering energy to the power system 1, it also delivers energy to the electrolyzer to electrolyze water into hydrogen and oxygen so that hydrogen can be used as fuel when there is no light.

[0034] The hydrogen fuel cell or the electrolyzer is converted based on the presence or absence of light. When there is light, the electrolyzer in the hydrogen fuel cell and the electrolyzer convertible structure 22 electrolyzes water to produce hydrogen. When there is no light, the hydrogen fuel cell and the electrolyzer convertible structure 22 are converted into a hydrogen fuel cell for power generation.

[0035] The power system 1 includes a propeller 11 and a motor 12. This solar and hydrogen hybrid aircraft adopts a front-mounted twin-engine power system 1, which is located at the front sides of both fuselages. When there is sunlight, the solar panels 52 on the wings 5 generate electrical energy and transmit it to the motor 12, thereby driving the propeller 11 to generate thrust; when there is no sunlight, the hydrogen fuel cell generates electrical energy and transmits it to the motor 12, thereby driving the propeller 11 to generate thrust; the solar panels 52, the hydrogen fuel cell, and the hydrogen fuel cell and electrolyzer convertible structure 22 are respectively connected to the motor 12 to ensure that the power system can still operate normally when there are problems with solar energy.

[0036] The energy supply system 2 mainly consists of a compressor 21, a hydrogen fuel cell and electrolyzer convertible structure 22, an energy management system 23, an exhaust hole 24, a hydrogen tank 25, and a water storage tank 26; when there is no sunlight, air enters from the air inlet duct, is compressed by the compressor 21, and then sent to the positive electrode 221 of the hydrogen fuel cell. The hydrogen tank 25 pumps hydrogen to the negative electrode 222 of the hydrogen fuel cell. At the same time, the energy management system 23 is connected to the hydrogen tank 25 and the compressor 21 to control the power of the hydrogen fuel cell. The hydrogen fuel cell 2 reacts to generate electrical energy to supply the on-board equipment and the aircraft power system 1; when there is sunlight, the hydrogen fuel cell and electrolyzer convertible structure 22 is converted into an electrolyzer. The solar panels 52 generate electrical energy through sunlight and transmit it to the electrolyzer. The water in the water storage tank 26 is electrolyzed in the electrolyzer to produce hydrogen and oxygen. The oxygen is transported to the atmosphere through the exhaust hole 24 through the anode 221 of the electrolyzer, and the hydrogen is transported to the hydrogen storage tank 25 through the cathode 222 of the electrolyzer.

[0037] The cabin 3 is located at the front side of the middle fuselage of the aircraft, and no more equipment is arranged in the middle fuselage to ensure a relatively large storage space.

[0038] The rear fuselage 4 mainly consists of a horizontal tail 41, an elevator 42, a vertical tail 43, and a rudder 44, which are used to control and trim the aircraft's flight in three-dimensional planes. The horizontal tail 41 ensures the horizontal stability of the aircraft; the elevator 42 is used to control the pitch motion of the aircraft; the vertical tail 43 ensures the lateral dynamic stability of the aircraft; the rudder 44 performs yaw operations on the aircraft.

[0039] The wing 5 adopts a conventional layout with a large aspect ratio and mainly includes a leading-edge slat 51, solar panels 52, spoilers 53, an outer aileron 54, and an inner aileron 55. When the leading-edge slat 51 is extended, it can increase the critical angle of attack of the aircraft; the solar panels 52 are distributed and laid on both ends of the wings, having a skin structure and a power generation function, and driving the motor to operate when there is sunlight; the spoilers 53 can reduce the lift of the wing; the outer aileron 54 and the inner aileron 55 are used to control the rolling motion of the aircraft around the longitudinal axis.

[0040] The solar panels 52 are distributed and laid on the two end wings 5, and each group of solar panel 52 components is equipped with a single maximum power point tracker MPPT to ensure that the system can output the maximum power. When there is light, the solar panels 52 deliver energy to the power system 1 through a circuit and at the same time deliver energy to the electrolyzer to electrolyze water into hydrogen and oxygen, so that hydrogen can be used as fuel when there is no light.

[0041] The hydrogen fuel cell and the electrolyzer are located in the same component and can transform by itself. When there is light and there is a power source, it can automatically switch. When there is light, it acts as an electrolyzer to electrolyze the water in the water storage tank 26. Hydrogen is precipitated at the cathode 222, and oxygen is precipitated at the anode 221. When there is no light, it acts as a hydrogen fuel cell, supplying hydrogen to the negative electrode 222 of the hydrogen fuel cell and oxygen to the cathode 221 for reaction.

[0042] The energy management system 23 is connected to the compressor 21 and the hydrogen tank 25. By controlling the air and hydrogen entering the hydrogen fuel cell, it controls the degree of the electrochemical reaction occurring in the hydrogen fuel cell, affects the power generation, and thus affects the system thrust.

[0043] A working method of a power system of an ultra-long endurance unmanned aerial vehicle based on a reversible electrochemical cycle disclosed in this embodiment is as follows:

[0044] When there is light, the solar panels 52 on the wings 5 generate electrical energy and deliver it to the motor 12, thereby driving the propeller 11 to generate thrust. At the same time, the solar panels 52 generate electrical energy through light and deliver it to the electrolyzer. The water in the water storage tank 26 is electrolyzed in the electrolyzer to generate hydrogen and oxygen. Oxygen is delivered to the atmosphere through the exhaust hole 24 at the anode 221 of the electrolyzer, and hydrogen is delivered to the hydrogen storage tank 25 through the cathode 222 of the electrolyzer. And the solar panels 52, the hydrogen fuel cell, and the convertible structure 22 of the electrolyzer are respectively connected to the motor to ensure that when there are problems with solar energy, the power system still operates normally and can use two kinds of energy simultaneously to meet certain specific working conditions.

[0045] When there is no light, air enters from the air inlet duct, is compressed by the compressor 21 and then sent to the positive electrode 221 of the hydrogen fuel cell. The hydrogen tank 25 pumps hydrogen to the negative electrode 222 of the hydrogen fuel cell. At the same time, the energy management system 23 is connected to the hydrogen tank 25 and the compressor 21 to control the power of the hydrogen fuel cell. The hydrogen fuel cell reacts to generate electrical energy and delivers it to the motor 12, thereby driving the propeller 11 to generate thrust.

[0046] At the same time, the aircraft can use the surplus photovoltaic energy to climb and use the gravitational potential energy to glide when there is no light, so as to reduce the energy consumption when there is no light.

[0047] The embodiments of the present invention disclosed above are only used to help illustrate the present invention. The embodiments do not describe all the details in detail, nor do they limit the invention to the specific embodiments described. According to the content of this specification, many modifications and variations can be made. These embodiments are selected and specifically described in this specification to better explain the principles and practical applications of the present invention, so that those skilled in the art can well understand and utilize the present invention.

Claims

1. An ultra-long endurance UAV power system based on a reversible electrochemical cycle, characterized in that: It includes two power systems (1), a cabin (3), two fuselages and two wings (5). Two fuselages are symmetrically installed on both sides of the cabin (3). Wings (5) are installed on the outside of each fuselage. A power system (1) is installed in front of each fuselage. The fuselage is divided into a front fuselage and a rear fuselage (4). An energy supply system (2) is installed in the front fuselage; The energy supply system (2) includes a compressor (21), a hydrogen fuel cell and an electrolyzer convertible structure (22), an energy management system (23), an exhaust hole (24), a hydrogen tank (25) and a water storage tank (26). The compressor (21), the hydrogen fuel cell and the electrolyzer convertible structure (22) and the hydrogen tank (25) are connected in sequence. An exhaust hole (24) is provided on the front fuselage. The hydrogen fuel cell and the electrolyzer convertible structure (22) can be converted into a hydrogen fuel cell and an electrolyzer according to the presence or absence of light. The energy management system (23) is connected to the hydrogen tank (25) and the compressor (21) to control the power of the hydrogen fuel cell. When there is light, the hydrogen fuel cell and the electrolyzer convertible structure (22) act as an electrolyzer to electrolyze water to produce hydrogen. When there is no light, the hydrogen fuel cell and the electrolyzer convertible structure (22) are converted into a hydrogen fuel cell to generate electricity. The water storage tank (26) is connected to the hydrogen fuel cell; The hydrogen fuel cell and the electrolyzer convertible structure (22) are assembled in the order of the positive electrode of the hydrogen fuel cell or the cathode plate (2221) of the electrolyzer, the positive electrode of the hydrogen fuel cell or the cathode flow channel (2222) of the electrolyzer, the positive electrode of the hydrogen fuel cell or the cathode diffusion layer (2223) of the electrolyzer, the positive electrode of the hydrogen fuel cell or the cathode catalyst layer (2224) of the electrolyzer, the proton exchange membrane (2215), the negative electrode of the hydrogen fuel cell or the anode catalyst (2214) of the electrolyzer, the negative electrode of the hydrogen fuel cell or the anode diffusion layer (2213) of the electrolyzer, the negative electrode of the hydrogen fuel cell or the anode flow channel (2212) of the electrolyzer, and the positive electrode of the hydrogen fuel cell or the anode plate (2211) of the electrolyzer; Solar panels (52) and MPPT controllers (521) are installed on the wings (5). The MPPT controller (521) and the hydrogen fuel cell and the electrolyzer convertible structure (22) are respectively connected to the power system (1). When there is light, the MPPT controller (521) controls the solar panels (52) to the maximum power. While delivering energy to the power system (1), it also delivers energy to the electrolyzer to electrolyze water into hydrogen and oxygen so that hydrogen can be used as fuel when there is no light.

2. The ultra-long endurance UAV power system based on reversible electrochemical cycle according to claim 1, wherein: When there is no light, air enters from the air intake and is compressed by the compressor (21) and then sent to the positive electrode (221) of the hydrogen fuel cell in the hydrogen fuel cell and the electrolyzer convertible structure (22). The hydrogen tank (25) pumps hydrogen to the negative electrode (222) of the hydrogen fuel cell. The hydrogen fuel cell reacts to generate electricity to supply the on-board equipment and the power system (1).

3. The ultra-long endurance UAV power system based on a reversible electrochemical cycle according to claim 2, wherein: When there is light, the hydrogen fuel cell and electrolyzer convertible structure (22) transforms into an electrolyzer. The solar panel (52) generates electrical energy through light and supplies it to the electrolyzer. The water in the water storage tank (26) is electrolyzed in the electrolyzer to produce hydrogen and oxygen. The oxygen is transported to the atmosphere through the exhaust hole (24) at the anode (221) of the electrolyzer, and the hydrogen is transported to the hydrogen storage tank (25) through the cathode (222) of the electrolyzer.

4. The ultra-long endurance UAV power system based on reversible electrochemical cycle according to claim 1, wherein: The power system (1) includes a propeller (11) and a motor (12). When there is light, the solar panel (52) generates electrical energy and supplies it to the motor (12), thereby driving the propeller (11) to generate thrust.

5. The ultra-long endurance UAV power system based on a reversible electrochemical cycle according to claim 4, wherein: When there is no light, the hydrogen fuel cell generates electrical energy and supplies it to the motor (12), thereby driving the propeller (11) to generate thrust.

6. The ultra-long endurance UAV power system based on a reversible electrochemical cycle according to claim 1, characterized in that: When there is light, the solar panel (52) generates electrical energy and supplies it to the lithium battery (27) for charging, so as to be used when the aircraft requires high power.

7. The ultra-long endurance UAV power system based on reversible electrochemical cycle according to claim 1, characterized in that: The solar panels (52) are distributed and laid on both wing tips (5), and each group of solar panels (52) is equipped with an MPPT controller (521) to ensure that the system can output the maximum power.

8. The ultra-long endurance UAV power system based on a reversible electrochemical cycle according to claim 1, characterized in that: The energy management system (23) controls the degree of the electrochemical reaction in the hydrogen fuel cell by controlling the intake of air and hydrogen into the hydrogen fuel cell.

9. The ultra-long endurance UAV power system based on a reversible electrochemical cycle according to claim 1, wherein: The rear fuselage (4) is used to control and trim the flight of the aircraft in a three-dimensional plane, including a horizontal tail (41), an elevator (42), a vertical tail (43), and a rudder (44). The horizontal tail (41) ensures the horizontal stability of the aircraft; the elevator (42) is used to control the pitch motion of the aircraft; the vertical tail (43) ensures the lateral dynamic stability of the aircraft; the rudder (44) performs yaw operations on the aircraft.

10. The ultra-long endurance UAV power system based on reversible electrochemical cycle according to claim 1, wherein: The wing (5) also includes a leading edge slat (51), spoilers (53), an outboard aileron (54), and an inboard aileron (55). When the leading edge slat (51) is extended, it can increase the critical angle of attack of the aircraft; the spoilers (53) can reduce the lift of the wing; the outboard aileron (54) and the inboard aileron (55) are used to control the roll motion of the aircraft around the longitudinal axis.

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