Hybrid power system and aircraft

Abstract

The utility model provides a kind of hybrid power system and aircraft, hybrid power system includes solar power generation unit, water electrolysis unit, fuel cell power generation unit and energy management unit, solar power generation unit is used to convert solar energy into electric energy;Water electrolysis unit is electrically connected with the solar power generation unit, for converting electric energy into hydrogen and oxygen storage;Fuel cell power generation unit is connected with the water electrolysis unit, for converting the chemical energy of stored hydrogen and oxygen into electric energy.The utility model more by solar power generation unit produces energy is stored by battery under the condition that power system weight remains unchanged, the above-mentioned energy is stored in the form of hydrogen and oxygen after water electrolysis unit electrolysis water, so that system can store more energy when sunlight is sufficient, can improve the endurance time of aircraft when sunlight is insufficient or there is no sunlight.

Description

Technical Field

[0001] This utility model relates to the field of power system technology, specifically to a hybrid power system and an aircraft. Background Technology

[0002] Solar-powered aircraft use solar energy, causing no pollution to the environment. They are flexible in use, low in cost, and have broad application prospects. In civilian applications, they can be used for atmospheric research, weather forecasting, environmental and disaster monitoring, crop remote sensing, traffic control, telecommunications and television services, nature reserve monitoring, and extraterrestrial exploration. In military applications, they can be used for border patrols, reconnaissance, communications relay, and electronic warfare missions. Due to the numerous advantages of solar-powered aircraft, many countries are conducting research on related technologies.

[0003] Since solar energy is the sole energy source for solar-powered aircraft, an energy storage device is typically installed to ensure normal flight even in low sunlight or at night. Existing solar-powered aircraft generally use a battery pack of a certain capacity, employing a solar cell-battery hybrid power system. The system works by using solar cells to power the aircraft's load and charge the battery when sunlight is abundant; when sunlight is insufficient or absent, the battery powers the aircraft. For example, Chinese patent CN108820230A discloses an energy management method for multi-day cyclic flight of a high-altitude solar-powered aircraft, which uses a hybrid power system of solar cells and batteries.

[0004] However, when there is ample sunlight, the batteries corresponding to solar-powered aircraft can only store a small amount of electrical energy from the solar cells, resulting in a significant amount of solar energy remaining unused. Therefore, in the event of prolonged periods of insufficient sunlight (such as continuous rainy weather), the energy stored in the batteries will be insufficient to support the aircraft's flight needs. The solar cells of solar-powered aircraft are highly dependent on weather conditions and cannot meet the requirements for long-term use. Utility Model Content

[0005] The purpose of this invention is to overcome the above-mentioned technical deficiencies and propose a hybrid power system and aircraft to solve the technical problem that the solar cells of existing solar-powered aircraft are greatly limited by weather and cannot meet the needs of long-term use.

[0006] To achieve the above-mentioned technical objectives, the present invention adopts the following technical solution: In a first aspect, this utility model provides a hybrid power system, comprising: A solar power generation unit used to convert solar energy into electrical energy; An electrolysis water unit, which is electrically connected to the solar power generation unit, is used to convert electrical energy into hydrogen and oxygen for storage. A fuel cell power generation unit, connected to the water electrolysis unit, is used to convert the chemical energy of stored hydrogen and oxygen into electrical energy; and An energy management unit, which is electrically connected to the solar power generation unit, the water electrolysis unit, and the fuel cell power generation unit, is used to control the external power supply of the solar power generation unit and / or the fuel cell power generation unit, and to control the opening or closing of the water electrolysis unit.

[0007] In some embodiments, the solar power generation unit includes a solar panel, a photovoltaic controller, and a first inverter, wherein the solar panel, the photovoltaic controller, and the first inverter are electrically connected in sequence via wires.

[0008] In some embodiments, the water electrolysis unit includes a water electrolysis device, a hydrogen storage tank, and an oxygen storage tank. The water electrolysis device is connected to the hydrogen storage tank and the oxygen storage tank via pipelines, respectively, for feeding hydrogen and oxygen into the hydrogen storage tank and the oxygen storage tank. The hydrogen storage tank and the oxygen storage tank are respectively equipped with a hydrogen supply valve and an oxygen supply valve, and the hydrogen supply valve and the oxygen supply valve are respectively connected to the fuel cell power generation unit via pipelines.

[0009] In some embodiments, a dryer is installed between the hydrogen storage tank and the oxygen storage tank and the water electrolysis device, and a gas replenishment port is installed on the hydrogen storage tank and the oxygen storage tank respectively.

[0010] In some embodiments, the fuel cell power generation unit includes a fuel cell power generation device, a second inverter, and a water storage tank. The fuel cell power generation device is connected to the water storage tank and is used to discharge water and exhaust gas into the water storage tank. The fuel cell power generation device is electrically connected to the second inverter via a wire.

[0011] In some embodiments, the water storage tank is provided with a water inlet.

[0012] In some embodiments, the fuel cell power generation unit further includes a water pump, which is connected to the water electrolysis unit via a pipeline for supplying water to the water electrolysis unit.

[0013] In some embodiments, the energy management unit includes an energy controller, and the solar power generation unit, the water electrolysis unit, and the fuel cell power generation unit are all electrically connected to the energy controller, which is connected to an external load via wires.

[0014] In some embodiments, the energy management unit further includes a first switch, a second switch, and a third switch. The first switch is electrically connected in series between the solar power generation unit and the energy controller to switch the external power supply of the solar power generation unit on and off. The second switch is electrically connected in series between the solar power generation unit and the water electrolysis unit to switch the power supply of the solar power generation unit to the water electrolysis unit on and off. The third switch is electrically connected in series between the fuel cell power generation unit and the energy controller to switch the external power supply of the fuel cell power generation unit on and off. The energy controller is electrically connected to the control terminals of the first switch, the second switch, and the third switch to control the on and off states of the first switch, the second switch, and the third switch.

[0015] Secondly, this utility model also provides an aircraft, including a hybrid power system as described in any of the above.

[0016] Compared with existing technologies, the hybrid power system provided by this utility model has a fuel cell energy density that is much higher than that of existing batteries. Therefore, while keeping the weight of the power system unchanged, it can store more energy generated by the solar power generation unit than batteries. After the energy is electrolyzed by the water electrolysis unit, it is stored in the form of hydrogen and oxygen, which allows the system to store more energy when there is sufficient sunlight. This can improve the endurance of the aircraft when there is insufficient sunlight or no sunlight, and improve the overall performance of the power system. Attached Figure Description

[0017] Figure 1 This is a schematic diagram of the hybrid power system provided in an embodiment of the present invention.

[0018] Explanation of reference numerals in the attached figures: 1. Solar power generation unit; 11. Solar cell panel; 12. Photovoltaic controller; 13. First inverter; 2. Water electrolysis unit; 21. Water electrolysis device; 22. Hydrogen storage tank; 221. Hydrogen supply valve; 23. Oxygen storage tank; 231. Oxygen supply valve; 24. Dryer; 25. Gas supply interface; 3. Fuel cell power generation unit; 31. Fuel cell power generation device; 32. Second inverter; 33. Water storage tank; 331. Water supply port; 34. Water pump; 4. Energy management unit; 41. Energy controller; 42. First switch; 43. Second switch; 44. Third switch. Detailed Implementation

[0019] 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. It should be understood that the specific embodiments described herein are merely illustrative of the present utility model and are not intended to limit the present utility model.

[0020] To address the technical problem that current solar cells in solar-powered aircraft are heavily limited by weather conditions and cannot meet the requirements for long-term use, this invention provides a hybrid power system. This system can store more energy generated by the solar power generation unit than a battery, while maintaining the same power system weight. This energy is then stored as hydrogen and oxygen after water electrolysis in an electrolysis unit. This allows the system to store more energy when there is ample sunlight, thereby increasing the aircraft's endurance when there is insufficient or no sunlight and improving the overall performance of the power system.

[0021] It should be noted that the hybrid power system described in this utility model is used in, but not limited to, aircraft. For ease of explanation, this utility model only uses the application of the hybrid power system in aircraft as an example. The principle of the hybrid power system applied to other types of equipment is essentially the same as that applied to aircraft, and will not be described in detail here.

[0022] Please see Figure 1 , Figure 1 This is a schematic diagram of a hybrid power system according to an embodiment of the present invention. The hybrid power system includes a solar power generation unit 1, a water electrolysis unit 2, a fuel cell power generation unit 3, and an energy management unit 4. The solar power generation unit 1 converts solar energy into electrical energy; the water electrolysis unit 2 is electrically connected to the solar power generation unit 1 and converts electrical energy into hydrogen and oxygen for storage; the fuel cell power generation unit 3 is connected to the water electrolysis unit 2 and converts the chemical energy of the stored hydrogen and oxygen into electrical energy; the energy management unit 4 is electrically connected to the solar power generation unit 1, the water electrolysis unit 2, and the fuel cell power generation unit 3, and controls the external power supply of the solar power generation unit 1 and / or the fuel cell power generation unit 3, as well as controlling the opening and closing of the water electrolysis unit 2.

[0023] In this embodiment, when there is sufficient sunlight, the solar power generation unit 1 independently supplies power to the external aircraft load and provides electrical energy to the water electrolysis unit 2, which is in operation, generating and storing hydrogen and oxygen through water electrolysis. When there is insufficient sunlight, the solar power generation unit 1 and the fuel cell power generation unit 3 simultaneously supply power to the external aircraft load, while the water electrolysis unit 2 is in a closed state. When there is no sunlight, the fuel cell power generation unit 3 independently supplies power to the external aircraft load, while the water electrolysis unit 2 and the solar power generation unit 1 are in a closed state.

[0024] In one embodiment, please refer to Figure 1To convert solar energy into electrical energy, the solar power generation unit 1 includes a solar panel 11, a photovoltaic controller 12, and a first inverter 13. The solar panel 11, the photovoltaic controller 12, and the first inverter 13 are electrically connected in sequence via wires. The solar panel 11 converts the solar energy contained in external sunlight into electrical energy. The solar panel 11 can be a monocrystalline silicon solar panel, a polycrystalline silicon solar panel, an amorphous silicon solar panel, a microcrystalline thin-film silicon solar panel, or other types. The solar panel 11 can be a group, or composed of multiple groups of solar panels connected in series or parallel. Its quantity and arrangement mainly depend on the overall design specifications such as the aircraft's external dimensions and total weight.

[0025] Understandably, the photovoltaic controller 12 is an existing mature device, and any feasible market specification model can be used. The photovoltaic controller 12 can quickly and in real time collect the current working status of the solar panel 11, including output voltage, output current, etc. The photovoltaic controller 12 also has data storage function, communication function, remote monitoring and control function, and comprehensive electrical protection function.

[0026] It should be noted that the first inverter 13 is not a mature existing device; any commercially available inverter of any feasible specification can be used. The first inverter 13 can convert the DC power output from the solar panel 11 into constant voltage DC or AC power. The first inverter 13 is provided with multiple power output ports, one of which is connected to the energy management unit 4, and another port is connected to the water electrolysis unit 2.

[0027] In one embodiment, please refer to Figure 1 For electrolysis, the water electrolysis unit 2 includes an electrolysis device 21, a hydrogen storage tank 22, and an oxygen storage tank 23. The electrolysis device 21 is connected to the hydrogen storage tank 22 and the oxygen storage tank 23 through pipelines, respectively, to supply hydrogen and oxygen to the hydrogen storage tank 22 and the oxygen storage tank 23. The electrolysis device 21 can use electrical energy to convert water into hydrogen and oxygen. The electrical energy used comes from the first inverter 13, and the water used comes from the water pump 34 or an independently set water supply unit.

[0028] Furthermore, the water electrolysis device 21 can be an alkaline water electrolysis device or a pure water electrolysis device. Existing mature electrolysis equipment can be used, and any feasible market specification or model can be adopted; no single limitation is made here. The rated power of the water electrolysis device 21 can be configured to be the same as the rated output power of the solar panel 11. The hydrogen storage tank 22 and the oxygen storage tank 23 are respectively equipped with a hydrogen supply valve 221 and an oxygen supply valve 231, and the hydrogen supply valve 221 and the oxygen supply valve 231 are respectively connected to the fuel cell power generation unit 3 through pipelines.

[0029] Furthermore, to dry the gas generated by electrolysis, both the hydrogen storage tank 22 and the oxygen storage tank 23 are equipped with dryers 24 between themselves and the water electrolysis device 21. The dryers 24, containing a desiccant, dry the hydrogen and oxygen from the water electrolysis device 21 separately, removing moisture and other impurities. The desiccant for the hydrogen can be activated alumina, molecular sieve adsorbents, or other materials. The desiccant for the oxygen can also be activated alumina, molecular sieve adsorbents, or other materials.

[0030] Specifically, the hydrogen produced by the water electrolysis device 21 is connected sequentially to the dryer 24, the hydrogen storage tank 22, and the hydrogen supply valve 221 via connecting pipes, and then connected to the anode of the fuel cell power generation device 31 in the fuel cell power generation unit 3 via connecting pipes; the oxygen produced by the water electrolysis device 21 is connected sequentially to the dryer 24, the oxygen storage tank 23, and the oxygen supply valve 231 via connecting pipes, and then connected to the cathode of the fuel cell power generation device 31 in the fuel cell power generation unit 3 via connecting pipes. The outlet pressure of the hydrogen and oxygen produced by the water electrolysis device 21 is approximately 1.6-3.2 MPa.

[0031] It is understood that both the oxygen storage tank 23 and the hydrogen storage tank 22 can be high-pressure gaseous hydrogen storage tanks, with a design pressure of approximately 1.6-3.2 MPa. Their materials can be metal, metal-glass fiber composite, metal-carbon fiber composite, plastic-carbon fiber composite, or other materials. The hydrogen storage tank 22 can also be a metal hydride hydrogen storage tank. There can be one or more oxygen storage tanks and hydrogen storage tanks 22.

[0032] In this embodiment, in order to replenish the hydrogen and oxygen required by the fuel cell before the aircraft takes off, or when the oxygen in the oxygen storage tank is used up due to prolonged lack of sunlight, or under other special circumstances, the hydrogen storage tank 22 and the oxygen storage tank 23 are respectively equipped with a gas replenishment interface 25 for active gas replenishment.

[0033] Understandably, the hydrogen supply valve 221 and oxygen supply valve 231 can be manual or electric valves, and valves with pressure regulation function can adjust the hydrogen or oxygen pressure to 0.05-0.5 MPa to adapt to the working pressure range of the fuel cell power generation unit 3. When the fuel cell power generation unit 3 is in operation, the hydrogen supply valve 221 and oxygen supply valve 231 are open, and when the fuel cell power generation unit 3 is in shutdown state, the hydrogen supply valve 221 and oxygen supply valve 231 are closed.

[0034] In one embodiment, please refer to Figure 1 In order to generate electricity from the fuel cell, treat the water and exhaust gas from the fuel cell, and recycle the water, the fuel cell power generation unit 3 includes a fuel cell power generation device 31, a second inverter 32, and a water storage tank 33. The fuel cell power generation device 31 is connected to the water storage tank 33 and is used to discharge water and exhaust gas into the water storage tank 33. The fuel cell power generation device 31 is electrically connected to the second inverter 32 through wires. The fuel cell power generation device 31 can convert the chemical energy of hydrogen and oxygen from the hydrogen storage tank 22 and oxygen storage tank 23 into electrical energy, and can be a proton exchange membrane fuel cell or a solid oxide fuel cell; the second inverter 32 can convert the DC power generated by the fuel cell power generation device 31 into constant voltage DC power or AC power; the water storage tank 33 can collect water and a small amount of exhaust gas and other products from the fuel cell power generation device 31; the water storage tank 33 is a non-sealed structure, and a small amount of exhaust gas from the fuel cell power generation device 31 can be discharged into the external environment through the water storage tank 33; the water storage tank 33 is equipped with a water inlet 331, and the water storage tank 33 needs to be filled with water to the maximum scale before the aircraft takes off to ensure the water demand of the water electrolysis device 21 during the flight; the water storage tank 33 is filled with deionized water or pure water.

[0035] Furthermore, the fuel cell power generation unit 3 also includes a water pump 34, which is connected to the water electrolysis unit 2 via a pipeline and is used to supply water to the water electrolysis unit 2. The water pump 34 is a variable frequency water pump, which can deliver water from the water storage tank 33 to the water electrolysis unit 21 at a corresponding flow rate according to the real-time water demand of the water electrolysis unit 21. The water pump 34 is turned on when the water electrolysis unit 21 is running and turned off when the water electrolysis unit 21 is shut down.

[0036] Understandably, during the process of pumping water from storage tank 33 to the water electrolysis device, a filtration device can also be installed to filter out impurities that may interfere with the water electrolysis device. The device can be set up according to the actual situation.

[0037] In one embodiment, please refer to Figure 1The energy management unit 4 includes an energy controller 41. The solar power generation unit 1, the water electrolysis unit 2, and the fuel cell power generation unit 3 are all electrically connected to the energy controller 41. The energy controller 41 is connected to an external load via wires. Based on sunlight and the aircraft load conditions, the unit controls the opening and closing of the water electrolysis unit, and simultaneously controls the solar power generation unit and the fuel cell power generation unit to supply power to the aircraft load simultaneously or individually.

[0038] Understandably, the energy controller 41 can be an all-in-one integrated controller, integrating the DC / DC converter, air compressor controller, hydrogen pump controller, power distribution unit (PDU), etc. into a single housing. The control modules can be combined according to the actual needs, and they share heat dissipation and communication interfaces. Alternatively, the energy controller 41 can be a PI / PID controller, both of which are existing mature energy control devices. The above logic control can be performed using conventional control methods.

[0039] Specifically, the energy management unit 4 further includes a first switch 42, a second switch 43, and a third switch 44. The first switch 42 is electrically connected in series between the solar power generation unit 1 and the energy controller 41, and is used to switch the external power supply of the solar power generation unit 1 on and off. The second switch 43 is electrically connected in series between the solar power generation unit 1 and the water electrolysis unit 2, and is used to switch the power supply of the solar power generation unit 1 to the water electrolysis unit. The third switch 44 is electrically connected in series between the fuel cell power generation unit 3 and the energy controller 41, and is used to switch the external power supply of the fuel cell power generation unit 3. The energy controller 41 is electrically connected to the control terminals of the first switch 42, the second switch 43, and the third switch 44, and is used to control the on and off of the first switch 42, the second switch 43, and the third switch 44.

[0040] The direct current generated by the solar panel 11 is sequentially connected to the photovoltaic controller 12 and the first inverter 13 via wires, and then connected to the energy controller 41 and the water electrolysis device 21 via the first switch 42 and the second switch 43, respectively. The first inverter 13 is provided with multiple power output ports, one of which is connected to the energy controller 41 via the first switch 42, and the other port is connected to the water electrolysis device 21 via the second switch 43. The electrical energy generated by the fuel cell power generation device 31 is converted by the second inverter 32 and then connected to the energy controller 41 via the third switch 44. The product outlet of the fuel cell power generation device 31 is sequentially connected to the water storage tank 33, the water pump 34, and the water electrolysis device 21 via connecting pipes.

[0041] To better understand this utility model, the following is combined with... Figure 1 The technical solution of this utility model is described in detail below: When there is sufficient sunlight, the energy controller 41 can control the first switch 42 and the second switch 43 to close, the third switch 44 to open, the hydrogen supply valve 221 and the oxygen supply valve 231 to close, the solar power generation unit starts and independently supplies power to the external aircraft load. At the same time, the solar power generation unit transmits the excess electrical energy to the water electrolysis unit, the water electrolysis unit starts, and the water electrolysis produces hydrogen and oxygen, which are stored in the hydrogen storage tank 22 and the oxygen storage tank 23, respectively.

[0042] When there is sunlight but insufficient sunlight, the energy controller 41 can control the first switch 42 to close, the second switch 43 to open, and the third switch 44 to close. The hydrogen supply valve 221 and the oxygen supply valve 231 will open, allowing the solar power generation unit and the fuel cell power generation unit to simultaneously supply power to the external aircraft load. The water electrolysis device 21 will remain closed. The energy controller 41 can regulate the output power of the solar power generation unit and the fuel cell power generation unit, ensuring that the solar power generation unit supplies power at its maximum power, with the fuel cell power generation unit providing the necessary power for any shortfall.

[0043] When there is no sunlight, the energy controller 41 can control the first switch 42 and the second switch 43 to open, the third switch 44 to close, the hydrogen supply valve 221 and the oxygen supply valve 231 to open, the fuel cell power generation unit to start, and hydrogen and oxygen to undergo an electrochemical reaction in the fuel cell power generation device 31 to generate electrical energy, which is independently supplied to the external aircraft load. The water electrolysis device 21 is in the off state.

[0044] This invention also provides an aircraft including a hybrid power system as described in any of the above embodiments.

[0045] The power system equipped with this device boasts a higher energy density, significantly extending the aircraft's endurance. Because the fuel cell's energy density far exceeds that of existing batteries, this patented technology stores more energy generated by solar cells than batteries, while maintaining the same power system weight. This energy is then stored as hydrogen and oxygen through water electrolysis. This means the system can store more energy in sunny conditions, greatly improving the aircraft's endurance in low-light or no-sunlight environments and significantly enhancing the overall performance of the power system.

[0046] Furthermore, resupply time is significantly reduced in emergencies, ensuring the aircraft can complete its return to flight in the shortest possible time. When sunlight is insufficient or absent, and the system's stored energy is depleted, ground-based maintenance of the power system is necessary. With existing solutions, maintenance personnel need at least 4-6 hours to charge the batteries. However, with the power system described in this patent, maintenance personnel can resupply the hydrogen and oxygen storage tanks in less than half an hour, ensuring the aircraft can complete its return to flight in the shortest possible time.

[0047] The specific embodiments of this utility model described above do not constitute a limitation on the scope of protection of this utility model. Any other corresponding changes and modifications made based on the technical concept of this utility model should be included within the scope of protection of the claims of this utility model.

Claims

1. A hybrid power system, characterized in that, include: A solar power generation unit used to convert solar energy into electrical energy; An electrolysis water unit, which is electrically connected to the solar power generation unit, is used to convert electrical energy into hydrogen and oxygen for storage. A fuel cell power generation unit, which is connected to the water electrolysis unit, is used to convert the chemical energy of stored hydrogen and oxygen into electrical energy. as well as An energy management unit, which is electrically connected to the solar power generation unit, the water electrolysis unit, and the fuel cell power generation unit, is used to control the external power supply of the solar power generation unit and / or the fuel cell power generation unit, and to control the opening or closing of the water electrolysis unit.

2. The hybrid power system according to claim 1, characterized in that, The solar power generation unit includes a solar panel, a photovoltaic controller, and a first inverter, which are electrically connected in sequence via wires.

3. The hybrid power system according to claim 1, characterized in that, The water electrolysis unit includes a water electrolysis device, a hydrogen storage tank, and an oxygen storage tank. The water electrolysis device is connected to the hydrogen storage tank and the oxygen storage tank via pipelines, respectively, for feeding hydrogen and oxygen into the hydrogen storage tank and the oxygen storage tank. The hydrogen storage tank and the oxygen storage tank are respectively equipped with a hydrogen supply valve and an oxygen supply valve, and the hydrogen supply valve and the oxygen supply valve are respectively connected to the fuel cell power generation unit via pipelines.

4. The hybrid power system according to claim 3, characterized in that, Both the hydrogen storage tank and the oxygen storage tank are equipped with dryers between themselves and the water electrolysis device, and each of the hydrogen storage tank and the oxygen storage tank is equipped with a gas replenishment port.

5. The hybrid power system according to claim 1, characterized in that, The fuel cell power generation unit includes a fuel cell power generation device, a second inverter, and a water storage tank. The fuel cell power generation device is connected to the water storage tank and is used to discharge water and exhaust gas into the water storage tank. The fuel cell power generation device is electrically connected to the second inverter via wires.

6. The hybrid power system according to claim 5, characterized in that, The water storage tank is equipped with a water inlet.

7. The hybrid power system according to claim 5, characterized in that, The fuel cell power generation unit also includes a water pump, which is connected to the water electrolysis unit via a pipeline to supply water to the water electrolysis unit.

8. The hybrid power system according to claim 1, characterized in that, The energy management unit includes an energy controller. The solar power generation unit, the water electrolysis unit, and the fuel cell power generation unit are all electrically connected to the energy controller. The energy controller is connected to an external load via wires.

9. The hybrid power system according to claim 8, characterized in that, The energy management unit further includes a first switch, a second switch, and a third switch. The first switch is electrically connected in series between the solar power generation unit and the energy controller to switch the external power supply of the solar power generation unit on and off. The second switch is electrically connected in series between the solar power generation unit and the water electrolysis unit to switch the power supply of the solar power generation unit to the water electrolysis unit on and off. The third switch is electrically connected in series between the fuel cell power generation unit and the energy controller to switch the external power supply of the fuel cell power generation unit on and off. The energy controller is electrically connected to the control terminals of the first switch, the second switch, and the third switch to control the on and off states of the first switch, the second switch, and the third switch.

10. An aircraft, characterized in that, Including the hybrid power system as described in any one of claims 1-9.

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