Hybrid power device and aircraft

Abstract

The invention provides a hybrid power device and an aircraft, and relates to the field of aircraft power systems. The hybrid power device comprises a power supply system and a control system. The power supply system comprises a solid oxide fuel cell module, a storage battery module and a super capacitor module. The solid oxide fuel cell module comprises an integrated plate type metal support solid oxide fuel cell or electric pile and has the advantages that the fuel gas sealing performance is good, the number and the weight of structural parts such as metal connecting bodies, end plates and sealing materials are reduced, the light weight can be realized, and the power-to-weight ratio is favorably improved. The control system comprises an operation control module and an energy management module; the energy management module is connected with the power input end of the aircraft to obtain the power requirement of the aircraft and calculates the output power of the solid oxide fuel cell module, the storage battery module and the super-capacitor module according to the requirement, the weight of a power system is reduced, the flight endurance time is prolonged, and the flight safety is improved. And the output performance and the service life of the hybrid power system are greatly improved.

Description

Technical Field

[0001] The present invention relates to the field of aircraft power systems, and in particular to a hybrid power device and an aircraft. Background Art

[0002] With the rapid development of communication, information, control, artificial intelligence and other technologies, drones are increasingly used in military and civilian fields. Military drones can perform battlefield reconnaissance, electronic warfare, relay communications, air strikes, swarm warfare and other tasks, while civilian drones play an irreplaceable role in agricultural plant protection, power inspections, meteorological monitoring, firefighting and disaster relief, and express delivery.

[0003] Lithium batteries are the main power source of traditional unmanned aerial vehicles. Due to their limited energy storage and short flight time, they cannot operate for a long time under high-current conditions such as high-frequency start-stop, anti-turbulence and changing flight postures. Excessive ambient temperature will also bring thermal safety hazards, and the cycle life is difficult to exceed 2,000 times, which seriously limits the development of unmanned aerial vehicles. Although supercapacitors have a cycle life of more than 100,000 times, their energy density is relatively low and cannot meet the power output requirements of unmanned aerial vehicles during long-distance flights.

[0004] New energy sources such as fuel cells and solar cells have begun to be used in the aerospace field. Using fuel cells as the power of unmanned aerial vehicles can greatly increase the endurance and range of activities. Compared with other types of fuel cells, solid oxide fuel cells (SOFCs) have the advantages of wide fuel adaptability, high energy conversion efficiency, all-solid-state, modular assembly, and zero pollution. They can directly use a variety of hydrocarbon fuels such as H2, CO, natural gas, liquefied gas, coal gas, and biomass gas. However, solid oxide fuel cells supported by anodes or electrolytes are relatively bulky, and the thermal shielding protection required for high-temperature operating environments further increases the overall weight and reduces the power-to-weight ratio of the SOFC system. This is also the main reason why SOFC is currently less used in portable power supplies, aircraft power supplies, and emergency power supplies. In addition, SOFC and other types of fuel cells have the defect of soft dynamic performance, which makes it difficult to meet the instantaneous high power output required by drones under conditions such as start-stop, hovering, anti-turbulence, and changing flight postures.

[0005] In view of this, the present application proposes a new type of hybrid power system power supply to solve the defects of the existing power supply of unmanned aerial vehicles. Summary of the invention

[0006] The purpose of the present invention includes, for example, providing a hybrid power device and an aircraft, which can realize the optimal configuration of the output power of each module in the hybrid power device, save fuel, and solve the defects of a single lithium battery as a power source. And it has the characteristics of light weight, self-sealing of gas, high output voltage, long endurance time, long service life and improved energy utilization.

[0007] The embodiments of the present invention can be implemented as follows:

[0008] In a first aspect, the present invention provides a hybrid power device, including a power system and a control system;

[0009] The power system comprises a solid oxide fuel cell module, a battery module and a super capacitor module arranged in a heat exchange power box; the heat exchange power box is provided with heat dissipation fins;

[0010] The solid oxide fuel cell module includes a battery / fuel cell stack, a heater, a fuel tank, an air pump, a heat exchanger, a burner, and a first DC-DC converter; the air pump and the fuel tank are respectively connected to the heat exchanger, the heat exchanger is respectively connected to the burner and the battery / fuel cell stack, and the battery / fuel cell stack is connected to the burner; the first DC-DC converter is connected to the power output end of the battery / fuel cell stack; the heat exchange power supply box is provided with an air inlet and an exhaust port for air circulation, and the air inlet and the exhaust port are respectively connected to the air path connected to the air pump; the control system includes an operation control module and an energy management module; the operation control module includes a sensor and a controller, the sensor is connected to the controller, and the sensor is respectively arranged on the air path connected to the fuel tank and the air pump; the heater is connected to the battery module and / or the supercapacitor module, and the heater is used to heat the battery / fuel cell stack;

[0011] The power output end of the first DC-DC converter, the output end of the battery module and the output end of the supercapacitor module are respectively connected to the input end of the energy management module;

[0012] The energy management module is connected to the controller, and the energy management module is used to connect to the power input terminal of the electrical appliance to obtain the required power of the electrical appliance, and calculate the output power of the solid oxide fuel cell module, the battery module and the supercapacitor module according to the required power of the electrical appliance; the controller controls the input parameters of the fuel tank and the air pump according to the output power of the solid oxide fuel cell module; wherein the input parameters include temperature, flow rate and pressure.

[0013] In an optional embodiment, during the startup phase of the solid oxide fuel cell module, the battery module and the super capacitor module jointly supply power to the solid oxide fuel cell module and the control system;

[0014] When the solid oxide fuel cell module is in a stable power generation stage, the battery / stack in the solid oxide fuel cell module charges the battery module and the supercapacitor module respectively; and the battery / stack supplies power to the control system, the heater and the air pump.

[0015] In an optional embodiment, the electrical appliance includes an aircraft, and when the aircraft is in a cruising state, the solid oxide fuel cell module supplies power to the aircraft; when the aircraft is in a takeoff, hovering or anti-turbulence state, the solid oxide fuel cell module combines with the supercapacitor module to supply power to the aircraft, or the solid oxide fuel cell module combines with the supercapacitor module and the battery module to supply power to the aircraft.

[0016] In an optional embodiment, the solid oxide fuel cell module includes an integrated plate battery / stack in which a plurality of batteries are integrated on a metal support; the metal support has a first surface and a second surface arranged opposite to each other and a self-sealing gas flow channel is formed between the first surface and the second surface; at least one of the first surface and the second surface is provided with a breathable through hole area including a plurality of through holes; the breathable through hole area is connected to the gas flow channel; the surface of the metal support is covered with an insulating layer; the through holes in the breathable through hole area penetrate the insulating layer; a battery is provided on the side of the insulating layer away from the metal support; each of the batteries corresponds one-to-one to the breathable through hole area, and a plurality of the batteries are connected in series and parallel.

[0017] In an optional embodiment, it includes a first pipeline, a second pipeline, a third pipeline, a fourth pipeline, a fifth pipeline and a sixth pipeline;

[0018] One end of the first pipeline is connected to the fuel tank, and the other end is connected to the inlet of the battery / fuel stack; the first pipeline passes through the heat exchanger;

[0019] One end of the second pipeline is connected to the burner, and the other end is connected to the first pipeline and is located between the heat exchanger and the battery / stack;

[0020] One end of the third pipeline is connected to the air pump, and the other end is connected to the inlet of the battery / fuel stack; the third pipeline passes through the heat exchanger;

[0021] One end of the fourth pipeline is connected to the burner, and the other end is connected to the third pipeline and is located between the heat exchanger and the battery / stack;

[0022] One end of the fifth pipeline is connected to the outlet of the battery / fuel cell stack, and the other end is connected to the burner;

[0023] One end of the sixth pipeline is connected to the burner, and the other end is connected to the heat exchanger;

[0024] The sensors include a flow sensor, a temperature sensor and a pressure sensor. The flow sensor, the temperature sensor and the pressure sensor are respectively provided on the first pipeline and the third pipeline; the flow sensor is respectively provided on the second pipeline and the fourth pipeline; and the temperature sensor is provided on the fifth pipeline.

[0025] In an optional embodiment, the battery module includes a first charger, a battery, and a second DC-DC converter connected in sequence; the input end of the first charger is connected to the output end battery / battery stack of the first DC-DC converter, and the output end of the second DC-DC converter is connected to the input end of the air pump and the energy management module respectively;

[0026] The supercapacitor module includes a second charger, a supercapacitor and a third DC-DC converter connected in sequence; the input end of the second charger is connected to the output battery / battery stack of the first DC-DC converter, and the output end of the third DC-DC converter is connected to the input end of the energy management module.

[0027] In an optional embodiment, the fuel gas flow channel further includes a reaction medium flow channel area, an inlet and an outlet, the reaction medium flow channel area is arranged between the first surface and the second surface and is spaced apart from the first surface and the second surface respectively; the inlet and the outlet are respectively connected to the reaction medium flow channel area;

[0028] The reaction medium flow channel area is arranged correspondingly to the air permeable through hole area, and the through holes of the air permeable through hole area are connected to the reaction medium flow channel area.

[0029] In an optional embodiment, the sensor further includes a power detector, and the power detector is used to connect to an electrical appliance to obtain the required power of the electrical appliance.

[0030] The power detector is connected to the battery module, the storage battery module and the super capacitor module respectively.

[0031] In an optional embodiment, it further includes a water tank, a first evaporator, a second evaporator and a condenser;

[0032] The water tank is connected to the first evaporator, the fuel tank is connected to the second evaporator, the first evaporator and the second evaporator are connected to the heat exchanger respectively, and the condenser is connected to the burner and the water tank respectively.

[0033] In an optional implementation, the battery module is connected to the first evaporator and the second evaporator respectively.

[0034] In a second aspect, the present invention provides an aircraft, comprising a hybrid power device as described in any one of the aforementioned embodiments.

[0035] The beneficial effects of the embodiments of the present invention include:

[0036] 1. The hybrid power device provided in the embodiment of the present invention, the power system includes a solid oxide fuel cell module, a battery module and a super capacitor module. The solid oxide fuel cell module can charge the battery module and the super capacitor module. The combined structure of the solid oxide fuel cell module, the battery module and the super capacitor module solves the shortcomings of each as a power source, greatly improves the cruising time and extends the service life, and saves energy. The solid oxide fuel cell module adopts an integrated plate battery / stack with several batteries integrated on a metal support; the metal support can realize the self-sealing of the gas, reduce the number and weight of structural parts such as metal connectors, end plates and sealing materials, achieve lightweight and improve the power-to-weight ratio, and have a high output voltage. And the use of a metal support has fast start-stop speed, good thermal shock resistance, and good robustness.

[0037] 2. The heat exchange power box is equipped with a heat dissipation fin structure. The gas from the air pump enters the heat exchanger after heat exchange in the heat exchange power box, which can effectively cool the battery module and supercapacitor module in the heat exchange power box, while improving the safety of the battery module and supercapacitor module, realizing energy recovery and saving energy.

[0038] The aircraft provided by the embodiment of the present invention includes the above-mentioned hybrid power device, which can achieve optimal power distribution of each module of the power system, which is beneficial to extending the service life of the power system and reducing fuel consumption. BRIEF DESCRIPTION OF THE DRAWINGS

[0039] In order to more clearly illustrate the technical solutions of the embodiments of the present invention, the drawings required for use in the embodiments are briefly introduced below. It should be understood that the following drawings only show certain embodiments of the present invention and therefore should not be regarded as limiting the scope. For ordinary technicians in this field, other related drawings can be obtained based on these drawings without creative work.

[0040] Figure 1A schematic block diagram of the composition of a hybrid power device provided by an embodiment of the present invention;

[0041] Figure 2 A schematic block diagram of the composition of a power supply system of a hybrid power device provided by an embodiment of the present invention;

[0042] Figure 3 A schematic diagram of the control principle of a hybrid power device provided by an embodiment of the present invention;

[0043] Figure 4 A schematic diagram of the structure of a battery stack of a hybrid power device provided by an embodiment of the present invention;

[0044] Figure 5 A schematic diagram of the structure of a single integrated plate-type battery of a hybrid power device provided by an embodiment of the present invention;

[0045] Figure 6 for Figure 5 A partial enlarged schematic diagram of the M in the middle;

[0046] Figure 7 A schematic block diagram of power supply of a solid oxide fuel cell module in a hybrid power device provided in an embodiment of the present invention during a startup phase;

[0047] Figure 8 A schematic block diagram of power supply of a solid oxide fuel cell module in an operation stage in a hybrid power device provided in an embodiment of the present invention.

[0048] Icons: 10-hybrid power device; 100-power system; 110-solid oxide fuel cell module; 111-battery / stack; 112-fuel tank; 113-air pump; 114-heat exchanger; 115-burner; 116-first DC-DC converter; 117-water tank; 118-first evaporator; 119-second evaporator; 120-condenser; 121-condensate collection pipe; 122-heater; 123-heat exchange power box; 124-pressure reducing valve; 130-integrated plate battery; 140-metal support; 141-reaction medium flow channel area; 142-inlet; 143-outlet; 144-ventilation through hole area; 145-insulating layer; 146-metal transition layer; 150-electric Cell; 151-anode; 152-electrolyte; 153-cathode; 154-connector; 155-solid section; 156-porous section; 161-first pipeline; 162-second pipeline; 163-third pipeline; 164-fourth pipeline; 165-fifth pipeline; 166-sixth pipeline; 170-battery module; 171-first charger; 172-battery; 173-second DC-DC converter; 180-supercapacitor module; 181-second charger; 182-supercapacitor; 183-third DC-DC converter; 200-control system; 211-flow solenoid valve; 212-temperature sensor; 213-pressure sensor; 230-energy management module; 300-aircraft. DETAILED DESCRIPTION

[0049] In order to make the purpose, technical solutions and advantages of the embodiments of the present invention clearer, the technical solutions in the embodiments of the present invention will be clearly and completely described below in conjunction with the drawings in the embodiments of the present invention. Obviously, the described embodiments are part of the embodiments of the present invention, not all of the embodiments. Generally, the components of the embodiments of the present invention described and shown in the drawings here can be arranged and designed in various different configurations.

[0050] Therefore, the following detailed description of the embodiments of the present invention provided in the accompanying drawings is not intended to limit the scope of the invention claimed for protection, but merely represents selected embodiments of the present invention. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the present invention.

[0051] It should be noted that similar reference numerals and letters denote similar items in the following drawings, and therefore, once an item is defined in one drawing, further definition and explanation thereof is not required in subsequent drawings.

[0052] In the description of the present invention, it should be noted that if the terms "upper", "lower", "inside", "outside", etc. appear to indicate an orientation or position relationship, they are based on the orientation or position relationship shown in the accompanying drawings, or are the orientation or position relationship in which the product of the invention is usually placed when used. They are only for the convenience of describing the present invention and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and therefore cannot be understood as a limitation on the present invention.

[0053] In addition, the terms “first”, “second”, etc., if used, are merely used to distinguish between the descriptions and should not be understood as indicating or implying relative importance.

[0054] It should be noted that, in the absence of conflict, the features in the embodiments of the present invention may be combined with each other.

[0055] As the main power source of traditional aircraft, lithium batteries have limited energy storage and short flight time, which seriously restricts the development of aircraft. New energy sources such as solid oxide fuel cells and solar cells have begun to be used in the field of aerospace. Using solid oxide fuel cells as the power of aircraft can greatly increase the flight time and range of activities. Compared with other types of solid oxide fuel cells, solid oxide fuel cells (SOFC) have the advantages of wide fuel adaptability, high energy conversion efficiency, all-solid state, modular assembly, and zero pollution. They can directly use a variety of hydrocarbon fuels such as H2, CO, natural gas, liquefied gas, coal gas and biomass gas. However, solid oxide fuel cells supported by anodes or electrolytes are relatively bulky, and the thermal shielding protection required for high-temperature operating environments further increases the overall weight and reduces the power-to-weight ratio of the SOFC system. This is also the main reason why SOFC is less used in portable power supplies, aircraft power supplies, and emergency power supplies.

[0056] SOFC and other types of solid oxide fuel cells have the disadvantage of weak dynamic performance, which makes it difficult to meet the instantaneous high power output required by UAVs in start-stop, hovering, anti-turbulence, changing flight postures, etc. Therefore, it is necessary to equip an auxiliary power supply that can provide high power in a short time. The hybrid power combined with solid oxide fuel cells and lithium batteries can achieve complementary power advantages and meet the needs of rapid changes in the load of unmanned aerial vehicles.

[0057] In order to overcome at least one defect in the prior art, the present application proposes a hybrid power device that can not only solve the instantaneous high-power output required for the UAV under conditions such as starting and stopping, hovering, anti-turbulence, and changing flight postures; it can also extend the flight endurance time and reduce fuel consumption while meeting the power requirements of the aircraft.

[0058] Please refer to Figure 1This embodiment provides a hybrid power device 10, including a power supply system 100 and a control system 200.

[0059] Combination Figure 2 , Figure 3 The power system 100 includes a solid oxide fuel cell module 110, a battery module 170 and a super capacitor module 180. The hybrid power system can realize complementary power advantages, which can not only extend the flight time, but also meet the instantaneous high power output of the aircraft 300, while ensuring that the power of the aircraft 300 is met, reduce fuel consumption and save energy.

[0060] Among them, the solid oxide fuel cell module 110 includes a battery / electrical stack 111, a heater 122, a fuel tank 112, an air pump 113, a heat exchanger 114, a burner 115, and a first DC-DC converter 116. The air pump 113 and the fuel tank 112 are respectively connected to the heat exchanger 114, the heat exchanger 114 is respectively connected to the burner 115 and the battery / electrical stack 111, and the battery / electrical stack 111 is connected to the burner 115; the first DC-DC converter 116 is connected to the power output end of the battery / electrical stack 111. The heater 122 is connected to the battery module 170 and / or the supercapacitor module 180, and the heater 122 is used to heat the battery / electrical stack 111. It can be understood that the heater 122 is only connected to the battery module 170. Alternatively, the heater 122 is only connected to the supercapacitor module 180. Alternatively, the battery module 170 and the supercapacitor module 180 are respectively connected to the heater 122 to realize power supply to the heater 122. The provision of the heater 122 is beneficial to improving the catalytic reforming reaction efficiency and improving the electrochemical reaction efficiency.

[0061] The solid oxide fuel cell module 110 includes an integrated plate-type battery / stack 111 in which a plurality of batteries 150 are integrated on a metal support 140; the metal support 140 has a first surface and a second surface arranged opposite to each other and a self-sealing gas flow channel formed between the first surface and the second surface. At least one of the first surface and the second surface is provided with a gas permeable through hole area 144 including a plurality of through holes; the gas permeable through hole area 144 is connected to the gas flow channel; the surface of the metal support 140 is covered with an insulating layer 145; the through holes of the gas permeable through hole area 144 penetrate the insulating layer 145; the side of the insulating layer 145 away from the metal support 140 is provided with a battery 150; each battery 150 corresponds to the gas permeable through hole area 144 one by one, and a plurality of batteries 150 are connected in series and parallel.

[0062] The control system 200 includes an operation control module and an energy management module 230. The operation control module includes a sensor and a controller, the sensor and the controller are connected, and the sensors are respectively arranged on the gas path connected to the fuel tank 112 and the air pump 113. The power output end of the battery / stack 111, the battery module 170 and the supercapacitor module 180 are respectively connected to the energy management module 230.

[0063] The power output terminal of the first DC-DC converter 116 , the output terminal of the battery module 170 , and the output terminal of the super capacitor module 180 are respectively connected to the input terminal of the energy management module 230 .

[0064] The energy management module 230 is connected to the controller, and the energy management module 230 is used to connect to the power input terminal of the aircraft 300 to obtain the power demand of the aircraft 300, and calculate the output power of the solid oxide fuel cell module 110, the battery module 170 and the super capacitor module 180 according to the required power of the aircraft 300; the controller controls the input parameters of the fuel tank 112 and the air pump 113 according to the output power of the solid oxide fuel cell module 110; wherein the input parameters include temperature, flow rate and pressure, etc.

[0065] The controller is also used to obtain the charging power requirements of the battery module 170 and the super capacitor module 180 to control the battery / fuel stack 111 to charge the battery module 170 and the super capacitor module 180 .

[0066] Combination Figures 4 to 6 The battery / cell stack 111 includes one or more stacked integrated plate batteries 130 . The integrated plate battery 130 includes a metal support 140 , an insulating layer 145 and a battery 150 .

[0067] The metal support 140 has a first surface and a second surface arranged opposite to each other, and has a self-sealing gas flow channel. The self-sealing gas flow channel includes a reaction medium flow channel area 141, an inlet 142 and an outlet 143. The reaction medium flow channel area 141 is arranged between the first surface and the second surface and is spaced from the first surface and the second surface respectively; the inlet 142 and the outlet 143 are respectively connected to the reaction medium flow channel area 141.

[0068] The reaction medium flow channel area 141 is arranged correspondingly to the air permeable through hole area 144, and the through holes of the air permeable through hole area 144 are connected to the reaction medium flow channel area 141. The first surface and the second surface are respectively provided with an insulating layer 145, and the air permeable holes penetrate the insulating layer 145. The battery 150 is arranged on the side of the insulating layer 145 away from the metal support body 140, each battery 150 corresponds to the air permeable through hole area 144 one by one, and multiple batteries 150 are connected in series and parallel.

[0069] The battery 150 includes a cathode 153, an anode 151, an electrolyte 152 and a connector 154. The anode 151 is disposed on the surface of the insulating layer 145, and the anode 151 completely covers the air permeable through-hole area 144. The surface of the anode 151 is the electrolyte 152, and the surface of the electrolyte 152 is the cathode 153. That is, the electrolyte 152 is located between the cathode 153 and the anode 151. Multiple batteries 150 are spaced apart from each other, and electrodes of the same polarity are not connected. The anode 151 has a portion of an exposed end that is not covered by the electrolyte 152, and the connector 154 covers the exposed end and is electrically connected to the cathode 153 of the adjacent battery 150, thereby realizing the series connection of multiple batteries 150. The connector 154 is isolated from the anode 151 of the adjacent battery 150 by the electrolyte 152.

[0070] The connector 154 is made of a highly conductive material. The connector 154 includes a connected solid segment 155 and a porous segment 156. The solid segment 155 covers the exposed anode 151 to achieve electrical connection with the anode 151. The porous segment 156 covers the side of the cathode 153 away from the electrolyte 152. In this way, the series connection of the batteries 150 is achieved.

[0071] Fuel and air etc. enter the battery / stack 111 through the inlet 142, and a reforming reaction occurs in the reaction medium flow channel area 141. The reformed synthesis gas reaches the anode 151 through the air vents, and an electrochemical reaction occurs to generate electricity. Small holes are provided on the porous section 156 of the connector 154, allowing air to reach the cathode 153 of the battery 150, providing oxygen for power generation. The unreacted fuel and air in the battery / stack 111 enter the burner 115 from the outlet 143 and burn.

[0072] Optionally, the porous reaction medium flow channel region 141 has a polyhedral lattice unit structure or a minimal surface structure, and the porosity of the reaction medium flow channel region 141 is about 40% to 80%, which can improve the reforming reaction efficiency. A metal transition layer 146 is provided between the surface of the metal support 140 and the insulating layer 145, which can reduce the difference in thermal expansion coefficient between the metal support 140 and the insulating layer 145, prevent structural delamination, and improve structural reliability.

[0073] In the battery / electrical stack 111, a metal support 140 is used, and the battery / electrical stack 111 has a fast start-stop speed and good thermal shock resistance. The metal support 140 can be formed in one piece, has good airtightness, and improves reaction efficiency. The reaction medium flow channel area 141 is arranged inside the metal support 140, and has a certain distance from the anode 151, which can reduce the carbon deposition of the reforming reaction at the anode 151, improve the activity of the anode 151, and improve the battery performance. In addition, the reaction medium flow channel area 141 is located inside the metal support 140, and the gas flow channel can be self-sealed by the metal support 140. If multiple integrated plate batteries 130 are stacked, there is no need to fill sealing materials between adjacent integrated plate batteries 130, which reduces the difficulty of sealing, reduces the process, improves production efficiency, and is conducive to improving the power-to-weight ratio of the battery / electrical stack 111. In addition, batteries 150 are respectively arranged on the two side surfaces of the metal support 140, so that the output voltage of a single integrated plate battery 130 is higher.

[0074] Optionally, the solid oxide fuel cell module 110 includes a first pipeline 161 , a second pipeline 162 , a third pipeline 163 , a fourth pipeline 164 , a fifth pipeline 165 and a sixth pipeline 166 .

[0075] One end of the first pipeline 161 is connected to the fuel tank 112, and the other end is connected to the inlet 142 of the battery / electrical stack 111; the first pipeline 161 passes through the heat exchanger 114. One end of the second pipeline 162 is connected to the burner 115, and the other end is connected to the first pipeline 161 and is located between the heat exchanger 114 and the battery / electrical stack 111. After the fuel in the fuel tank 112 is preheated by the heat exchanger 114, a part of the fuel enters the inlet 142 of the battery / electrical stack 111 along the first pipeline 161 for reforming reaction. Another part of the fuel enters the burner 115 along the second pipeline 162 for combustion, providing heat for the heat exchanger 114.

[0076] One end of the third pipeline 163 is connected to the air pump 113, and the other end is connected to the inlet 142 of the battery / electrical stack 111. The third pipeline 163 passes through the heat exchanger 114. One end of the fourth pipeline 164 is connected to the burner 115, and the other end is connected to the third pipeline 163 and is located between the heat exchanger 114 and the battery / electrical stack 111. After the air from the air pump 113 is preheated by the heat exchanger 114, a part of the air enters the inlet 142 of the battery / electrical stack 111 along the third pipeline 163 for reforming reaction. Another part of the air enters the burner 115 along the fourth pipeline 164 for combustion, providing heat for the heat exchanger 114.

[0077] One end of the fifth pipeline 165 is connected to the outlet 143 of the battery / fuel stack 111, and the other end is connected to the burner 115. The fuel and air entering the battery / fuel stack 111 undergo a reforming reaction, and the mixed gas of the incompletely reacted fuel and air enters the burner 115 along the fifth pipeline 165 to burn, providing heat for the heat exchanger 114.

[0078] It can be understood that one end of the sixth pipeline 166 is connected to the burner 115, and the other end is connected to the heat exchanger 114. The tail gas after combustion in the burner 115 enters the heat exchanger 114 through the sixth pipeline 166, exchanges heat with the heat exchanger 114, and then is discharged from the tail gas pipe.

[0079] Optionally, if wet reforming is adopted. The solid oxide fuel cell module 110 also includes a water tank 117, a first evaporator 118, a second evaporator 119 and a condenser 120. The water tank 117 is connected to the first evaporator 118, the fuel tank 112 is connected to the second evaporator 119, the first evaporator 118 and the second evaporator 119 are respectively connected to the heat exchanger 114, and the condenser 120 is respectively connected to the burner 115 and the water tank 117. The water in the water tank 117 evaporates through the first evaporator 118, and the fuel in the fuel tank 112 evaporates through the second evaporator 119. The evaporated water and the fuel are preheated together through the heat exchanger 114. A part of the preheated mixed fuel enters the battery / stack 111 for reforming reaction, and the other part enters the burner 115 to burn and release heat. It can be understood that the combustion raw materials in the burner 115 come from two parts. One part is the fuel and air that directly enters the burner 115, and the other part is the incompletely reacted fuel and air that are discharged from the outlet 143 of the battery / fuel stack 111. The tail gas after combustion in the burner 115 enters the heat exchanger 114 for heat exchange, then enters the condenser 120 for condensation, and then is discharged along the tail pipe.

[0080] Optionally, a condensed water collection pipe 121 is provided between the condenser 120 and the water tank 117. The water condensed in the condenser 120 can flow back to the water tank 117, so as to realize the recycling of water and save raw materials. If used in the unmanned aerial vehicle 300, this can reduce the amount of water carried by the aircraft 300, reduce the overall weight of the aircraft 300, improve flight efficiency and carrying capacity, and reduce energy consumption.

[0081] Of course, if the battery / stack 111 adopts a dry reforming method, the water tank 117, evaporator and other components can be omitted. No specific limitation is made here.

[0082] It should be noted that the battery / stack 111 is provided with a total material inlet 142 and a material outlet 143, and the material inlet 142 and the material outlet 143 are respectively welded to the corresponding pipes to improve the sealing of the gas path. Alternatively, the inlet 142 and the outlet 143 on each metal support 140 are respectively welded to the corresponding pipes to achieve the sealing of the gas path. When multiple integrated plate batteries 130 are stacked, the multiple integrated plate batteries 130 are connected in series and parallel through highly conductive materials.

[0083] The sensor includes a flow sensor, a temperature sensor 212, a pressure sensor 213 and a power detector. The flow sensor, the temperature sensor 212, the pressure sensor 213 and the power detector are connected to the controller respectively. The power detector is connected to the aircraft 300, the solid oxide fuel cell module 110, the battery module 170 and the super capacitor module 180 respectively. The sensor is mainly used to detect the flow, temperature and pressure on each pipeline, and to detect the required power of the aircraft 300. Of course, the power detector can also detect the output power or charging required power of each module in the power supply system 100.

[0084] Figure 3 The DC / DC in the figure represents a direct current-to-direct current converter, S represents a flow solenoid valve 211 , P represents a pressure sensor 213 , and T represents a temperature sensor 212 .

[0085] Optionally, a flow sensor, a temperature sensor 212 and a pressure sensor 213 are provided on the first pipeline 161 and the third pipeline 163, respectively. A flow sensor is provided between the water tank 117 and the first evaporator 118 to detect the water flow entering the first evaporator 118. A flow sensor is provided between the fuel tank 112 and the second evaporator 119 to detect the flow of fuel entering the second evaporator 119. A flow sensor, a temperature sensor 212 and a pressure sensor 213 are provided in sequence at the first pipeline 161 near the inlet 142 of the battery / fuel stack 111 to detect the flow, temperature and pressure of the fuel entering the inlet 142 of the battery / fuel stack 111. A flow sensor is provided on the second pipeline 162 to detect the flow of fuel entering the burner 115.

[0086] A flow sensor is provided between the air pump 113 and the heat exchanger 114 to detect the flow rate of air entering the heat exchanger 114. A flow sensor, a temperature sensor 212 and a pressure sensor 213 are provided in sequence on the third pipeline 163 near the inlet 142 of the battery / fuel stack 111 to detect the flow rate, temperature and pressure of the air entering the inlet 142 of the battery / fuel stack 111. A flow sensor is provided on the fourth pipeline 164 to detect the flow rate of air entering the burner 115.

[0087] A temperature sensor 212 is provided on the fifth pipeline 165 for detecting the temperature of the gas entering the burner 115 from the outlet 143 of the battery / fuel stack 111 .

[0088] Optionally, the flow sensor and the flow solenoid valve 211 are integrated into one, which can realize the functions of flow control and monitoring at the same time.

[0089] The power output end of the battery / cell stack 111 is respectively connected to the power input end of the battery module 170, the super capacitor module 180 and the energy management module 230. It is easy to understand that the power output end of the battery / cell stack 111 is modulated by the first DC-DC converter 116 and then stably supplies power to the battery module 170, the super capacitor module 180 and the energy management module 230.

[0090] Optionally, the battery module 170 includes a first charger 171, a battery 172, and a second DC-DC converter 173 connected in sequence. The input end of the first charger 171 is connected to the power output end of the battery / stack 111. The first charger 171 is an anti-overcharge charger used to charge the battery 172. The output end of the battery 172 is modulated and output by the second DC-DC converter 173. The output end of the second DC-DC converter 173 is respectively connected to the input end of the air pump 113 and the energy management module 230. The battery 172 is used to provide power for the operation of the air pump 113, and to supply instantaneous high power to the aircraft 300 when necessary. The instantaneous high power supply scenarios of the aircraft 300 include take-off, hovering, flight posture change, etc. The battery 172 can be a lithium battery, a sodium battery, or other types of solid-state batteries.

[0091] It is understandable that if the solid oxide fuel cell module 110 further includes a first evaporator 118 and a second evaporator 119 , the battery 172 is also connected to the first evaporator 118 and the second evaporator 119 respectively to provide electricity to the first evaporator 118 and the second evaporator 119 .

[0092] The supercapacitor module 180 includes a second charger 181, a supercapacitor 182 and a third DC-DC converter 183 connected in sequence. The input end of the second charger 181 is connected to the power output end of the battery / stack 111. The second charger 181 is an anti-overcharge charger for charging the supercapacitor 182. The output end of the supercapacitor 182 is connected to the third DC-DC converter 183. The third DC-DC converter 183 is connected to the energy management module 230. It can be understood that the output end of the supercapacitor 182 is connected to the input end of the energy management module 230 after being modulated by the third DC-DC converter 183. The output end of the supercapacitor 182 is used to supply instantaneous high power to the aircraft 300, such as supplying power to the aircraft 300 in situations such as takeoff, hovering, maneuvering, flight posture change, high-frequency start and stop, and anti-turbulence of the aircraft 300.

[0093] Although the energy density of supercapacitor 182 is relatively low, its cycle life is relatively high, which is more than 100,000 times. In addition, it has the characteristics of fast charging, fast response speed, high specific power, wide temperature range, and no explosion and combustion risks. It has absolute advantages in improving the power performance, thermal safety performance, durability and reliability of the unmanned aerial vehicle 300 in starting and stopping, changing flight postures, etc.

[0094] The power supply system 100 also includes a heat exchange power supply box 123, in which the battery module 170 and the super capacitor module 180 are arranged. The heat exchange power supply box 123 is provided with an air inlet and an exhaust port for air circulation, and the air inlet and the exhaust port are respectively connected to the air path connected to the air pump 113. After the air comes out of the air pump 113, it first enters the heat exchange power supply box 123, cools the heat exchange power supply box 123, and then enters the heat exchanger 114. Heat exchange power supply box 123 is provided with heat dissipation fins. Since the battery module 170 and the super capacitor module 180 are encapsulated in the heat exchange power supply box 123. Arranging heat dissipation fins around the battery module 170 and the super capacitor module 180 is conducive to air flow and heat dissipation. The heat exchange power supply box 123 and the heat dissipation fins realize energy recovery and energy saving while improving the safety of the battery module 170 and the super capacitor module 180.

[0095] Optionally, a temperature sensor 212 is provided in the heat exchange power box 123 for real-time detection of the temperature of the heat exchange power box 123. A temperature sensor 212 is provided on the pipeline between the air pump 113 and the heat exchange power box 123 for detecting the temperature of the air entering the heat exchange power box 123. The heat exchange power box 123 is connected to a pressure reducing valve 124. When the air pressure in the heat exchange power box 123 is greater than the preset air pressure, the pressure can be released through the pressure reducing valve 124 to ensure the stability of the air pressure in the heat exchange power box 123 and improve safety.

[0096] In this embodiment, the first pipeline 161 is connected to the fuel inlet of the anode 151 of the battery / fuel stack 111. The water in the water tank 117 evaporates through the first evaporator 118, and the fuel in the fuel tank 112 evaporates through the second evaporator 119. The evaporated water and the fuel enter the heat exchanger 114 for preheating. The preheated mixed fuel passes through the flow solenoid valve 211, the temperature sensor 212 and the pressure sensor 213 in sequence and enters the fuel inlet of the anode 151 of the battery / fuel stack 111.

[0097] The third pipeline 163 is connected to the air inlet of the cathode 153 of the battery / electrical stack 111. The hole on the porous section 156 of the connector 154 is the air inlet of the cathode 153. The air from the air pump 113 passes through the heat exchange power box 123, the temperature sensor 212, the flow solenoid valve 211, the heat exchanger 114, the flow solenoid valve 211, the temperature sensor 212, and the pressure sensor 213 in sequence and enters the air inlet of the cathode 153 of the battery / electrical stack 111. If the air pressure in the heat exchange power box 123 is overpressured, the air entering the heat exchange power box 123 will be partially discharged from the pressure reducing valve 124.

[0098] The tail gas outlet 143 of the battery / stack 111 is connected to the inlet of the burner 115 after passing through the temperature sensor 212. The outlet 143 of the second pipeline 162 and the outlet 143 of the fourth pipeline 164 are respectively connected to the inlet of the burner 115. The outlet 143 of the burner 115 is connected to the heat exchanger 114, and the tail gas outlet 143 of the heat exchanger 114 is connected to the inlet 142 of the condenser 120, and the outlet 143 of the condenser 120 is connected to the water tank 117. The air cools the battery module 170 and the supercapacitor module 180 and then enters the heat exchanger 114, and the generated water vapor is condensed and recovered to the water tank 117. It can be understood that the water vapor generated by the electrochemical reaction and the combustion reaction can be condensed by the condenser 120 and recovered to the water tank 117.

[0099] The temperature sensor 212 is mainly used to detect the air temperature entering the heat exchange power box 123, the fuel temperature entering the anode 151 of the battery / electrical stack 111, the air temperature entering the cathode 153 of the battery / electrical stack 111, and the temperature of the exhaust gas leaving the battery / electrical stack 111. The pressure sensor 213 is mainly used to detect the fuel gas pressure entering the anode 151 of the battery / electrical stack 111 and the air pressure entering the cathode 153 of the battery / electrical stack 111. The flow sensor is mainly used to detect and control the flow of air entering the heat exchange power box 123, the air and fuel entering the burner 115, and the anode 151 fuel and cathode 153 air entering the battery / electrical stack 111. The power detector is connected to the energy management module 230 and is mainly used to monitor the required power of the aircraft 300. Of course, in some embodiments, a power detector can also be set to detect the output power of the battery / electrical stack 111, the battery 172 and the supercapacitor 182, and to detect the charging required power of the battery 172 and the supercapacitor 182. The controller is used to receive signal data fed back by the temperature sensor 212, the pressure sensor 213, the flow sensor and the power detector, process the received signal data and output corresponding decision signals to control the introduction of each reaction gas.

[0100] The controller may adopt a general-purpose processor, including but not limited to a central processing unit (CPU), a network processor (NP), etc.; it may also be a digital signal processor (DSP), an application-specific integrated circuit (ASIC), a field-programmable gate array (FPGA), or other programmable logic devices, discrete gate or transistor logic devices, discrete hardware components, etc. Of course, the controller may also be integrated into a PLC controller, a single-chip microcomputer, etc., which is not specifically limited here.

[0101] The embodiment of the present invention further provides an aircraft 300 , comprising the hybrid power device 10 as described in any one of the above embodiments. The energy management module 230 is connected to the power input terminal of the aircraft 300 to supply power to the aircraft 300 .

[0102] The battery 172 is mainly used for starting heating of the battery / fuel stack 111 and for supplying power to the heater 122. The battery 172 can also supply power to the air pump 113, the first evaporator 118, the second evaporator 119, etc. Of course, in special occasions where necessary, it can also supply instantaneous high-power power to the aircraft 300. In the present embodiment, it is mainly used to supply power to the heater 122 to achieve starting heating of the battery / fuel stack 111. The supercapacitor 182 is used to supply instantaneous high-power power to the aircraft 300 for starting, stopping, hovering, maneuvering, etc. The solid oxide fuel cell module 110 is mainly used for cruising of the aircraft 300, and for charging the battery 172 and the supercapacitor 182 respectively.

[0103] The operation control module monitors the gas path temperature, pressure, flow rate and power of each module in the system through various sensors, and feeds back relevant signals to the controller, which processes the received various sensor signals and outputs corresponding decision signals to control the safe and stable operation of the power system 100. Among them, the power detector includes real-time monitoring of the output power of the battery / stack 111, the output power of the battery 172, the output power of the supercapacitor 182, the charging demand power of the battery 172, the charging demand power of the supercapacitor 182 and the demand power of the aircraft 300.

[0104] The energy management module 230 optimizes the power output of the battery / stack 111, the storage battery 172 and the supercapacitor 182 according to the power demand of the aircraft 300, controls the optimal distribution of the power demand of the aircraft 300, reduces the weight of the power system, extends the flight endurance, and greatly improves the output performance and service life of the hybrid power system. Optionally, the energy management module 230 or the controller can also control the battery / stack 111 to charge the storage battery 172 and the supercapacitor 182 according to the charging power demand of the storage battery 172 and the supercapacitor 182.

[0105] It should be noted that the hybrid power device 10 provided in this embodiment is not only suitable for aircraft 300, such as unmanned aerial vehicles, spacecraft, drones, etc., but also suitable for other electrical appliances, including but not limited to airplanes, vehicles, ships, underwater equipment, rockets, engineering equipment, agricultural machinery and equipment or other equipment that requires a power device.

[0106] Combination Figure 7It can be understood that during the startup phase of the solid oxide fuel cell module 110, the battery module 170 and the super capacitor module 180 jointly supply power to the solid oxide fuel cell module 110 and the control system 200 to ensure the smooth startup of the solid oxide fuel cell module 110. The battery module 170 and the super capacitor module 180 include but are not limited to supplying power to various sensors, controllers, air pumps 113, first evaporators 118, second evaporators 119, heaters 122, and the like.

[0107] Combination Figure 8 In the operation phase, i.e., the stable power generation phase, of the solid oxide fuel cell module 110, the battery / stack 111 in the solid oxide fuel cell module 110 charges the storage battery module 170 and the supercapacitor module 180 respectively, and the battery / stack 111 supplies power to the control system 200, including but not limited to supplying power to various sensors, controllers, etc. The battery / stack 111 supplies power to the air pump 113, the first evaporator 118, the second evaporator 119, the heater 122, etc. respectively, to maintain the power required for the battery / stack 111 to generate power.

[0108] Taking the aircraft 300 as an example of an electrical appliance, the aircraft 300 is in a cruising state, and the solid oxide fuel cell module 110 supplies power to the aircraft 300. When the aircraft 300 is in a take-off, hovering or anti-turbulence state, the solid oxide fuel cell module 110 and the super capacitor module 180 supply power to the aircraft 300; or, the solid oxide fuel cell module 110 and the super capacitor module 180 and the battery module 170 jointly supply power to the aircraft 300. Among them, the solid oxide fuel cell module 110 and the super capacitor module 180 are the main power sources for the aircraft 300. Only in extreme cases, such as when the solid oxide fuel cell module 110 and the super capacitor module 180 are insufficiently powered, the battery module 170 will assist in assuming part of the power supply, that is, the solid oxide fuel cell module 110, the super capacitor module 180 and the battery module 170 jointly supply power to the aircraft 300.

[0109] The combined structure of the solid oxide fuel cell module 110, the battery module 170 and the super capacitor module 180 solves the shortcomings of each of them as a power source, greatly improves the cruising time and extends the service life, and saves energy.

[0110] In summary, the hybrid power device 10 and the aircraft 300 provided by the embodiment of the present invention have the following beneficial effects, including:

[0111] 1. The hybrid power device 10 provided in the embodiment of the present invention, the power system 100 includes a solid oxide fuel cell module 110, a battery module 170 and a super capacitor module 180. The solid oxide fuel cell module 110 can charge the battery module 170 and the super capacitor module 180 to extend the endurance time. The combination structure of the solid oxide fuel cell module 110, the battery module 170 and the super capacitor module 180 solves the shortcomings of each as a power source, greatly improves the cruising time and extends the service life, and saves energy.

[0112] 2. The solid oxide fuel cell module 110 uses a metal support 140 to achieve indirect internal reforming, reduce carbon deposition on the anode 151, and improve battery performance. The special structural design of the metal support 140 can achieve self-sealing of the fuel flow channel, and reduce the number and weight of structural parts such as metal connectors, end plates, and sealing materials, which can achieve lightweight and improve power-to-weight ratio, and high output voltage. The metal support 140 has fast start-stop speed and good thermal shock resistance.

[0113] 3. The air passes through the heat exchange power box 123 to effectively cool the battery 172 and the super capacitor 182 and improve the energy utilization rate. The water vapor in the exhaust gas is recovered to reduce the amount of water carried by the aircraft 300 during takeoff, thereby improving the lightweight and integration of the hybrid power device 10. While improving the safety of the battery module 170 and the super capacitor module 180, energy recovery is achieved to save energy.

[0114] The aircraft 300 provided in the embodiment of the present invention includes the above-mentioned hybrid power device 10, which can realize the optimized power distribution of each module of the power supply system 100, which is beneficial to prolonging the service life of the power supply system 100 and reducing fuel consumption.

[0115] The above is only a specific embodiment of the present invention, but the protection scope of the present invention is not limited thereto. Any changes or substitutions that can be easily thought of by a person skilled in the art within the technical scope disclosed by the present invention should be included in the protection scope of the present invention. Therefore, the protection scope of the present invention should be based on the protection scope of the claims.

Claims

1. A hybrid power device, characterized in that: Including power supply system and control system; The power system comprises a solid oxide fuel cell module, a battery module and a super capacitor module arranged in a heat exchange power box; the heat exchange power box is provided with heat dissipation fins; The solid oxide fuel cell module includes a battery / fuel cell stack, a heater, a fuel tank, an air pump, a heat exchanger, a burner, and a first DC-DC converter; the air pump and the fuel tank are respectively connected to the heat exchanger, the heat exchanger is respectively connected to the burner and the battery / fuel cell stack, and the battery / fuel cell stack is connected to the burner; the first DC-DC converter is connected to the power output end of the battery / fuel cell stack; the heat exchange power supply box is provided with an air inlet and an exhaust port for air circulation, and the air inlet and the exhaust port are respectively connected to the air path connected to the air pump; the heater is connected to the battery module and / or the supercapacitor module, and the heater is used to heat the battery / fuel cell stack; The control system includes an operation control module and an energy management module; The operation control module includes a sensor and a controller, the sensor is connected to the controller, and the sensor is respectively arranged on the gas path connected to the fuel tank and the air pump; The power output end of the first DC-DC converter, the output end of the battery module and the output end of the supercapacitor module are respectively connected to the input end of the energy management module; The energy management module is connected to the controller, and the energy management module is used to connect to the power input terminal of the electrical appliance to obtain the required power of the electrical appliance, and calculate the output power of the solid oxide fuel cell module, the battery module and the supercapacitor module according to the required power of the electrical appliance; the controller controls the input parameters of the fuel tank and the air pump according to the output power of the solid oxide fuel cell module; wherein the input parameters include temperature, flow rate and pressure.

2. The hybrid power device according to claim 1, characterized in that: During the startup phase of the solid oxide fuel cell module, the battery module and the super capacitor module jointly supply power to the solid oxide fuel cell module and the control system; When the solid oxide fuel cell module is in a stable power generation stage, the battery / stack in the solid oxide fuel cell module charges the battery module and the supercapacitor module respectively; and the battery / stack supplies power to the control system, the heater and the air pump.

3. The hybrid power device according to claim 1, characterized in that: The electrical appliance includes an aircraft. When the aircraft is in a cruising state, the solid oxide fuel cell module supplies power to the aircraft; when the aircraft is in a takeoff, hovering or anti-turbulence state, the solid oxide fuel cell module is combined with a supercapacitor module to supply power to the aircraft, or the solid oxide fuel cell module is combined with a supercapacitor module and the battery module to supply power to the aircraft.

4. The hybrid power device according to claim 1, characterized in that: The solid oxide fuel cell module includes an integrated plate battery / stack with a plurality of batteries integrated on a metal support body; the metal support body has a first surface and a second surface arranged opposite to each other and a self-sealing gas flow channel is formed between the first surface and the second surface; at least one of the first surface and the second surface is provided with a breathable through hole area including a plurality of through holes; the breathable through hole area is connected to the gas flow channel; the surface of the metal support body is covered with an insulating layer; the through holes in the breathable through hole area penetrate the insulating layer; a battery is provided on the side of the insulating layer away from the metal support body; each of the batteries corresponds one-to-one to the breathable through hole area, and a plurality of the batteries are connected in series and parallel.

5. The hybrid power device according to claim 1, characterized in that: The solid oxide fuel cell module comprises a first pipeline, a second pipeline, a third pipeline, a fourth pipeline, a fifth pipeline and a sixth pipeline; One end of the first pipeline is connected to the fuel tank, and the other end is connected to the inlet of the battery / fuel stack; the first pipeline passes through the heat exchanger; One end of the second pipeline is connected to the burner, and the other end is connected to the first pipeline and is located between the heat exchanger and the battery / stack; One end of the third pipeline is connected to the air pump, and the other end is connected to the inlet of the battery / fuel stack; the third pipeline passes through the heat exchanger; One end of the fourth pipeline is connected to the burner, and the other end is connected to the third pipeline and is located between the heat exchanger and the battery / fuel cell stack; One end of the fifth pipeline is connected to the outlet of the battery / fuel stack, and the other end is connected to the burner; One end of the sixth pipeline is connected to the burner, and the other end is connected to the heat exchanger; The sensors include a flow sensor, a temperature sensor and a pressure sensor. The flow sensor, the temperature sensor and the pressure sensor are respectively provided on the first pipeline and the third pipeline; the flow sensor is respectively provided on the second pipeline and the fourth pipeline; and the temperature sensor is provided on the fifth pipeline.

6. The hybrid power device according to claim 1, characterized in that: The battery module comprises a first charger, a battery and a second DC-DC converter connected in sequence; the input end of the first charger is connected to the output end of the first DC-DC converter, and the output end of the second DC-DC converter is connected to the input end of the air pump and the energy management module respectively; The supercapacitor module includes a second charger, a supercapacitor and a third DC-DC converter connected in sequence; the input end of the second charger is connected to the output end of the first DC-DC converter, and the output end of the third DC-DC converter is connected to the input end of the energy management module.

7. The hybrid power device according to claim 4, characterized in that: The fuel gas flow channel further includes a reaction medium flow channel area, an inlet and an outlet. The reaction medium flow channel area is arranged between the first surface and the second surface and is spaced apart from the first surface and the second surface respectively. The inlet and the outlet are respectively connected to the reaction medium flow channel area. The reaction medium flow channel area is arranged correspondingly to the air permeable through hole area, and the through holes of the air permeable through hole area are connected to the reaction medium flow channel area.

8. The hybrid power device according to claim 1, characterized in that: The sensor further includes a power detector, which is used to be connected to the electrical appliance to obtain the required power of the electrical appliance.

9. The hybrid power device according to any one of claims 1 to 8, characterized in that: Also includes a water tank, a first evaporator, a second evaporator and a condenser; The water tank is connected to the first evaporator, the fuel tank is connected to the second evaporator, the first evaporator and the second evaporator are connected to the heat exchanger respectively, the condenser is connected to the burner and the water tank respectively; the battery module is connected to the first evaporator and the second evaporator respectively.

10. An aircraft, characterized in that: Comprising a hybrid power device as claimed in any one of claims 1 to 9.

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