Thermophotovoltaic Brayton cycle power generation system for aircraft and control method

Abstract

The invention discloses a thermal photovoltaic Brayton cycle power generation system for an aircraft and a control method. The aircraft comprises a combustion chamber and a cooling channel, the system comprises a fuel assembly, the fuel assembly comprises a fuel storage tank and a first diverter valve in pipeline connection with the fuel storage tank, an outlet pipeline of the first diverter valve is connected with a cooling pipeline, and an outlet pipeline of the cooling pipeline is connected to the combustion chamber; the thermophotovoltaic power generation assembly is arranged outside the cooling channel; the cooling pipeline is arranged in the cooling channel, and fuel in the cooling pipeline is used for cooling the cooling channel and the photovoltaic power generation assembly; and the Brayton cycle power generation assembly comprises a cooler, and the cooling pipeline is connected with a first inlet pipeline of the cooler. On the basis of Brayton cycle power generation, a thermal photovoltaic power generation system is coupled, so that the generating capacity can be increased while cooling of a cooling channel is ensured, and the thermoelectric conversion efficiency of the system is improved.

Description

Technical Field

[0001] The present application belongs to the technical field of aircraft, and in particular, relates to a thermal photovoltaic Brayton cycle power generation system and a control method for aircraft. Background Art

[0002] Hypersonic vehicle is a new type of aircraft used for hypersonic flight. It can be used in many fields. It has received great attention from researchers at home and abroad and represents an important development direction in the field of future aircraft.

[0003] As the flight Mach number increases, the fuel supply system, radar navigation system and environmental control system of hypersonic aircraft need to consume a lot of electrical energy, so the power demand of hypersonic aircraft is also increasing. The traditional airborne power generation method currently used by hypersonic aircraft is limited by flight conditions.

[0004] As the flight Mach number increases, the demand for thermal protection and power consumption increases. There is an urgent need for a new thermoelectric conversion system to meet the thermal protection and power consumption requirements of hypersonic aircraft at higher flight Mach numbers. Summary of the invention

[0005] The embodiment of the present application provides a thermal photovoltaic Brayton cycle power generation system and control method for an aircraft, which can couple a thermal photovoltaic power generation system based on Brayton cycle power generation to increase power generation and improve the system's thermoelectric conversion efficiency while ensuring cooling of the cooling channel.

[0006] In one aspect, an embodiment of the present application provides a thermal photovoltaic Brayton cycle power generation system for an aircraft, wherein the aircraft includes a combustion chamber and a cooling channel, and the system includes:

[0007] A fuel assembly, the fuel assembly comprising a fuel storage tank and a first diverter valve connected to a pipeline of the fuel storage tank, an outlet pipeline of the first diverter valve is connected to a cooling pipeline, and an outlet pipeline of the cooling pipeline is connected to the combustion chamber, wherein the fuel storage tank is used to store fuel;

[0008] A thermophotovoltaic power generation component, which is arranged outside the cooling channel and is used to absorb heat energy generated by the combustion of fuel in the combustion chamber and convert the heat energy generated by the combustion chamber into electrical energy;

[0009] The cooling pipeline is arranged in the cooling channel, and the fuel in the cooling pipeline is used to cool the cooling channel;

[0010] A Brayton cycle power generation component, the Brayton cycle power generation component includes a cooler, the cooling pipeline is connected to the first inlet pipeline of the cooler, the fuel in the cooling pipeline is used to cool the circulating working fluid in the cooler, and the Brayton cycle power generation component is used for thermoelectric conversion.

[0011] Optionally, the thermophotovoltaic power generation assembly comprises:

[0012] a radiator, the radiator being installed in the cooling passage and close to the combustion chamber;

[0013] A filter, the filter being mounted on a side of the radiator away from the combustion chamber;

[0014] A photovoltaic power generation panel is installed on a side of the filter away from the combustion chamber, and an output end of the photovoltaic power generation panel is connected to an electric energy output end, and the electric energy output end is used to connect to a power source of the aircraft.

[0015] Optionally, the radiator is made of silicon carbide.

[0016] Optionally, the thermophotovoltaic power generation assembly further comprises:

[0017] An energy storage component, wherein the input end of the energy storage component is connected to the electric energy output end, and the energy storage component is used to store the electric energy generated by the thermophotovoltaic power generation assembly.

[0018] Optionally, the cooling pipeline includes a first pipeline, an inlet of the first pipeline is connected to a first outlet pipeline of the first diverter valve, and an outlet of the first pipeline is connected to the combustion chamber pipeline;

[0019] The fuel flowing in the first pipeline is used to cool the Brayton cycle power generation component.

[0020] Optionally, the fuel assembly further comprises:

[0021] a first booster pump, wherein an input end of the first booster pump is connected to the fuel storage tank, and an output end of the first booster pump is connected to the first diverter valve;

[0022] The first booster pump is used to increase a first flow rate of the fuel in the cooling pipeline.

[0023] Optionally, the thermal photovoltaic Brayton cycle power generation system for an aircraft further comprises:

[0024] a controller electrically connected to the Layton cycle power generation assembly and the fuel assembly;

[0025] The Brayton cycle power generation assembly comprises:

[0026] A circulating working fluid storage tank, wherein the circulating working fluid storage tank is used to store the circulating working fluid;

[0027] a second diverter valve, wherein a first inlet of the second diverter valve is connected to a pipeline of the circulating working fluid storage tank;

[0028] A compressor, wherein the outlet of the second diverter valve is connected to the inlet pipeline of the compressor;

[0029] a second pipeline, the second pipeline being arranged in the cooling channel, the inlet of the second pipeline being connected to the outlet of the compressor, and the second pipeline being used to cool the thermophotovoltaic power generation assembly and the cooling channel;

[0030] a turbine, wherein the inlet of the turbine is connected to the outlet pipeline of the second pipeline, the outlet of the turbine is connected to the second inlet of the cooler, and the second outlet of the cooler is connected to the second inlet of the second diverter valve;

[0031] The compressor and the second diverter valve are both electrically connected to the controller;

[0032] The controller is used to control the opening of the second diverter valve to adjust the flow rate of the circulating medium in the second pipeline so that the circulating medium cools the wall of the thermophotovoltaic power generation assembly and the cooling channel.

[0033] Optionally, the cooling pipeline also includes a third pipeline, the inlet of the third pipeline is connected to the second outlet pipeline of the first diverter valve, the outlet of the third pipeline is connected to the combustion chamber pipeline, and the third pipeline is arranged in the cooling channel.

[0034] Optionally, the photovoltaic power generation panel is arranged between the inlet and the outlet of the third pipeline.

[0035] Optionally, a flow meter is provided between the second diverter valve and the compressor, and the flow meter is electrically connected to the controller;

[0036] A motor is arranged between the turbine and the compressor, and the motor is electrically connected to the compressor, the turbine and the controller respectively;

[0037] The flow meter is used to detect a second flow rate of the circulating working medium in the second pipeline and transmit the second flow rate to the controller;

[0038] The controller is used to control the motor to start when the second flow rate is lower than a preset flow rate threshold, so as to increase the flow rate of the circulating working medium in the second pipeline.

[0039] On the other hand, an embodiment of the present application provides a control method for a thermophotovoltaic Brayton cycle power generation system for an aircraft, which is applied to the thermophotovoltaic Brayton cycle power generation system for an aircraft according to the first aspect, and the method includes:

[0040] Acquiring a first temperature of the cooling channel and a second temperature of the thermophotovoltaic power generation assembly;

[0041] When the fuel is burned in the combustion chamber, the opening of the first diverter valve is controlled based on the first temperature to control the flow rate of the fuel in the cooling pipeline, so that the fuel in the cooling pipeline cools the thermal photovoltaic power generation component and the cooling channel;

[0042] The opening of the second diverter valve is controlled based on the second temperature so that the circulating working fluid flows into the second pipeline to cool the thermophotovoltaic power generation assembly and the cooling channel.

[0043] Optionally, when the fuel is burned in the combustion chamber, the opening of the first diverter valve is controlled based on the first temperature to control the flow rate of the fuel in the cooling pipeline, so that the fuel in the cooling pipeline cools the thermal photovoltaic power generation component and the cooling channel, including:

[0044] When the first temperature is greater than a first preset temperature threshold and / or the second temperature is greater than a second preset temperature threshold, the opening of the first diverter valve is increased to increase the flow rate of the fuel into the cooling channel so that the fuel cools the cooling channel and the thermal photovoltaic power generation component.

[0045] Optionally, when the fuel is burned in the combustion chamber, the opening of the second diverter valve is controlled based on the second temperature so that the circulating working medium flows into the second pipeline to cool the thermophotovoltaic power generation assembly and the cooling channel, including:

[0046] Obtaining the flight speed of the aircraft;

[0047] When the flight speed is greater than the first preset flight threshold, increasing the opening of the second diverter valve to allow the circulating working fluid in the circulating working fluid storage tank to flow into the second pipeline;

[0048] The motor is controlled to start to increase the flow rate of the circulating medium in the second pipeline, so that the circulating medium cools the cooling channel and the thermal photovoltaic power generation assembly.

[0049] In another aspect, an embodiment of the present application provides a controller, the controller comprising: a processor and a memory storing computer program instructions;

[0050] When the processor executes the computer program instructions, the control method for the thermal photovoltaic Brayton cycle power generation system for an aircraft as described in the first aspect is implemented.

[0051] On the other hand, an embodiment of the present application provides a computer storage medium having computer program instructions stored thereon, and when the computer program instructions are executed by a processor, the control method for a thermophotovoltaic Brayton cycle power generation system for an aircraft as described in the first aspect is implemented.

[0052] On the other hand, an embodiment of the present application provides a computer program product. When the instructions in the computer program product are executed by the processor of the controller, the controller executes the control method for the thermal photovoltaic Brayton cycle power generation system for an aircraft as described in the first aspect.

[0053] The thermo-photovoltaic Brayton cycle power generation system and control method for aircraft of the embodiment of the present application can, after starting the aircraft, allow the fuel in the fuel storage tank to enter the combustion chamber through the cooling pipeline and start to burn. During the process of fuel combustion in the combustion chamber, the thermo-photovoltaic power generation component absorbs the heat generated by the fuel combustion and converts the heat energy generated by the combustion chamber into electrical energy. At the same time, the Brayton cycle power generation component converts the heat energy generated by the combustion chamber into mechanical energy and then into electrical energy. The thermo-photovoltaic power generation component converts the heat energy into electrical energy, and the Brayton cycle power generation component converts the heat energy into mechanical energy and then into electrical energy, thereby increasing the power generation to increase the thermo-electric conversion efficiency and meet the power demand of the aircraft. In addition, during the process of fuel combustion, in order to keep the temperature of the aircraft stable, since the fuel is a low-temperature medium, the fuel can cool the thermo-photovoltaic power generation component, the Brayton cycle power generation component and the cooling channel during the process of fuel flowing in the cooling pipeline, so as to reduce the temperature of the Brayton cycle power generation component, the thermo-photovoltaic power generation component and the cooling channel caused by the high temperature during fuel combustion, thereby ensuring the temperature stability of the aircraft. BRIEF DESCRIPTION OF THE DRAWINGS

[0054] In order to more clearly illustrate the technical solution of the embodiments of the present application, the following is a brief introduction to the drawings required for use in the embodiments of the present application. For ordinary technicians in this field, other drawings can be obtained based on these drawings without any creative work.

[0055] Figure 1 is a schematic structural diagram of a thermophotovoltaic Brayton cycle power generation system for an aircraft provided by an embodiment of the present application;

[0056] Figure 2 is a schematic structural diagram of a thermophotovoltaic Brayton cycle power generation system for an aircraft provided by another embodiment of the present application;

[0057] Figure 3is a structural block diagram of a thermophotovoltaic Brayton cycle power generation system for an aircraft provided by one embodiment of the present application, provided by another embodiment of the present application;

[0058] Figure 4 It is a flow chart of a control method for a thermophotovoltaic Brayton cycle power generation system for an aircraft provided by an embodiment of the present application;

[0059] Figure 5 It is a structural diagram of a controller provided in yet another embodiment of the present application.

[0060] Description of reference numerals:

[0061] 1. Engine; 11. Engine inlet; 12. Combustion chamber; 13. Engine tail nozzle; 14. Cooling channel; 2. Fuel assembly; 21. Fuel storage tank; 22. First booster pump; 23. First diverter valve; 24. Cooling pipeline; 241. First pipeline; 242. Third pipeline; 3. Brayton cycle power generation assembly; 31. Cooler; 32. Circulating working fluid storage tank; 33. Second diverter valve; 34. Compressor; 35. Second pipeline; 36. Turbine; 37. Motor; 38. Flow meter; 39. Second booster pump; 4. Thermal photovoltaic power generation assembly; 41. Radiator; 42. Filter; 43. Photovoltaic power generation panel; 44. Energy storage component; 5. Controller; 6. First temperature sensor; 7. Second temperature sensor. DETAILED DESCRIPTION

[0062] The features and exemplary embodiments of various aspects of the present application will be described in detail below. In order to make the purpose, technical solutions and advantages of the present application clearer, the present application will be further described in detail below in conjunction with the accompanying drawings and specific embodiments. It should be understood that the specific embodiments described herein are only intended to explain the present application, rather than to limit the present application. For those skilled in the art, the present application can be implemented without the need for some of these specific details. The following description of the embodiments is only to provide a better understanding of the present application by illustrating the examples of the present application.

[0063] It should be noted that, in this article, relational terms such as first and second, etc. are only used to distinguish one entity or operation from another entity or operation, and do not necessarily require or imply any such actual relationship or order between these entities or operations. Moreover, the terms "include", "comprise" or any other variants thereof are intended to cover non-exclusive inclusion, so that a process, method, article or device including a series of elements includes not only those elements, but also other elements not explicitly listed, or also includes elements inherent to such process, method, article or device. In the absence of further restrictions, the elements defined by the statement "include..." do not exclude the presence of other identical elements in the process, method, article or device including the elements.

[0064] In order to solve the problems of the prior art, the embodiment of the present application provides a thermal photovoltaic Brayton cycle power generation system and control method for an aircraft. After the aircraft is started, the fuel in the fuel storage tank enters the combustion chamber through the cooling pipeline and begins to burn. During the combustion of the fuel in the combustion chamber, the thermal photovoltaic power generation component absorbs the heat generated by the fuel combustion and converts the heat energy generated in the combustion chamber into electrical energy. At the same time, the Brayton cycle power generation component converts the heat energy into mechanical energy and then into electrical energy. The thermal energy is converted into electrical energy by the thermal photovoltaic power generation component, and the Brayton cycle power generation component converts the heat energy into mechanical energy and then into electrical energy. The power generation is increased to increase the thermoelectric conversion efficiency and meet the power demand of the aircraft. In addition, during the combustion of the fuel, in order to keep the temperature of the aircraft stable, since the fuel is a low-temperature medium, the fuel can cool the thermal photovoltaic power generation component, the Brayton cycle power generation component and the cooling channel during the flow of the cooling pipeline, so as to reduce the temperature of the Brayton cycle power generation component, the thermal photovoltaic power generation component and the cooling channel caused by the high temperature during the combustion of the fuel, thereby ensuring the temperature stability of the aircraft.

[0065] The following first introduces the thermophotovoltaic Brayton cycle power generation assembly for aircraft provided in the embodiments of the present application.

[0066] Figure 1 A schematic structural diagram of a thermophotovoltaic Brayton cycle power generation system for an aircraft provided by an embodiment of the present application is shown.

[0067] In some embodiments, the aircraft may include an engine 1 , which may include a combustion chamber 12 , an engine inlet 11 , and an engine tail nozzle 13 , wherein the combustion chamber 12 , the engine inlet 11 , and the engine tail nozzle 13 are all connected, and fuel is burned in the combustion chamber 12 .

[0068] As an example, the type of engine 1 may be a ramjet engine 1 .

[0069] In some embodiments, the aircraft may further include a cooling passage 14 , which is disposed inside the aircraft at a wall surface of the combustion chamber 12 .

[0070] like Figure 1 As shown, a thermal photovoltaic Brayton cycle power generation system for an aircraft may include:

[0071] The fuel assembly 2 may include a fuel storage tank 21 and a first diverter valve 23 connected to the fuel storage tank 21 by a pipeline, the outlet pipeline of the first diverter valve 23 is connected to a cooling pipeline 24, and the outlet pipeline of the cooling pipeline 24 is connected to the combustion chamber 12, wherein the fuel storage tank 21 is used to store fuel;

[0072] Thermophotovoltaic power generation assembly 4, the thermophotovoltaic power generation assembly 4 is arranged outside the cooling channel 14, and the thermophotovoltaic power generation assembly 4 is used to absorb the heat energy generated by the combustion of the fuel in the combustion chamber 12, and convert the heat energy generated by the combustion chamber 12 into electrical energy;

[0073] The cooling pipeline 24 is disposed in the cooling channel 14, and the fuel in the cooling pipeline 24 is used to cool the cooling channel 14;

[0074] The Brayton cycle power generation component 3 includes a cooler 31, a cooling pipeline 24 is connected to a first inlet pipeline of the cooler 31, the fuel in the cooling pipeline 24 is used to cool the circulating working fluid in the cooler 31, and the Brayton cycle power generation component 3 is used for thermoelectric conversion.

[0075] In some embodiments, during the power generation process of the thermal photovoltaic power generation component 4, the high-temperature combustion gas generated by the combustion of fuel in the combustion chamber 12 can be used as the hot end to facilitate the thermal photovoltaic power generation component 4 to generate electricity, and then the fuel in the cooling channel 14 is used as the cold end to cool the thermal photovoltaic power generation component 4 to keep the temperature of the thermal photovoltaic power generation component 4 stable, so as to achieve thermal protection for the thermal photovoltaic power generation component 4.

[0076] In some embodiments, during the power generation process of the Brayton cycle power generation component 3 , the low-temperature fuel in the cooling channel 14 can also cool the Brayton cycle power generation component 3 to achieve thermal protection for the Brayton cycle power generation component 3 .

[0077] In some embodiments, after starting the aircraft, the fuel in the fuel storage tank 21 enters the combustion chamber 12 through the cooling pipeline 24 and begins to burn. During the combustion of the fuel in the combustion chamber 12, the thermophotovoltaic power generation component 4 absorbs the heat generated by the fuel combustion and converts the heat energy generated by the combustion chamber 12 into electrical energy. At the same time, the Brayton cycle power generation component 3 converts the heat energy into mechanical energy and then into electrical energy. The heat energy is converted into electrical energy by the thermophotovoltaic power generation component 4 and the Brayton cycle power generation component 3 converts the heat energy into mechanical energy and then into electrical energy, so as to increase the fuel-electricity conversion rate and increase the power generation to meet the power demand of the aircraft. In addition, during the combustion of the fuel, in order to keep the temperature of the aircraft stable, since the fuel is a low-temperature medium, the fuel can cool the thermophotovoltaic power generation component 4, the Brayton cycle power generation component 3 and the cooling channel 14 during the flow of the cooling pipeline 24, so as to reduce the temperature of the Brayton cycle power generation component 3, the thermophotovoltaic power generation component 4 and the cooling channel 14 caused by the high temperature during the combustion of the fuel, thereby ensuring the temperature stability of the aircraft.

[0078] Reference Figure 1 In some embodiments, the thermophotovoltaic power generation assembly 4 may include:

[0079] A radiator 41, which is installed outside the cooling channel 14 and close to the combustion chamber 12;

[0080] A filter 42, the filter 42 is mounted on a side of the radiator 41 away from the combustion chamber 12;

[0081] The photovoltaic power generation panel 43 is installed on the side of the filter 42 away from the burner 12. The output end of the photovoltaic power generation panel 43 is connected to the power output end, and the power output end is used to connect to the power supply of the aircraft.

[0082] In this embodiment, the radiator 41 can be a high-temperature thermal radiator 41, that is, the high-temperature thermal radiator 41 can emit photons to the photovoltaic panel 43 in the form of infrared radiation. The photovoltaic panel 43 absorbs photons through the photovoltaic effect to generate electricity, and transmits the electric energy generated by the photovoltaic panel 43 to the aircraft through the power output end.

[0083] In this embodiment, during the power generation process of the thermal photovoltaic power generation component 4, first in the combustion chamber 12, the fuel begins to burn and produces high-temperature combustion gas, and then the high-temperature combustion gas heats the radiator 41. At this time, the radiator 41 begins to heat up and then emits photons in the form of infrared radiation through the filter 42 to the photovoltaic power generation panel 43, and the photovoltaic power generation panel 43 generates electricity through the photovoltaic effect.

[0084] It is worth noting that in this process, since the fuel in the cooling channel 14 is a low-temperature fuel, the fuel can cool down the photovoltaic panel 43 when flowing through the cooling channel 14 to maintain the temperature of the photovoltaic panel 43 stable.

[0085] In other embodiments, coupling the thermal photovoltaic power generation component 4 to the Brayton cycle power generation component 3 for supplementary power generation can improve the thermoelectric conversion efficiency of the power generation system and increase the power generation to ensure the power demand of the aircraft.

[0086] In some other embodiments, the radiator 41 may be made of silicon carbide.

[0087] In this embodiment, silicon carbide material is used as the wall of the combustion chamber 12 and / or the radiator 41, which has better temperature resistance and can ensure the operation of the aircraft under higher operating conditions. At the same time, since silicon carbide material is lighter than other materials, it can reduce the weight of the aircraft and ensure the safe operation of the aircraft.

[0088] In some embodiments, the thermophotovoltaic power generation assembly 4 may further include an energy storage component 44 , the input end of the energy storage component 44 is connected to the electric energy output end, and the energy storage component 44 is used to store the electric energy generated by the thermophotovoltaic power generation assembly 4 .

[0089] In this embodiment, when the electric energy generated by the photovoltaic panel 43 is large, the excess electric energy generated by the photovoltaic panel 43 can be transmitted to the energy storage component 44 through the electric energy output terminal, and the energy storage component 44 stores the excess electric energy.

[0090] As an example, the energy storage component 44 may be an energy storage battery.

[0091] Reference Figure 1 , Figure 2 and Figure 3 In some other embodiments, the cooling pipeline 24 may include a first pipeline 241, the inlet of the first pipeline 241 is connected to the first outlet pipeline of the first diverter valve 23, the outlet of the first pipeline 241 is connected to the pipeline of the combustion chamber 12, and the fuel flowing in the first pipeline 241 is used to cool the Brayton cycle power generation component 3.

[0092] In this embodiment, in the process of controlling the fuel to enter the combustion chamber 12, the fuel enters the combustion chamber 12 through the fuel storage tank 21, the first diverter valve 23 and the first pipeline 241 in sequence. The fuel can cool the Brayton cycle power generation component 3 while flowing in the first pipeline 241. In the process of the fuel cooling the cooling channel 14, since the thermophotovoltaic power generation component 4 is arranged in the cooling channel, the thermophotovoltaic power generation component 4 can be indirectly cooled.

[0093] In some other embodiments, in order to increase the first flow rate of the fuel in the cooling pipeline 24, the fuel assembly 2 may further include:

[0094] A first booster pump 22, wherein an input end of the first booster pump 22 is connected to the fuel storage tank 21, and an output end of the first booster pump 22 is connected to a first diverter valve 23;

[0095] The first boosting pump 22 is used to increase a first flow rate of the fuel in the cooling pipeline 24 .

[0096] In this embodiment, in order to increase the first flow rate of the fuel in the cooling pipeline 24 to quickly cool down the Brayton cycle power generation component 3 and the cooling channel 14, the fuel can be pressurized by the first booster pump 22 to increase the pressure of the fuel, thereby increasing the first flow rate of the fuel in the cooling pipeline 24, thereby achieving cooling of the Brayton cycle power generation component 3 and the cooling channel 14.

[0097] Reference Figure 2 In some other embodiments, the thermal photovoltaic Brayton cycle power generation system for an aircraft may further include a controller 5 , which is electrically connected to the Brayton cycle power generation assembly 3 and the fuel assembly 2 .

[0098] Specifically, the controller 5 is electrically connected to the first boosting pump 22 ; that is, the controller 5 can control the start-up of the first boosting pump 22 and the output speed of the first boosting pump 22 to control the flow rate of the fuel in the cooling channel 14 .

[0099] Reference Figure 1 and Figure 2 In this embodiment, the Brayton cycle power generation assembly 3 includes:

[0100] A circulating working fluid storage tank 32, the circulating working fluid storage tank 32 is used to store the circulating working fluid;

[0101] A second diverter valve 33, wherein a first inlet of the second diverter valve 33 is connected to a pipeline of a circulating working fluid storage tank 32;

[0102] The compressor 34, the outlet of the second diverter valve 33 is connected to the inlet pipeline of the compressor 34;

[0103] A second pipeline 35, the second pipeline 35 is arranged in the cooling channel 14, the inlet of the second pipeline 35 is connected to the outlet of the compressor 34, and the second pipeline 35 is used to cool the thermophotovoltaic power generation assembly 4 and the wall surface of the cooling channel 14;

[0104] a turbine 36, wherein the inlet of the turbine 36 is connected to the outlet pipeline of the second pipeline 35, the outlet of the turbine 36 is connected to the second inlet of the cooler 31, and the second outlet of the cooler 31 is connected to the second inlet of the second diverter valve 33;

[0105] The compressor 34 and the second diverter valve 33 are both electrically connected to the controller 5;

[0106] The controller 5 is used to control the opening of the second diverter valve 33 to adjust the flow rate of the circulating medium in the second pipeline 35 so that the circulating medium cools the wall of the thermophotovoltaic power generation assembly 4 and the cooling channel 14 .

[0107] In this embodiment, when the Brayton cycle power generation component 3 is generating electricity, the circulating working fluid in the circulating working fluid storage tank 32 is compressed by the compressor 34, increasing the pressure of the circulating working fluid to increase the second flow rate of the circulating working fluid. After that, the circulating working fluid enters the second pipeline 35 through the second diverter valve 33, enters the turbine 36 from the second pipeline 35, and enters the cooler 31 after coming out of the turbine 36, and then flows back to the second diverter valve 33 from the cooler 31 to form a closed loop.

[0108] When the circulating working fluid enters the turbine 36, the circulating working fluid starts to generate electricity.

[0109] When the circulating working fluid enters the cooling channel 14, the circulating working fluid can be used as a cold source for the low-temperature section of the combustion chamber 12, and the fuel can be used as a cold source for the high-temperature section of the combustion chamber 12. The cooling channel 14 is cooled in different areas, and then the combustion chamber 12 is cooled in different areas through the cooling channel.

[0110] It is worth noting that the low-temperature section of the combustion chamber 12 can be a section far away from the fuel entering the combustion chamber 12, that is, a section close to the engine inlet 11, and the high-temperature section of the combustion chamber 12 can be a section close to the fuel entering the combustion chamber 12, that is, a section close to the engine tail nozzle 13.

[0111] In this embodiment, the thermophotovoltaic power generation component 4 is arranged in the low-temperature section of the cooling channel close to the combustion chamber 12, that is, the circulating working fluid in the second pipeline 35 cools the thermophotovoltaic power generation component 4 and the cooling channel at the corresponding position, and the fuel in the cooling pipeline 24 cools the cooling channel 14.

[0112] In this embodiment, the controller 5 can control the opening of the second diverter valve 33 to adjust the flow of the circulating working fluid in the second pipeline 35 to ensure that there is enough circulating working fluid to cool the thermophotovoltaic power generation component 4 and maintain the temperature of the thermophotovoltaic power generation component 4 stable.

[0113] In some other embodiments, the second pipeline 35 is arranged on the side of the photovoltaic panel 43 away from the filter 42, that is, the second pipeline 35 is arranged inside the cooling channel 14, and the circulating working fluid in the second pipeline 35 can cool down both the photovoltaic panel 43 and the cooling channel 14.

[0114] Reference Figure 3In some other embodiments, in order to further improve the cooling effect and ensure the temperature stability of the thermal photovoltaic power generation component 4, the cooling pipeline 24 also includes a third pipeline 242, the inlet of the third pipeline 242 is connected to the second outlet pipeline of the first diverter valve 23, and the outlet of the third pipeline 242 is connected to the pipeline of the combustion chamber 12, and the third pipeline 242 is arranged in the cooling pipe.

[0115] In this embodiment, when cooling the thermal photovoltaic power generation component 4, the Brayton cycle power generation component 3 and the cooling channel 14, the low-temperature fuel flowing out of the fuel storage tank 21 is first divided into two parts by the first diverter valve 23. The fuel flowing into the first pipeline 241 flows into the cooler 31 to cool the circulating working fluid, the fuel flowing into the third pipeline 242 and the circulating working fluid flowing into the second pipeline 35 enter the cooling channel 14, and each flows through a part of the cooling channel 14 to cool the photovoltaic power generation panel 43. Finally, the two parts of the fuel are combined and enter the combustion chamber 12 for combustion, and the circulating working fluid flowing into the second pipeline 35 is heated and enters the turbine 36 to drive the blades in the turbine 36 to rotate and generate power.

[0116] In this embodiment, the photovoltaic panel 43 is disposed between the inlet and the outlet of the third pipeline 242 .

[0117] In this embodiment, the fuel in the third pipeline 242 can cool the photovoltaic panel 43 in the cooling channel 14. Since the photovoltaic panel 43 is arranged between the inlet and the outlet of the third pipeline 242, the fuel in the third pipeline 242 can cool the photovoltaic panel 43 as a whole, thereby ensuring the overall temperature stability of the photovoltaic panel 43.

[0118] In some other embodiments, in order to accurately control the Brayton cycle power generation assembly 3 , a flow meter 38 is provided between the second diverter valve 33 and the compressor 34 , and the flow meter 38 is electrically connected to the controller 5 .

[0119] In this embodiment, the second flow rate of the circulating working fluid is monitored by the flow meter 38, that is, the second flow rate of the circulating working fluid in the second pipeline 35 can be calculated by the flow meter 38. After the second flow rate is higher than the preset flow rate threshold or the flow reaches the set value, the controller 5 can close the filling of the second diverter valve 33. When the second flow rate is lower than the preset flow rate threshold or the flow does not reach the set value, the controller 5 can open the second diverter valve 33 to allow the circulating working fluid in the circulating working fluid storage tank 32 to enter the second pipeline 35.

[0120] In some other embodiments, in order to increase the second flow rate of the circulating medium in the second pipeline 35, a motor 37 is provided between the turbine 36 and the compressor 34, and the motor 37 is electrically connected to the compressor 34, the turbine 36 and the controller 5 respectively.

[0121] In this embodiment, when the second flow rate is lower than the preset flow rate threshold, the controller 5 can control the motor 37 to start, and then the motor 37 increases the rotation speed of the compressor 34 to increase the second flow rate of the circulating working medium in the second pipeline 35.

[0122] In some other embodiments, in order to increase the flow rate of the circulating working fluid in the second pipeline 35, a second boosting pump 39 is arranged between the circulating working fluid storage tank 32 and the second diverter valve 33, the input end of the second boosting pump 39 is connected to the pipeline of the circulating working fluid storage tank 32, the output end of the second boosting pump 39 is connected to the pipeline of the second diverter valve 33, and the second boosting pump 39 is electrically connected to the controller 5.

[0123] When the flow rate of the circulating medium in the second pipeline 35 needs to be increased, the controller 5 can control the second booster pump 39 to start, so as to increase the second flow rate of the circulating medium in the second pipeline 35 .

[0124] As an optional example, the electric energy of the motor 37 can be provided in part by the electric energy generated by the turbine 36, or by the electric energy generated by the thermophotovoltaic power generation assembly 4, or by the aircraft, which is not limited here.

[0125] In some other embodiments, in order to more accurately control the temperature of the power generation system, a first temperature sensor 6 is provided on the cooling channel 14, and a second temperature sensor 7 is provided on the photovoltaic panel 43, and both the first temperature sensor 6 and the second temperature sensor 7 are electrically connected to the controller 5.

[0126] When cooling the cooling channel 14 and the photovoltaic panel 43, the first temperature sensor 6 detects the temperature of the cooling channel 14 to obtain a first temperature, and the second temperature sensor 7 collects the temperature of the thermal photovoltaic power generation component 4 to obtain a second temperature. Then the controller 5 controls the opening of the first diverter valve 23 and the second diverter valve 33 according to the first temperature and the second temperature, respectively, so as to increase the flow rate of the fuel and the circulating working fluid to achieve the purpose of cooling the photovoltaic panel 43 and the cooling channel 14.

[0127] Specifically, the first temperature of the cooling channel 14 is detected by the first temperature sensor 6. When the first temperature exceeds the tolerance temperature of the wall material of the cooling channel 14, the opening of the first diverter valve 23 flowing into the cooling channel 14 is increased, and the flow rate of fuel flowing into the cooling channel 14 is increased to reduce the temperature.

[0128] As an example, the withstand temperature of the wall material of the cooling channel 14 may be 1100K.

[0129] In this embodiment, the second temperature of the photovoltaic panel 43 is detected by the second temperature sensor 7. When the second temperature exceeds the tolerance temperature of the photovoltaic panel 43, the controller 5 controls the opening of the first diverter valve 23 to increase, and increases the flow rate of the fuel in the third pipeline 242 to ensure that the photovoltaic panel 43 is within the normal temperature range; at the same time, the controller 5 can control the motor 37 to start, increase the opening of the second diverter valve 33, and increase the rotation speed of the compressor 34 through the motor 37 to increase the flow rate of the circulating working fluid in the second pipeline 35, and increase the flow rate of the circulating working fluid to ensure the cooling effect of the cooling channel 14.

[0130] As an example, the resistant temperature of the material of the photovoltaic panel 43 may be 500K.

[0131] Accordingly, the controller 5 can reduce the flow rate of the fuel flowing into the cooling channel 14 by controlling the opening of the first diverter valve 23 to decrease, so as to control the temperature change of the cooling channel 14 and the photovoltaic panel 43 .

[0132] Reference Figure 4 Based on the thermophotovoltaic Brayton cycle power generation system for an aircraft provided in the above embodiment, the present application embodiment further provides a control method for the thermophotovoltaic Brayton cycle power generation system for an aircraft, and the method may include:

[0133] S401, obtaining a first temperature of the cooling channel and a second temperature of the thermophotovoltaic power generation assembly;

[0134] S402, when the fuel is burned in the combustion chamber, controlling the opening of the first diverter valve based on the first temperature to control the flow rate of the fuel in the cooling pipeline, so that the fuel in the cooling pipeline cools the thermal photovoltaic power generation component and the cooling channel;

[0135] S403, controlling the opening of the second diverter valve based on the second temperature so that the circulating working fluid flows into the second pipeline to cool the thermophotovoltaic power generation assembly and the cooling channel.

[0136] In this embodiment, when the thermal photovoltaic power generation component and the Brayton cycle power generation component are generating electricity, in order to ensure the temperature stability of the thermal photovoltaic power generation component and the Brayton cycle power generation component and to achieve thermal protection, the first temperature of the cooling channel and the second temperature of the thermal photovoltaic power generation component can be obtained to control the opening of the first diverter valve and the second diverter valve, thereby achieving cooling of the cooling channel, the thermal photovoltaic power generation component and the Brayton cycle power generation component to ensure the stable operation of the thermal photovoltaic power generation component and the Brayton cycle power generation component.

[0137] Specifically, S402 may include:

[0138] When the first temperature is greater than the first preset temperature threshold and / or the second temperature is greater than the second preset temperature threshold, the opening of the first diverter valve is increased to increase the flow rate of fuel into the cooling channel, so that the fuel cools the cooling channel and the thermal photovoltaic power generation component.

[0139] In this embodiment, as an example, the first preset temperature threshold may be the tolerance temperature of the cooling channel wall material, which may be 1000K, and the second preset temperature threshold may be the tolerance temperature of the photovoltaic panel, which may be 500K.

[0140] When cooling, the opening of the first diverter valve can be determined by the first temperature and the first preset temperature threshold and the second temperature and the second preset temperature threshold to cool the cooling channel and thus maintain the temperature of the photovoltaic panel stable.

[0141] In some other embodiments, S403 may specifically include:

[0142] Get the flight speed of the aircraft;

[0143] When the flight speed is greater than the first preset flight threshold, increasing the opening of the second diverter valve to allow the circulating working fluid in the circulating working fluid storage tank to flow into the second pipeline;

[0144] The motor is controlled to start to increase the flow rate of the circulating medium in the second pipeline, so that the circulating medium cools the cooling channel and the thermal photovoltaic power generation component.

[0145] In this embodiment, when using the Brayton cycle power generation component for cooling, the opening of the second diverter valve can be adjusted according to the flight speed of the aircraft, that is, when the flight speed of the aircraft is greater than the first preset flight threshold, the fuel is accelerated in the combustion chamber, so the temperature of the cooling channel and the thermal photovoltaic power generation component rises rapidly, so it is necessary to increase the opening of the second diverter valve to increase the flow rate of the circulating working fluid, thereby ensuring the stability of the temperature of the cooling channel and the thermal photovoltaic power generation component, so as to achieve thermal protection, ensure the stable operation of the thermal photovoltaic power generation component, increase power generation, and thus improve the thermoelectric conversion efficiency of the system.

[0146] Figure 5 A schematic diagram of the hardware structure of the controller provided in an embodiment of the present application is shown.

[0147] The controller may include a processor 501 and a memory 502 storing computer program instructions.

[0148] Specifically, the processor 501 may include a central processing unit (CPU), or an application specific integrated circuit (ASIC), or may be configured to implement one or more integrated circuits of the embodiments of the present application.

[0149] The memory 502 may include a large capacity memory for data or instructions. By way of example and not limitation, the memory 502 may include a hard disk drive (HDD), a floppy disk drive, a flash memory, an optical disk, a magneto-optical disk, a magnetic tape, or a universal serial bus (USB) drive or a combination of two or more of these. In one example, the memory 502 may include a removable or non-removable (or fixed) medium, or the memory 502 is a non-volatile solid-state memory. The memory 502 may be inside or outside the integrated gateway disaster recovery device.

[0150] In one example, the memory 502 may be a read-only memory (ROM). In one example, the ROM may be a mask-programmed ROM, a programmable ROM (PROM), an erasable PROM (EPROM), an electrically erasable PROM (EEPROM), an electrically rewritable ROM (EAROM), or a flash memory, or a combination of two or more of these.

[0151] The memory 502 may include a read-only memory (ROM), a random access memory (RAM), a magnetic disk storage medium device, an optical storage medium device, a flash memory device, an electrical, optical or other physical / tangible memory storage device. Thus, typically, the memory includes one or more tangible (non-transitory) computer-readable storage media (e.g., a memory device) encoded with software including computer-executable instructions, and when the software is executed (e.g., by one or more processors), it is operable to perform the operations described with reference to the control method for a thermophotovoltaic Brayton cycle power generation system for an aircraft according to the second aspect of the present disclosure.

[0152] The processor 501 reads and executes the computer program instructions stored in the memory 502 to implement Figure 1 A control method for a thermophotovoltaic Brayton cycle power generation system for an aircraft in the illustrated embodiment.

[0153] In one example, the controller may further include a communication interface 503 and a bus 504. Figure 5As shown, the processor 501, the memory 502, and the communication interface 503 are connected via a bus 504 and communicate with each other.

[0154] The communication interface 503 is mainly used to implement communication between various modules, devices, units and / or equipment in the embodiments of the present application.

[0155] Bus 504 includes hardware, software or both, and the components of controller are coupled to each other. For example, but not limitation, bus may include accelerated graphics port (Accelerated Graphics Port, AGP) or other graphics bus, enhanced industry standard architecture (Extended Industry Standard Architecture, EISA) bus, front side bus (FrontSide Bus, FSB), Hyper Transport (Hyper Transport, HT) interconnection, industry standard architecture (Industry Standard Architecture, ISA) bus, infinite bandwidth interconnection, low pin count (LPC) bus, memory bus, micro channel architecture (MCA) bus, peripheral component interconnection (PCI) bus, PCI-Express (PCI-X) bus, serial advanced technology attachment (SATA) bus, video electronics standard association local (VLB) bus or other suitable bus or two or more of these combinations. In appropriate cases, bus 504 may include one or more buses. Although the present application embodiment describes and shows a specific bus, the application considers any suitable bus or interconnection.

[0156] The controller can execute the control method for the thermal photovoltaic Brayton cycle power generation system for aircraft in the embodiment of the present application, thereby realizing the combination Figure 4 A control method for a thermophotovoltaic Brayton cycle power generation system for an aircraft is described.

[0157] In addition, in combination with the control method for the thermophotovoltaic Brayton cycle power generation system for an aircraft in the above embodiments, the present application embodiment may provide a computer storage medium for implementation. The computer storage medium stores computer program instructions; when the computer program instructions are executed by the processor, any one of the control methods for the thermophotovoltaic Brayton cycle power generation system for an aircraft in the above embodiments is implemented.

[0158] In an optional embodiment, in combination with the control method for a thermophotovoltaic Brayton cycle power generation system for an aircraft in the above-mentioned embodiments, the embodiment of the present application may provide a computer program product for implementation, and the instructions in the computer program product are executed by a processor of a controller, so that the controller can implement any one of the control methods for a thermophotovoltaic Brayton cycle power generation system for an aircraft in the above-mentioned embodiments.

[0159] It should be clear that the present application is not limited to the specific configuration and processing described above and shown in the figures. For the sake of simplicity, a detailed description of the known method is omitted here. In the above embodiments, several specific steps are described and shown as examples. However, the method process of the present application is not limited to the specific steps described and shown, and those skilled in the art can make various changes, modifications and additions, or change the order between the steps after understanding the spirit of the present application.

[0160] The functional blocks shown in the above block diagram can be implemented as hardware, software, firmware or a combination thereof. When implemented in hardware, it can be, for example, an electronic circuit, an application specific integrated circuit (ASIC), appropriate firmware, a plug-in, a function card, etc. When implemented in software, the elements of the present application are programs or code segments that are used to perform the required tasks. The program or code segment can be stored in a machine-readable medium, or transmitted on a transmission medium or a communication link by a data signal carried in a carrier wave. "Machine-readable medium" can include any medium capable of storing or transmitting information. Examples of machine-readable media include electronic circuits, semiconductor memory devices, ROM, flash memory, erasable ROM (EROM), floppy disks, CD-ROMs, optical disks, hard disks, optical fiber media, radio frequency (RF) links, etc. The code segment can be downloaded via a computer network such as the Internet, an intranet, etc.

[0161] It should also be noted that the exemplary embodiments mentioned in this application describe some methods or systems based on a series of steps or devices. However, this application is not limited to the order of the above steps, that is, the steps can be performed in the order mentioned in the embodiment, or in a different order from the embodiment, or several steps can be performed simultaneously.

[0162] Aspects of the present disclosure are described above with reference to the flowchart and / or block diagram of the method, device (system) and computer program product according to the embodiment of the present disclosure. It should be understood that each box in the flowchart and / or block diagram and the combination of each box in the flowchart and / or block diagram can be implemented by computer program instructions. These computer program instructions can be provided to a processor of a general-purpose computer, a special-purpose computer, or other programmable data processing device to produce a machine so that these instructions executed by the processor of the computer or other programmable data processing device enable the implementation of the function / action specified in one or more boxes of the flowchart and / or block diagram. Such a processor can be, but is not limited to, a general-purpose processor, a special-purpose processor, a special application processor, or a field programmable logic circuit. It can also be understood that each box in the block diagram and / or flowchart and the combination of boxes in the block diagram and / or flowchart can also be implemented by dedicated hardware that performs a specified function or action, or can be implemented by a combination of dedicated hardware and computer instructions.

[0163] The above are only specific implementation methods of the present application. Those skilled in the art can clearly understand that for the convenience and simplicity of description, the specific working processes of the systems, modules and units described above can refer to the corresponding processes in the aforementioned method embodiments, and will not be repeated here. It should be understood that the protection scope of the present application is not limited to this. Any technician familiar with the technical field can easily think of various equivalent modifications or replacements within the technical scope disclosed in this application, and these modifications or replacements should be included in the protection scope of this application.

Claims

1. A thermophotovoltaic Brayton cycle power generation system for an aircraft, the aircraft comprising a combustion chamber (12), characterized in that: The aircraft further comprises a cooling channel (14), and the system comprises: A fuel assembly (2), the fuel assembly (2) comprising a fuel storage tank (21) and a first diverter valve (23) connected to the fuel storage tank (21) by a pipeline, the outlet pipeline of the first diverter valve (23) being connected to a cooling pipeline (24), the outlet pipeline of the cooling pipeline (24) being connected to the combustion chamber (12), wherein the fuel storage tank (21) is used to store fuel; a thermophotovoltaic power generation component (4), the thermophotovoltaic power generation component (4) being arranged outside the cooling channel (14), the thermophotovoltaic power generation component (4) being used to absorb heat energy generated by combustion of fuel in the combustion chamber (12), and convert the heat energy generated by the combustion chamber (12) into electrical energy; The cooling pipeline (24) is arranged in the cooling channel (14), and the fuel in the cooling pipeline (24) is used to cool the cooling channel (14); A Brayton cycle power generation assembly (3), the Brayton cycle power generation assembly (3) comprising a cooler (31), the cooling pipeline (24) being connected to a first inlet pipeline of the cooler (31), the fuel in the cooling pipeline (24) being used to cool the circulating working fluid in the cooler (31), and the Brayton cycle power generation assembly (3) being used to perform thermoelectric conversion.

2. The thermophotovoltaic Brayton cycle power generation system for aircraft according to claim 1, characterized in that: The thermophotovoltaic power generation assembly (4) comprises: a radiator (41), the radiator (41) being installed in the cooling channel (14) and close to the combustion chamber (12); a filter (42), the filter (42) being mounted on a side of the radiator (41) away from the combustion chamber (12); A photovoltaic power generation panel (43), wherein the photovoltaic power generation panel (43) is installed on a side of the filter (42) away from the combustion chamber (12), and an output end of the photovoltaic power generation panel (43) is connected to an electric energy output end, and the electric energy output end is used to connect to a power source of the aircraft.

3. The thermophotovoltaic Brayton cycle power generation system for aircraft according to claim 2, characterized in that: The radiator (41) is made of silicon carbide.

4. The thermophotovoltaic Brayton cycle power generation system for aircraft according to claim 2, characterized in that: The thermophotovoltaic power generation assembly (4) further comprises: An energy storage component (44), the input end of the energy storage component (44) being connected to the electric energy output end, and the energy storage component (44) being used to store the electric energy generated by the thermophotovoltaic power generation assembly (4).

5. The thermophotovoltaic Brayton cycle power generation system for aircraft according to any one of claims 2 to 4, characterized in that: The cooling pipeline (24) comprises a first pipeline (241), the inlet of the first pipeline (241) is connected to the first outlet pipeline of the first diverter valve (23), and the outlet of the first pipeline (241) is connected to the pipeline of the combustion chamber (12); The fuel flowing in the first pipeline (241) is used to cool the Brayton cycle power generation component (3).

6. The thermophotovoltaic Brayton cycle power generation system for aircraft according to claim 5, characterized in that: The fuel assembly (2) further comprises: A first boosting pump (22), wherein an input end of the first boosting pump (22) is connected to the fuel storage tank (21), and an output end of the first boosting pump (22) is connected to the first diverter valve (23); The first boosting pump (22) is used to increase a first flow rate of the fuel in the cooling pipeline (24).

7. The thermophotovoltaic Brayton cycle power generation system for aircraft according to any one of claims 2 to 4, characterized in that: The thermal photovoltaic Brayton cycle power generation system for an aircraft further comprises: A controller (5), the controller (5) being electrically connected to the Brayton cycle power generation assembly and the fuel assembly (2); The Brayton cycle power generation assembly (3) comprises: A circulating working fluid storage tank (32), wherein the circulating working fluid storage tank (32) is used to store the circulating working fluid; A second diverter valve (33), wherein a first inlet of the second diverter valve (33) is connected to a pipeline of the circulating working fluid storage tank (32); A compressor (34), wherein the outlet of the second diverter valve (33) is connected to an inlet pipeline of the compressor (34); a second pipeline (35), the second pipeline (35) being arranged in the cooling channel (14), the inlet of the second pipeline (35) being connected to the outlet of the compressor (34), and the second pipeline (35) being used to cool the wall surface of the thermophotovoltaic power generation assembly (4) and the cooling channel (14); a turbine (36), wherein the inlet of the turbine is connected to the outlet pipeline of the second pipeline (35), the outlet of the turbine (36) is connected to the second inlet of the cooler (31), and the second outlet of the cooler (31) is connected to the second inlet of the second diverter valve (33); The compressor (34) and the second diverter valve (33) are both electrically connected to the controller (5); The controller (5) is used to control the opening of the second diverter valve (33) to adjust the flow rate of the circulating medium in the second pipeline (35) so that the circulating medium cools the thermophotovoltaic power generation assembly (4) and the cooling channel (14).

8. The thermophotovoltaic Brayton cycle power generation system for aircraft according to claim 7, characterized in that: The cooling pipeline (24) further comprises a third pipeline (242), the inlet of the third pipeline being connected to the second outlet pipeline of the first diverter valve (23), the outlet of the third pipeline (242) being connected to the pipeline of the combustion chamber (12), and the third pipeline (242) being arranged in the cooling channel (14).

9. The thermophotovoltaic Brayton cycle power generation system for aircraft according to claim 8, characterized in that: The photovoltaic power generation panel (43) is arranged between the inlet and the outlet of the third pipeline (242).

10. The thermophotovoltaic Brayton cycle power generation system for aircraft according to claim 7, characterized in that: A flow meter (38) is provided between the second diverter valve (33) and the compressor (34), and the flow meter is electrically connected to the controller (5); A motor (37) is provided between the turbine (36) and the compressor (34), and the motor is electrically connected to the compressor (34), the turbine (36) and the controller (5) respectively; The flow meter (38) is used to detect a second flow rate of the circulating medium in the second pipeline (35) and transmit the second flow rate to the controller (5); The controller (5) is used to control the motor (37) to start when the second flow rate is lower than a preset flow rate threshold, so as to increase the flow rate of the circulating working medium in the second pipeline (35).

11. A control method for a thermophotovoltaic Brayton cycle power generation system for an aircraft, characterized in that: Applied to the thermophotovoltaic Brayton cycle power generation system for an aircraft as claimed in any one of claims 1 to 10, the method comprising: Acquiring a first temperature of the cooling channel and a second temperature of the thermophotovoltaic power generation assembly; When the fuel is burned in the combustion chamber, the opening of the first diverter valve is controlled based on the first temperature to control the flow rate of the fuel in the cooling pipeline, so that the fuel in the cooling pipeline cools the thermal photovoltaic power generation component and the cooling channel; The opening of the second diverter valve is controlled based on the second temperature so that the circulating working fluid flows into the second pipeline to cool the thermophotovoltaic power generation assembly and the cooling channel.

12. The method according to claim 11, characterized in that When the fuel is burned in the combustion chamber, the opening of the first diverter valve is controlled based on the first temperature to control the flow rate of the fuel in the cooling pipeline, so that the fuel in the cooling pipeline cools the thermal photovoltaic power generation component and the cooling channel, including: When the first temperature is greater than a first preset temperature threshold and / or the second temperature is greater than a second preset temperature threshold, the opening of the first diverter valve is increased to increase the flow rate of the fuel flowing into the cooling channel, so that the fuel cools the cooling channel and the thermal photovoltaic power generation component.

13. The method according to claim 11 or 12, characterized in that: When the fuel is burned in the combustion chamber, the opening of the second diverter valve is controlled based on the second temperature so that the circulating working medium flows into the second pipeline to cool the thermophotovoltaic power generation assembly and the cooling channel, including: Obtaining the flight speed of the aircraft; When the flight speed is greater than the first preset flight threshold, increasing the opening of the second diverter valve to allow the circulating working fluid in the circulating working fluid storage tank to flow into the second pipeline; The motor is controlled to start to increase the flow rate of the circulating medium in the second pipeline, so that the circulating medium cools the cooling channel and the thermal photovoltaic power generation assembly.

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