Superconducting hydrogen electric propulsion aircraft thermal management system and working method

Abstract

The invention provides a superconducting hydrogen electric propulsion aircraft thermal management system and a working method. Comprising a propulsion loop, a cooling loop and a cooling loop. The propulsion loop comprises an aero-engine, a superconducting generator, a superconducting power transmission and distribution device, a superconducting motor, a liquid hydrogen storage tank, a precooler, a first valve and a second valve. The cooling loop comprises a liquid hydrogen-secondary refrigerant heat exchanger, a first heating element, a second heating element, a third heating element, a third valve and a fourth valve. The cold taking loop comprises a heat storage device, a ram air heat exchanger, a compressor and a fifth valve. According to the refrigeration loop, various modes such as ram air refrigeration, skin cooling, phase change heat storage, consumable working medium refrigeration and liquid hydrogen cooling are comprehensively applied, and the problems of cooperative heat dissipation of airborne equipment and insufficient cold sources of an airborne environment are solved. According to the invention, the energy cooperative utilization of each device in the thermal management system is effectively improved, and meanwhile, the design concept of comprehensive thermal management of airplanes is better conformed.

Description

Technical Field

[0001] The present invention relates to the technical field of aircraft environment control systems, and in particular to a superconducting hydrogen-electric propulsion aircraft thermal management system and a working method thereof. Background Art

[0002] Superconducting hydrogen-electric propulsion technology is one of the most promising research directions for achieving the power requirements of high-power avionics propulsion aircraft. Hydrogen-electric hybrid aircraft will introduce a large number of multi-electric devices, which will lead to insufficient heat sink in climb conditions and redundant heat sink in cruise conditions under the constraints of the flight envelope and overall design, making it impossible for traditional aircraft thermal management systems to meet the heat dissipation requirements.

[0003] At the same time, the use of superconducting hydrogen-electric technology requires that the superconducting engine be kept in a low-temperature environment for a long time, which requires more heat sinks, resulting in an increasingly scarce cooling capacity for the existing propulsion system. In addition, the traditional aircraft thermal management system is mainly based on aircraft environmental control, and the heat of each system is isolated without unified management and scheduling, resulting in a lot of waste. Summary of the invention

[0004] The purpose of the present invention is to solve the problems of lack of comprehensive management and increasingly scarce cooling capacity of the thermal management system of a superconducting hydrogen-electric propulsion system, and to provide a superconducting hydrogen-electric propulsion aircraft thermal management system and a working method.

[0005] The present invention adopts the following technical solution:

[0006] A superconducting hydrogen-electric propulsion aircraft thermal management system, comprising:

[0007] Propulsion circuit, cooling circuit and cooling circuit. The propulsion circuit includes: aircraft engine, superconducting generator, superconducting power transmission and distribution device, superconducting motor, tail nozzle propeller fan, liquid hydrogen storage tank, precooler, first valve and second valve;

[0008] The cooling circuit includes a liquid hydrogen-coolant heat exchanger, a first heating element, a second heating element, a third heating element, a third valve and a fourth valve;

[0009] The cooling circuit comprises: a heat storage device, a ram air heat exchanger, a compressor and a fifth valve.

[0010] The superconducting generator, superconducting power transmission and distribution device and superconducting engine together constitute a superconducting engine, the aircraft engine is connected to the superconducting engine, and the micro-nozzle propeller fan is connected to the superconducting engine. The outlet of the liquid hydrogen storage tank is connected to the second inlet of the superconducting engine through the first pipeline; the outlet of the superconducting engine is connected to the first inlet of the liquid hydrogen-coolant heat exchanger through the second pipeline. The first outlet of the liquid hydrogen-coolant heat exchanger is connected to the first inlet of the precooler through the third pipeline, and the outlet of the superconducting engine is connected to the third pipeline through the fourth pipeline; the first valve is installed on the fourth pipeline, and the second valve is installed on the second pipeline; the first outlet of the precooler is connected to the first inlet of the aircraft engine through the fifth pipeline; the second outlet of the precooler is connected to the second inlet of the aircraft engine through the sixth pipeline.

[0011] The first heating element, the second heating element and the third heating element together constitute an airborne heating element system. The second outlet of the liquid hydrogen-coolant heat exchanger is connected to the inlet of the airborne heating element system through the seventh pipeline, the outlet of the airborne heating element system is connected to the first inlet of the heat storage through the eighth pipeline, the first outlet of the heat storage is connected to the second inlet of the liquid hydrogen-coolant heat exchanger through the ninth pipeline, the outlet of the airborne heating element system is connected to the ninth pipeline through the tenth pipeline, the third valve is installed on the eighth pipeline, and the fourth valve is installed on the tenth pipeline.

[0012] The second outlet of the heat storage device is connected to the inlet of the compressor through an eleventh pipe, the outlet of the compressor is connected to the first inlet of the ram air heat exchanger through a twelfth pipe, the first outlet of the ram air heat exchanger is connected to the second inlet of the heat storage device through a thirteenth pipe, and the fifth valve is installed on the thirteenth pipe.

[0013] Optionally, the cooling circuit further includes: a coolant storage tank, wherein the coolant storage tank is disposed on a seventh pipeline between the onboard heating element system and the liquid hydrogen-coolant heat exchanger.

[0014] Optionally, the cooling circuit also includes: a skin heat exchanger, wherein the skin heat exchanger is arranged on a fourteenth pipe between a first connection point and the liquid hydrogen-refrigerant heat exchanger, and the first connection point is a connection point between the ninth pipe and the tenth pipe.

[0015] Optionally, the cooling circuit further includes: a consumable working fluid heat exchanger, wherein the consumable working fluid heat exchanger is arranged on the fourteenth pipeline between the skin heat exchanger and the liquid hydrogen-refrigerant heat exchanger.

[0016] Optionally, the heating element is composed of a heating element unit and a heating element heat exchanger unit, the heating element unit corresponds to the heating element heat exchanger unit one-to-one, and multiple heating elements are connected in parallel. The airborne heating element system includes but is not limited to high-power, high-heat-flow airborne equipment such as motors, lasers and radars. The inlet of the heating element heat exchanger unit is connected to the second outlet of the liquid hydrogen-refrigerant heat exchanger through the seventh pipeline, and the outlet of the heating element heat exchanger unit is connected to the first inlet of the heat storage through the fourteenth pipeline.

[0017] Optionally, the cooling circuit further includes: a refrigerant pump, and a refrigerant pump is installed on a seventh pipeline connecting the refrigerant storage tank and the onboard heating element system.

[0018] Optionally, the cooling circuit further includes: a gas-liquid separator, which is arranged on an eleventh pipeline between the heat storage device and the compressor.

[0019] On the other hand, the present invention provides a method for operating a thermal management system of a superconducting hydrogen-electric propulsion aircraft.

[0020] S1. When the onboard equipment is in low heat load working state, including:

[0021] The first valve is opened and the second valve is closed, so that the propulsion circuit is disconnected from the cooling circuit, and the cooling circuit does not exchange heat with the liquid hydrogen in the propulsion circuit. At the same time, the third valve is closed, the fourth valve is opened, and the fifth valve is closed, so that the cooling circuit is disconnected from the cooling circuit, and the cooling circuit does not exchange heat with the refrigerant in the cooling circuit. The consumable working fluid storage tank is closed, and the onboard heating element system transfers heat to the coolant in the cooling circuit through the heating element heat exchanger unit, and exchanges heat with the ambient air intake outside the cabin in the skin heat exchanger through the cooling circuit coolant pump.

[0022] S2. When the onboard equipment is in a low heat load working state, including:

[0023] The first valve is opened and the second valve is closed, so that the propulsion circuit is disconnected from the cooling circuit, and the cooling circuit does not exchange heat with the liquid hydrogen in the propulsion circuit. The third valve is opened and the fourth valve is closed, closing the consumable working tank. The onboard heating element system transfers heat to the coolant in the cooling circuit through the heating element heat exchanger unit. The cooling circuit coolant pump first obtains heat from the refrigerant in the heat storage tank through the solid-liquid phase change of the phase change material, and then exchanges heat with the ambient air outside the cabin in the skin heat exchanger. At the same time, the fifth valve is opened, and the refrigerant in the cold circuit stores the cold in the phase change material through the gas-liquid phase change in the heat storage tank.

[0024] S3. When the onboard equipment is in a high heat load working state, including:

[0025] The third valve is opened and the fourth valve is closed. The onboard heating element system transfers heat to the coolant in the cooling circuit through the heating element heat exchanger unit. The phase change material in the heat storage device first obtains heat from the refrigerant through a solid-liquid phase change through the cooling circuit coolant pump, and then exchanges heat with the ambient air outside the cabin in the skin heat exchanger. The fifth valve is opened, and the refrigerant in the cold extraction circuit stores the cold in the phase change material through a gas-liquid phase change in the heat storage device. At the same time, choose whether to enable the consumable working fluid heat exchanger according to actual needs, and use consumable work to provide additional cold. Finally, the first valve is closed and the second valve is opened, so that the propulsion circuit and the cooling circuit can achieve heat exchange through the liquid hydrogen-coolant heat exchanger.

[0026] Beneficial effects of the present invention:

[0027] The present invention firstly utilizes the ultra-low temperature characteristics of liquid hydrogen to cool the superconducting engine to meet the heat dissipation demand of the superconducting engine with a relatively high heat load. Secondly, heat is exchanged between the cooling circuit and the propulsion circuit through a liquid hydrogen-refrigerant heat exchanger, and the low-temperature liquid hydrogen in the propulsion circuit absorbs heat, thereby realizing the transfer of heat generated in the cooling circuit to the propulsion circuit. Then, the liquid hydrogen is exchanged with the engine intake air through a precooler to cool the engine intake air. The cooled engine intake air serves as the main cold source of engine components. Finally, the liquid hydrogen that has undergone multi-stage heat exchange enters the aircraft engine at a relatively high temperature for full combustion, thereby realizing multi-stage utilization of liquid hydrogen cooling capacity.

[0028] At the same time, facing the high heat load of multiple heating elements in the cooling circuit, four cold sources are used to meet the needs of instantaneous high heat load, namely, the evaporative cycle fuselage air inlet extracts cold from ram air, the skin extracts cold from the outside air in contact with it, the consumable working fluid cold and the phase change material in the heat storage device absorbs heat. The four cold sources all exchange heat with the refrigerant through the heat exchanger. The four heat exchangers are arranged from low to high according to the temperature of the cold source, and can be adjusted in response to changes in actual environmental conditions.

[0029] The superconducting hydrogen-electric propulsion aircraft thermal management system of the present invention solves the problems of low energy utilization rate of the aircraft thermal management system, coordinated heat dissipation of multiple instantaneous high heat load airborne equipment, and insufficient airborne environmental cold source. BRIEF DESCRIPTION OF THE DRAWINGS

[0030] Figure 1 A schematic diagram of the structure of a superconducting hydrogen-electric propulsion aircraft thermal management system provided by an embodiment of the present invention;

[0031] Figure 2 This is a schematic diagram of the low heat load workflow for airborne equipment;

[0032] Figure 3 This is a schematic diagram of the working process of low heat load for airborne equipment;

[0033] Figure 4 Schematic diagram of the workflow for high heat load of airborne equipment.

[0034] In the figure: 1-aircraft engine, 2-superconducting generator, 3-superconducting power transmission and distribution device, 4-superconducting motor, 5-tail nozzle propeller fan, 6-liquid hydrogen storage tank, 7-liquid hydrogen-refrigerant heat exchanger, 8-precooler, 9-first valve, 10-second valve, 11-refrigerant storage tank, 12-refrigerant pump, 13-first heating element, 14-second heating element, 15-third heating element, 16-third valve, 17-heat storage, 18-skin heat exchanger, 19-consumable working fluid heat exchanger, 20-consumable working fluid storage tank, 21-fourth valve, 22-gas-liquid separator, 23-compressor, 24-ram air heat exchanger, 25-fifth valve. DETAILED DESCRIPTION

[0035] In order to make the purpose, technical solution and advantages of the present invention clearer, the technical solution of the present invention is described clearly and completely below. Obviously, the described embodiments are part of the embodiments of the present invention, not all of the embodiments. 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.

[0036] The embodiment of the present invention provides a superconducting hydrogen-electric propulsion aircraft thermal management system. Superconducting hybrid electric propulsion technology is currently a key research direction in the field of aviation power. It mainly faces the problem of insufficient heat sink due to the increase in the total amount of heat load and the lack of coordinated heat dissipation of airborne equipment. In this way, the present invention uses the ultra-low temperature characteristics of liquid hydrogen to cool the superconducting engine, airborne high heat load equipment and engine intake in turn. After multi-stage cold utilization, it enters the aircraft engine for combustion to generate power. The engine intake cooled by liquid hydrogen serves as the main cold source for engine components. At the same time, in order to cope with various airborne equipment with increasing heat loads, it further combines ram air refrigeration, phase change heat storage, skin cooling and consumable working fluid refrigeration to solve the problem of insufficient cold generated by instantaneous high heat load equipment, and at the same time improves the utilization efficiency of airborne energy.

[0037] like Figure 1 As shown, a superconducting hydrogen-electric propulsion aircraft thermal management system provided by an embodiment of the present invention includes a propulsion circuit, a cooling circuit and a cooling circuit.

[0038] The propulsion circuit includes: an aircraft engine 1, a superconducting generator 2, a superconducting power transmission and distribution device 3, a superconducting motor 4, a micro-nozzle propeller fan 5, a liquid hydrogen storage tank 6, a precooler 8, a first valve 9 and a second valve 10.

[0039] The liquid hydrogen storage tank 6 is used to store liquid hydrogen. The aircraft engine 1 is used to generate thrust and power. The superconducting generator 2, the superconducting power transmission and distribution device 3, and the superconducting motor 4 together constitute a superconducting engine. The superconducting engine is connected to the aircraft engine 1, and the superconducting generator 2 is driven by the turbine of the aircraft engine 1 to generate electricity. The superconducting power transmission and distribution device 3 is electrically connected to the superconducting generator 2 and the superconducting motor 4. The superconducting power transmission and distribution device 3 is used to transmit the electricity generated by the superconducting generator 2 to the superconducting motor 4 according to demand. The function of the superconducting motor 4 is to convert the electrical energy generated by the superconducting generator 2 into kinetic energy. The function of the tail nozzle propeller fan 5 is to discharge the exhaust gas after combustion in the aircraft engine 1 to the atmosphere. The micro nozzle propeller fan 5 is connected to the superconducting engine. The outlet of the liquid hydrogen storage tank 6 is connected to the second inlet of the superconducting engine through the first pipeline, the second outlet of the superconducting engine is connected to the first inlet of the hydrogen storage-coolant heat exchanger 7 through the second pipeline, and the first outlet of the liquid hydrogen-coolant heat exchanger 7 is connected to the first inlet of the precooler 8 through the third pipeline. The superconducting engine is connected to the third pipeline through the fourth pipeline, and the first outlet of the precooler 8 is connected to the first inlet of the aircraft engine 1 through the fifth pipeline. The second outlet of the precooler 8 is connected to the second inlet of the aircraft engine 1 through the sixth pipeline. The function of the precooler is to exchange heat between liquid hydrogen and the engine intake air that is about to enter the aircraft engine 1. The first valve 9 is arranged on the fourth pipeline, and the second valve 10 is arranged on the second pipeline. The first valve 9 and the second valve 10 jointly control the connection between the propulsion circuit and the cooling circuit.

[0040] The cooling circuit includes a first heating element 13 , a second heating element 14 , a third heating element 15 , a liquid hydrogen-coolant heat exchanger 7 , a third valve 16 , and a fourth valve 21 .

[0041] The first heating element 13, the second heating element 14 and the third heating element 15 together constitute an onboard heating element system. The function of the liquid hydrogen-coolant heat exchanger 7 is to exchange heat between the cooling circuit and the propulsion circuit, and absorb heat through the low-temperature liquid hydrogen in the propulsion circuit, so as to realize the transfer of heat generated by the high heat load equipment in the cooling circuit to the propulsion circuit. The second outlet of the liquid hydrogen-coolant heat exchanger 7 is connected to the inlet of the onboard heating element system through the seventh pipeline, and the outlet of the onboard heating element is connected to the first inlet of the heat storage 17 through the eighth pipeline. The first outlet of the heat storage 17 is connected to the second inlet of the liquid hydrogen-coolant heat exchanger 7 through the ninth pipeline, and the outlet of the onboard heating element system is connected to the ninth pipeline through the tenth pipeline. The third valve 16 is installed on the eighth pipeline, and the fourth valve 21 is installed on the tenth pipeline. The third valve 16 and the fourth valve 21 jointly control the connection between the cold extraction circuit and the cooling circuit.

[0042] The cooling circuit includes a heat storage 17, a compressor 23, a ram air heat exchanger 24, and a fifth valve 25. The function of the heat storage 17 is to exchange heat between the cooling circuit and the cooling circuit, thereby transferring the heat generated by the high heat load equipment in the cooling circuit to the refrigerant in the cooling circuit. At the same time, the phase change material in the heat storage 17 absorbs a large amount of heat in a short period of time to meet the heat dissipation requirements of some airborne equipment such as lasers with high heat loads in a short period of time. The function of the compressor 23 is to compress low-pressure, low-temperature refrigerant vapor into high-pressure, high-temperature refrigerant vapor.

[0043] The second outlet of the heat storage 17 is connected to the inlet of the compressor 23 through the eleventh pipeline. The second inlet of the ram air heat exchanger 24 is connected to the ram air pipeline, and the second outlet is connected to the outside atmosphere. The first inlet of the ram air heat exchanger 24 is connected to the outlet of the compressor 23 through the twelfth pipeline, and the first outlet of the ram air heat exchanger 24 is connected to the second inlet of the heat storage 17 through the thirteenth pipeline. The fifth valve 25 is installed on the thirteenth pipeline. The function of the ram air heat exchanger 24 is to exchange heat between the ram air and the refrigerant in the cold extraction circuit, and transfer the heat of the refrigerant in the cold extraction circuit to the ram air. The function of the fifth valve 25 is to control the on and off of the cold extraction circuit.

[0044] Optionally, the cooling circuit further includes: a refrigerant storage tank 11 for storing the working fluid in the cooling circuit, and the refrigerant storage tank 11 is arranged on the seventh pipeline between the onboard heating element system and the liquid hydrogen-refrigerant heat exchanger 7.

[0045] Optionally, the cooling circuit also includes: a skin heat exchanger 18, wherein the skin heat exchanger 18 is arranged on the fourteenth pipe between the first connection point and the liquid hydrogen-refrigerant heat exchanger 7, and the first connection point is the connection point between the ninth pipe and the tenth pipe, and the aircraft skin 18 is used to extract cold energy from the low-temperature air outside the cabin that is in contact with it.

[0046] Optionally, the cooling circuit further includes: a consumable working fluid heat exchanger 19, which is arranged on the fourteenth pipeline between the skin heat exchanger 18 and the liquid hydrogen-coolant heat exchanger 7, and uses the consumable working fluid carried by the aircraft to extract standby cooling capacity, and the consumable working fluid can use liquid nitrogen. And the consumable working fluid storage tank 20 is connected to the consumable working fluid heat exchanger.

[0047] Optionally, the heating element is composed of a heating element unit and a heating element heat exchanger unit, the heating element heat exchanger units all use the refrigerant as a heat sink, the heating element units correspond to the heating element heat exchanger units one-to-one, and multiple heating elements are connected in parallel to realize multi-branch heat exchange at the same time, the outlets of the heating element heat exchanger units are connected to the first inlet of the heat storage 17 through the eighth pipeline, and the inlets of the heating element heat exchanger units are connected to the second outlet of the liquid hydrogen-refrigerant heat exchanger 7 through the seventh pipeline, and the heating element heat exchanger units are used to realize heat exchange between the refrigerant in the cooling circuit and the heating element.

[0048] Optionally, the airborne heating element system includes but is not limited to high-power, high-heat-flow airborne equipment such as motors, lasers and radars. The inlet of the heating element heat exchanger unit is connected to the second outlet of the liquid hydrogen-refrigerant heat exchanger 7 through the seventh pipeline, and the outlet of the heating element heat exchanger unit is connected to the first inlet of the heat storage tank 17 through the fourteenth pipeline.

[0049] Optionally, the cooling circuit further includes: a coolant pump 12 for realizing the circulation of the cooling circuit, and the coolant pump 12 is installed on the seventh pipeline connecting the coolant storage tank 11 and the onboard heating element system.

[0050] Optionally, the cooling circuit also includes: a gas-liquid separator 22, which is used to separate the refrigerant gas and liquid generated in the heat storage device 17 from each other, thereby ensuring the normal operation of the cooling circuit, and is arranged on the eleventh pipeline between the heat storage device 17 and the compressor 23.

[0051] In actual applications, the heat storage device 17, the skin heat exchanger 18, the consumable working fluid heat exchanger 19 and the liquid hydrogen-refrigerant heat exchanger 7 are arranged in order from high to low according to the temperature of the cold source and away from the heating elements, and corresponding adjustments can be made according to changes in actual environmental conditions.

[0052] The working process of the superconducting hydrogen-electric propulsion aircraft thermal management system provided by the embodiment of the present invention is as follows:

[0053] like Figure 2 As shown, when the onboard equipment is in a low heat load working state, the first valve 9 is opened and the second valve 10 is closed, so that the propulsion circuit is disconnected from the cooling circuit, and the cooling circuit does not exchange heat with the liquid hydrogen in the propulsion circuit. At the same time, the third valve 16 is closed, the fourth valve 21 is opened, and the fifth valve 25 is closed, so that the cooling circuit is disconnected from the cooling circuit, and the cooling circuit does not exchange heat with the refrigerant in the cooling circuit, and the consumable working fluid storage tank 20 is closed. The onboard heating element system transfers heat to the coolant in the cooling circuit through the heating element heat exchanger unit, and exchanges heat with the ambient air intake outside the cabin in the skin heat exchanger 18 through the cooling circuit coolant pump 12.

[0054] like Figure 3 As shown, when the onboard equipment is in a relatively low heat load working state, the first valve 9 is opened and the second valve 10 is closed, so that the propulsion circuit is disconnected from the cooling circuit, and the cooling circuit does not exchange heat with the liquid hydrogen in the propulsion circuit. The third valve 16 is opened, the fourth valve 21 is closed, and the consumable working storage tank 20 is closed. The onboard heating element system transfers heat to the coolant in the cooling circuit through the heating element heat exchanger unit. The cooling circuit coolant pump 12 first obtains heat from the refrigerant in the heat storage 17 through the solid-liquid phase change of the phase change material, and then exchanges heat with the ambient air outside the cabin in the skin heat exchanger 18. At the same time, the fifth valve 25 is opened, and the refrigerant in the cold extraction circuit stores the cold in the phase change material through the gas-liquid phase change in the heat storage 17.

[0055] like Figure 4 As shown, when the onboard equipment is in a relatively high heat load working state, the third valve 16 is opened and the fourth valve 21 is closed. The onboard heating element system transfers heat to the coolant in the cooling circuit through the heating element heat exchanger unit. The cooling circuit coolant pump 12 first causes the phase change material to obtain heat from the refrigerant through a solid-liquid phase change in the heat storage device 17, and then exchanges heat with the ambient air outside the cabin in the skin heat exchanger 18. The fifth valve 25 is opened, and the refrigerant in the cold circuit stores cold energy in the phase change material through a gas-liquid phase change in the heat storage device 17. At the same time, whether to enable the consumable working fluid heat exchanger 19 is selected according to actual needs, and consumable work is used to provide additional cold energy. Finally, the first valve 9 is closed and the second valve 10 is opened, so that the propulsion circuit and the cooling circuit can achieve heat exchange through the liquid hydrogen-coolant heat exchanger.

[0056] Finally, it should be noted that the above embodiments are only used to illustrate the technical solutions of the present invention, rather than to limit it. Although the present invention has been described in detail with reference to the aforementioned embodiments, those skilled in the art should understand that they can still modify the technical solutions described in the aforementioned embodiments, or make equivalent replacements for some of the technical features therein. However, these modifications or replacements do not deviate the essence of the corresponding technical solutions from the spirit and scope of the technical solutions of the embodiments of the present invention.

Claims

1. A superconducting hydrogen electric propulsion aircraft thermal management system, characterized in that ,include: Propulsion circuit, cooling circuit and cold extraction circuit; The propulsion circuit includes: an aircraft engine, a superconducting generator, a superconducting power transmission and distribution device, a superconducting motor, a liquid hydrogen storage tank, a precooler, a first valve and a second valve; The cooling circuit includes a liquid hydrogen-coolant heat exchanger, a first heating element, a second heating element, a third heating element, a third valve and a fourth valve; The cooling circuit comprises: a heat storage device, a ram air heat exchanger, a compressor and a fifth valve; The superconducting generator, the superconducting power transmission and distribution device and the superconducting engine together constitute a superconducting engine, the aircraft engine is connected to the superconducting engine, the outlet of the liquid hydrogen storage tank is connected to the second inlet of the superconducting engine through the first pipeline; the outlet of the superconducting engine is connected to the first inlet of the liquid hydrogen-coolant heat exchanger through the second pipeline, the first outlet of the liquid hydrogen-coolant heat exchanger is connected to the first inlet of the precooler through the third pipeline, and the outlet of the superconducting engine is connected to the third pipeline through the fourth pipeline; the first valve is installed on the fourth pipeline, and the second valve is installed on the second pipeline; the first outlet of the precooler is connected to the first inlet of the aircraft engine through the fifth pipeline, and the second outlet of the precooler is connected to the second inlet of the aircraft engine through the sixth pipeline; The first heating element, the second heating element and the third heating element together constitute an airborne heating element system, the second outlet of the liquid hydrogen-coolant heat exchanger is connected to the inlet of the airborne heating element system through the seventh pipeline, the outlet of the airborne heating element system is connected to the first inlet of the heat storage device through the eighth pipeline, the first outlet of the heat storage device is connected to the second inlet of the liquid hydrogen-coolant heat exchanger through the ninth pipeline, the outlet of the airborne heating element system is connected to the ninth pipeline through the tenth pipeline, the third valve is installed on the eighth pipeline, and the fourth valve is installed on the tenth pipeline; The second outlet of the heat storage device is connected to the inlet of the compressor through an eleventh pipe, the outlet of the compressor is connected to the first inlet of the ram air heat exchanger through a twelfth pipe, the first outlet of the ram air heat exchanger is connected to the second inlet of the heat storage device through a thirteenth pipe, and the fifth valve is installed on the thirteenth pipe.

2. The superconducting hydrogen electric propulsion aircraft thermal management system according to claim 1, characterized in that: The cooling circuit also includes a coolant storage tank, which is arranged on a seventh pipeline between the onboard heating element system and the liquid hydrogen-coolant heat exchanger.

3. The superconducting hydrogen electric propulsion aircraft thermal management system according to claim 1, characterized in that: The cooling circuit also includes: a skin heat exchanger, which is arranged on a fourteenth pipeline between a first connection point and the liquid hydrogen-coolant heat exchanger, and the first connection point is a connection point between the ninth pipeline and the tenth pipeline.

4. The superconducting hydrogen electric propulsion aircraft thermal management system according to claim 3, characterized in that: The cooling circuit also includes: a consumable working fluid heat exchanger, which is arranged on the fourteenth pipeline between the skin heat exchanger and the liquid hydrogen-coolant heat exchanger.

5. The superconducting hydrogen electric propulsion aircraft thermal management system according to claim 2, characterized in that: The heating element is composed of a heating element unit and a heating element heat exchanger unit. The heating element unit corresponds to the heating element heat exchanger unit one by one. Multiple heating elements are connected in parallel. The inlets of the heating element heat exchanger units are connected to the second outlet of the liquid hydrogen-refrigerant heat exchanger through the seventh pipeline, and the outlets of the heating element heat exchanger units are connected to the first inlet of the heat storage through the fourteenth pipeline.

6. The superconducting hydrogen electric propulsion aircraft thermal management system according to claim 1, characterized in that: The cooling circuit further includes: a coolant pump, which is installed on a seventh pipeline connecting the coolant storage tank and the onboard heating element system.

7. The superconducting hydrogen electric propulsion aircraft thermal management system according to claim 1, characterized in that: The cooling circuit also includes: a gas-liquid separator, which is arranged on the eleventh pipeline between the heat storage device and the compressor.

8. The operating method of the thermal management system of a superconducting hydrogen electric propulsion aircraft according to any one of claims 1 to 7, characterized in that: When the onboard equipment is in low heat load working state, including: Step (1) the first valve is opened and the second valve is closed, so that the propulsion circuit is disconnected from the cooling circuit, and the cooling circuit does not exchange heat with the liquid hydrogen in the propulsion circuit; Step (2) the third valve is closed, the fourth valve is opened, and the fifth valve is closed, so that the cooling circuit is disconnected from the cooling circuit, and the cooling circuit does not exchange heat with the refrigerant in the cooling circuit; Step (3). Close the consumable working fluid storage tank, and the onboard heating element system transfers the heat to the coolant in the cooling circuit through the heating element heat exchanger unit, and exchanges heat with the ambient air intake outside the cabin in the skin heat exchanger through the cooling circuit coolant pump.

9. The operating method of the thermal management system of a superconducting hydrogen electric propulsion aircraft according to any one of claims 1 to 7, characterized in that: When the onboard equipment is in a low heat load working state, including: Step (1) the first valve is opened and the second valve is closed, so that the propulsion circuit is disconnected from the cooling circuit, and the cooling circuit does not exchange heat with the liquid hydrogen in the propulsion circuit; Step (2). The third valve is opened, the fourth valve is closed, the consumable working tank is closed, and the onboard heating element system transfers heat to the coolant in the cooling circuit through the heating element heat exchanger unit. The coolant pump in the cooling circuit first obtains heat from the refrigerant in the heat storage device through the solid-liquid phase change of the phase change material, and then exchanges heat with the ambient air outside the cabin in the skin heat exchanger; Step (3). The fifth valve is opened, and the refrigerant in the cooling circuit stores the cold energy in the phase change material through a gas-liquid phase change in the heat storage device.

10. The working method of the thermal management system of a superconducting hydrogen electric propulsion aircraft according to any one of claims 1 to 7, characterized in that: When the onboard equipment is in a high heat load working state, including: Step (1). The third valve is opened, the fourth valve is closed, the onboard heating element system transfers heat to the refrigerant in the cooling circuit through the heating element heat exchanger unit, and the cooling circuit refrigerant pump first causes the phase change material to obtain heat from the refrigerant through a solid-liquid phase change in the heat storage device, and then exchanges heat with the ambient air outside the cabin in the skin heat exchanger; Step (2) The fifth valve is opened, and the refrigerant in the cooling circuit stores the cold in the phase change material through a gas-liquid phase change in the heat storage device; Step (3). Choose whether to enable the consumable working fluid heat exchanger according to actual needs, and use consumable work to provide additional cooling capacity; Step (4). The first valve is closed and the second valve is opened, so that the propulsion circuit and the cooling circuit can achieve heat exchange through the liquid hydrogen-refrigerant heat exchanger.

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