Engine power system for unmanned reconnaissance aircraft and control method

Abstract

The invention belongs to the technical field of engine power system design, and particularly relates to an engine power system for an unmanned reconnaissance plane and a control method.The engine power system for the unmanned reconnaissance plane comprises an engine, a liquid hydrogen storage tank, a hydrogen fuel cell and a storage battery; an external superconducting generator is arranged on a transmission gear box of the engine, is provided with a cooling flow path and is connected to an engine power supply system; the liquid hydrogen storage tank is arranged outside the engine and communicates with the cooling flow path inlet through a liquid hydrogen pipeline; the hydrogen fuel cell is arranged outside the engine, is communicated with an outlet of the cooling flow path through a gas hydrogen pipeline and is connected to a power supply system of the unmanned reconnaissance aircraft; and the storage battery is arranged outside the engine, is connected with the external superconducting generator and the hydrogen fuel cell through lines, and is connected to an engine power supply system and an unmanned reconnaissance plane power supply system.

Description

Technical Field

[0001] The present application belongs to the technical field of engine power system design, and specifically relates to an engine power system and a control method for an unmanned reconnaissance aircraft. Background Art

[0002] Unmanned reconnaissance aircraft are equipped with a large number of electronic optical, infrared, radar and other electronic reconnaissance equipment. When conducting reconnaissance on targets, a large amount of power needs to be extracted from the engine to generate electricity for use by the electronic reconnaissance equipment.

[0003] Unmanned reconnaissance aircraft usually need to fly at 0.6Ma for a long time at high altitude. At this time, the engine is usually at the left boundary of the working envelope, with small thrust and low stability margin. If a large amount of power is extracted from the engine to generate electricity and supply electronic reconnaissance equipment, the stability of the engine will be greatly reduced, which will have an adverse effect on the stable flight of the unmanned reconnaissance aircraft, increase the engine's fuel consumption rate, and reduce the unmanned reconnaissance aircraft's stay in the air time.

[0004] In addition, currently most power is extracted from the engine through gear transmission to generate electricity. When extracting large amounts of power, wear is prone to occur, leading to transmission failure.

[0005] This application is proposed in view of the above-mentioned technical defects. Summary of the invention

[0006] The purpose of this application is to provide an engine power system and control method for an unmanned reconnaissance aircraft to overcome or alleviate at least one of the known technical deficiencies.

[0007] The technical solution of this application is: On the one hand, an engine power system for an unmanned reconnaissance aircraft is provided, including an engine, a liquid hydrogen storage tank, a hydrogen fuel cell, and a battery; An external superconducting generator is arranged on the transmission gearbox of the engine, a cooling flow path is provided on the external superconducting generator, and the external superconducting generator is connected to the engine power supply system; The liquid hydrogen storage tank is arranged outside the engine and connected to the cooling flow path inlet through a liquid hydrogen pipeline; The hydrogen fuel cell is arranged outside the engine, connected to the cooling flow path outlet through a gas-hydrogen pipeline, and connected to the power supply system of the unmanned reconnaissance aircraft; The battery is installed outside the engine and connected to the external superconducting generator, hydrogen fuel cell, engine power supply system and unmanned reconnaissance aircraft power supply system through lines; When starting the engine, the external superconducting generator can be controlled to be in electric mode, and the battery can be used to power the external superconducting generator, so that the external superconducting generator drives the engine to rotate through the transmission gear box. After the engine speed reaches the speed required for starting, the battery is used to power the engine power supply system to supply fuel and ignite the engine; After the engine is successfully started, the external superconducting generator can be controlled to be in power generation mode, and the engine is driven to generate electricity through the transmission gear box. The electric energy generated by the external superconducting generator is supplied to the engine power supply system for use, and is transmitted to the battery for storage. When the electric energy generated by the external superconducting generator cannot meet the power demand of the engine power supply system, the battery is used to supply power to the engine power supply system; After the engine is started successfully, the liquid hydrogen storage tank can be controlled to supply liquid hydrogen to the cooling flow path through the liquid hydrogen pipeline. The liquid hydrogen absorbs the heat generated by the external superconducting generator along the way to cool the external superconducting generator. The liquid hydrogen absorbs heat and vaporizes into gaseous hydrogen, which flows to the hydrogen fuel cell through the gaseous hydrogen pipeline, so that the hydrogen fuel cell works to generate electricity. The electric energy generated by the hydrogen fuel cell is supplied to the power supply system of the unmanned reconnaissance aircraft and is transmitted to the battery for storage. When the electric energy generated by the hydrogen fuel cell cannot meet the power demand of the power supply system of the unmanned reconnaissance aircraft, the battery is used to supply power to the power supply system of the unmanned reconnaissance aircraft.

[0008] Optionally, in the above-mentioned engine power system for the unmanned reconnaissance aircraft, the starting power of the external superconducting generator W1 = A×W2, where W2 is the power required to start the engine, and A is the calculation coefficient, and the value range is 1.1~1.2.

[0009] Optionally, in the above-mentioned engine power system for the unmanned reconnaissance aircraft, the rated power generation power of the external superconducting generator is W3=0.8W4, wherein W4 is the maximum power consumption within the full flight envelope of the engine power supply system.

[0010] Optionally, in the above-mentioned engine power system for unmanned reconnaissance aircraft, the rated power generation power W7 of the hydrogen fuel cell is the larger value of the maximum power W10 of the unmanned reconnaissance aircraft power supply system and the power W11 generated by the maximum flow rate of liquid hydrogen for cooling the external superconducting generator; The maximum power W10 of the power supply system of the unmanned reconnaissance aircraft is the sum of the maximum power W8 of the unmanned reconnaissance aircraft platform and the maximum power W9 of the electronic reconnaissance equipment; The maximum flow rate of liquid hydrogen used to cool the external superconducting generator is the flow rate during the ground takeoff phase.

[0011] Optionally, in the above-mentioned engine power system for the unmanned reconnaissance aircraft, the capacity of the battery Q1=120×(W1+W4+W8).

[0012] On the other hand, a method for controlling an engine power system for an unmanned reconnaissance aircraft is provided, which is used to control the engine power system for the unmanned reconnaissance aircraft, comprising: When starting the engine, the external superconducting generator is controlled to be in electric mode, and the battery is used to power the external superconducting generator, so that the external superconducting generator drives the engine to rotate through the transmission gear box. After the engine speed reaches the speed required for starting, the battery is used to power the engine power supply system, and the engine is fueled and ignited to complete the engine starting; After the engine is successfully started, the external superconducting generator is controlled to be in the power generation mode, and the engine is driven to generate electricity through the transmission gear box. The electric energy generated by the external superconducting generator is supplied to the engine power supply system for use, and is transmitted to the battery for storage. When the electric energy generated by the external superconducting generator cannot meet the power demand of the engine power supply system, the battery is used to supply power to the engine power supply system; After the engine is successfully started, the liquid hydrogen storage tank is controlled to supply liquid hydrogen to the cooling flow path through the liquid hydrogen pipeline. The liquid hydrogen absorbs the heat generated by the external superconducting generator along the way to cool the external superconducting generator. The liquid hydrogen absorbs heat and vaporizes into gaseous hydrogen, which flows to the hydrogen fuel cell through the gaseous hydrogen pipeline, so that the hydrogen fuel cell works to generate electricity. The electricity generated by the hydrogen fuel cell is supplied to the power supply system of the unmanned reconnaissance aircraft and is transmitted to the battery for storage. When the electricity generated by the hydrogen fuel cell cannot meet the power demand of the power supply system of the unmanned reconnaissance aircraft, the battery is used to supply power to the power supply system of the unmanned reconnaissance aircraft.

[0013] This application has at least the following beneficial technical effects: Provided are an engine power system and a control method for an unmanned reconnaissance aircraft. The power consumption of the engine mainly comes from an external superconducting generator. The power consumption on the unmanned reconnaissance aircraft mainly comes from a hydrogen fuel cell. The battery can store excess electric energy, adjust the difference in power consumption, avoid heat loss caused by the reflux of the mechanical system, and can greatly reduce the transmission power of the transmission gearbox, reduce the stress of the transmission gearbox, reduce the wear of the transmission gearbox, ensure the reliability of the transmission gearbox, and greatly reduce the impact on the working stability of the engine, thereby ensuring the stable flight of the unmanned reconnaissance aircraft, reducing the fuel consumption rate of the engine, and ensuring the airborne time of the unmanned reconnaissance aircraft. BRIEF DESCRIPTION OF THE DRAWINGS

[0014] Figure 1 is a schematic diagram of an engine power system for an unmanned reconnaissance aircraft provided in an embodiment of the present application; in: 1-Engine; 2-Liquid hydrogen storage tank; 3-Hydrogen fuel cell; 4-Battery; 11-transmission gear box; 12-external superconducting generator; 41-Engine power supply system; 42-Unmanned reconnaissance aircraft power supply system.

[0015] In order to better illustrate the present embodiment, some contents of the drawings may be omitted, enlarged or reduced, which is only used for illustrative purposes and should not be construed as limiting the present application. DETAILED DESCRIPTION

[0016] In order to make the technical solution and advantages of the present application clearer, the technical solution of the present application will be further described in detail in detail with reference to the accompanying drawings. It can be understood that the specific embodiments described here are only partial embodiments of the present application, which are only used to explain the present application, not to limit the present application. It should be noted that, for the convenience of description, only the parts related to the present application are shown in the accompanying drawings, and other related parts can refer to the general design.

[0017] In addition, unless otherwise defined, the technical terms or scientific terms used in the description of this application should be the common meanings understood by those skilled in the art in the field to which this application belongs. The term "include" used in the description of this application means that the concepts appearing before the term include the concepts listed after the term and their equivalents, without excluding other related concepts.

[0018] In addition, the words indicating orientation used in the description of this application are only used to indicate relative directions or positional relationships. When the absolute position of the object being described changes, its relative positional relationship may also change accordingly. It should also be noted that, unless otherwise clearly specified and limited, the words "installation", "connection" and other similar words used in the description of this application should be understood in a broad sense. For example, the connection can be a fixed connection or a detachable connection; it can be a mechanical connection or an electrical connection; it can be a direct connection or an indirect connection through an intermediate medium. Technical personnel in the field can understand its specific meaning in this application according to the specific circumstances.

[0019] An engine power system for an unmanned reconnaissance aircraft, such as Figure 1 As shown, it includes an engine 1, a liquid hydrogen storage tank 2, a hydrogen fuel cell 3, and a battery 4.

[0020] An external superconducting generator 12 is arranged on the transmission gear box 11 of the engine 1 , a cooling flow path is provided on the external superconducting generator 12 , and the external superconducting generator 12 is connected to the engine power supply system 41 .

[0021] The liquid hydrogen storage tank 2 is arranged outside the engine 1 and is connected to the cooling flow path inlet through the liquid hydrogen pipeline 21.

[0022] The hydrogen fuel cell 3 is arranged outside the engine 1 , connected to the cooling flow path outlet through the gas hydrogen pipeline 22 , and connected to the power supply system 42 of the unmanned reconnaissance aircraft.

[0023] The storage battery 4 is arranged outside the engine 1 , and is connected to the external superconducting generator 12 , the hydrogen fuel cell 3 , and is connected to the engine power supply system 41 and the unmanned reconnaissance aircraft power supply system 42 through lines.

[0024] When starting the engine 1, the external superconducting generator 12 can be controlled to be in the electric mode, and the battery 4 can be used to power the external superconducting generator 12, so that the external superconducting generator 12 drives the engine 1 to rotate through the transmission gear box 11. After the speed of the engine 1 reaches the speed required for starting, the battery 4 is used to power the engine power supply system 41 to supply fuel and ignite the engine 1 to complete the starting of the engine 1. In this process, the lubrication of the engine 1, the nozzle actuation and other actions are also powered by the battery 4.

[0025] After the engine 1 is successfully started, the external superconducting generator 12 can be controlled to be in the power generation mode, and the engine 1 is driven to generate electricity through the transmission gear box 11. The electric energy generated by the external superconducting generator 12 is supplied to the engine power supply system 41 for use, and is transmitted to the battery 4 for storage. When the electric energy generated by the external superconducting generator 12 cannot meet the power demand of the engine power supply system 41, the battery 4 is used to supply power to the engine power supply system 41.

[0026] After the engine 1 is successfully started, the liquid hydrogen storage tank 2 can be controlled to simultaneously supply liquid hydrogen to the cooling flow path through the liquid hydrogen pipeline 21. The liquid hydrogen absorbs the heat generated by the external superconducting generator 12 along the way, and cools the external superconducting generator 12 to maintain the low temperature required for the superconductivity of the external superconducting generator 12 and maintain a high power generation capacity. The liquid hydrogen absorbs heat and vaporizes into gaseous hydrogen, which flows to the hydrogen fuel cell 3 through the gaseous hydrogen pipeline 22, so that the hydrogen fuel cell 3 works to generate electricity. The electric energy generated by the hydrogen fuel cell 3 is supplied to the unmanned reconnaissance aircraft power supply system 42 for use, and is transmitted to the battery 4 for storage. When the electric energy generated by the hydrogen fuel cell 3 cannot meet the power demand of the unmanned reconnaissance aircraft power supply system 42, the battery 4 is used to supply power to the unmanned reconnaissance aircraft power supply system 42. For example, when the unmanned reconnaissance aircraft takes off, the power generation power of the hydrogen fuel cell 3 is usually low, and it is difficult to meet the power demand of the unmanned reconnaissance aircraft power supply system 42. At this time, the battery 4 can supply power to the unmanned reconnaissance aircraft power supply system 42.

[0027] In the engine power system for the unmanned reconnaissance aircraft disclosed in the above embodiment, the power consumption of the engine 1 mainly comes from the external superconducting generator 12, the power consumption on the unmanned reconnaissance aircraft mainly comes from the hydrogen fuel cell 3, and the battery 4 can realize the regulation of current imbalance.

[0028] According to the full flight envelope analysis of the power consumption of the engine power supply system 41 and the unmanned reconnaissance aircraft power supply system 42, the power of the external superconducting generator 12 and the hydrogen fuel cell 3 can be determined to achieve a lightweight and low fuel consumption design for the engine 1 under the comprehensive full flight envelope.

[0029] The starting power W1=A×W2 of the external superconducting generator 12 can be determined according to the power W2 required for starting the engine 1 , where A is a calculation coefficient and has a value range of 1.1 to 1.2 to meet the starting time requirement of the engine 1 .

[0030] The ground operating speed and high-altitude operating speed of the external superconducting starting generator 12 vary by less than 40%, and its rated power generation W3 appears in the take-off state. Its power generation W5 in the high-altitude long-term working state is attenuated by less than 40% compared with W3. The maximum power consumption W4 of the engine power supply system 41 in the full flight envelope appears in the maximum state on the ground, and the power consumption W6 required for the high-altitude long-term working state is less than 30% of W4. Therefore, the rated power generation W3=0.8W4 of the external superconducting starting generator 12 can be determined based on the maximum power consumption W4 in the full flight envelope of the engine power supply system 41. Taking a smaller value for W3 can meet the power demand of the engine power supply system 41.

[0031] In order to ensure the power demand of the unmanned reconnaissance aircraft during the high-altitude reconnaissance stage and to ensure that the external superconducting generator 12 is in a reliable cooling state, the rated power generation power W7 of the hydrogen fuel cell 3 takes the larger value of the maximum power W10 of the unmanned reconnaissance aircraft power supply system 42 and the power W11 generated by the maximum flow rate of liquid hydrogen for cooling the external superconducting generator 12, that is, W7=max{W10, W11}, among which the maximum power W10 of the unmanned reconnaissance aircraft power supply system 42 can be taken as the sum of the maximum power W8 of the unmanned reconnaissance aircraft platform and the maximum power W9 of the electronic reconnaissance equipment, that is, W10= W8+W9, and the maximum flow rate of liquid hydrogen for cooling the external superconducting generator 12 can be taken as the flow rate during the ground takeoff stage.

[0032] The maximum capacity of battery 4 usually occurs during the startup phase of engine 1 and the unmanned reconnaissance aircraft. The startup time of engine 1 can be preliminarily designed to be 60 seconds, leaving a 1-fold margin to ensure rapid startup of engine 1 and reliable takeoff of the unmanned reconnaissance aircraft. The capacity of battery 4 is Q1=120×(W1+W4+W8).

[0033] In typical examples, W1≈1.5W4, W1≈W8, W1≈0.8W9.

[0034] In the prior art solution, the power of the unmanned reconnaissance aircraft and the engine 1 are both transmitted by the transmission gearbox 11, and the maximum power transmitted by the transmission gearbox 11 is 0.3W4+W8+W9=2.45W1. In the engine power system for the unmanned reconnaissance aircraft disclosed in the above embodiment, the maximum power transmitted by the transmission gearbox 11 is W1, which is 40% of the prior art solution. It can greatly reduce the transmission power of the transmission gearbox 11, reduce the force on the transmission gearbox 11, reduce the wear of the transmission gearbox 11, and ensure the reliability of the transmission gearbox 11. In addition, when working at high altitude for a long time, the power required to be extracted from the engine 1 is 0.3W4, which is numerically equal to 0.2W1, which is 8% of the prior art solution. It can greatly reduce the impact on the working stability of the engine 1, ensure the stable flight of the unmanned reconnaissance aircraft, and reduce the fuel consumption rate of the engine 1 to ensure the airborne time of the unmanned reconnaissance aircraft.

[0035] In the engine power system for the unmanned reconnaissance aircraft disclosed in the above embodiment, by using the battery 4, excess electrical energy can be stored, the difference in electricity consumption can be adjusted, the heat loss caused by the reflux of the mechanical system can be avoided, the fuel consumption rate of the engine 1 can be reduced, and the airborne time of the unmanned reconnaissance aircraft can be increased.

[0036] The engine power system for the unmanned reconnaissance aircraft disclosed in the above embodiment can be controlled by referring to the following method.

[0037] When starting the engine 1, the external superconducting generator 12 is controlled to be in the electric mode, and the battery 4 is used to power the external superconducting generator 12, so that the external superconducting generator 12 drives the engine 1 to rotate through the transmission gear box 11. After the speed of the engine 1 reaches the speed required for starting, the battery 4 is used to power the engine power supply system 41, and the engine 1 is fueled and ignited to complete the starting of the engine 1.

[0038] After the engine 1 is successfully started, the external superconducting generator 12 is controlled to be in the power generation mode, and the engine 1 is driven to generate electricity through the transmission gear box 11. The electric energy generated by the external superconducting generator 12 is supplied to the engine power supply system 41 for use, and is transmitted to the battery 4 for storage. When the electric energy generated by the external superconducting generator 12 cannot meet the power demand of the engine power supply system 41, the battery 4 is used to supply power to the engine power supply system 41.

[0039] After the engine 1 is successfully started, the liquid hydrogen storage tank 2 is controlled to pass liquid hydrogen into the cooling flow path through the liquid hydrogen pipeline 21. The liquid hydrogen absorbs the heat generated by the external superconducting generator 12 along the way, cools the external superconducting generator 12, maintains the low temperature required for the superconductivity of the external superconducting generator 12, and maintains a high power generation capacity. The liquid hydrogen absorbs heat and vaporizes into gaseous hydrogen, which flows to the hydrogen fuel cell 3 through the gaseous hydrogen pipeline 22, so that the hydrogen fuel cell 3 works to generate electricity. The electric energy generated by the hydrogen fuel cell 3 is supplied to the unmanned reconnaissance aircraft power supply system 42 for use, and is transmitted to the battery 4 for storage. When the electric energy generated by the hydrogen fuel cell 3 cannot meet the power demand of the unmanned reconnaissance aircraft power supply system 42, the battery 4 is used to supply power to the unmanned reconnaissance aircraft power supply system 42.

[0040] So far, the technical solution of the present application has been described in conjunction with the preferred embodiments shown in the accompanying drawings. Those skilled in the art should understand that the scope of protection of the present application is obviously not limited to these specific embodiments. Without departing from the principles of the present application, those skilled in the art can make equivalent changes or substitutions to the relevant technical features, and the technical solutions after these changes or substitutions will fall within the scope of protection of the present application.

Claims

1. An engine power system for an unmanned reconnaissance aircraft, characterized in that: It comprises an engine (1), a liquid hydrogen storage tank (2), a hydrogen fuel cell (3), and a battery (4); An external superconducting generator (12) is arranged on a transmission gearbox (11) of an engine (1); a cooling flow path is provided on the external superconducting generator (12), and the external superconducting generator (12) is connected to an engine power supply system (41); The liquid hydrogen storage tank (2) is arranged outside the engine (1) and is connected to the cooling flow path inlet via a liquid hydrogen pipeline (21); The hydrogen fuel cell (3) is arranged outside the engine (1), connected to the cooling flow path outlet through the gas hydrogen pipeline (22), and connected to the power supply system (42) of the unmanned reconnaissance aircraft; The storage battery (4) is arranged outside the engine (1), and is connected to the external superconducting generator (12), the hydrogen fuel cell (3), and is connected to the engine power supply system (41) and the unmanned reconnaissance aircraft power supply system (42) through lines; When starting the engine (1), the external superconducting generator (12) can be controlled to be in an electric mode, and the storage battery (4) can be used to supply power to the external superconducting generator (12), so that the external superconducting generator (12) drives the engine (1) to rotate through the transmission gear box (11), and after the engine (1) speed reaches the speed required for starting, the storage battery (4) supplies power to the engine power supply system (41), and the engine (1) is fueled and ignited; After the engine (1) is successfully started, the external superconducting generator (12) can be controlled to be in a power generation mode, and the engine (1) is driven to generate electricity through the transmission gear box (11). The electric energy generated by the external superconducting generator (12) is supplied to the engine power supply system (41) for use, and is transmitted to the storage battery (4) for storage. When the electric energy generated by the external superconducting generator (12) cannot meet the power demand of the engine power supply system (41), the storage battery (4) supplies power to the engine power supply system (41); After the engine (1) is successfully started, the liquid hydrogen storage tank (2) can be controlled to pass liquid hydrogen into the cooling flow path through the liquid hydrogen pipeline (21). The liquid hydrogen absorbs heat generated by the external superconducting generator (12) along the way to cool the external superconducting generator (12). The liquid hydrogen absorbs heat and gasifies into gaseous hydrogen, which flows to the hydrogen fuel cell (3) through the gaseous hydrogen pipeline (22), so that the hydrogen fuel cell (3) works to generate electricity. The electric energy generated by the hydrogen fuel cell (3) is supplied to the power supply system (42) of the unmanned reconnaissance aircraft for use, and is transmitted to the storage battery (4) for storage. When the electric energy generated by the hydrogen fuel cell (3) cannot meet the power demand of the power supply system (42) of the unmanned reconnaissance aircraft, the storage battery (4) supplies power to the power supply system (42) of the unmanned reconnaissance aircraft.

2. The engine power system for an unmanned reconnaissance aircraft according to claim 1, characterized in that: The starting power W1 of the external superconducting generator (12) is W2=A×W2, wherein W1 is the power required for starting the engine (1), and A is a calculation coefficient, with a value range of 1.1 to 1.

2.

3. The engine power system for an unmanned reconnaissance aircraft according to claim 2, characterized in that: The rated power generation power of the external superconducting generator (12) is W3=0.8W4, wherein W4 is the maximum power consumption of the engine power supply system (41) within the full flight envelope.

4. The engine power system for an unmanned reconnaissance aircraft according to claim 3, characterized in that: The rated power generation power W7 of the hydrogen fuel cell (3) is the larger value of the maximum power W10 of the power supply system (42) of the unmanned reconnaissance aircraft and the power W11 generated by the maximum flow rate of liquid hydrogen for cooling the external superconducting generator (12); The maximum power W10 of the unmanned reconnaissance aircraft power supply system (42) is the sum of the maximum power W8 of the unmanned reconnaissance aircraft platform and the maximum power W9 of the electronic reconnaissance equipment; The maximum flow rate of liquid hydrogen used for cooling the external superconducting generator (12) is the flow rate during the ground take-off stage.

5. The engine power system for an unmanned reconnaissance aircraft according to claim 4, characterized in that: The capacity of the battery (4) is Q1=120×(W1+W4+W8).

6. A method for controlling an engine power system for an unmanned reconnaissance aircraft, for controlling the engine power system for an unmanned reconnaissance aircraft according to claim 1, characterized in that: include: When starting the engine (1), the external superconducting generator (12) is controlled to be in an electric mode, and the storage battery (4) is used to supply power to the external superconducting generator (12), so that the external superconducting generator (12) drives the engine (1) to rotate through the transmission gear box (11). After the rotation speed of the engine (1) reaches the rotation speed required for starting, the storage battery (4) is used to supply power to the engine power supply system (41), and the engine (1) is fueled and ignited, thereby completing the starting of the engine (1); After the engine (1) is successfully started, the external superconducting generator (12) is controlled to be in a power generation mode, and the engine (1) is driven to generate electricity through the transmission gear box (11). The electric energy generated by the external superconducting generator (12) is supplied to the engine power supply system (41) for use, and is transmitted to the storage battery (4) for storage. When the electric energy generated by the external superconducting generator (12) cannot meet the power demand of the engine power supply system (41), the storage battery (4) supplies power to the engine power supply system (41); After the engine (1) is successfully started, the liquid hydrogen storage tank (2) is controlled to pass liquid hydrogen into the cooling flow path through the liquid hydrogen pipeline (21). The liquid hydrogen absorbs heat generated by the external superconducting generator (12) along the way to cool the external superconducting generator (12). The liquid hydrogen absorbs heat and turns into gaseous hydrogen, which flows to the hydrogen fuel cell (3) through the gaseous hydrogen pipeline (22), so that the hydrogen fuel cell (3) works to generate electricity. The electric energy generated by the hydrogen fuel cell (3) is supplied to the unmanned reconnaissance aircraft power supply system (42) for use, and is transmitted to the storage battery (4) for storage. When the electric energy generated by the hydrogen fuel cell (3) cannot meet the power demand of the unmanned reconnaissance aircraft power supply system (42), the storage battery (4) supplies power to the unmanned reconnaissance aircraft power supply system (42).

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