Unmanned reconnaissance aerial vehicle engine power system and control method thereof

Abstract

The invention relates to an unmanned reconnaissance aircraft engine power system and a control method thereof.The unmanned reconnaissance aircraft engine power system comprises an engine, a superconducting motor, a liquid hydrogen storage tank, a hydrogen-fired generator and a comprehensive energy management system; the superconducting motor has an electric mode and a power generation mode, is arranged in a front cavity of the engine and comprises a motor rotor and a motor stator, and the motor rotor is connected to a high-pressure shaft of the engine in a sleeving mode; the periphery of the motor rotor is sleeved with the motor stator, the motor stator is connected to the inner side of the engine front cavity through a pull rod, and heat exchange channels are formed in the periphery of the motor stator. The liquid hydrogen storage tank is arranged on the outer side of the engine and communicates with the heat exchange channel through a liquid hydrogen pipeline; the hydrogen-fired generator is arranged on the outer side of the engine and communicates with the heat exchange channel through a gas hydrogen pipeline; the comprehensive energy management system has an electric energy storage function, is arranged on the outer side of the engine, is connected with the superconducting motor and the hydrogen-fired generator through cables, and is connected to the unmanned aerial vehicle power supply system and the engine power supply system.

Description

Technical Field

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

[0002] A large number of electro-optical, infrared, radar and other electronic reconnaissance devices are carried on the unmanned reconnaissance aircraft. When conducting reconnaissance on targets, a large amount of power needs to be extracted from the engine for power generation to supply the electronic reconnaissance devices for use.

[0003] The unmanned reconnaissance aircraft usually needs to fly at 0.6Ma at high altitude for a long time. 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 for power generation to supply the electronic reconnaissance devices for use, it will greatly reduce the working stability of the engine, have an adverse impact on the stable flight of the unmanned reconnaissance aircraft, and increase the fuel consumption rate of the engine, reducing the endurance time of the unmanned reconnaissance aircraft.

[0004] In addition, currently, power is mostly extracted from the engine for power generation through a gear transmission method, which is prone to wear, resulting in transmission failure, and uses a large number of hydraulic systems, which are heavy and have a risk of oil leakage, which is not conducive to the reliable operation of the engine.

[0005] In view of the existence of the above technical defects, this application is proposed. Summary of the Invention

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

[0007] The technical solution of this application is as follows:

[0008] On the one hand, an engine power system of an unmanned reconnaissance aircraft is provided, including an engine, a superconducting motor, a liquid hydrogen storage tank, a hydrogen combustion generator, and an integrated energy management system;

[0009] The superconducting motor has an electric mode and a power generation mode, and is arranged in the front cavity of the engine, including a motor rotor and a motor stator. Among them, the motor rotor is sleeved on the high-pressure shaft of the engine; the motor stator is sleeved on the outer periphery of the motor rotor, is connected to the inner side of the front cavity of the engine through a pull rod, and a heat exchange channel is arranged on the outer periphery of the motor stator;

[0010] The liquid hydrogen storage tank is arranged outside the engine and is connected to the heat exchange channel through a liquid hydrogen pipeline;

[0011] The hydrogen combustion generator is arranged outside the engine and is connected to the heat exchange channel through a gaseous hydrogen pipeline;

[0012] The integrated energy management system has an electric energy storage function. It is set outside the engine and is connected to the superconducting motor, hydrogen combustion generator through cables, and is connected to the UAV power supply system and the engine power supply system.

[0013] When starting the engine, the integrated energy management system can control the superconducting motor to be in the electric mode and supply power to the superconducting motor, so that the superconducting motor drives the high-pressure shaft to rotate. When the speed of the high-pressure shaft reaches the engine starting speed requirement, the integrated energy management system can supply power to the engine fuel supply system through the engine power supply system, so that the engine fuel supply system supplies fuel to the combustion chamber, and supplies power to the engine ignition system, so that the ignition plug ignites the fuel injected into the engine combustion chamber to start the engine.

[0014] After the engine starts and the speed of the high-pressure shaft reaches the power extraction speed requirement, the integrated energy management system can control the superconducting motor to be in the power generation mode, and the high-pressure shaft drives the superconducting motor to generate electricity. The electric energy generated by the superconducting motor is stored in the integrated energy management system and supplied for use by the UAV power supply system and the engine power supply system.

[0015] The engine power system of the unmanned reconnaissance aircraft has a superconducting power generation mode and a conventional power generation mode.

[0016] When the engine power system of the unmanned reconnaissance aircraft is in the superconducting power generation mode, the integrated energy management system controls the superconducting motor to be in the power generation mode, controls the hydrogen combustion generator to start working, and controls the liquid hydrogen storage tank to introduce liquid hydrogen into the heat exchange channel through the liquid hydrogen pipeline. The liquid hydrogen introduced into the heat exchange channel can absorb the heat of the motor stator along the way, cool the motor stator, maintain the low temperature required for the superconductivity of the superconducting motor, and at the same time the liquid hydrogen gasifies, and then flows to the hydrogen combustion generator through the gas hydrogen pipeline to make the hydrogen combustion generator generate electricity. The electric energy generated by the hydrogen combustion generator is stored in the integrated energy management system and supplied for use by the UAV power supply system and the engine power supply system.

[0017] When the engine power system of the unmanned reconnaissance aircraft is in the conventional power generation mode, the integrated energy management system can control the superconducting motor to be in the power generation mode, control the hydrogen combustion generator to stop working, and control the liquid hydrogen storage tank to stop introducing liquid hydrogen into the heat exchange channel through the liquid hydrogen pipeline.

[0018] Optionally, in the above-mentioned engine power system of the unmanned reconnaissance aircraft, the liquid hydrogen pipeline, the gas hydrogen pipeline, and the cable connecting the superconducting motor to the integrated energy management system are led out through the front support plate of the engine.

[0019] Optionally, in the above-mentioned engine power system of the unmanned reconnaissance aircraft, cooling air intake holes are provided on the front support plate to connect the air intake duct of the engine and the front cavity.

[0020] Optionally, in the above unmanned reconnaissance aircraft engine power system, the hydrogen combustion generator includes a front compressor, a hydrogen combustion chamber, a power turbine, and a tail nozzle arranged in sequence. Among them, the front compressor and the power turbine are connected by a central rotating shaft. The front end of the central rotating shaft extends in front of the front compressor and is connected to the generator;

[0021] The integrated energy management system is connected to the generator and the ignition igniter of the hydrogen combustion generator through cables;

[0022] The outlet of the gaseous hydrogen pipeline is connected to the fuel nozzle of the hydrogen combustion generator;

[0023] When starting the hydrogen combustion generator, the integrated energy management system can control the starting generator to be in the electric mode and supply power to the starting generator to drive the central rotating shaft to rotate by the starting generator. When the rotational speed of the central rotating shaft reaches the starting rotational speed requirement of the hydrogen combustion generator, the integrated energy management system supplies power to the ignition igniter of the hydrogen combustion generator to ignite the hydrogen gas sprayed into the hydrogen combustion chamber through the fuel nozzle by the gaseous hydrogen pipeline, so as to start the hydrogen combustion generator;

[0024] After the hydrogen combustion generator starts working and the rotational speed of the central rotating shaft reaches the power extraction rotational speed requirement, the integrated energy management system can control the starting generator to be in the power generation mode, drive the starting generator to generate electricity by the central rotating shaft, and the electric energy generated by the starting generator is stored in the integrated energy management system and supplied for use by the unmanned aircraft power supply system and the engine power supply system.

[0025] On the other hand, a control method for an unmanned reconnaissance aircraft engine power system is provided to control the above unmanned reconnaissance aircraft engine power system, including:

[0026] After the engine starts, the integrated energy management system controls the unmanned reconnaissance aircraft engine power system to be in the conventional power generation mode;

[0027] When the electric energy stored in the integrated energy management system is less than 40%, if the unmanned reconnaissance aircraft turns on the electronic reconnaissance equipment, the unmanned reconnaissance aircraft engine power system is controlled to be in the superconducting power generation mode. Thereafter, when the electric energy stored in the integrated energy management system is not less than 60%, the unmanned reconnaissance aircraft engine power system is controlled to be in the conventional power generation mode, or when the electric energy stored in the integrated energy management system is not less than 40% and the unmanned reconnaissance aircraft turns off the electronic reconnaissance equipment, the unmanned reconnaissance aircraft engine power system is controlled to be in the conventional power generation mode.

[0028] The present application has at least the following beneficial technical effects:

[0029] Provided is an engine power system for an unmanned reconnaissance aircraft and its control method. It is designed to use liquid hydrogen to cool and generate electricity for the built-in superconducting motor, and supply the gasified liquid hydrogen to a hydrogen combustion generator for power generation. This can reduce the electrical energy extracted from the engine, weaken the impact of power extraction on the engine's working stability, ensure the stable flight of the unmanned reconnaissance aircraft, and reduce the fuel consumption rate of the engine, ensuring the endurance time of the unmanned reconnaissance aircraft. BRIEF DESCRIPTION OF THE DRAWINGS

[0030] Figure 1 is a schematic diagram of the engine power system of the unmanned reconnaissance aircraft provided by an embodiment of the present application;

[0031] Figure 2 is a schematic diagram of the hydrogen combustion generator provided by an embodiment of the present application;

[0032] Wherein:

[0033] 1 - engine; 2 - superconducting motor; 3 - liquid hydrogen storage tank; 4 - hydrogen combustion generator; 5 - integrated energy management system;

[0034] 11 - fan; 12 - compressor; 13 - combustion chamber; 14 - high-pressure turbine; 15 - low-pressure turbine; 16 - nozzle; 17 - high-pressure shaft; 18 - front support plate;

[0035] 21 - motor rotor; 22 - motor stator; 23 - tie rod; 24 - liquid hydrogen pipeline; 25 - gaseous hydrogen pipeline;

[0036] 41 - front compressor; 42 - hydrogen combustion chamber; 43 - power turbine; 44 - tail nozzle; 45 - central rotating shaft; 46 - starter generator;

[0037] 51 - unmanned aircraft power supply system; 52 - engine power supply system.

[0038] For better illustration of this embodiment, some contents in the drawings are omitted, enlarged or reduced, and are only for exemplary illustration and should not be construed as a limitation to the present application. DETAILED DESCRIPTION OF THE EMBODIMENTS

[0039] To make the technical solutions and their advantages of the present application clearer, the technical solutions of the present application will be further described clearly and completely below in conjunction with the drawings. It can be understood that the specific embodiments described herein are only partial embodiments of the present application, which are only used to explain the present application and are not a limitation to 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 drawings, and other related parts can refer to the normal design.

[0040] In addition, unless otherwise defined, the technical terms or scientific terms used in the description of this application shall have the ordinary meanings understood by those of ordinary skill in the art to which this application pertains. The term "including" used in the description of this application indicates that the concept appearing before this word encompasses the concepts listed after this word and their equivalents, without excluding other related concepts.

[0041] In addition, the words indicating directions used in the description of this application are only used to represent 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 terms such as "installed" and "connected" used in the description of this application should be understood in a broad sense. For example, "connected" can be a fixed connection, 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. Those skilled in the art can understand their specific meanings in this application according to the specific circumstances.

[0042] An engine power system for an unmanned reconnaissance aircraft, as Figure 1 shown, includes an engine 1, a superconducting motor 2, a liquid hydrogen storage tank 3, a hydrogen combustion generator 4, and an integrated energy management system 5.

[0043] The engine 1 includes a fan 11, a compressor 12, a combustion chamber 13, a high-pressure turbine 14, a low-pressure turbine 15, and a nozzle 16 arranged in sequence.

[0044] The superconducting motor 2 is arranged in the front cavity of the engine 1 and includes a motor rotor 21 and a motor stator 22. Among them, the motor rotor 21 is sleeved on the high-pressure shaft 17 of the engine 1; the motor stator 22 is sleeved on the outer periphery of the motor rotor 21 and is connected to the inner side of the front cavity of the engine 1 through a pull rod 23, and a heat exchange channel is arranged on the outer periphery of the motor stator 22. The superconducting motor 2 has an electric mode and a power generation mode.

[0045] The liquid hydrogen storage tank 3 is arranged outside the engine 1 and is connected to the heat exchange channel through a liquid hydrogen pipeline 24. A flow control valve can be arranged on the liquid hydrogen pipeline 24 to control the liquid hydrogen flow rate introduced from the liquid hydrogen storage tank 3 into the heat exchange channel.

[0046] The hydrogen combustion generator 4 is arranged outside the engine 1 and is connected to the heat exchange channel through a gaseous hydrogen pipeline 25.

[0047] The integrated energy management system 5 has an electric energy storage function, is arranged outside the engine 1, and is connected to the superconducting motor 2, the hydrogen combustion generator 4 through cables, and is connected to the power supply system 51 of the unmanned aircraft and the engine power supply system 52.

[0048] The integrated energy management system 5 can control the superconducting motor 2 to be in the electric mode or the power generation mode.

[0049] When starting the engine 1, the integrated energy management system 5 can control the superconducting motor 2 to be in the electric mode and supply power to the superconducting motor 2, so that the superconducting motor 2 drives the high-pressure shaft 17 to rotate. When the rotational speed of the high-pressure shaft 17 reaches the engine starting speed requirement, the integrated energy management system 5 supplies power to the engine fuel supply system through the engine power supply system 52, so that the engine fuel supply system supplies fuel to the combustion chamber 13 and supplies power to the engine ignition system, and the ignition plug ignites the fuel injected into the combustion chamber 13 to start the engine 1.

[0050] After the engine 1 starts and the rotational speed of the high-pressure shaft 17 reaches the power extraction speed requirement, the integrated energy management system 5 can control the superconducting motor 2 to be in the power generation mode, and the high-pressure shaft 1 drives the superconducting motor 2 to generate electricity. The electric energy generated by the superconducting motor 2 is stored in the integrated energy management system 5 and supplied to the UAV power supply system 51 and the engine power supply system 52 for use.

[0051] Considering that the power consumption demand of the unmanned reconnaissance aircraft varies greatly when the electronic reconnaissance equipment is turned on and off, in order to balance the power demand, the engine power system of the unmanned reconnaissance aircraft is designed to have a superconducting power generation mode and a conventional power generation mode.

[0052] When the engine power system of the unmanned reconnaissance aircraft is in the superconducting power generation mode, the integrated energy management system 5 controls the superconducting motor 2 to be in the power generation mode, controls the hydrogen combustion generator 4 to start working, and controls the liquid hydrogen storage tank 3 to introduce liquid hydrogen into the heat exchange channel through the liquid hydrogen pipeline 24. The liquid hydrogen introduced into the heat exchange channel will absorb the heat of the motor stator 22 along the way, cool the motor stator 22, maintain the low temperature required for the superconductivity of the superconducting motor 2, so that the superconducting motor 2 can have a high power generation capacity. At the same time, the liquid hydrogen will be vaporized and then flow to the hydrogen combustion generator 4 through the gaseous hydrogen pipeline 25 to make the hydrogen combustion generator 4 generate electricity. The electric energy generated by the hydrogen combustion generator 4 is stored in the integrated energy management system 5 and supplied to the UAV power supply system 51 and the engine power supply system 52 for use.

[0053] When the engine power system of the unmanned reconnaissance aircraft is in the conventional power generation mode, the integrated energy management system 5 controls the superconducting motor 2 to be in the power generation mode, controls the hydrogen combustion generator 4 to stop working, and controls the liquid hydrogen storage tank 3 to stop introducing liquid hydrogen into the heat exchange channel through the liquid hydrogen pipeline 24. At this time, the superconducting motor 2 lacks liquid hydrogen cooling and cannot effectively maintain the low temperature required for superconductivity, and the power generation capacity is small.

[0054] When the engine power system of the unmanned reconnaissance aircraft is in the superconducting power generation mode, the superconducting motor 2 and the hydrogen combustion generator 4 generate electricity at the same time, and can maintain the low temperature required for the superconductivity of the superconducting motor 2, so that the superconducting motor 2 can have a high power generation capacity and can generate a large amount of electric energy, which is applicable to the situation where the unmanned reconnaissance aircraft turns on the electronic reconnaissance equipment and has a large demand for electric energy.

[0055] When the engine power system of the unmanned reconnaissance aircraft is in the conventional power generation mode, only the superconducting motor 2 generates electricity, and it is unable to maintain the low temperature required for the superconductivity of the superconducting motor 2. The power generation capacity of the superconducting motor 2 is small, and the generated electric energy is small, which is applicable to the situation where the unmanned reconnaissance aircraft shuts down the electronic reconnaissance equipment and has less demand for electric energy.

[0056] In order to ensure that the power supply system 51 and the engine power supply system 52 of the unmanned aerial vehicle can be powered for a period of time in case of failure, the following relevant designs are carried out:

[0057] Determine the maximum power consumption W3 when the unmanned reconnaissance aircraft turns on the electronic reconnaissance equipment, and determine the maximum power consumption W4 of the engine when the unmanned aircraft turns off the electronic reconnaissance equipment;

[0058] Take the rated power generation of the hydrogen combustion generator W5 = 1.1W3, and then determine the rated flow rate Q of liquid hydrogen introduced into the heat exchange channel by the liquid hydrogen storage tank through the liquid hydrogen pipeline;

[0059] When the engine power system of the unmanned reconnaissance aircraft is in the conventional power generation mode, take the rated power generation of the superconducting motor W1 = W4, and when the engine power system of the unmanned reconnaissance aircraft is in the superconducting power generation mode, take the rated power generation of the superconducting motor W2 = 1.2W1;

[0060] Take the electric energy N stored in the integrated energy management system = 600 * W4.

[0061] In order to prevent the liquid hydrogen pipeline 24, the gaseous hydrogen pipeline 25, and the cables connecting the superconducting motor 2 to the integrated energy management system 5 from being impacted by the intake air flow of the engine 1, and to avoid interfering with the intake air flow and reducing the stability margin of the engine 1, design the liquid hydrogen pipeline 24, the gaseous hydrogen pipeline 25, and the cables connecting the superconducting motor 2 to the integrated energy management system 5 to be led out through the front support plate 18 of the engine 1, and cooling air intake holes connecting the intake air duct of the engine 1 and the front cavity can be opened on the front support plate 18, so as to introduce the low-temperature gas in the intake air duct into the front cavity to cool the superconducting motor 2.

[0062] The engine power system of the unmanned reconnaissance aircraft disclosed in the above embodiments uses liquid hydrogen to cool and generate electricity for the built-in superconducting motor 2, and uses the gasified liquid hydrogen to supply the hydrogen combustion generator 4 for power generation, which can reduce the electric energy extracted from the engine 1 body, weaken the influence of power extraction on the working stability of the engine 1, ensure the stable flight of the unmanned reconnaissance aircraft, and can reduce the fuel consumption rate of the engine 1 and ensure the endurance time of the unmanned reconnaissance aircraft.

[0063] The engine power system of the unmanned reconnaissance aircraft disclosed in the above embodiments uses the built-in superconducting motor 2 to start the engine 1 and extract power from the engine 1 for power generation. The starter and generator are integrally designed inside the engine 1, and a series of accessories such as gear transmission are cancelled, which can reduce the risk of mechanical wear and oil leakage, improve the working stability of the engine 1, and the use of the superconducting motor 2 can achieve the miniaturized design of the electrical system and reduce the overall weight of the system. In addition, through the use of the integrated energy management system 5, the engine power system of the unmanned reconnaissance aircraft can be switched between the superconducting power generation mode and the conventional power generation mode, minimizing the amount of hydrogen used.

[0064] When a certain unmanned reconnaissance aircraft shuts down the electronic reconnaissance equipment, the conventional power consumption is about 40 kW, and the power consumption required to turn on the electronic reconnaissance equipment is about 30 kW. According to the existing technical solutions, when the electronic reconnaissance equipment is turned on, the 70 kW of electrical power required on the unmanned reconnaissance aircraft needs to be extracted entirely from the engine 1. However, when using the engine power system of the unmanned reconnaissance aircraft disclosed in the above embodiments, only 40 kW of electrical power needs to be extracted from the engine 1, and the power extracted from the engine 1 is reduced by 43%, which can significantly improve the working stability of the engine 1 at high altitudes.

[0065] The hydrogen-fueled generator 4 includes a front compressor 41, a hydrogen combustion chamber 42, a power turbine 43, and a tail nozzle 44 arranged in sequence. Among them, the front compressor 41 and the power turbine 43 are connected by a central rotating shaft 45. The front end of the central rotating shaft 45 extends in front of the front compressor 41 and is connected to the generator 46. As Figure 2 shown, the generator 46 can be fixed by an external support structure.

[0066] The integrated energy management system 5 is connected to the generator 46 through a cable and is also connected to the ignition spark plug of the hydrogen-fueled generator 4. The integrated energy management system 5 can control the generator 46 to be in the electric mode or the power generation mode.

[0067] The outlet of the gaseous hydrogen pipeline 25 is connected to the fuel nozzle of the hydrogen-fueled generator 4.

[0068] When starting the hydrogen-fueled generator 4, the integrated energy management system 5 can control the generator 46 to be in the electric mode and supply power to the generator 46 to drive the central rotating shaft 45 to rotate by the generator 46. When the rotational speed of the central rotating shaft 45 reaches the starting rotational speed requirement of the hydrogen-fueled generator, the integrated energy management system 5 supplies power to the ignition spark plug of the hydrogen-fueled generator 4 to ignite the hydrogen gas sprayed into the hydrogen combustion chamber 42 through the fuel nozzle by the gaseous hydrogen pipeline 25, starting the hydrogen-fueled generator 4.

[0069] When the hydrogen combustion generator 4 starts to operate and the rotational speed of the central rotating shaft 45 reaches the power extraction rotational speed requirement, the integrated energy management system 5 can control the starter-generator 46 to be in the power generation mode, drive the starter-generator 46 to generate electricity with the central rotating shaft 45, store the electric energy generated by the starter-generator 46 in the integrated energy management system 5, and supply it to the UAV power supply system 51 and the engine power supply system 52 for use.

[0070] The hydrogen combustion generator 4 uses hydrogen fuel combustion. Since the hydrogen flame propagation speed is fast and the combustion time is short, the hydrogen combustion generator 4 can be miniaturized, and the starter-generator 46 of the hydrogen combustion generator 4 is designed in an external front-mounted mode. On the one hand, it can reduce the working temperature of the starter-generator 46, and on the other hand, it can simplify the design of the hydrogen combustion generator 4 body and reduce the design difficulty.

[0071] Based on the above, the embodiment of the present application takes the remaining power of the integrated energy management system 5 as the control target and provides a control method for the above-mentioned UAV engine power system, which is specifically as follows:

[0072] After the engine 1 starts, the integrated energy management system 5 controls the UAV engine power system to be in the conventional power generation mode;

[0073] When the electric energy stored in the integrated energy management system 5 is less than 40%, if the UAV turns on the electronic reconnaissance equipment, then control the UAV engine power system to be in the superconducting power generation mode. After that, when the electric energy stored in the integrated energy management system 5 is not less than 60%, control the UAV engine power system to be in the conventional power generation mode, or when the electric energy stored in the integrated energy management system 5 is not less than 40% and the UAV turns off the electronic reconnaissance equipment, control the UAV engine power system to be in the conventional power generation mode.

[0074] So far, the technical solution of the present application has been described in combination with the preferred embodiments shown in the drawings. Those skilled in the art should understand that the protection scope of the present application is obviously not limited to these specific embodiments. Without departing from the principle 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 all fall within the protection scope of the present application.

Claims

1. An engine power system for an unmanned reconnaissance aircraft, characterized in that: It includes an engine (1), a superconducting motor (2), a liquid hydrogen storage tank (3), a hydrogen-burning generator (4), and an integrated energy management system (5); The superconducting motor (2) has an electric mode and a power generation mode, is arranged in the front cavity of the engine (1), and comprises a motor rotor (21) and a motor stator (22), wherein the motor rotor (21) is sleeved on the high-pressure shaft (17) of the engine (1); the motor stator (22) is sleeved on the outer periphery of the motor rotor (21) and connected to the inner side of the front cavity of the engine (1) via a pull rod (23), and a heat exchange groove is arranged on the outer periphery of the motor stator (22); The liquid hydrogen storage tank (3) is arranged outside the engine (1) and is connected to the heat exchange channel via a liquid hydrogen pipeline (24); The hydrogen-burning generator (4) is arranged outside the engine (1) and is connected to the heat exchange channel via a gas-hydrogen pipeline (25); The integrated energy management system (5) has an electric energy storage function, is arranged outside the engine (1), is connected to the superconducting motor (2), the hydrogen-burning generator (4) through cables, and is connected to the UAV power supply system (51) and the engine power supply system (52); When the engine (1) is started, the integrated energy management system (5) can control the superconducting motor (2) to be in an electric mode and supply power to the superconducting motor (2), so that the superconducting motor (2) drives the high-voltage shaft (17) to rotate. When the rotation speed of the high-voltage shaft (17) reaches the engine starting rotation speed requirement, the integrated energy management system (5) can supply power to the engine fuel supply system through the engine power supply system (52), so that the engine fuel supply system supplies fuel to the combustion chamber (13), and supply power to the engine ignition system, so that the ignition nozzle ignites the fuel injected into the combustion chamber (13) of the engine (1), so that the engine (1) is started; When the engine (1) is started and the rotation speed of the high-voltage shaft (17) reaches the power extraction rotation speed requirement, the integrated energy management system (5) can control the superconducting motor (2) to be in a power generation mode, so that the high-voltage shaft (1) drives the superconducting motor (2) to generate electricity, and the electric energy generated by the superconducting motor (2) is stored in the integrated energy management system (5) and supplied to the UAV power supply system (51) and the engine power supply system (52) for use; The engine power system of the unmanned reconnaissance aircraft has superconducting power generation mode and conventional power generation mode; When the engine power system of the unmanned reconnaissance aircraft is in the superconducting power generation mode, the integrated energy management system (5) controls the superconducting motor (2) to be in the power generation mode, controls the hydrogen-burning generator (4) to start working, and controls the liquid hydrogen storage tank (3) to pass liquid hydrogen into the heat exchange channel through the liquid hydrogen pipeline (24). The liquid hydrogen passed into the heat exchange channel can absorb the heat of the motor stator (22) along the way, cool the motor stator (22), and maintain the low temperature required for the superconductivity of the superconducting motor (2). At the same time, the liquid hydrogen is gasified and then flows to the hydrogen-burning generator (4) through the gas-hydrogen pipeline (25), so that the hydrogen-burning generator (4) generates electricity. The electric energy generated by the hydrogen-burning generator (4) is stored in the integrated energy management system (5) and supplied to the unmanned aircraft power supply system (51) and the engine power supply system (52). When the engine power system of the unmanned reconnaissance aircraft is in a conventional power generation mode, the integrated energy management system (5) can control the superconducting motor (2) to be in the power generation mode, control the hydrogen-fired generator (4) to stop working, and control the liquid hydrogen storage tank (3) to stop supplying liquid hydrogen to the heat exchange channel through the liquid hydrogen pipeline (24).

2. The unmanned reconnaissance aircraft engine power system according to claim 1, characterized in that: The liquid hydrogen pipeline (24), the gas hydrogen pipeline (25), and the cables connecting the superconducting motor (2) to the integrated energy management system (5) are led out through the front support plate (18) of the engine (1).

3. The engine power system of the unmanned reconnaissance aircraft according to claim 2, characterized in that: The front support plate (18) is provided with a cooling air inlet hole which is connected to the air inlet passage of the engine (1) and the front cavity.

4. The engine power system of the unmanned reconnaissance aircraft according to claim 3, characterized in that: The hydrogen-fired generator (4) comprises a front compressor (41), a hydrogen combustion chamber (42), a power turbine (43), and a tail nozzle (44) which are arranged in sequence, wherein the front compressor (41) and the power turbine (43) are connected via a central rotating shaft (45), and the front end of the central rotating shaft (45) extends to the front of the front compressor (41) and is connected to a generator (46); The integrated energy management system (5) is connected to the generator (46) and the ignition nozzle of the hydrogen-burning generator (4) through cables; The outlet of the gas hydrogen pipeline (25) is connected to the fuel nozzle of the hydrogen-burning generator (4); When the hydrogen-burning generator (4) is started, the integrated energy management system (5) can control the starter generator (46) to be in an electric mode and supply power to the starter generator (46), so that the starter generator (46) drives the central rotating shaft (45) to rotate. When the rotation speed of the central rotating shaft (45) reaches the starting rotation speed requirement of the hydrogen-burning generator, the integrated energy management system (5) supplies power to the ignition nozzle of the hydrogen-burning generator (4), ignites the hydrogen injected into the hydrogen combustion chamber (42) through the fuel nozzle from the gas hydrogen pipeline (25), and starts the hydrogen-burning generator (4); When the hydrogen-fired generator (4) starts to work and the rotation speed of the central rotating shaft (45) reaches the power extraction rotation speed requirement, the integrated energy management system (5) can control the generator (46) to be in the power generation mode, so that the central rotating shaft (45) drives the generator (46) to generate electricity. The electric energy generated by the generator (46) is stored in the integrated energy management system (5) and supplied to the UAV power supply system (51) and the engine power supply system (52).

5. A method for controlling an engine power system of an unmanned reconnaissance aircraft, for controlling the engine power system of an unmanned reconnaissance aircraft according to claim 4, characterized in that: include: After the engine (1) is started, the integrated energy management system (5) controls the engine power system of the unmanned reconnaissance aircraft to be in a conventional power generation mode; When the electric energy stored in the integrated energy management system (5) is less than 40%, if the unmanned reconnaissance aircraft turns on its electronic reconnaissance equipment, the engine power system of the unmanned reconnaissance aircraft is controlled to be in a superconducting power generation mode. Thereafter, when the electric energy stored in the integrated energy management system (5) is not less than 60%, the engine power system of the unmanned reconnaissance aircraft is controlled to be in a conventional power generation mode. Alternatively, when the electric energy stored in the integrated energy management system (5) is not less than 40% and the unmanned reconnaissance aircraft turns off its electronic reconnaissance equipment, the engine power system of the unmanned reconnaissance aircraft is controlled to be in a conventional power generation mode.

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