Hybrid power generation system for unmanned aerial vehicles

Abstract

The present invention discloses a hybrid power generation system for unmanned aerial vehicles, which includes a micro-turbine generator, a generator controller, an engine controller, a flight control module and an aircraft fuel system; the generator controller is electrically connected to the micro-turbine generator, the generator controller receives the target instruction of the power generation and the feedback information of the micro-turbine generator, and controls the output power, output voltage and output current of the micro-turbine generator; the engine controller controls the fuel supply of the micro-turbine generator; the flight control module sends operation instructions to the generator controller and the engine controller; the aircraft fuel system provides fuel to the micro-turbine generator. The present invention can work efficiently with the aircraft core control unit, accurately follow the dynamic changes of the DC power grid, and can be connected to the DC power grid and disconnected from the grid at any time according to the needs of the aircraft flight control module.

Description

Technical Field

[0001] The present invention relates to the technical field of unmanned aerial vehicles, and in particular to a hybrid power generation system dedicated to unmanned aerial vehicles. Background Art

[0002] Electric-driven unmanned aerial vehicles have developed rapidly in recent years and have been widely used in many fields and played an important role. However, since the propellers of the aircraft require a lot of work power during vertical take-off and landing, most of the battery power on the aircraft is consumed, and the energy-to-mass density of high-power batteries manufactured by existing technologies is relatively low, which makes the aircraft's endurance limited, the air time is short, and it is impossible to provide a large effective load. In order to increase the range and air time, some electric-driven unmanned aerial vehicles used in special occasions add a simple generator set to provide part of the energy for the aircraft, but because the engine, generator and energy storage unit cannot fully cooperate, the efficiency cannot be maximized. In addition, the prior art uses an AC generator, which is converted into DC power by rectification and works in parallel with the energy storage unit and the drive motor. During the working process, the current pulsation impact is large, the power factor of the generator set is low, the equipment is overloaded, and the failure rate is high; the generator set is in an open-loop working state, and cannot be closed-loop controlled, cannot be accurately coordinated with the aircraft master control, and cannot be intelligently interactively controlled. Summary of the invention

[0003] In order to solve the deficiencies of the prior art, the present invention provides a hybrid power generation system dedicated to an unmanned aerial vehicle that can efficiently cooperate with a core control unit of the aircraft.

[0004] To achieve the above object, the present invention provides the following technical solutions:

[0005] A hybrid power generation system for unmanned aerial vehicles, comprising a micro-turbine generator, a generator controller, an engine controller, a flight control module and an aircraft fuel system. The generator controller is electrically connected to the micro-turbine generator, receives target instructions for power generation and feedback information from the micro-turbine generator, and controls the output power, output voltage and output current of the micro-turbine generator. The generator controller converts the AC power generated by the micro-turbine generator into DC power; the engine controller controls the fuel supply of the micro-turbine generator; the flight control module sends operation instructions to the generator controller and the engine controller; and the aircraft fuel system provides fuel to the micro-turbine generator.

[0006] In some embodiments, the hybrid power generation system for unmanned aerial vehicles further includes an energy storage unit electrically connected to the generator controller, and at least a portion of the direct current converted by the generator controller is stored in the energy storage unit.

[0007] In some embodiments, the micro-turbine generator includes a casing, a main shaft, a compressor impeller, a stator, a rotor, a turbine impeller, a compressor casing and a fuel combustion device. Both ends of the main shaft pass through the casing, and the main shaft is rotatably connected to the casing; the compressor impeller is connected to one end of the main shaft; the stator is connected to the casing, and the generator controller is electrically connected to the stator; the rotor is arranged on the compressor impeller, and the rotor rotates with the compressor impeller and generates current in the stator; the turbine impeller is connected to the other end of the main shaft; an air inlet is arranged at one end of the compressor casing, the compressor casing is arranged on the outer sides of the compressor impeller and the casing, and an air inlet passage connected to the air inlet is arranged between the compressor casing and the compressor impeller; the air inlet passage is connected to the fuel combustion device and is used to provide combustion-supporting gas to the fuel combustion device, and the fuel combustion device is used to burn fuel and the generated gas drives the turbine impeller to rotate around the axis of the main shaft; the aircraft fuel system is connected to the fuel combustion device and provides fuel to the fuel combustion device; the compressor casing and / or the fuel combustion device are fixedly connected to the casing.

[0008] In some embodiments, the fuel combustion device includes a turbine casing, a fuel supply nozzle and a spark plug. One end of the turbine casing is connected to the compressor casing, and an exhaust port is provided at one end of the turbine casing away from the compressor casing. A boost chamber and a combustion chamber are provided inside the turbine casing, and one end of the intake passage is connected to the boost chamber. The turbine casing is also provided with a plurality of air holes that connect the boost chamber with the combustion chamber. An exhaust passage connected to the exhaust port is provided between the turbine casing and the turbine impeller, and one end of the exhaust passage is connected to the combustion chamber. The fuel supply nozzle and the spark plug are both connected to the turbine casing and the engine controller, and the fuel supply nozzle is also connected to the aircraft fuel system. One end of the fuel supply nozzle and the spark plug is located in the combustion chamber.

[0009] In some embodiments, the turbine housing includes a plenum housing and a combustion chamber housing connected to each other, the combustion chamber housing is enclosed in the plenum housing, and the air holes are arranged on the combustion chamber housing.

[0010] In some embodiments, the compressor impeller can rotate synchronously with the main shaft, and the main shaft can drive the turbine impeller to rotate synchronously.

[0011] In some embodiments, the rotor is a permanent magnet and the stator is a coil structure.

[0012] In some embodiments, the casing includes a base, a flange mounting plate, a cover plate, and a sleeve. The stator is embedded in the base, and one end of the base is open; the flange mounting plate is detachably connected to the open end of the base, and a through hole is provided on the flange mounting plate; the cover plate is connected to the flange mounting plate to block the through hole; one end of the sleeve is connected to the base, and the other end of the sleeve is connected to the cover plate; the main shaft passes through the base and the cover plate in sequence, and the sleeve is sleeved on the main shaft, and the sleeve is rotatably connected to the main shaft.

[0013] In some embodiments, the base is connected to the compressor casing via fasteners, and the flange mounting plate is connected to the turbine casing via fasteners.

[0014] In some embodiments, a bearing is provided between the sleeve and the main shaft.

[0015] Compared with the prior art, the present invention can efficiently cooperate with the aircraft core control unit, can accurately control the output voltage and current of the micro-turbine generator, accurately follow the dynamic changes of the DC power grid, and can be connected to or disconnected from the DC power grid at any time according to the needs of the aircraft flight control module, which is safe and fast; the micro-turbine generator in the present invention cooperates with the generator controller of the flight control module to work in a closed loop, and the current pulsation impact is small during operation, and mechanical energy is converted into a controllable DC power supply, which can be accurately connected to the DC power grid with the energy storage unit; in addition, the present invention can adjust the power generation according to the needs of the flight control module, realize interconnection, and plan and execute the power generation condition according to the route strategy. BRIEF DESCRIPTION OF THE DRAWINGS

[0016] In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings required for use in the embodiments or the description of the prior art will be briefly introduced below. Obviously, the drawings described below are only some embodiments of the present invention. For ordinary technicians in this field, other drawings can be obtained based on these drawings without paying creative work.

[0017] Figure 1 It is a schematic diagram of the structure of a micro-turbine generator in an embodiment of the present invention.

[0018] Figure 2 It is a cross-sectional view of a micro-turbine generator in an embodiment of the present invention.

[0019] Figure 3 2 is a cross-sectional view of a casing in an embodiment of the present invention, which is symmetrical from top to bottom and only shows the upper half.

[0020] Figure 4 yes Figure 2 A magnified partial view of point A in the middle.

[0021] The following are the descriptions of the reference numerals:

[0022] In the figure: 100, micro-turbine generator; 200, generator controller; 300, engine controller; 400, flight control module; 500, aircraft fuel system; 600, energy storage unit; 1, casing; 101, base; 102, flange mounting plate; 103, cover plate; 104, sleeve; 2, main shaft; 3, compressor impeller; 4, stator; 5, rotor; 6, turbine impeller; 7, compressor casing; 8, fuel combustion device; 801, turbine casing; 8011, boost chamber casing; 8012, combustion chamber casing; 802, spark plug; 803, fuel supply nozzle; 9, fastener; 10, bearing; 11, air inlet; 12, air inlet passage; 13, boost chamber; 14, exhaust passage; 15, exhaust port; 16, combustion chamber; 17, air hole; 18, bolt. DETAILED DESCRIPTION

[0023] To make the purpose, technical solution and advantages of the present invention clearer, the technical solution of the present invention will be described in detail below. Obviously, the described embodiments are only part of the embodiments of the present invention, rather than all the embodiments. Based on the embodiments of the present invention, all other implementation methods obtained by ordinary technicians in this field without creative work belong to the scope of protection of the present invention.

[0024] See also Figure 1-Figure 4 As shown, the present invention provides a hybrid power generation system for unmanned aerial vehicles, which includes a micro-turbine generator 100, a generator controller 200, an engine controller 300, a flight control module 400 and an aircraft fuel system 500. The generator controller 200 is electrically connected to the micro-turbine generator 100, the generator controller 200 receives the target instruction of power generation and the feedback information of the micro-turbine generator 100, and controls the output power, output voltage and output current of the micro-turbine generator 100. The generator controller 200 converts the AC power generated by the micro-turbine generator 100 into DC power; the engine controller 300 controls the fuel supply of the micro-turbine generator 100; the flight control module 400 sends operation instructions to the generator controller 200 and the engine controller 300; and the aircraft fuel system 500 provides fuel to the micro-turbine generator 100.

[0025] In some embodiments, the hybrid power generation system for unmanned aerial vehicles further includes an energy storage unit 600 electrically connected to the generator controller 200, and at least part of the DC power converted by the generator controller 200 is stored in the energy storage unit 600. In a specific implementation, the energy storage unit 600 may be a lithium battery.

[0026] The generator controller 200 in the present invention is mainly composed of a computer and power electronic devices. The three-phase cable of the micro-turbine generator 100 is connected to the U, V, and W terminals of the motor controller. After the power electronic devices are converted by the computer, the AC power is converted into an adjustable DC power supply, which is output from the DC terminal and connected to the DC power grid for use. The computer receives the target instructions for power generation and the sensor feedback information on the micro-turbine generator 100. After calculation, the micro-turbine generator 100 is excited or weakly magnetically controlled through the power electronic devices to achieve the purpose of adjusting the output power, output voltage, and output current, so that the power generation system becomes a controllable and editable DC power supply.

[0027] The generator controller 200 and the engine controller 300 jointly monitor the operating state of the micro-turbine generator 100, and receive the operation instructions of the flight control module 400 through the 1553B bus. In order to achieve the goal of the above-mentioned operation instructions, the conditions and parameters required for the operation of the micro-turbine generator 100 are calculated, the operating conditions of the micro-turbine generator 100 are met through the actuator, and the operating state is monitored by the sensor. After calculation, dynamic adjustment is performed to allow the system to meet the goals issued by the flight control module 400 in the best operating state.

[0028] One or more fuels such as aviation kerosene, natural gas, alcohol, etc. are converted into mechanical energy through the micro-turbine generator. The micro-turbine generator and the generator controller 200 work in a closed loop with the flight control module 400 to convert mechanical energy into a controllable DC power supply, which can be accurately connected to the DC grid with the energy storage unit 600 to provide power for the aircraft. The generator controller 200 can adopt a high-speed permanent magnet generator controller 200, which can accurately control the output voltage and current of the micro-turbine generator 100, accurately follow the dynamic changes of the DC power grid, and can be connected to and disconnected from the DC power grid at any time according to the needs of the aircraft flight control module 400, which is safe and fast. After being connected to the grid, the power generation can be adjusted according to the needs of the flight control module 400, to achieve interconnection and collaborative work, and the power generation condition can be planned and executed according to the route strategy.

[0029] The generator controller 200 in the present invention can enhance the excitation or weaken the magnetic field of the generator through a computer and power electronic devices, and can adjust the power generation according to the target value, that is, the power, voltage, and current can be controlled by a certain magnetic flux angle to control the magnetic field, so that the power generation of the micro-turbine generator 100 is controllable. The computer in the generator controller 200 can obtain the power generation information through the 1553B bus, and can also work in coordination with the micro-turbine generator 100 to create the conditions required for the power generation process. When the DC power grid at the power consumption end changes, the generator controller 200 can also monitor through sensors and feedback to the computer in the generator controller 200 for calculation and adjustment, so as to accurately follow the dynamic changes of the DC power grid and adjust the output. The present invention is equipped with a high-precision controllable power generation component, which can quickly realize the functions of grid connection, grid disconnection, dynamic adjustment, etc. after calculating and receiving the task.

[0030] The generator controller 200 and the engine controller 300 can calculate the workload required by the micro-turbine generator 100 after receiving instructions from the flight control module 400, optimize the best working parameters according to the characteristic table of the micro-turbine generator 100, and issue and execute them to optimize the system working state.

[0031] See also Figures 2 to 4As shown, the above-mentioned micro-turbine generator 100 includes a casing 1, a main shaft 2, a compressor impeller 3, a stator 4, a rotor 5, a turbine impeller 6, a compressor casing 7 and a fuel combustion device 8. Among them, both ends of the main shaft 2 pass through the casing 1, and the main shaft 2 is rotatably connected to the casing 1, and the main shaft 2 can rotate around its own axis; the compressor impeller 3 is connected to the left end of the main shaft 2, and the main shaft 2 can drive the compressor impeller 3 to rotate when it rotates; the stator 4 is fixedly connected to the casing 1, and the rotor 5 is arranged on the compressor impeller 3, and the rotor 5 rotates with the compressor impeller 3 and makes the stator 4 generate current; the stator 4 is electrically connected to the U, V, and W ends of the generator controller 200 through a three-phase cable; in a specific implementation, the rotor 5 is a permanent magnet and the stator 4 is a coil structure; when the compressor impeller 3 rotates, the rotor 5 rotates relative to the stator 4, and the stator 4 cuts the magnetic flux lines of the rotor 5 to generate current in the stator 4; the turbine impeller 6 is connected to the right end of the main shaft 2, and the turbine impeller 6 drives the main shaft 2 to rotate when it rotates; An air inlet 11 for the entry of combustion-supporting gas is provided at one end of the casing 7. The compressor casing 7 is provided on the outside of the compressor impeller 3 and the casing 1. An air inlet passage 12 connected to the air inlet 11 is provided between the compressor casing 7 and the compressor impeller 3. The blades on the compressor impeller 3 are located in the air inlet passage 12. When the compressor impeller 3 rotates, the air at the air inlet 11 is sucked into the air inlet passage 12; the air inlet passage 12 is connected to the fuel combustion device 8 and is used to provide combustion-supporting gas (such as air) to the fuel combustion device 8. The fuel combustion device 8 is used to burn fuel and the generated combustion gas drives the turbine impeller 6 to rotate around the axis of the main shaft 2; the aircraft fuel system 500 is connected to the fuel combustion device 8 and provides fuel to the fuel combustion device 8; the compressor casing 7 and / or the fuel combustion device 8 are fixedly connected to the casing 1.

[0032] The principle of the micro-turbine generator 100 in the present invention is: the high-pressure gas generated by the combustion reaction in the fuel combustion device 8 drives the turbine impeller 6 to rotate during the discharge process, and then the turbine impeller 6 drives the main shaft 2 to rotate. At the same time, the compressor impeller 3 fixed on the main shaft 2 rotates together with the main shaft 2. Under the action of the blades on the compressor impeller 3, the air at the air inlet 11 is sucked into the air inlet channel 12, and the air in the air inlet channel 12 then enters the fuel combustion device 8 to provide combustion-supporting gas for the fuel combustion device 8.

[0033] In the micro-turbine generator 100 provided by the present invention, the compressor impeller 3 and the turbine impeller 6 share the same shaft system, breaking the current situation that the engine, generator, and compressor need to be independently designed and produced, and integrating the functions of the engine, generator, and compressor. It does not need to be equipped with a reducer, the transmission mechanism is simpler, and the overall length of the shaft system is shorter, so that the overall size of the generator is reduced, the weight is reduced, and it is conducive to improving the power-to-weight ratio. When it is used in an aircraft, it can effectively improve the range and load capacity of the aircraft, and greatly improve the overall performance of the aircraft.

[0034] In some embodiments, the fuel combustion device 8 includes a turbine housing 801, a fuel supply nozzle 803 and a spark plug 802. The left end of the turbine housing 801 is connected to the compressor housing 7, and the end of the turbine housing 801 away from the compressor housing 7 is provided with an exhaust port 15. The turbine housing 801 is provided with a boost chamber 13 and a combustion chamber 16. One end of the air inlet passage 12 is connected to the boost chamber 13. The turbine housing 801 is also provided with a plurality of air holes that connect the boost chamber 13 with the combustion chamber 16. An exhaust channel 14 connected to the exhaust port 15 is provided between the turbine housing 801 and the turbine impeller 6. The blades on the turbine impeller 6 are located in the exhaust channel 14. 4, one end of the exhaust passage 14 is connected to the combustion chamber 16; the fuel supply nozzle 803 and the spark plug 802 are both connected to the turbine housing 801 and the engine controller 300, one end of the fuel supply nozzle 803 and the spark plug 802 are located in the combustion chamber 16, and the other end of the fuel supply nozzle 803 is connected to the fuel supply pipeline, and the fuel supply nozzle 803 is used to spray atomized fuel into the combustion chamber 16; the fuel supply nozzle 803 is also connected to the aircraft fuel system 500, and the aircraft fuel system 500 provides fuel to the fuel supply nozzle 803. The structural design of the above fuel combustion device 8 is relatively simple, which is conducive to further reducing the size of the integrated generator, thereby improving the power-to-weight ratio.

[0035] In some embodiments, Figure 2 As shown, the turbine housing 801 includes a boost chamber housing 8011 and a combustion chamber housing 8012 that are connected to each other. The combustion chamber housing 8012 is enclosed in the boost chamber housing 8011, so the combustion chamber 16 will be inside the boost chamber 13, and the air holes are evenly arranged on the combustion chamber housing 8012. The combustion-supporting gas in the air intake passage 12 enters the boost chamber 13 under the action of the compressor impeller 3. After the combustion-supporting gas enters the boost chamber 13, the flow rate decreases, and the pressure of the combustion-supporting gas in the boost chamber 13 increases. The combustion-supporting gas enters the combustion chamber 16 through the air holes and is fully mixed with the fuel. By making the combustion chamber 16 inside the boost chamber 13 and evenly arranged on the combustion chamber housing 8012, the combustion-supporting gas can enter the combustion chamber 16 from different directions, which is conducive to fully and evenly mixing the combustion-supporting gas with the fuel, thereby achieving full combustion of the fuel.

[0036] In some embodiments, the compressor impeller 3 and the turbine impeller 6 are both fixedly connected to the main shaft 2, the compressor impeller 3 can rotate synchronously with the main shaft 2, the main shaft 2 can drive the turbine impeller 6 to rotate synchronously, and the compressor impeller 3 and the turbine impeller 6 have the same rotation speed.

[0037] In some embodiments, the casing 1 includes a base 101, a flange mounting plate 102, a cover plate 103 and a sleeve 104. The stator 4 is embedded in the left end surface of the base 101, and the right end of the base 101 is an open structure; the flange mounting plate 102 is connected to the open end of the base 101 by bolts, and the flange mounting plate 102 is provided with a through hole, and the cover plate 103 is connected to the flange mounting plate 102 to block the through hole on the flange mounting plate 102, and the base 101, the flange mounting plate 102 and the cover plate 103 together constitute a closed cavity; one end of the sleeve 104 is fixedly connected to the base 101 by bolts 18, and the other end of the sleeve 104 is fixedly connected to the cover plate 103 by bolts 18; the main shaft 2 passes through the base 101 and the cover plate 103 in sequence, and the sleeve 104 is sleeved on the main shaft 2, and the sleeve 104 and the main shaft 2 are rotatably connected. In some embodiments, in order to achieve a rotatable connection between the sleeve 104 and the main shaft 2 , two bearings 10 may be disposed between the sleeve 104 and the main shaft 2 .

[0038] In some embodiments, the base 101 is connected to the compressor housing 7 through fasteners 9, and the flange mounting plate 102 is connected to the turbine housing 801 through fasteners 9. This connection method has the advantages of being simple and fast, and is conducive to improving assembly efficiency.

[0039] The above is only a specific embodiment of the present invention, but the protection scope of the present invention is not limited thereto. Any person skilled in the art can easily think of changes or substitutions within the technical scope disclosed by the present invention, which should be included in the protection scope of the present invention. Therefore, the protection scope of the present invention should be based on the protection scope of the claims.

Claims

1. A hybrid power generation system for unmanned aerial vehicles, characterized in that: include: A micro-turbine generator, wherein the micro-turbine generator comprises a sensor, and the sensor is used to monitor the operating state of the micro-turbine generator; An energy storage unit, the energy storage unit is electrically connected to the generator controller, and at least part of the direct current converted by the generator controller is stored in the energy storage unit; A generator controller, which is electrically connected to the micro-turbine generator, and includes power electronic devices and a computer. The generator controller converts the AC power generated by the micro-turbine generator into DC power, and connects the DC power to the energy storage unit. The generator controller controls the micro-turbine generator to or from the DC power grid according to the requirements of the flight control module. When in the grid-connected state, the computer receives the target instruction of power generation and the feedback information of the sensor, and adjusts the output power, output voltage and output current of the micro-turbine generator through power electronic devices based on excitation control or weak magnetic control; An engine controller that controls the amount of fuel supplied to the micro-turbine generator; A flight control module, which sends operation instructions to the generator controller and the engine controller; An aircraft fuel system, which provides fuel to the micro-turbine generator; Among them, after receiving the operation instructions sent by the flight control module, the generator controller and the engine controller calculate the workload required by the micro-turbine generator, and optimize the optimal working parameters according to the characteristic table of the micro-turbine generator.

2. The hybrid power generation system for unmanned aerial vehicles according to claim 1, characterized in that: The micro-turbine generator integrated machine comprises: Receiver; A main shaft, both ends of which pass through the casing, and the main shaft is rotatably connected to the casing; A compressor impeller, the compressor impeller being connected to one end of the main shaft; A stator, wherein the stator is connected to the casing, and the generator controller is electrically connected to the stator; A rotor, wherein the rotor is disposed on the compressor impeller, and the rotor rotates with the compressor impeller and causes the stator to generate current; a turbine impeller connected to the other end of the main shaft; A compressor casing, one end of which is provided with an air inlet, the compressor casing is arranged outside the compressor impeller and the casing, and an air inlet passage communicating with the air inlet is provided between the compressor casing and the compressor impeller; A fuel combustion device, wherein the air inlet passage is connected to the fuel combustion device and used to provide combustion-supporting gas to the fuel combustion device, wherein the fuel combustion device is used to burn fuel and the generated gas drives the turbine impeller to rotate around the axis of the main shaft; the aircraft fuel system is connected to the fuel combustion device and provides fuel to the fuel combustion device; The compressor casing and / or the fuel combustion device are fixedly connected to the casing.

3. The hybrid power generation system for unmanned aerial vehicles according to claim 2, characterized in that: The fuel combustion device comprises: a turbine casing, one end of the turbine casing being connected to the compressor casing, an end of the turbine casing away from the compressor casing being provided with an exhaust port, a boost chamber and a combustion chamber being provided inside the turbine casing, one end of the intake passage being communicated with the boost chamber, a plurality of air holes being provided on the turbine casing for communicating the boost chamber with the combustion chamber, an exhaust passage being communicated with the exhaust port being provided between the turbine casing and the turbine impeller, and one end of the exhaust passage being communicated with the combustion chamber; A fuel supply nozzle and a spark plug, wherein the fuel supply nozzle and the spark plug are both connected to the turbine housing and the engine controller, and the fuel supply nozzle is also connected to the aircraft fuel system, and one end of the fuel supply nozzle and the spark plug is located in the combustion chamber.

4. The hybrid power generation system for unmanned aerial vehicles according to claim 3, characterized in that: The turbine housing includes a boost chamber housing and a combustion chamber housing connected to each other, the combustion chamber housing is enclosed in the boost chamber housing, and the air holes are arranged on the combustion chamber housing.

5. The hybrid power generation system for unmanned aerial vehicles according to claim 4, characterized in that: The compressor impeller rotates synchronously with the main shaft, and the main shaft drives the turbine impeller to rotate synchronously.

6. The hybrid power generation system for unmanned aerial vehicles according to claim 5, characterized in that: The rotor is a permanent magnet, and the stator is a coil structure.

7. The hybrid power generation system for unmanned aerial vehicles according to any one of claims 2 to 6, characterized in that: The casing comprises: A machine base, in which the stator is embedded, and one end of the machine base is open; A flange mounting plate, the flange mounting plate is detachably connected to the open end of the base, and a through hole is provided on the flange mounting plate; A cover plate connected to the flange mounting plate to block the through hole; A shaft sleeve, one end of which is connected to the machine base, and the other end of which is connected to the cover plate; The main shaft passes through the machine base and the cover plate in sequence, the shaft sleeve is sleeved on the main shaft, and the shaft sleeve is rotatably connected to the main shaft.

8. The hybrid power generation system for unmanned aerial vehicles according to claim 7, characterized in that: The base is connected to the compressor casing via fasteners, and the flange mounting plate is connected to the turbine casing via fasteners.

9. The hybrid power generation system for unmanned aerial vehicles according to claim 7, characterized in that: A bearing is arranged between the shaft sleeve and the main shaft.

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