Hybrid aircraft power supply system and hybrid aircraft

Abstract

The utility model relates to a hybrid power aircraft power supply system and a hybrid power aircraft. A direct-current power generation module is connected with an auxiliary power device and a low-voltage direct-current bus bar, and the low-voltage direct-current bus bar is connected with a direct-current load; the alternating-current power generation module is connected with the auxiliary power device, the rectifying and voltage-stabilizing device and the alternating-current bus bar; the rectifying and voltage-stabilizing device is connected with the first high-voltage direct-current bus bar, the second high-voltage direct-current bus bar and the battery pack module; the battery pack module is connected with the first high-voltage direct-current bus bar and the second high-voltage direct-current bus bar; the AC bus bar is connected with an AC load, the first high-voltage DC bus bar is connected with the first electronic speed controller, the second high-voltage DC bus bar is connected with the second electronic speed controller, and the first high-voltage DC bus bar is connected with the second high-voltage DC bus bar. According to the utility model, the safety and reliability of the airplane power supply system are ensured, the reasonable distribution of the power supply is realized, and the normal and independent operation of the other motor can be ensured when a single motor breaks down.

Description

Technical Field

[0001] The utility model relates to the technical field of aviation electrical and power supply, in particular to a hybrid power aircraft power supply system and a hybrid power aircraft. Background Art

[0002] With the global shortage of fuel energy and increasingly prominent environmental problems, it has become an irreversible trend for various types of transportation to use new energy as power. The development of pure electric aircraft is limited by the endurance of power batteries, so a transition solution is needed from traditional engine drive to pure electric drive, namely hybrid drive. However, the power supply system of existing hybrid aircraft cannot switch to the best working mode in time under different working conditions, the energy distribution efficiency of the aircraft is poor, and when the generator fails, the lack of electricity causes its safety and reliability to be low. Therefore, it is an urgent problem to design a suitable hybrid aircraft power supply system for hybrid aircraft to improve the safety and reliability of the aircraft power supply system. Utility Model Content

[0003] In order to solve the above technical problems, the utility model provides a hybrid power aircraft power supply system and a hybrid power aircraft.

[0004] To achieve the above objectives, the present invention provides a hybrid power aircraft power supply system, comprising:

[0005] A DC power generation module, wherein a first port of the DC power generation module is connected to a first port of an auxiliary power unit, a second port of the DC power generation module is connected to a first port of a low-voltage DC bus bar, and a second port of the low-voltage DC bus bar is connected to a DC load of a hybrid aircraft;

[0006] An AC power generation module, wherein a first port of the AC power generation module is connected to a second port of the auxiliary power unit, and a second port of the AC power generation module is respectively connected to a first port of a rectifying and voltage stabilizing device and a first port of an AC bus bar;

[0007] The second port of the rectifying and voltage-stabilizing device is respectively connected to the first port of the first high-voltage DC busbar and the first port of the second high-voltage DC busbar, the third port of the rectifying and voltage-stabilizing device is connected to the first port of the battery module, and the second port of the battery module is respectively connected to the first port of the first high-voltage DC busbar and the first port of the second high-voltage DC busbar;

[0008] The second port of the AC bus is connected to the AC load of the hybrid aircraft, the second port of the first high-voltage DC bus is connected to one end of the first electric regulator, the second port of the second high-voltage DC bus is connected to one end of the second electric regulator, and the first high-voltage DC bus is connected to the second high-voltage DC bus through a power switch.

[0009] Further, the hybrid aircraft power supply system also includes a battery, a battery bus bar and a ground maintenance interface;

[0010] The battery is connected to the battery bus bar;

[0011] The battery bus is respectively connected to the ground maintenance interface, the third port of the DC power generation module and the third port of the low-voltage DC bus.

[0012] Furthermore, the hybrid aircraft power supply system also includes a DC / DC converter, a static converter and a FADEC full authority electronic controller;

[0013] One end of the DC / DC converter is connected to the fourth port of the low-voltage DC bus, and the other end is connected to the third port of the second high-voltage DC bus;

[0014] The FADEC full authority electronic controller is connected to the fifth port of the low voltage DC bus;

[0015] One end of the static converter is connected to the third port of the first high-voltage DC busbar, and the other end is connected to the third port of the AC busbar.

[0016] Further, the DC power generation module includes a DC starter generator, a first voltage regulator and a first generator control unit;

[0017] One end of the first voltage regulator is connected to the DC starter generator, and the other end is connected to one end of the first generator control unit;

[0018] The other end of the first generator control unit is connected to the first port of the low-voltage DC bus;

[0019] The DC starter generator is connected to the first port of the auxiliary power device, the first port of the low-voltage DC bus bar and the battery bus bar respectively through the first port, the second port and the third port of the DC power generation module.

[0020] Further, the AC power generation module includes an AC generator, a second voltage regulator and a second generator control unit;

[0021] One end of the second voltage regulator is connected to the AC generator, and the other end is connected to one end of the second generator control unit;

[0022] The other end of the second generator control unit is connected to the first port of the rectifying and voltage stabilizing device;

[0023] The AC generator is connected to the second port of the auxiliary power unit and the first port of the rectifying and voltage stabilizing device respectively through the first port and the second port of the AC power generation module.

[0024] Further, the battery pack module includes a first battery pack, a second battery pack and a battery management unit;

[0025] The battery management unit is connected to the first battery pack and the second battery pack respectively;

[0026] One end of the first battery pack is connected to the third port of the rectifying and voltage stabilizing device, and the other end is connected to the first port of the first high-voltage DC bus bar;

[0027] One end of the second battery pack is connected to the third port of the rectifying and voltage stabilizing device, and the other end of the second battery pack is connected to the first port of the second high-voltage DC busbar.

[0028] Further, the first electric speed controller is connected to the first motor, and the first motor is connected to the first propeller;

[0029] The second electric speed controller is connected to the second motor, and the second motor is connected to the second propeller.

[0030] Furthermore, the hybrid aircraft power supply system also includes a plurality of power switches, specifically including:

[0031] The AC power generation module is connected to the rectifying and voltage stabilizing device through a first power switch, the AC bus is connected to the AC power generation module through the first power switch and the second power switch, the DC power generation module is connected to the low-voltage DC bus through a third power switch, the battery bus is connected to the DC power generation module through a fourth power switch, the battery bus is connected to the low-voltage DC bus through a fifth power switch, the low-voltage DC bus is connected to the DC / DC converter through a sixth power switch, the second high-voltage DC bus is connected to the rectifying and voltage stabilizing device through a seventh power switch, the second high-voltage DC bus is connected to the second electric regulator through an eighth power switch, the first high-voltage DC bus is connected to the first electric regulator through a ninth power switch, the first high-voltage DC bus is connected to the second high-voltage DC bus through a tenth power switch, the rectifying and voltage stabilizing device is connected to the first high-voltage DC bus through an eleventh power switch, and the AC bus is connected to the static converter through a twelfth power switch.

[0032] Furthermore, the hybrid aircraft power supply system also includes a plurality of fuses, specifically including:

[0033] The low-voltage DC bus is connected to the DC load of the hybrid aircraft through a first fuse, the FADEC full authority electronic controller is connected to the low-voltage DC bus through a second fuse, the AC load of the hybrid aircraft is connected to the AC bus through a third fuse, the DC / DC converter is connected to the second high-voltage DC bus through a fourth fuse, and the first high-voltage DC bus is connected to the static converter through a fifth fuse.

[0034] On the other hand, a hybrid aircraft is provided, which comprises the hybrid aircraft power supply system mentioned above.

[0035] Compared with the prior art, the utility model ensures the safety and reliability of the aircraft power supply system through redundancy design, realizes the reasonable distribution of power by integrating the DC and AC power supplies of the battery and the auxiliary power system, and is based on dual electric regulators to connect dual motors to ensure that when a single motor fails, the other motor can operate normally and independently. BRIEF DESCRIPTION OF THE DRAWINGS

[0036] In order to more clearly illustrate the technical solutions in the embodiments of the present invention, the drawings required for use in the description of the embodiments 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 creative work.

[0037] Figure 1 It is a schematic diagram of the overall structure of the hybrid power aircraft power supply system of the utility model.

[0038] In the figure: 1. DC power generation module; 101. DC starter generator; 102. First generator control unit; 103. First voltage regulator; 2. AC power generation module; 201. AC generator; 202. Second generator control unit; 203. Second voltage regulator; 3. Battery pack module; 301. Second battery pack; 302. First battery pack; 303. Battery management unit; 4. Auxiliary power unit; 5. AC load of hybrid aircraft; 6. AC bus bar; 7. Rectifier and voltage regulator ; 8. Static converter; 9. First high-voltage DC bus; 10. First electric regulator; 11. First motor; 12. First propeller; 13. Second motor; 14. Second electric regulator; 15. Second high-voltage DC bus; 16. DC / DC converter; 17. FADEC full authority electronic controller; 18. Hybrid aircraft DC load; 19. Ground maintenance interface; 20. Battery bus; 21. Battery; 22. Low-voltage DC bus; 23. Second propeller. DETAILED DESCRIPTION

[0039] In order to make the purpose, technical solution and advantages of the utility model clearer, the technical solution in the embodiment of the utility model will be clearly and completely described below in conjunction with the drawings in the embodiment of the utility model. Obviously, the described embodiment is only a part of the embodiment of the utility model, not all of the embodiments. Based on the embodiment of the utility model, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the utility model.

[0040] Example 1: Reference below Figure 1 A structural block diagram of a hybrid power aircraft power supply system according to an embodiment of the utility model is described, including:

[0041] A DC power generation module 1, wherein a first port of the DC power generation module 1 is connected to a first port of an auxiliary power unit 4, a second port of the DC power generation module 1 is connected to a first port of a low-voltage DC bus 22, and a second port of the low-voltage DC bus 22 is connected to a hybrid aircraft DC load 18;

[0042] An AC power generation module 2, wherein a first port of the AC power generation module 2 is connected to a second port of the auxiliary power unit 4, and a second port of the AC power generation module 2 is respectively connected to a first port of a rectifying and voltage stabilizing device 7 and a first port of an AC bus bar 6;

[0043] The second port of the rectifying and voltage-stabilizing device 7 is connected to the first port of the first high-voltage DC bus 9 and the first port of the second high-voltage DC bus 15 respectively, the third port of the rectifying and voltage-stabilizing device 7 is connected to the first port of the battery module 3, and the second port of the battery module 3 is connected to the first port of the first high-voltage DC bus 9 and the first port of the second high-voltage DC bus 15 respectively;

[0044] The second port of the AC bus 6 is connected to the hybrid aircraft AC load 5, the second port of the first high-voltage DC bus 9 is connected to one end of the first electric regulator 10, the second port of the second high-voltage DC bus 15 is connected to one end of the second electric regulator 14, and the first high-voltage DC bus 9 is connected to the second high-voltage DC bus 15 through a power switch.

[0045] In some specific embodiments, when the hybrid aircraft is started, the auxiliary power unit 4 drives the DC power generation module 1 and the AC power generation module 2 to generate electricity using aviation fuel. The DC power generation module 1 generates electricity to the hybrid aircraft DC load 18 through the low-voltage DC bus 22, and the AC power generated by the AC power generation module 2 is rectified and stabilized into DC power through the rectifier and voltage stabilizer 7, and the DC power is generated to the electric regulator through the first high-voltage DC bus 9 and the second high-voltage DC bus 15. When a single electric regulator and motor are damaged, the other electric regulator and motor can be guaranteed to work normally to provide power for the aircraft, and the AC load 5 of the hybrid aircraft is generated through the AC bus 6, and the battery module 3 is generated. In this application, based on the constant speed characteristics of the auxiliary power unit 4, a constant frequency and constant voltage AC motor can be installed. This motor generates less heat and has a higher power conversion efficiency than a variable speed motor, which can achieve more efficient conversion of chemical energy and electrical energy, and integrate the DC and AC power supplies of the battery and the auxiliary power unit 4 to achieve reasonable distribution of power.

[0046] In some embodiments, the hybrid aircraft power supply system further includes a battery 21, a battery bus 20, and a ground maintenance interface 19;

[0047] The battery 21 is connected to the battery bus bar 20;

[0048] The battery bus bar 20 is connected to the ground maintenance interface 19 , the third port of the DC power generation module 1 , and the third port of the low-voltage DC bus bar 22 , respectively.

[0049] In the above embodiment, the battery 21 can provide power to the aircraft through the battery bus 20 in the event of a power outage, ground maintenance, or starting of the auxiliary power unit 4. During ground maintenance, ground maintenance can be performed through the battery 21 or the ground maintenance interface 19, and the safety and reliability of the aircraft power supply system can be ensured through a redundant design.

[0050] In some embodiments, the hybrid aircraft power supply system further includes a DC / DC converter 16, a static converter 8 and a FADEC full authority electronic controller 17;

[0051] One end of the DC / DC converter 16 is connected to the fourth port of the low-voltage DC bus 22, and the other end is connected to the third port of the second high-voltage DC bus 15;

[0052] The FADEC full authority electronic controller 17 is connected to the fifth port of the low voltage DC bus 22;

[0053] One end of the static converter 8 is connected to the third port of the first high-voltage DC bus 9 , and the other end is connected to the third port of the AC bus 6 .

[0054] In the above embodiment, the static inverter 8 is used to convert the high-voltage direct current generated by the battery module 3 into alternating current, and the alternating current directly provided by the alternating current generation module 2 is used together to power the AC load 5 of the hybrid aircraft. This design can continue to ensure that the onboard high-power equipment is available when the auxiliary power unit 4 is shut down. The FADEC full authority electronic controller 17 can be powered by the battery 21 to control the start, fuel supply, operation and shutdown of the auxiliary power unit 4. The high-voltage direct current can be stepped down into low-voltage direct current through the DC / DC converter 16 to provide power for low-voltage electrical equipment. The safety and reliability of the aircraft power supply system can be further improved through redundancy design.

[0055] In some embodiments, the DC power generation module 1 includes a DC starter generator 101, a first voltage regulator 103 and a first generator control unit 102;

[0056] One end of the first voltage regulator 103 is connected to the DC starter generator 101, and the other end is connected to one end of the first generator control unit 102;

[0057] The other end of the first generator control unit 102 is connected to the first port of the low voltage DC bus 22;

[0058] The DC starter generator 101 is connected to the first port of the auxiliary power device 4, the first port of the low-voltage DC bus 22 and the battery bus 20 through the first port, the second port and the third port of the DC power generation module 1 respectively.

[0059] In the above embodiment, the DC starter generator 101 can drive the auxiliary power unit 4 to rotate to a certain speed when starting, the auxiliary power unit 4 ignites and supplies fuel to the rated speed, and switches to the power generation mode to provide DC power for the aircraft, so as to provide power for the DC load 18 equipment of the aircraft.

[0060] In some embodiments, the AC power generation module 2 includes an AC generator 201, a second voltage regulator 203, and a second generator control unit 202;

[0061] One end of the second voltage regulator 203 is connected to the AC generator 201, and the other end is connected to one end of the second generator control unit 202;

[0062] The other end of the second generator control unit 202 is connected to the first port of the rectifying and voltage stabilizing device 7;

[0063] The AC generator 201 is connected to the second port of the auxiliary power unit 4 and the first port of the rectifying and voltage stabilizing device 7 through the first port and the second port of the AC power generation module 2 respectively.

[0064] In the above embodiment, the AC generator 201 rotates to generate AC power of a specific voltage and frequency. The AC power passes through the voltage regulator and the generator control unit, reaches the required frequency and voltage, and is output in two ways. One way enters the AC bus 6 to power the onboard high-power AC equipment, and the other way enters the rectifier and voltage stabilizer 7. The rectifier and voltage stabilizer 7 rectifies and stabilizes the AC power generated by the generator into DC power, and then outputs in two ways. One way enters the high-voltage DC bus to power the electric regulator, and the other way charges the batteries in the battery pack module 3. The redundancy design can further improve the safety and reliability of the aircraft power supply system.

[0065] In some embodiments, the battery pack module 3 includes a first battery pack 302 , a second battery pack 301 , and a battery management unit 303 ;

[0066] The battery management unit 303 is connected to the first battery pack 302 and the second battery pack 301 respectively;

[0067] One end of the first battery pack 302 is connected to the third port of the rectifying and voltage stabilizing device 7, and the other end is connected to the first port of the first high-voltage DC bus bar 9;

[0068] One end of the second battery pack 301 is connected to the third port of the rectifying and voltage stabilizing device 7 , and the other end is connected to the first port of the second high-voltage DC busbar 15 .

[0069] In the above-mentioned embodiment, the battery pack in the battery pack module 3 can provide power for the normal operation of the aircraft, and the battery management unit 303 (BMS management unit) can intelligently manage and maintain each battery cell in the battery pack. Among them, electric aircraft generally use high-power density batteries, and high-power density batteries may cause battery damage or even rupture and explosion when overcharged and over-discharged. The BMS management unit can automatically cut off the voltage input of the rectifier and voltage regulator 7 after the battery is fully charged, and start the charging mode when the battery power is less than a certain level, effectively preventing the battery from being overcharged and over-discharged, extending the battery life, and monitoring the battery status.

[0070] In some embodiments, the first ESC 10 is connected to the first motor 11 , and the first motor 11 is connected to the first propeller 12 ;

[0071] The second electric regulator 14 is connected to the second motor 13 , and the second motor 13 is connected to the second propeller 23 .

[0072] In the above embodiment, the electric motor is a brushless motor, and the electric regulator can provide power and control for the brushless motor to drive the propeller to rotate and provide power for the aircraft. By designing a dual motor, when a single motor fails, the other motor can be guaranteed to operate normally and independently, thereby further improving the safety and reliability of the aircraft power supply system.

[0073] In some specific embodiments, the hybrid aircraft power supply system further includes a plurality of power switches, specifically including:

[0074] The AC power generation module 2 is connected to the rectifying and voltage stabilizing device 7 through the first power switch, the AC bus 6 is connected to the AC power generation module 2 through the first power switch and the second power switch, the DC power generation module 1 is connected to the low-voltage DC bus 22 through the third power switch, the battery bus 20 is connected to the DC power generation module 1 through the fourth power switch, the battery bus 20 is connected to the low-voltage DC bus 22 through the fifth power switch, the low-voltage DC bus 22 is connected to the DC / DC converter 16 through the sixth power switch, the second high-voltage DC bus 15 is connected to the rectifying and voltage stabilizing device 7 through the seventh power switch, the second high-voltage DC bus 15 is connected to the second electric regulator 14 through the eighth power switch, the first high-voltage DC bus 9 is connected to the first electric regulator 10 through the ninth power switch, the first high-voltage DC bus 9 is connected to the second high-voltage DC bus 15 through the tenth power switch, the rectifying and voltage stabilizing device 7 is connected to the first high-voltage DC bus 9 through the eleventh power switch, and the AC bus 6 is connected to the static converter 8 through the twelfth power switch.

[0075] In the above embodiment, the first power switch, the second power switch, the third power switch, the fourth power switch, the fifth power switch, the sixth power switch, the seventh power switch, the eighth power switch, the ninth power switch, the tenth power switch, the eleventh power switch and the twelfth power switch are KM1, KM2, KM3, KM4, KM5, KM6, KM7, KM8, KM9, KM10, KM11 and KM12 respectively, wherein KM1 is connected between the power generated by the AC generator 201 and the aircraft power grid by controlling the main relay of the AC generator 201, KM2 isolates the rectifying and voltage stabilizing device 7 from the AC bus 6, and isolates the rectifying and voltage stabilizing device 7 from the AC power grid when it fails, KM3 is disconnected when the DC starter generator 101 fails, and KM4 is disconnected when the auxiliary power unit 4 It is closed at starting to provide power to the DC starter generator 101. KM5 is closed when ground maintenance is required. KM6 is closed when the aircraft is working normally to provide power to the low-voltage bus. When KM7 is closed, the rectifier and voltage stabilizer 7 provides power to the second high-voltage DC bus 15. When KM8 is closed, the second motor 13 starts to work. When KM9 is closed, the first motor 11 starts to work. When KM10 is closed, the first high-voltage DC bus 9 and the second high-voltage DC bus 15 are connected to the grid and work. When KM11 is closed, the rectifier and voltage stabilizer 7 provides power to the first high-voltage DC bus 9. When KM12 is closed, the static converter 8 acts as a secondary power supply to provide AC power to the AC bus 6. The power supply status of the aircraft is controlled based on the above-mentioned power switch, thereby further improving the safety and reliability of the aircraft power supply system.

[0076] In some specific embodiments, the hybrid aircraft power supply system further includes a plurality of fuses, specifically including:

[0077] The low-voltage DC bus 22 is connected to the hybrid aircraft DC load 18 through a first fuse, the FADEC full authority electronic controller 17 is connected to the low-voltage DC bus 22 through a second fuse, the hybrid aircraft AC load 5 is connected to the AC bus 6 through a third fuse, the DC / DC converter 16 is connected to the second high-voltage DC bus 15 through a fourth fuse, and the first high-voltage DC bus 9 is connected to the static converter 8 through a fifth fuse.

[0078] In the above embodiment, the first fuse, the second fuse, the third fuse, the fourth fuse and the fifth fuse are FU1, FU2, FU3, FU4 and FU5 respectively, and the above fuses can be selected according to the corresponding models of the specific equipment to prevent the equipment from burning.

[0079] Working principle: When the aircraft is working normally, the auxiliary power unit drives the DC starter generator and the AC generator to generate electricity through two output shafts. The AC generator rotates to generate AC power of a specific voltage and frequency. After the AC power passes through the voltage regulator and the generator control unit and reaches the required frequency and voltage, one path enters the AC bus to power the onboard high-power AC equipment, and the other path enters the rectifier and voltage regulator. The rectifier and voltage regulator rectifies and stabilizes the AC power generated by the generator into DC power, and outputs it in two paths. One path enters the high-voltage DC bus after rectification and voltage regulation to power the electric regulator, so that the motor drives the propeller to rotate to provide power for the aircraft, and the other path charges the battery in the battery pack module after rectification and voltage regulation; the DC starter generator drives the auxiliary power unit to rotate to a certain speed, the auxiliary power unit ignites and supplies fuel to the rated speed, and switches to the power generation mode to provide DC power for the aircraft. When the aircraft is powered off, ground maintenance or the auxiliary power unit is started, the battery provides power to the aircraft. This application realizes the reasonable distribution of power by integrating the DC and AC power supplies of the battery and the auxiliary power unit, and improves the safety and reliability of the aircraft power supply by adopting a redundant design to power the hybrid aircraft.

[0080] Embodiment 2: Corresponding to the above-mentioned embodiment 1, the embodiment of the present application also provides a hybrid aircraft, which is equipped with the combined power aircraft power supply system in the above-mentioned embodiment 1. In this embodiment, for the contents that are the same or corresponding to the embodiment 1, please refer to the above introduction and will not be repeated later.

[0081] Note that the above are only preferred embodiments of the present invention and the technical principles used. Those skilled in the art will understand that the present invention is not limited to the specific embodiments described herein, and that various obvious changes, readjustments and substitutions can be made by those skilled in the art without departing from the scope of protection of the present invention. Therefore, although the present invention is described in more detail through the above embodiments, the present invention is not limited to the above embodiments, and may include more other equivalent embodiments without departing from the concept of the present invention, and the scope of the present invention is determined by the scope of the appended claims.

Claims

1. A hybrid power aircraft power supply system, characterized in that: The hybrid aircraft power supply system comprises: A DC power generation module, wherein a first port of the DC power generation module is connected to a first port of an auxiliary power unit, a second port of the DC power generation module is connected to a first port of a low-voltage DC bus bar, and a second port of the low-voltage DC bus bar is connected to a DC load of a hybrid aircraft; An AC power generation module, wherein a first port of the AC power generation module is connected to a second port of the auxiliary power unit, and a second port of the AC power generation module is respectively connected to a first port of a rectifying and voltage stabilizing device and a first port of an AC bus bar; The second port of the rectifying and voltage-stabilizing device is respectively connected to the first port of the first high-voltage DC busbar and the first port of the second high-voltage DC busbar, the third port of the rectifying and voltage-stabilizing device is connected to the first port of the battery module, and the second port of the battery module is respectively connected to the first port of the first high-voltage DC busbar and the first port of the second high-voltage DC busbar; The second port of the AC bus is connected to the AC load of the hybrid aircraft, the second port of the first high-voltage DC bus is connected to one end of the first electric regulator, the second port of the second high-voltage DC bus is connected to one end of the second electric regulator, and the first high-voltage DC bus is connected to the second high-voltage DC bus through a power switch.

2. The hybrid power aircraft power supply system according to claim 1, characterized in that: The hybrid aircraft power supply system also includes a battery, a battery bus bar and a ground maintenance interface; The battery is connected to the battery bus bar; The battery bus is respectively connected to the ground maintenance interface, the third port of the DC power generation module and the third port of the low-voltage DC bus.

3. The hybrid aircraft power supply system according to claim 1, characterized in that: The hybrid aircraft power supply system also includes a DC / DC converter, a static converter and a FADEC full authority electronic controller; One end of the DC / DC converter is connected to the fourth port of the low-voltage DC bus, and the other end is connected to the third port of the second high-voltage DC bus; The FADEC full authority electronic controller is connected to the fifth port of the low voltage DC bus; One end of the static converter is connected to the third port of the first high-voltage DC busbar, and the other end is connected to the third port of the AC busbar.

4. The hybrid aircraft power supply system according to claim 1, characterized in that: The DC power generation module includes a DC starter generator, a first voltage regulator and a first generator control unit; One end of the first voltage regulator is connected to the DC starter generator, and the other end is connected to one end of the first generator control unit; The other end of the first generator control unit is connected to the first port of the low-voltage DC bus; The DC starter generator is connected to the first port of the auxiliary power device, the first port of the low-voltage DC bus bar and the battery bus bar respectively through the first port, the second port and the third port of the DC power generation module.

5. The hybrid aircraft power supply system according to claim 1, characterized in that: The AC power generation module includes an AC generator, a second voltage regulator and a second generator control unit; One end of the second voltage regulator is connected to the AC generator, and the other end is connected to one end of the second generator control unit; The other end of the second generator control unit is connected to the first port of the rectifying and voltage stabilizing device; The AC generator is connected to the second port of the auxiliary power unit and the first port of the rectifying and voltage stabilizing device respectively through the first port and the second port of the AC power generation module.

6. The hybrid aircraft power supply system according to claim 1, characterized in that: The battery pack module includes a first battery pack, a second battery pack and a battery management unit; The battery management unit is connected to the first battery pack and the second battery pack respectively; One end of the first battery pack is connected to the third port of the rectifying and voltage stabilizing device, and the other end is connected to the first port of the first high-voltage DC bus bar; One end of the second battery pack is connected to the third port of the rectifying and voltage stabilizing device, and the other end of the second battery pack is connected to the first port of the second high-voltage DC busbar.

7. The hybrid power aircraft power supply system according to claim 1, characterized in that: The first electric regulator is connected to the first motor, and the first motor is connected to the first propeller; The second electric speed controller is connected to the second motor, and the second motor is connected to the second propeller.

8. The hybrid power aircraft power supply system according to claim 1, characterized in that: The hybrid aircraft power supply system further includes a plurality of power switches, specifically including: The AC power generation module is connected to the rectifying and voltage stabilizing device through a first power switch, the AC bus is connected to the AC power generation module through the first power switch and the second power switch, the DC power generation module is connected to the low-voltage DC bus through a third power switch, the battery bus is connected to the DC power generation module through a fourth power switch, the battery bus is connected to the low-voltage DC bus through a fifth power switch, the low-voltage DC bus is connected to the DC / DC converter through a sixth power switch, the second high-voltage DC bus is connected to the rectifying and voltage stabilizing device through a seventh power switch, the second high-voltage DC bus is connected to the second electric regulator through an eighth power switch, the first high-voltage DC bus is connected to the first electric regulator through a ninth power switch, the first high-voltage DC bus is connected to the second high-voltage DC bus through a tenth power switch, the rectifying and voltage stabilizing device is connected to the first high-voltage DC bus through an eleventh power switch, and the AC bus is connected to the static converter through a twelfth power switch.

9. The hybrid power aircraft power supply system according to claim 1, characterized in that: The hybrid aircraft power supply system further includes a plurality of fuses, specifically including: The low-voltage DC bus is connected to the DC load of the hybrid aircraft through a first fuse, the FADEC full authority electronic controller is connected to the low-voltage DC bus through a second fuse, the AC load of the hybrid aircraft is connected to the AC bus through a third fuse, the DC / DC converter is connected to the second high-voltage DC bus through a fourth fuse, and the first high-voltage DC bus is connected to the static converter through a fifth fuse.

10. A hybrid aircraft, characterized in that: The hybrid power aircraft power supply system comprises the hybrid power aircraft power supply system as claimed in any one of claims 1 to 9.

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