Aircraft hybrid transmission system and transmission method thereof

Abstract

The invention discloses an aircraft hybrid transmission system and a transmission method thereof, and belongs to the technical field of aircraft transmission. The input shaft is connected with the engine and the output shaft, the electric / power generation integrated motor, the first planet row and the C1 clutch are arranged on the outer side, the C1 clutch is connected with the input shaft, the first planet row and the second planet row, and the first planet row is connected with the electric / power generation integrated motor and the outer shell; the second planet row is arranged on the outer side of the output shaft in a sleeving mode and connected with the C2 clutch, the C2 clutch is connected with the outer shell, and the output shaft is connected with the flange plate external propeller. The technical defects of a traditional aircraft hybrid transmission system are overcome, the size and mass of the system are reduced, the structural compactness is optimized, the potential safety hazard of power interruption of the traditional system is solved, decoupling transmission of mechanical power and electric power is achieved, the abrasion risk of electro-corrosion to mechanical parts is reduced, and the service life of the system is prolonged. The starting reliability of the system and the emergency capacity in a fault state are improved, and the requirement for full-working-condition operation of the aircraft is met.

Description

Technical Field

[0001] This invention relates to a hybrid transmission system and transmission method for aircraft, belonging to the field of aircraft transmission technology. Background Technology

[0002] Existing aircraft (such as drones and rotorcraft) typically employ a hybrid transmission system combining direct engine drive and generator charging. This system offers advantages such as simple structure and a clear power transmission path, but it also suffers from significant technical drawbacks: Firstly, when the engine fails, the transmission system will completely lose its power output capability, causing the aircraft to be unable to continue operating. Secondly, in hybrid systems, the motor is prone to electro-corrosion during operation, which accelerates the wear of mechanical parts and causes safety hazards. Third, compared to the coaxial transmission system structure, this mode is larger in size and mass, which is not conducive to the lightweight design of the aircraft. Summary of the Invention

[0003] To address the problems existing in the background art, the present invention provides a hybrid transmission system for aircraft and its transmission method.

[0004] To achieve the above objectives, the present invention adopts the following technical solution: a hybrid transmission system for an aircraft, comprising a flange-connected external propeller, a C2 clutch, a C1 clutch, an integrated electric / generator motor, an input shaft, an output shaft, a first planetary gear set, and a second planetary gear set; the input end of the input shaft is fixedly connected to the engine power end, and the output end of the input shaft is coaxially arranged and rotatably connected to the input end of the output shaft; the integrated electric / generator motor, the first planetary gear set, and the C1 clutch are sequentially and coaxially mounted on the outside of the input shaft; the inner hub of the C1 clutch is fixedly connected to the input shaft, and the outer plate of the C1 clutch is connected to both the first and second planetary gear sets; the first planetary gear set is connected to the motor shaft and the outer casing of the integrated electric / generator motor; the second planetary gear set is coaxially mounted on the outside of the input end of the output shaft, and the second planetary gear set is connected to the inner hub of the C2 clutch; the outer plate of the C2 clutch is connected to the outer casing; and the output end of the output shaft is coaxially and fixedly connected to the flange-connected external propeller.

[0005] Furthermore, the first planetary gear set includes a first planetary carrier, a first external gear ring, a first sun gear, and first planet gears; the first planetary carrier is fixedly connected to the outer disk of the C1 clutch, the first planet gear is mounted on the first planetary carrier, the first planet gear is meshed with the first external gear ring and the first sun gear, the first external gear ring is fixedly mounted on the outer casing, and the first sun gear is coaxially rotatably mounted on the outside of the input shaft and fixedly connected to the motor shaft of the electric / generator integrated motor.

[0006] Furthermore, the second planetary gear set includes a second planetary carrier, a second external gear ring, a second sun gear, and second planet gears; the second sun gear is fixedly connected to the outer disk of the C1 clutch, the second sun gear is coaxially rotatably mounted on the outside of the output shaft, the second sun gear is meshed with the second planet gears, the second planet gears are mounted on the second planetary carrier and mesh with the second external gear ring, the second planetary carrier is coaxially fixedly mounted on the outside of the output shaft, and the second external gear ring is fixedly connected to the inner hub of the C2 clutch.

[0007] Furthermore, a ceramic bearing for the electric / generator is coaxially mounted on the outer side of the motor shaft of the electric / generator integrated motor.

[0008] The present invention discloses a method for operating a hybrid power transmission system for an aircraft in power generation mode, the method comprising the following steps: S1: Engages clutch C1, disengages clutch C2, charges the electric motor / generator, and ignites the engine. S2: The input shaft receives the engine input torque and begins to rotate; S3: The input shaft drives the first planetary carrier and the second sun gear to rotate synchronously through the engaged C1 clutch; S4: The first planetary carrier drives the first planetary gear to rotate; S5: The first planetary gear drives the first sun gear to rotate; S6: The first sun gear drives the motor shaft to rotate, charging the electric / generator motor.

[0009] The present invention discloses a method for operating a hybrid transmission system for an aircraft in parallel direct drive mode, the method comprising the following steps: S1: Engages both clutches C1 and C2; puts the electric / generator motor in drive mode and the engine in ignition mode. S2: The input shaft receives the engine input torque and begins to rotate; at the same time, the electric / generator integrated motor drives the first sun gear to rotate through the motor shaft, the first sun gear drives the first planetary gear to rotate, and the first planetary gear drives the first planetary carrier to rotate. S3: The first planetary carrier and the input shaft together drive the C1 clutch to rotate; S4: Clutch C1 drives the second sun gear to rotate; S5: The second sun gear drives the second planetary gear to rotate; S6: The second planetary gear drives the second planetary carrier to rotate; S7: The second planetary carrier drives the output shaft to rotate; S8: The output shaft drives the external propeller of the flange to rotate, outputting torque.

[0010] The present invention discloses a method for operating a hybrid transmission system for an aircraft in direct drive and power generation modes, the method comprising the following steps: S1: Engages both clutches C1 and C2, puts the electric / generator motor in charging mode, and ignites the engine. S2: The input shaft receives the engine input torque and begins to rotate; S3: The input shaft drives the first planetary carrier and the second sun gear to rotate synchronously through the engaged C1 clutch; S4: The first planetary carrier drives the first planetary gear to rotate, the first planetary gear drives the first sun gear to rotate, and the first sun gear drives the motor shaft to rotate, thus charging the electric / generator integrated motor; S5: The second sun gear drives the second planetary gear to rotate, the second planetary gear drives the second planetary carrier to rotate, the second planetary carrier drives the output shaft to rotate, and the output shaft drives the external propeller of the flange to rotate, outputting torque.

[0011] The present invention discloses a method for operating a hybrid transmission system for aircraft in a direct-drive, non-generating mode using an integrated generator / electric generator motor, the method comprising the following steps: S1: Engage both clutches C1 and C2, idling the electric / generator motor and igniting the engine. S2: The input shaft receives the engine input torque and begins to rotate; S3: The input shaft drives the first planetary carrier and the second sun gear to rotate synchronously through the engaged C1 clutch; S4: The second sun gear drives the second planetary gear to rotate, the second planetary gear drives the second planetary carrier to rotate, the second planetary carrier drives the output shaft to rotate, and the output shaft drives the external propeller of the flange to rotate, outputting torque.

[0012] The present invention discloses a method for operating an engine in a reverse-draft start-up mode of a hybrid powertrain system for an aircraft, the method comprising the following steps: S1: Engages clutch C1, disengages clutch C2, puts the electric motor / generator in drive mode, and puts the engine in standby mode. S2: The electric / generator integrated motor drives the first sun gear to rotate through the motor shaft; S3: The first sun gear drives the first planetary gear to rotate; S4: The first planetary gear drives the first planetary carrier to rotate; S5: The first planetary carrier drives the input shaft and the second sun gear to rotate synchronously through the C1 clutch; S6: Input shaft starts the engine.

[0013] The present invention discloses a method for operating a hybrid transmission system of an aircraft in pure electric drive mode, the method comprising the following steps: S1: Disengages clutch C1, engages clutch C2, puts the electric motor / generator in drive mode, and puts the engine in fault mode. S2: The electric / generator integrated motor drives the first sun gear to rotate through the motor shaft; S3: The first sun gear drives the first planetary gear to rotate; S4: The first planetary gear drives the first planetary carrier to rotate; S5: The first planetary carrier drives the second sun gear to rotate through the C1 clutch; S6: The second sun gear drives the second planetary gear to rotate; S7: The second planetary gear drives the second planetary carrier to rotate; S8: The second planetary carrier drives the output shaft to rotate; S9: The output shaft drives the external propeller of the flange to rotate, outputting torque.

[0014] Compared with the prior art, the beneficial effects of the present invention are: This invention achieves flexible switching between six operating modes through a coaxial layout and coordinated control of dual clutches, overcoming the technical defects of traditional aircraft hybrid transmission systems, reducing system size and weight, and optimizing structural compactness. Through separate clutch control, the power path can be promptly disconnected in the event of engine failure, enabling a smooth landing in conjunction with the integrated electric / generator motor, thus resolving the safety hazards of power interruption in traditional systems. The integrated design of the integrated electric / generator motor and planetary gear mechanism achieves decoupled transmission of mechanical and electrical power, reducing the risk of wear on mechanical components due to electro-corrosion. Simultaneously, it is compatible with both engine-back-start mode and pure electric drive mode, improving system startup reliability and emergency response capabilities in fault conditions, meeting the full-condition operation requirements of the aircraft. Attached Figure Description

[0015] Figure 1 This is a schematic diagram of the structure of the present invention; Figure 2 This is a schematic diagram of the transmission process of the power generation mode of the present invention; Figure 3 This is a schematic diagram of the transmission process in the parallel direct drive mode of the present invention; Figure 4 This is a schematic diagram of the transmission process in the direct drive and power generation modes of the present invention; Figure 5 This is a schematic diagram of the transmission process of the direct-drive non-generating mode of the integrated generator / electric generator motor of the present invention; Figure 6 This is a schematic diagram of the transmission process of the engine reverse-dragging start mode of the present invention; Figure 7 This is a schematic diagram of the transmission process in the pure electric drive mode of the present invention. Detailed Implementation

[0016] The technical solutions of the present invention will be clearly and completely described below with reference to the accompanying drawings of the embodiments of the present invention. Obviously, the described embodiments are only some embodiments of the invention, not all embodiments. All other embodiments obtained by those skilled in the art based on the embodiments of the present invention without creative effort are within the scope of protection of the present invention.

[0017] A hybrid transmission system for an aircraft includes a flange-mounted propeller 1, a C2 clutch 3, a C1 clutch 5, an integrated electric motor (MG) 8, an input shaft 10, an output shaft 19, a first planetary gear set, and a second planetary gear set. The input end of the input shaft 10 is fixedly connected to the engine power end. The output end of the input shaft 10 is coaxially arranged with the input end of the output shaft 19 and rotatably connected via a bearing 3 15. The MG 8, the first planetary gear set, and the C1 clutch 5 are coaxially mounted on the outer side of the input shaft 10 along the input-to-output direction. The inner hub of the C1 clutch 5 is fixedly connected to the input shaft 10, and the outer plate of the C1 clutch 5 is connected to both the first and second planetary gear sets. The first planetary gear set is connected to the motor shaft 9 of the MG 8 and its housing. The second planetary gear set is coaxially mounted on the outer side of the input end of the output shaft 19. The second planetary gear set is connected to the inner hub of the C2 clutch 3, and the outer plate of the C2 clutch 3 is connected to the housing. The output end of the output shaft 19 is coaxially fixedly connected to the flange-mounted propeller 1. Clutch C15 controls whether to generate electricity, and clutch C23 controls whether to output power. The opening and closing of clutches C15 and C23 determine the output speed ratio and working mode.

[0018] The motor shaft 9 is supported by bearing 11 and bearing 12, and is coaxial with the input shaft 10. The output shaft 19 is supported by bearing 18.

[0019] Furthermore, the first planetary gear set includes a first planetary carrier 6, a first external gear ring 7, a first sun gear 14, and first planet gears 20; the first planetary carrier 6 is fixedly connected to the outer disk of the C1 clutch 5, the first planetary carrier 6 is equipped with the first planet gears 20, the first planet gears 20 are meshed with the first external gear ring 7 and the first sun gear 14, the first external gear ring 7 is fixedly mounted on the outer shell, and the first sun gear 14 is coaxially rotatably mounted on the outside of the input shaft 10 and fixedly connected to the motor shaft 9 of the electric / generator integrated motor 8.

[0020] Furthermore, the second planetary gear set includes a second planetary carrier 2, a second external gear ring 4, a second sun gear 17, and a second planetary gear 21; the second sun gear 17 is fixedly connected to the outer disk of the C1 clutch 5, the second sun gear 17 is coaxially rotatably mounted on the outside of the output shaft 19, the second sun gear 17 is meshed with the second planetary gear 21, the second planetary gear 21 is mounted on the second planetary carrier 2 and meshes with the second external gear ring 4, the second planetary carrier 2 is coaxially fixedly mounted on the outside of the output shaft 19, and the second external gear ring 4 is fixedly connected to the inner hub of the C2 clutch 3.

[0021] Furthermore, the outer side of the motor shaft 9 of the electric / generator integrated motor 8 is coaxially fitted with an electric / generator integrated motor ceramic bearing 13, which is used in conjunction with a conductive ring to prevent current corrosion of the reducer.

[0022] The present invention discloses a method for operating a hybrid propulsion system for an aircraft in power generation mode (vertical takeoff and landing condition). In power generation mode, the propulsion system generates electricity only, which, together with the battery pack, supplies power to the elevator. The method includes the following steps: S1: Engage clutch C1 5, disengage clutch C2 3, charge electric / generator motor 8, and ignite the engine. S2: Input shaft 10 receives the engine input torque and begins to rotate; S3: The input shaft 10 drives the first planetary carrier 6 and the second sun gear 17 to rotate synchronously through the engaged C1 clutch 5; since the C2 clutch 3 is in the disengaged state, the second external gear ring 4 is in the free state, so the torque of the second sun gear 17 is insufficient to drive the second planetary carrier 2 to drive the output shaft 19 to rotate. S4: The first planetary carrier 6 drives the first planetary gear 20 to rotate; S5: The first planetary gear 20 drives the first sun gear 14 to rotate; S6: The first sun gear 14 drives the motor shaft 9 to rotate, charging the electric / generator motor 8.

[0023] The present invention discloses a method for operating a hybrid powertrain system for aircraft in parallel direct drive mode (transitional and climb modes), wherein an integrated electric / generator motor 8 is torque-coupled with the engine to jointly power the propeller; the method includes the following steps: S1: Both clutches C1 5 and C2 3 are engaged; the electric / generator motor 8 is in drive mode and the engine is in ignition mode. S2: Input shaft 10 receives the input torque from the engine and begins to rotate; at the same time, electric / generator integrated motor 8 drives the first sun gear 14 to rotate through motor shaft 9, the first sun gear 14 drives the first planetary gear 20 to rotate, the first planetary gear 20 drives the first planetary carrier 6 to rotate; S3: The first planetary carrier 6 and the input shaft 10 together drive the C1 clutch 5 to rotate; S4: Clutch 5 in C1 drives the second sun gear 17 to rotate; S5: The second sun gear 17 drives the second planetary gear 21 to rotate; S6: The second planetary gear 21 drives the second planetary carrier 2 to rotate; S7: The second planetary carrier 2 drives the output shaft 19 to rotate; S8: Output shaft 19 drives the external propeller 1 of the flange to rotate, outputting torque.

[0024] The present invention discloses a method for operating a hybrid transmission system for an aircraft in direct drive and power generation mode (cruise condition). The engine directly drives the propeller while the battery pack is in SOC (State of Charge) state. A portion of the engine's torque is allocated to drive an integrated electric / generator motor to generate electricity and charge the battery pack. The method includes the following steps: S1: Both C1 clutch 5 and C2 clutch 3 are engaged, the electric / generator integrated motor 8 is charging, and the engine is ignited. S2: Input shaft 10 receives the engine input torque and begins to rotate; S3: The input shaft 10 drives the first planetary carrier 6 and the second sun gear 17 to rotate synchronously through the engaged C1 clutch 5; S4: The first planetary carrier 6 drives the first planetary gear 20 to rotate, the first planetary gear 20 drives the first sun gear 14 to rotate, the first sun gear 14 drives the motor shaft 9 to rotate, and charges the electric / generator integrated motor 8; S5: The second sun gear 17 drives the second planetary gear 21 to rotate, the second planetary gear 21 drives the second planetary carrier 2 to rotate, the second planetary carrier 2 drives the output shaft 19 to rotate, and the output shaft 19 drives the external propeller 1 of the flange to rotate, outputting torque.

[0025] The present invention discloses a method for operating a hybrid transmission system for aircraft in a direct-drive, non-generating mode (cruise or glide path) of an integrated generator / generator motor. The method includes the following steps: S1: Both C1 clutch 5 and C2 clutch 3 are engaged, the electric / generator motor 8 is in idle state, and the engine is in ignition state. S2: Input shaft 10 receives the engine input torque and begins to rotate; S3: The input shaft 10 drives the first planetary carrier 6 and the second sun gear 17 to rotate synchronously through the engaged C1 clutch 5; the first planetary carrier 6 drives the first planetary gear 20 to rotate, the first planetary gear 20 drives the first sun gear 14 to rotate, and the first sun gear 14 drives the motor shaft 9 to rotate without generating electricity. S4: The second sun gear 17 drives the second planetary gear 21 to rotate, the second planetary gear 21 drives the second planetary carrier 2 to rotate, the second planetary carrier 2 drives the output shaft 19 to rotate, and the output shaft 19 drives the external propeller 1 of the flange to rotate, outputting torque.

[0026] The present invention discloses a method for operating an engine in a hybrid powertrain system of an aircraft in a reverse-draft start-up mode (engine start-up condition), the method comprising the following steps: S1: Engage clutch C1 5, disengage clutch C2 3, put electric / generator motor 8 into drive mode, and put engine into standby mode. S2: The electric / generator integrated motor 8 drives the first sun gear 14 to rotate through the motor shaft 9; S3: The first sun gear 14 drives the first planetary gear 20 to rotate; S4: The first planetary gear 20 drives the first planetary carrier 6 to rotate; S5: The first planetary carrier 6 drives the input shaft 10 and the second sun gear 17 to rotate synchronously through the C1 clutch 5; since the C2 clutch 3 is in the disengaged state, the second external gear ring 4 is in the free state, so the torque of the second sun gear 17 is insufficient to drive the second planetary carrier 2 to drive the output shaft 19 to rotate. S6: Input shaft 10 to start the engine.

[0027] The present invention discloses a method for operating a hybrid powertrain system of an aircraft in pure electric drive mode (engine failure condition), the method comprising the following steps: S1: This puts clutch C1 5 in the disengaged state, clutch C2 3 in the engaged state, the electric / generator motor 8 in the driving state, and the engine in the fault state. S2: The electric / generator integrated motor 8 drives the first sun gear 14 to rotate through the motor shaft 9; S3: The first sun gear 14 drives the first planetary gear 20 to rotate; S4: The first planetary gear 20 drives the first planetary carrier 6 to rotate; S5: The first planetary carrier 6 drives the second sun gear 17 to rotate through the C1 clutch 5; S6: The second sun gear 17 drives the second planetary gear 21 to rotate; S7: The second planetary gear 21 drives the second planetary carrier 2 to rotate; S8: The second planetary carrier 2 drives the output shaft 19 to rotate; S9: Output shaft 19 drives the external propeller 1 of the flange to rotate, outputting torque.

[0028] Table 1 Summary of Various Working Modes

[0029] It will be apparent to those skilled in the art that the present invention is not limited to the details of the exemplary embodiments described above, and that the invention can be implemented in other forms without departing from its spirit or essential characteristics. Therefore, the embodiments should be considered in all respects as exemplary and non-limiting, and the scope of the invention is defined by the appended claims rather than the foregoing description. Thus, all variations falling within the meaning and scope of the equivalents of the claims are intended to be included within the present invention. No reference numerals in the claims should be construed as limiting the scope of the claims.

[0030] Furthermore, it should be understood that although this specification describes embodiments, not every embodiment contains only one independent technical solution. This narrative style is merely for clarity. Those skilled in the art should consider the specification as a whole, and the technical solutions in each embodiment can also be appropriately combined to form other embodiments that can be understood by those skilled in the art.

Claims

1. A hybrid transmission system for an aircraft, characterized in that: The system includes an external flange-mounted propeller (1), a C2 clutch (3), a C1 clutch (5), an integrated electric / generator motor (8), an input shaft (10), an output shaft (19), a first planetary gear set, and a second planetary gear set. The input end of the input shaft (10) is fixedly connected to the engine power end, and the output end of the input shaft (10) is coaxially arranged and rotatably connected to the input end of the output shaft (19). The integrated electric / generator motor (8), the first planetary gear set, and the C1 clutch (5) are coaxially mounted on the outside of the input shaft (10). The inner hub of the clutch (5) is fixedly connected to the input shaft (10). The outer plate of the C1 clutch (5) is connected to both the first planetary gear set and the second planetary gear set. The first planetary gear set is connected to the motor shaft (9) and the housing of the electric / generator integrated motor (8). The second planetary gear set is coaxially mounted on the outside of the input end of the output shaft (19). The second planetary gear set is connected to the inner hub of the C2 clutch (3). The outer plate of the C2 clutch (3) is connected to the housing. The output end of the output shaft (19) is coaxially fixedly connected to the external propeller (1) of the flange.

2. The hybrid transmission system for an aircraft according to claim 1, characterized in that: The first planetary gear set includes a first planetary carrier (6), a first external gear ring (7), a first sun gear (14), and a first planetary gear (20). The first planetary carrier (6) is fixedly connected to the outer disk of the C1 clutch (5). The first planetary gear (20) is mounted on the first planetary carrier (6). The first planetary gear (20) is meshed with the first external gear ring (7) and the first sun gear (14). The first external gear ring (7) is fixedly mounted on the outer shell. The first sun gear (14) is coaxially rotated and mounted on the outside of the input shaft (10) and is fixedly connected to the motor shaft (9) of the electric / generator integrated motor (8).

3. The hybrid transmission system for an aircraft according to claim 2, characterized in that: The second planetary gear set includes a second planetary carrier (2), a second external gear ring (4), a second sun gear (17), and a second planetary gear (21). The second sun gear (17) is fixedly connected to the outer disk of the C1 clutch (5). The second sun gear (17) is coaxially rotated and mounted on the outside of the output shaft (19). The second sun gear (17) is meshed with the second planetary gear (21). The second planetary gear (21) is mounted on the second planetary carrier (2) and meshes with the second external gear ring (4). The second planetary carrier (2) is coaxially fixedly mounted on the outside of the output shaft (19). The second external gear ring (4) is fixedly connected to the inner hub of the C2 clutch (3).

4. The hybrid transmission system for an aircraft according to claim 3, characterized in that: The electric / generator integrated motor (8) has a ceramic bearing (13) coaxially mounted on the outside of the motor shaft (9).

5. A method for operating the power generation mode of an aircraft hybrid transmission system according to any one of claims 1-4, characterized in that: The method includes the following steps: S1: Engage C1 clutch (5), disengage C2 clutch (3), charge the electric / generator motor (8), and ignite the engine. S2: The input shaft (10) receives the engine input torque and begins to rotate; S3: The input shaft (10) drives the first planetary carrier (6) and the second sun gear (17) to rotate synchronously through the engaged C1 clutch (5); S4: The first planetary carrier (6) drives the first planetary gear (20) to rotate; S5: The first planetary gear (20) drives the first sun gear (14) to rotate; S6: The first sun gear (14) drives the motor shaft (9) to rotate, charging the electric / generator motor (8).

6. A method for operating a hybrid powertrain system for an aircraft in parallel direct drive mode according to any one of claims 1-4, characterized in that: The method includes the following steps: S1: Both C1 clutch (5) and C2 clutch (3) are engaged; the electric / generator motor (8) is in drive mode and the engine is in ignition mode; S2: The input shaft (10) receives the input torque from the engine and begins to rotate; at the same time, the electric / generator motor (8) drives the first sun gear (14) to rotate through the motor shaft (9), the first sun gear (14) drives the first planetary gear (20) to rotate, and the first planetary gear (20) drives the first planetary carrier (6) to rotate. S3: The first planetary carrier (6) and the input shaft (10) together drive the C1 clutch (5) to rotate; S4: Clutch (5) C1 drives the second sun gear (17) to rotate; S5: The second sun gear (17) drives the second planetary gear (21) to rotate; S6: The second planetary gear (21) drives the second planetary carrier (2) to rotate; S7: The second planetary carrier (2) drives the output shaft (19) to rotate; S8: The output shaft (19) drives the external propeller (1) of the flange to rotate, outputting torque.

7. A method for operating a hybrid powertrain system for an aircraft in direct drive and power generation modes according to any one of claims 1-4, characterized in that: The method includes the following steps: S1: Both C1 clutch (5) and C2 clutch (3) are engaged, the electric / generator motor (8) is charging, and the engine is ignited. S2: The input shaft (10) receives the engine input torque and begins to rotate; S3: The input shaft (10) drives the first planetary carrier (6) and the second sun gear (17) to rotate synchronously through the engaged C1 clutch (5); S4: The first planetary carrier (6) drives the first planetary gear (20) to rotate, the first planetary gear (20) drives the first sun gear (14) to rotate, the first sun gear (14) drives the motor shaft (9) to rotate, and charges the electric / generator integrated motor (8); S5: The second sun gear (17) drives the second planetary gear (21) to rotate, the second planetary gear (21) drives the second planetary carrier (2) to rotate, the second planetary carrier (2) drives the output shaft (19) to rotate, the output shaft (19) drives the external propeller (1) of the flange to rotate, and outputs torque.

8. A method for operating a hybrid powertrain system for an aircraft in a direct-drive, non-generating mode using an integrated generator / generator motor according to any one of claims 1-4, characterized in that: The method includes the following steps: S1: Both C1 clutch (5) and C2 clutch (3) are engaged, the electric / generator motor (8) is in idle state, and the engine is in ignition state. S2: The input shaft (10) receives the engine input torque and begins to rotate; S3: The input shaft (10) drives the first planetary carrier (6) and the second sun gear (17) to rotate synchronously through the engaged C1 clutch (5); S4: The second sun gear (17) drives the second planetary gear (21) to rotate, the second planetary gear (21) drives the second planetary carrier (2) to rotate, the second planetary carrier (2) drives the output shaft (19) to rotate, the output shaft (19) drives the external propeller (1) of the flange to rotate, and outputs torque.

9. A method for operating the engine in a reverse-draft start-up mode of an aircraft hybrid transmission system according to any one of claims 1-4, characterized in that: The method includes the following steps: S1: Engage clutch (5), disengage clutch (3), drive electric / generator motor (8), and put engine into standby mode. S2: The electric / generator motor (8) drives the first sun gear (14) to rotate through the motor shaft (9); S3: The first sun gear (14) drives the first planetary gear (20) to rotate; S4: The first planetary gear (20) drives the first planetary carrier (6) to rotate; S5: The first planetary carrier (6) drives the input shaft (10) and the second sun gear (17) to rotate synchronously through the C1 clutch (5); S6: Input shaft (10) starts the engine.

10. A method for operating a hybrid powertrain system for an aircraft in pure electric drive mode according to any one of claims 1-4, characterized in that: The method includes the following steps: S1: Make C1 clutch (5) disengaged, make C2 clutch (3) engaged, make electric / generator motor (8) driven, and make engine faulty. S2: The electric / generator motor (8) drives the first sun gear (14) to rotate through the motor shaft (9); S3: The first sun gear (14) drives the first planetary gear (20) to rotate; S4: The first planetary gear (20) drives the first planetary carrier (6) to rotate; S5: The first planetary carrier (6) drives the second sun gear (17) to rotate through the C1 clutch (5); S6: The second sun gear (17) drives the second planetary gear (21) to rotate; S7: The second planetary gear (21) drives the second planetary carrier (2) to rotate; S8: The second planetary carrier (2) drives the output shaft (19) to rotate; S9: The output shaft (19) drives the external propeller (1) of the flange to rotate, outputting torque.

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