A tiltable power system and method for an electric vertical takeoff and landing aircraft

Abstract

The application relates to a tiltable power system and method for an electric vertical take-off and landing (eVTOL) aircraft. The application comprises a tiltable nacelle, the tiltable nacelle comprising a tilting bracket and a mounting bracket connected to each other, the tilting bracket comprising a fixed shaft and a bracket body rotatable around a central axis of the fixed shaft, one end of the fixed shaft being provided with a wing mechanical interface for being connected to a wing of the eVTOL aircraft, the tilting bracket being provided with a rudder mechanical interface at an end away from the fixed shaft; a propulsion motor mounted on the mounting bracket; a propeller connected to a driving end of the propulsion motor for receiving rotational power of the propulsion motor to rotate; a tilting rudder connected to the rudder mechanical interface; a rudder controller electrically connected to the tilting rudder; and the tilting rudder being capable of driving the tiltable nacelle to tilt around the fixed shaft according to a flight control instruction received by the rudder controller, so as to realize flight attitude switching of the eVTOL aircraft. The application improves design simplicity and overall reliability of the eVTOL power system.

Description

Technical Field

[0001] This invention relates to the field of electric powertrain technology, and in particular to a tiltable power system and method for an electric vertical takeoff and landing aircraft. Background Technology

[0002] Electric vertical take-off and landing (eVTOL) aircraft can take off and land vertically without a runway, making them particularly suitable for future urban short-distance transportation and urban passenger transport. eVTOLs generally use distributed electric propulsion, which has the characteristics of high energy efficiency, low noise, zero emissions and green environmental protection. They are representative products in the field of low-altitude general aviation and have become a current research hotspot.

[0003] like Figure 1 As shown, a certain type of eVTOL aircraft uses six electric rotors (M2-M5 are tiltrotors, M1 and M6 are fixed rotors). Its flight states include a multi-rotor phase (6 rotors for vertical takeoff and hovering, 4 rotors for emergency landing), a tilt transition phase, and a fixed-wing phase (4 rotors for horizontal cruise). M2, M3, M4, and M5 use variable-pitch propellers, which can provide lift during vertical takeoff and hovering, and can also provide power to the fixed-wing aircraft during climb, cruise, and descent by tilting. M1 and M6 use fixed-pitch propellers, which can provide lift during vertical takeoff and hovering, but do not have tilting capabilities.

[0004] Therefore, there is an urgent need to provide a tiltable eVTOL power system to improve the modularity, integration level and structural simplicity of the eVTOL power system. Summary of the Invention

[0005] Therefore, the present invention provides a tiltable propulsion system and method for electric vertical take-off and landing (eVTOL) aircraft, which can realize power output and attitude switching in different flight states. By adopting a modular and integrated electric powertrain architecture, the power system structure is more compact and the layout is more reasonable, thereby improving the design simplicity and overall reliability of the eVTOL power system.

[0006] To address the aforementioned technical problems, this invention provides a tiltable propulsion system for an electric vertical takeoff and landing (EVTOL) aircraft, comprising: The tilting nacelle includes a tilting support and a mounting bracket connected to each other. The tilting support includes a fixed shaft and a support body rotatable about the central axis of the fixed shaft. One end of the fixed shaft is provided with a wing mechanical interface for connecting with the wing of an electric vertical take-off and landing aircraft, and the end of the tilting support away from the fixed shaft is provided with a servo mechanical interface. The propulsion motor is mounted on the mounting bracket. The propeller is connected to the drive end of the propulsion motor and is used to receive the rotational power of the propulsion motor to rotate. A tilt servo motor, connected to the servo motor mechanical interface; The servo controller is electrically connected to the tilt servo. The tilt servo can drive the tilt nacelle to tilt around the fixed axis according to the flight control command received by the servo controller, thereby realizing the flight attitude switching of the electric vertical take-off and landing aircraft.

[0007] In one embodiment of the present invention, the fixed shaft is provided with a support bearing, and the support body tilts about the fixed shaft via the support bearing.

[0008] In one embodiment of the present invention, the support bearing includes tapered roller bearings located at both ends of the fixed shaft.

[0009] In one embodiment of the present invention, the fixed shaft is a hollow structure so that flight control signal lines and power lines are laid through the hollow structure of the fixed shaft.

[0010] In one embodiment of the present invention, the tilt servo includes a cooperating drive motor, a reducer, and a brake. The drive motor and the reducer are connected. The servo mechanical interface includes a fixed shaft stationary part and a support body stationary part. The rotating end of the tilt servo is connected to the fixed shaft stationary part, and the mounting stationary part of the tilt servo is connected to the support body stationary part.

[0011] In one embodiment of the present invention, the tilting nacelle includes an upper support, a middle support, and a lower support that are connected in sequence and are respectively in an annular shape. The upper end face of the upper support is provided with a plurality of mounting ears for mounting the propulsion motor. The outer peripheral ends of the middle support and the lower support are used for mounting the outer skin structure.

[0012] In one embodiment of the present invention, the outer peripheral ends of the middle support and the lower support are provided with fixing holes for fixing the outer skin structure, the tilting support is installed on the middle support, a lower support rod is connected between the middle support and the lower support, and an auxiliary support rod is connected between the middle support and the tilting support.

[0013] In one embodiment of the present invention, the outer skin structure includes a first outer skin and a second outer skin, wherein the first outer skin is installed between the upper support and the middle support, and the second outer skin is installed between the middle support and the lower support.

[0014] In one embodiment of the present invention, a ventilation gap is left between the side of the outer skin structure near the propeller and the outer periphery of the propulsion motor, and a tail air outlet is provided between the bottom end of the lower bracket and the outer skin structure; The middle support has through holes on its flat surface to serve as a heat dissipation airflow channel; A mounting ear gap communicating with the ventilation gap is formed between the plurality of mounting ears and the upper end face of the upper bracket; The upper bracket and the middle bracket are provided with a first mounting area that communicates with the mounting ear gap; The middle support and the lower support are provided with a second mounting area, and the servo controller and the tilt support are installed in the second mounting area; The propulsion motor is equipped with a cooling fan and a radiator installed in the first installation area; The airflow generated by the propeller flows through the ventilation gap, passes through the propulsion motor, reaches the upper bracket, and enters the first mounting area through the mounting ear gap. It is then drawn in by the cooling fan of the propulsion motor and flows through the radiator. After being cooled, the airflow enters the second mounting area through the through hole of the middle bracket, flows through the tilt servo and the servo controller, and is finally discharged from the tail exhaust port.

[0015] The present invention also provides a control method for a tiltable propulsion system of an electric vertical takeoff and landing (EVTOL) aircraft. Utilizing the aforementioned tiltable propulsion system for an EVTOL aircraft, the control method includes: The servo controller receives the flight attitude switching command from the flight control system and sends a drive signal to the tilt servo, causing the tilt servo to drive the tilt nacelle to tilt around the fixed axis, thereby realizing the attitude switching of the electric vertical take-off and landing aircraft. During the operation of the tilting power system, the airflow generated by the rotation of the propeller is used as a heat dissipation air source. The airflow generated by the propeller flows through the ventilation gap, passes through the propulsion motor, reaches the upper bracket, and enters the first installation area through the mounting ear gap. It is then drawn in by the cooling fan of the propulsion motor and flows through the radiator. After being cooled, the airflow enters the second mounting area through the through hole of the middle bracket, flows through the tilt servo and the servo controller, and is finally discharged from the tail exhaust port, thereby achieving heat dissipation for the propulsion motor, servo controller and tilt servo.

[0016] The technical solution of the present invention has the following advantages compared with the prior art: The present invention discloses a tiltable propulsion system and method for an electric vertical takeoff and landing (eVTOL) aircraft, which integrates a propeller, a propulsion motor, a tilt servo, a servo controller, and a tilt nacelle. As an independent power unit, this power system only needs to be mechanically fixedly connected to the wingtip of the eVTOL aircraft and connected to the power lines of the energy system / electrical system and the signal lines of the flight control system to achieve power output and tilting around the wingtip. The modular and integrated design of the electric powertrain architecture facilitates rapid installation and integration with the eVTOL, greatly improving the simplified design of the eVTOL power system. This invention employs a bearing-supported tilting structure. The main support body achieves smooth tilting through tapered roller bearings arranged at both ends of a fixed shaft. The bearings simultaneously bear the radial and axial loads of the system, allowing the tilting servo to output only tilting torque without being affected by structural external forces. This design significantly reduces the mechanical burden on the servo, improves servo lifespan and system control accuracy, and ensures smoothness and safety during flight attitude transitions.

[0017] The fixed axis and tilt servo of this invention adopt a hollow structure design. The internal space is used for the laying of flight control signal lines and power lines, avoiding the exposure of external cables, improving the safety and anti-interference of wiring harnesses, and reducing structural complexity, making the internal wiring of the assembly simpler and more reliable.

[0018] The tilting nacelle of this invention adopts a three-stage load-bearing structure consisting of an upper support, a middle support, and a lower support. Combined with the annular wrapping design of the outer skin, it forms a nacelle frame with continuous aerodynamic shape and high structural strength. Through the rational arrangement of the upper strut, lower strut, and auxiliary struts, a mechanical layout that balances high rigidity and lightweight is achieved, ensuring the overall stability of the tilting structure during high-speed rotation and attitude switching.

[0019] This invention addresses the heat dissipation requirements of the high-power propulsion motor and servo system in eVTOL by proposing an integrated air-cooling ventilation solution. The airflow generated by the propeller rotation enters the upper support through the ventilation gap between the outer skin and the propulsion motor, is drawn in by the cooling fan through the mounting lugs, flows through the radiator, and sequentially cools the propulsion motor, tilt servo, and servo controller before being exhausted through the tail exhaust vent. This heat dissipation path utilizes the natural guidance of flight airflow to form a circulating cooling channel, achieving continuous and efficient heat dissipation without additional energy consumption, ensuring the system maintains a stable temperature under high load and long-term operating conditions. Attached Figure Description

[0020] To make the content of this invention easier to understand, the invention will be further described in detail below with reference to specific embodiments and accompanying drawings.

[0021] Figure 1 This is a diagram showing the layout of the power unit for an electric vertical takeoff and landing (EVTOL) aircraft.

[0022] Figure 2 This invention provides the composition and schematic diagram of a tiltable propulsion system for an electric vertical takeoff and landing aircraft.

[0023] Figure 3 This is a schematic diagram of the overall external structure of a tiltable propulsion system for an electric vertical takeoff and landing aircraft according to the present invention.

[0024] Figure 4 This is a schematic diagram of the internal structure of a tiltable propulsion system for an electric vertical takeoff and landing aircraft according to the present invention. Figure 1 .

[0025] Figure 5 This is a schematic diagram of the internal structure of a tiltable propulsion system for an electric vertical takeoff and landing aircraft according to the present invention. Figure 2 .

[0026] Figure 6 This is a schematic diagram of a tiltable nacelle structure for a tiltable propulsion system of an electric vertical takeoff and landing aircraft according to the present invention. Figure 1 .

[0027] Figure 7 This is a schematic diagram of a tiltable nacelle structure for a tiltable propulsion system of an electric vertical takeoff and landing aircraft according to the present invention. Figure 2 .

[0028] Figure 8 This is a schematic diagram of the tilting nacelle of a tilting propulsion system for an electric vertical takeoff and landing aircraft according to the present invention.

[0029] Figure 9 This is a partial schematic diagram of the mechanical interface of a tiltable propulsion system for an electric vertical takeoff and landing aircraft according to the present invention.

[0030] Figure 10 This is a schematic diagram of a tilt servo mechanism structure for a tiltable propulsion system of an electric vertical takeoff and landing aircraft according to the present invention.

[0031] Figure 11 This is a schematic diagram of the heat dissipation of a tiltable propulsion system for an electric vertical takeoff and landing aircraft according to the present invention.

[0032] Explanation of reference numerals in the instruction manual: 1. Propeller; 2. Propulsion motor; 3. First outer skin; 3a. Ventilation gap; 4. Second outer skin; 5. Wing mechanical interface; 6. Tilting nacelle; 7. Servo controller; 8. Tilting servo; 8a. Mounting stationary part; 9. Tail vent; 10. Upper support; 10a. Mounting lug; 10b. Mounting lug gap; 11. Upper strut; 12. Middle support; 12a. Middle support through hole; 13. Tilting support; 14. Lower support; 15. Lower strut; 16. Auxiliary strut; 17. Fixed shaft; 18. Support bearing; 19. Hollow structure; 20. Servo mechanical interface; 20a. Fixed shaft stationary part; 20b. Support body stationary part; 21. Support body; 22. Reducer; 23. Brake; 24. Drive motor; 25. Cooling fan; 26. Radiator. Detailed Implementation

[0033] The present invention will be further described below with reference to the accompanying drawings and specific embodiments, so that those skilled in the art can better understand and implement the present invention. However, the embodiments described are not intended to limit the present invention.

[0034] In this invention, when directions (up, down, left, right, front, and back) are described, it is only for the convenience of describing the technical solution of this invention, and does not indicate or imply that the technical features referred to must have a specific orientation, or be constructed and operated in a specific orientation. Therefore, it should not be construed as a limitation of this invention.

[0035] In this invention, "several" means one or more, "multiple" means two or more, "greater than," "less than," "exceeding," etc., are understood to exclude the stated number; "above," "below," "within," etc., are understood to include the stated number. In the description of this invention, the terms "first" and "second" are used only to distinguish technical features and should not be construed as indicating or implying relative importance, or implicitly indicating the number of indicated technical features, or implicitly indicating the order of the indicated technical features.

[0036] In this invention, unless otherwise explicitly defined, the terms "setting," "installing," and "connecting" should be interpreted broadly. For example, they can refer to a direct connection or an indirect connection through an intermediate medium; a fixed connection, a detachable connection, or an integrally formed connection; a mechanical connection, an electrical connection, or a connection capable of mutual communication; or the internal connection of two components or the interaction between two components. Those skilled in the art can reasonably determine the specific meaning of the above terms in this invention based on the specific content of the technical solution.

[0037] Reference Figure 2 As shown, a tiltable propulsion system for an electric vertical takeoff and landing aircraft according to the present invention includes: The tilting nacelle 6 includes a tilting support 13 and a mounting bracket connected to each other. The tilting support 13 includes a fixed shaft 17 and a support body 21 rotatable around the central axis of the fixed shaft 17. One end of the fixed shaft 17 is provided with a wing mechanical interface 5 for connecting to the wing of the electric vertical takeoff and landing (eVTOL) aircraft. The end of the tilting support 13 away from the fixed shaft 17 is provided with a servo mechanical interface 20. As the core of the tilting nacelle 6 structure, the tilting support 13 provides a fixed connection to the eVTOL wing on one side and provides the installation of the tilting servo 8 on the other side, realizing the support and tilting of the entire tilting nacelle 6. The propulsion motor 2 is mounted on the mounting bracket; The propeller 1 is connected to the drive end of the propulsion motor 2 and is used to receive the rotational power of the propulsion motor 2 to rotate. The tilt servo motor 8 is connected to the servo motor mechanical interface 20; Servo controller 7 is electrically connected to the tilt servo 8; servo controller 7 is a microcontroller (MCU). The tilt servo 8 can drive the tilt nacelle 6 to tilt around the fixed axis 17 according to the flight control command received by the servo controller 7, thereby realizing the flight attitude switching of the electric vertical take-off and landing aircraft.

[0038] Furthermore, it should be noted that this tiltable propulsion system is fixedly connected to the wingtip of the eVTOL wing via the wing mechanical interface 5, connected to the energy system or power system via the electrical interface, and connected to the flight control system via the signal interface. Its working principle is as follows: the propulsion motor 2 converts electrical energy from the energy system or power system into mechanical energy to drive the propeller 1 to rotate; the servo controller 7 receives commands from the flight control system and controls the tilt servo 8 to move, thereby driving the tilt nacelle 6 to rotate around the fixed axis 17, realizing the switching of the eVTOL's flight attitude.

[0039] By integrating key components such as propeller 1, propulsion motor 2, tilt servo 8, servo controller 7, and tilt nacelle 6 into a single independent power module, a fully detachable electric powertrain unit is formed. This module can be directly installed on the wingtip of the eVTOL aircraft, enabling rapid connection and commissioning through mechanical, electrical, and signal interfaces. This significantly improves the integration and assembly efficiency of the power system, facilitating maintenance, replacement, and future expansion, thereby achieving modular and standardized management of the power system.

[0040] In one embodiment, refer to Figure 8As shown, the fixed shaft 17 is equipped with a support bearing 18, and the support body 21 tilts about the fixed shaft 17 via the support bearing 18. Specifically, the support bearing 18 includes (two) tapered roller bearings located at both ends of the fixed shaft 17, but is not limited thereto. The two tapered roller bearings enable the support body 21 to tilt about the fixed shaft 17 and withstand external loads.

[0041] In one embodiment, refer to Figure 8 As shown, the fixed shaft 17 is a hollow structure 19, so that flight control signal lines and power lines can be laid through the hollow structure 19 of the fixed shaft 17 to provide control signals and power to the electric powertrain architecture.

[0042] In one embodiment, refer to Figure 9 , Figure 10 As shown, the tilt servo 8 includes a cooperating drive motor 24, a reducer 22, and a brake 23. The drive motor 24 and the reducer 22 are connected. The servo mechanical interface 20 includes a fixed shaft stationary part 20a and a support body stationary part 20b. The rotating end of the tilt servo 8 is connected to the fixed shaft stationary part 20a, and the mounting stationary part 8a of the tilt servo 8 is connected to the support body stationary part 20b, thereby realizing the drive of the tilt nacelle 6 by the tilt servo 8, causing the nacelle to rotate around the fixed shaft 17 to achieve attitude switching.

[0043] Furthermore, the tilt servo 8 employs a hollow design to facilitate wiring. Figure 8 As shown in the structure, the tilt servo 8 only provides tilt torque and does not bear the external load of the electric powertrain architecture.

[0044] See Figure 4 and Figure 5 As shown, the tilt nacelle 6 constitutes the main support and installation platform of the electric powertrain architecture; the servo controller 7, as the control device of the tilt servo 8, receives signals from the flight control system and controls the rotation of the tilt servo 8 to drive the electric powertrain architecture to tilt around the fixed axis 17.

[0045] In one embodiment, refer to Figure 6 As shown, the tilting nacelle 6 includes an upper support 10, a middle support 12 and a lower support 14 connected in sequence and forming an annular shape. The upper end face of the upper support 10 is provided with a plurality of mounting ears 10a for mounting the propulsion motor 2. The outer peripheral ends of the middle support 12 and the lower support 14 are used for mounting the outer skin structure.

[0046] Specifically, the outer peripheral ends of the middle support 12 and the lower support 14 are provided with fixing holes for fixing the outer skin structure. The tilting support 13 is installed on the middle support 12. A lower support rod 15 is connected between the middle support 12 and the lower support 14. An auxiliary support rod 16 is connected between the middle support 12 and the tilting support 13.

[0047] In one embodiment, refer to Figure 3 As shown, the outer skin structure includes a first outer skin 3 and a second outer skin 4. The first outer skin 3 is installed between the upper support 10 and the middle support 12, and the second outer skin 4 is installed between the middle support 12 and the lower support 14. The tilting nacelle 6 adopts, but is not limited to, structural component splicing, and can be selected according to actual application requirements. The first outer skin 3 and the second outer skin 4 can be fixed to the outside of the tilting nacelle 6 by screws or rivets.

[0048] The tilting nacelle 6 adopts a three-stage load-bearing structure consisting of an upper support 10, a middle support 12, and a lower support 14. Combined with the annular wrapping design of the outer skin structure, it forms a nacelle frame with continuous aerodynamic shape and high structural strength. Through the rational arrangement of the upper strut 11, lower strut 15, and auxiliary strut 16, a mechanical layout that balances high rigidity and lightweight is achieved, ensuring the overall stability of the tilting structure during high-speed rotation and attitude switching.

[0049] See Figure 3 The tiltable propulsion system is an independent module. The propeller 1 generates thrust, and the propulsion motor 2 is the core power component. The first outer skin 3 and the second outer skin 4 form the aerodynamic shape, which can be optimized according to the design requirements of the eVTOL. The wing mechanical interface 5 is the structural interface connecting the tiltable propulsion system to the eVTOL wing and is part of the fixed shaft 17. A triangularly distributed bolt connection can be used, but it is not limited to this; different connection methods can be selected according to the actual application scenario.

[0050] In one embodiment, refer to Figure 5 , Figure 11 As shown, considering the heat dissipation requirements of the high-power propulsion motor 2, the tilting power system incorporates an air-cooled heat dissipation structure in its design. A ventilation gap 3a is provided between the side of the outer skin structure closest to the propeller 1 and the outer periphery of the propulsion motor 2. A tail exhaust vent 9 is provided between the bottom end of the lower support 14 and the outer skin structure; the tail exhaust vent 9 serves as the final outlet for internal airflow cooling. The middle support 12 has a through hole 12a on its plane to serve as a heat dissipation airflow channel; A mounting ear gap 10b communicating with the ventilation gap 3a is formed between the plurality of mounting ears 10a and the upper end face of the upper bracket 10; The upper bracket 10 and the middle bracket 12 are provided with a first mounting area that communicates with the mounting ear gap 10b; The middle support 12 and the lower support 14 are provided with a second installation area, and the servo controller 7 and the tilt support 13 are installed in the second installation area; The propulsion motor 2 is equipped with a cooling fan 25 and a radiator 26 installed in the first installation area; The airflow generated by the propeller 1 flows through the ventilation gap 3a, passes through the propulsion motor 2, reaches the upper bracket 10, and enters the first installation area through the mounting ear gap 10b. It is then drawn in by the cooling fan 25 of the propulsion motor 2 and flows through the radiator 26. The cooled airflow enters the second mounting area through the through-hole 12a of the central support, flows through the tilt servo 8 and the servo controller 7, and is finally discharged from the tail exhaust vent 9, entering the outside of the electric powertrain. This process is repeated continuously to achieve sustained heat dissipation. This heat dissipation path utilizes the natural guidance of flight airflow to form a circulating cooling channel, achieving continuous and efficient heat dissipation without additional energy consumption, ensuring the system maintains a stable temperature under high load and long-term operating conditions.

[0051] During operation, the servo controller 7 receives flight attitude switching commands from the flight control system and sends drive signals to the tilt servo 8, causing the tilt servo 8 to drive the tilt nacelle 6 to tilt around the fixed axis 17, thereby achieving attitude switching of the electric vertical take-off and landing aircraft. During the operation of the tilt power system, the airflow generated by the rotation of the propeller 1 is used as a heat dissipation source. The airflow generated by the propeller 1 flows along the ventilation gap 3a, passes through the propulsion motor 2, reaches the upper support 10, and enters the first installation area through the mounting lug gap 10b. It is then drawn in by the cooling fan 25 of the propulsion motor 2 and flows through the radiator 26. After being cooled, the airflow enters the second installation area through the through hole 12a of the middle bracket, flows through the tilt servo 8 and the servo controller 7, and is finally discharged from the tail exhaust port 9, so as to achieve heat dissipation for the propulsion motor 2, the servo controller 7 and the tilt servo 8.

[0052] In summary, the tiltable electric powertrain architecture of this invention achieves smooth tilting around the fixed shaft 17 through a bearing support structure. The bearing bears all structural loads, preventing the tilting servo motor 8 from bearing external torque and allowing it to provide only tilting drive force. The fixed shaft 17 adopts a hollow design, facilitating signal and power wiring. The tilting nacelle 6 structure integrates heat dissipation airflow channels, improving the system's thermal management performance. The entire electric powertrain architecture is modular and integrated, facilitating rapid docking and installation with eVTOL, significantly improving the simplicity and maintainability of the power system.

[0053] Finally, it should be noted that the above specific embodiments are only used to illustrate the technical solutions of the present invention and not to limit it. Although the present invention has been described in detail with reference to examples, those skilled in the art should understand that modifications or equivalent substitutions can be made to the technical solutions of the present invention without departing from the spirit and scope of the technical solutions of the present invention, and all such modifications or substitutions should be covered within the scope of the claims of the present invention.

Claims

1. A tiltable propulsion system for an electric vertical takeoff and landing aircraft, characterized in that, include: The tilting nacelle (6) includes a tilting support (13) and a mounting bracket connected to each other. The tilting support (13) includes a fixed shaft (17) and a support body (21) rotatable about the central axis of the fixed shaft (17). One end of the fixed shaft (17) is provided with a wing mechanical interface (5) for connecting with the wing of an electric vertical take-off and landing aircraft. The end of the tilting support (13) away from the fixed shaft (17) is provided with a servo mechanical interface (20). The propulsion motor (2) is mounted on the mounting bracket; The propeller (1) is connected to the drive end of the propulsion motor (2) and is used to receive the rotational power of the propulsion motor (2) and rotate. A tilt servo (8) is connected to the servo mechanical interface (20); The servo controller (7) is electrically connected to the tilt servo (8); The tilt servo (8) can drive the tilt nacelle (6) to tilt around the fixed axis (17) according to the flight control command received by the servo controller (7), thereby realizing the flight attitude switching of the electric vertical take-off and landing aircraft. The tilting nacelle (6) includes an upper support (10), a middle support (12) and a lower support (14) connected in sequence and forming an annular shape. The upper end face of the upper support (10) is provided with a plurality of mounting ears (10a) for mounting the propulsion motor (2). The outer peripheral ends of the middle support (12) and the lower support (14) are used for mounting the outer skin structure. A ventilation gap (3a) is left between the side of the outer skin structure near the propeller (1) and the outer periphery of the propulsion motor (2), and a tail air outlet (9) is provided between the bottom end of the lower bracket (14) and the outer skin structure. The middle support (12) has a through hole (12a) on its plane to serve as a heat dissipation airflow channel; A mounting ear gap (10b) communicating with the ventilation gap (3a) is formed between the plurality of mounting ears (10a) and the upper end face of the upper bracket (10). The upper bracket (10) and the middle bracket (12) are provided with a first mounting area that communicates with the mounting ear gap (10b); The middle support (12) and the lower support (14) are provided with a second installation area, and the servo controller (7) and the tilt support (13) are installed in the second installation area; The propulsion motor (2) is equipped with a cooling fan (25) and a radiator (26) installed in the first installation area. The airflow generated by the propeller (1) flows through the ventilation gap (3a) and the propulsion motor (2) to the upper bracket (10), and enters the first installation area through the mounting ear gap (10b). It is then drawn in by the cooling fan (25) of the propulsion motor (2) and flows through the radiator (26). After the heat is dissipated, the airflow enters the second installation area through the through hole (12a) of the middle bracket, flows through the tilt servo (8) and the servo controller (7), and is finally discharged from the tail exhaust port (9).

2. The tiltable propulsion system for an electric vertical takeoff and landing aircraft according to claim 1, characterized in that, The fixed shaft (17) is provided with a support bearing (18), and the support body (21) tilts around the fixed shaft (17) via the support bearing (18).

3. The tiltable propulsion system for an electric vertical takeoff and landing aircraft according to claim 2, characterized in that, The support bearing (18) includes tapered roller bearings located at both ends of the fixed shaft (17).

4. The tiltable propulsion system for an electric vertical takeoff and landing aircraft according to claim 1, characterized in that, The fixed shaft (17) is a hollow structure (19) so that the flight control signal line and the power line can be laid through the hollow structure (19) of the fixed shaft (17).

5. A tiltable propulsion system for an electric vertical takeoff and landing aircraft according to claim 1, characterized in that, The tilt servo (8) includes a drive motor (24), a reducer (22) and a brake (23) that cooperate with it. The drive motor (24) and the reducer (22) are connected. The servo mechanical interface (20) includes a fixed shaft stationary part (20a) and a support body stationary part (20b). The rotating end of the tilt servo (8) is connected to the fixed shaft stationary part (20a), and the mounting stationary part (8a) of the tilt servo (8) is connected to the support body stationary part (20b).

6. The tiltable propulsion system for an electric vertical takeoff and landing aircraft according to claim 1, characterized in that, The outer periphery of the middle support (12) and the lower support (14) are provided with fixing holes for fixing the outer skin structure. The tilting support (13) is installed on the middle support (12). A lower support rod (15) is connected between the middle support (12) and the lower support (14). An auxiliary support rod (16) is connected between the middle support (12) and the tilting support (13).

7. A tiltable propulsion system for an electric vertical takeoff and landing aircraft according to claim 1, characterized in that, The outer skin structure includes a first outer skin (3) and a second outer skin (4). The first outer skin (3) is installed between the upper support (10) and the middle support (12), and the second outer skin (4) is installed between the middle support (12) and the lower support (14).

8. A control method for a tiltable propulsion system of an electric vertical takeoff and landing aircraft, characterized in that, The control method using the tiltable propulsion system for an electric vertical takeoff and landing aircraft as described in claim 7 includes: The servo controller (7) receives the flight attitude switching command from the flight control system and sends a drive signal to the tilt servo (8) so that the tilt servo (8) drives the tilt nacelle (6) to tilt around the fixed axis (17) to achieve attitude switching of the electric vertical take-off and landing aircraft. During the operation of the tilting power system, the airflow generated by the rotation of the propeller (1) is used as the heat dissipation air source. The airflow generated by the propeller (1) flows through the ventilation gap (3a) and the propulsion motor (2) to the upper bracket (10). After entering the first installation area through the mounting ear gap (10b), it is drawn in by the cooling fan (25) of the propulsion motor (2) and flows through the radiator (26). After the heat is dissipated, the airflow enters the second installation area through the through hole (12a) of the middle bracket, flows through the tilt servo (8) and the servo controller (7), and is finally discharged from the tail exhaust port (9) to achieve heat dissipation of the propulsion motor (2), the servo controller (7) and the tilt servo (8).

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