Tilting rotor mechanism of electric vertical take-off and landing aircraft

Abstract

The invention relates to the technical field of aircrafts, and particularly discloses a tilting rotor mechanism of an electric vertical take-off and landing aircraft, a rotor assembly is integrated in a nacelle assembly, a tilting driving assembly is integrated in a wing, the tilting driving assembly comprises a driving part and a tilting shaft, the driving part can drive the tilting shaft to rotate, and the tilting shaft can drive the rotor assembly to rotate. The nacelle assembly is fixedly connected to the tilting shaft. The tilting driving assembly is adopted to directly drive tilting of the nacelle assembly, introduction of complex structures such as a connecting rod or a gear set is avoided, the overall structure assembly is simplified, the machining and manufacturing difficulty is reduced, the lightweight design is achieved, the nacelle assembly is driven by driving the tilting shaft as a core component, the force transmission path is clear and direct, and the structure is simple. The stability and control precision of tilting motion are ensured, 360-degree omnidirectional vector thrust is achieved, meanwhile, the tilting driving assembly is arranged in the wing, the space is utilized to the maximum extent, integration of a power transmission path and a motion structure is achieved, and the integration degree of the whole structure is improved.

Description

TECHNICAL FIELD

[0001] The present application relates to the field of aircraft technology, in particular to a tilting rotor mechanism of an electric vertical take-off and landing aircraft. BACKGROUND

[0002] The electric vertical take-off and landing aircraft is a new type of transportation tool that combines helicopter and unmanned aerial vehicle technology. It is driven by electricity and can take off and land vertically and hover in the air like a helicopter. Its core goal is to provide quiet, environmentally friendly and efficient "air taxis" for cities in the future through autonomous driving technology, in order to alleviate ground traffic congestion and build future three-dimensional transportation networks.

[0003] At present, the tilting rotor mechanism widely used in electric vertical take-off and landing aircrafts usually consists of dozens of key components, mainly including actuators, precision bearings, slip rings, and various types of drive motors, etc. This structure design has high complexity, and puts forward very strict requirements on the machining precision of parts and the assembly process precision during the manufacturing process. In addition, since the mechanism applies a large number of metal components such as high-strength alloy frames, precision gear box housings, etc., the overall mass is relatively large, which reduces the effective payload capacity and endurance range of the aircraft.

[0004] Therefore, there is an urgent need for a tilting rotor mechanism of an electric vertical take-off and landing aircraft to solve the above problems. SUMMARY

[0005] The purpose of the present application is to provide a tilting rotor mechanism of an electric vertical take-off and landing aircraft, which can simplify the overall structure assembly, reduce the manufacturing difficulty, and realize lightweight design.

[0006] In order to achieve the above purpose, the technical scheme adopted by the present application is as follows:

[0007] The present application provides a tilting rotor mechanism of an electric vertical take-off and landing aircraft, comprising a plurality of tilting rotor units, wherein each tilting rotor unit comprises a nacelle assembly, a rotor assembly, and a tilting drive assembly, the rotor assembly is integrated in the nacelle assembly, the tilting drive assembly is integrally arranged in a wing, and the tilting drive assembly comprises a driving member and a tilting shaft, the output end of the driving member is drivingly connected to the tilting shaft, the driving member can drive the tilting shaft to rotate, and the nacelle assembly is fixedly connected to the tilting shaft.

[0008] As a preferred technical scheme of the tilting rotor mechanism of the electric vertical take-off and landing aircraft, the tilting drive assembly further comprises a first limiting plate, the first limiting plate is fixedly arranged at one end of the wing, a first through hole is formed in the first limiting plate, the tilting shaft passes through the first through hole and is fixedly connected to the nacelle assembly.

[0009] As a preferred technical scheme of the tilting rotor mechanism of the electric vertical take-off and landing aircraft, the tilting driving assembly further comprises a first supporting rod, a second supporting rod and a mounting plate, the first supporting rod and the second supporting rod are oppositely and spacedly arranged, and the first supporting rod and the second supporting rod are fixedly connected to the first limiting plate, the mounting plate is fixedly connected to the first supporting rod and the second supporting rod, and the driving member is fixedly installed to the mounting plate.

[0010] As a preferred technical scheme of the tilting rotor mechanism of the electric vertical take-off and landing aircraft, the tilting driving assembly further comprises a second limiting plate, the first limiting plate and the second limiting plate are spacedly arranged, the second limiting plate is fixedly connected to the first supporting rod and the second supporting rod, and a second through hole is formed in the second limiting plate, and the tilting shaft is sequentially arranged through the second through hole and the first through hole and fixedly connected to the nacelle assembly.

[0011] As a preferred technical scheme of the tilting rotor mechanism of the electric vertical take-off and landing aircraft, the tilting driving assembly further comprises a mounting seat and a plurality of fasteners, the plurality of fasteners are arranged through the mounting seat to fix the driving member between the mounting seat and the mounting plate.

[0012] As a preferred technical scheme of the tilting rotor mechanism of the electric vertical take-off and landing aircraft, the mounting seat has a receiving groove, the driving member is arranged in the receiving groove, and a plurality of mounting lugs are arranged along the outer periphery of the receiving groove, the plurality of fasteners and the plurality of mounting lugs are arranged one-to-one, and the fasteners are arranged through the mounting lugs and fixedly connected to the mounting plate.

[0013] As a preferred technical scheme of the tilting rotor mechanism of the electric vertical take-off and landing aircraft, the tilting driving assembly further comprises an output shaft, one end of the output shaft is connected to the output end of the driving member, and the other end of the output shaft is connected to the tilting shaft.

[0014] As a preferred technical scheme of the tilting rotor mechanism of the electric vertical take-off and landing aircraft, the tilting shaft is provided with a shaft hole, the other end of the output shaft is inserted into the shaft hole, the tilting driving assembly further comprises a connecting piece, the connecting piece is sequentially arranged through the outer peripheral wall of the tilting shaft and the other end of the output shaft along the radial direction to fixedly connect the tilting shaft and the output shaft in the circumferential direction.

[0015] As a preferred technical scheme of the tilting rotor mechanism of the electric vertical take-off and landing aircraft, the driving member is an electric motor.

[0016] As a preferred technical scheme of the tilting rotor mechanism of the electric vertical take-off and landing aircraft, the electric vertical take-off and landing aircraft comprises a fuselage body, and a plurality of the tilting rotor units are arranged in a longitudinal and / or transverse distribution manner along the fuselage body.

[0017] The present application has the following beneficial effects:

[0018] The present application provides a tilting rotor mechanism of an electric vertical take-off and landing aircraft, which comprises a plurality of tilting rotor units, wherein each tilting rotor unit comprises a nacelle assembly, a rotor assembly integrated in the nacelle assembly, and a tilting drive assembly arranged in a wing, and the tilting drive assembly comprises a driving member and a tilting shaft, the output end of the driving member is transmissionally connected to the tilting shaft, the driving member can drive the tilting shaft to rotate, and the nacelle assembly is fixedly connected to the tilting shaft. BRIEF DESCRIPTION OF DRAWINGS

[0019] Figure 1 A structure diagram of the tilting rotor mechanism of the electric vertical take-off and landing aircraft provided by the present application Figure One ;

[0020] Figure 2 A structure diagram of the tilting rotor mechanism of the electric vertical take-off and landing aircraft provided by the present application Figure Two ;

[0021] Figure 3 A structure diagram of the tilting rotor mechanism of the electric vertical take-off and landing aircraft provided by the present application Figure Three .

[0022] Wherein:

[0023] 1, nacelle assembly; 2, rotor assembly;

[0024] 3, driving member; 4, tilting shaft; 5, first limiting plate; 6, first supporting rod; 7, second supporting rod; 8, mounting plate; 9, second limiting plate;

[0025] 10, mounting seat; 101, mounting lug;

[0026] 11, fastener; 12, output shaft; 13, connecting member; 14, wing. DETAILED DESCRIPTION

[0027] Embodiments of the present application are described in detail below with reference to the attached drawing figures, wherein the same or like reference numerals and characters in the drawings represent the same or like elements among which detailed descriptions are not repeatedly rendered. The embodiments described below are exemplary, and are intended to explain the present application, and are not intended to limit the present application.

[0028] In the description of the present application, it should be noted that the terms "center", "upper", "lower", "left", "right", "vertical", "horizontal", "inner", "outer", and the like indicate the orientation or positional relationship shown in the drawings based on the orientation or positional relationship shown in the drawings, and are only for the purpose of facilitating the description of the present application and simplifying the description, and therefore cannot be understood as indicating or implying that the device or element referred to must have a particular orientation, be constructed and operated in a particular orientation, and therefore cannot be understood as limiting the present application. In addition, the terms "first" and "second" are only for the purpose of description, and cannot be understood as indicating or implying relative importance. Among them, the terms "first position" and "second position" are two different positions.

[0029] Unless otherwise explicitly specified and limited, the terms "mounting", "connecting", "connecting", "fixing" should be understood broadly, for example, it can be fixed connection, or it can be detachable connection; it can be mechanical connection, or it can be electrical connection; it can be directly connected, or it can be indirectly connected through an intermediate medium; it can be the internal communication of two elements or the interaction relationship between two elements. For those skilled in the art, the specific meaning of the above terms in the present application can be understood according to the specific circumstances.

[0030] Unless otherwise explicitly specified and limited, "on" or "under" of the first feature to the second feature can include that the first feature and the second feature are in direct contact, or the first feature and the second feature are not in direct contact but are in contact through another feature between them. Moreover, "on", "above" and "above" of the first feature to the second feature include that the first feature is directly above and obliquely above the second feature, or only indicates that the horizontal height of the first feature is higher than that of the second feature. The "below", "below" and "below" of the first feature to the second feature include that the first feature is directly below and obliquely below the second feature, or only indicates that the horizontal height of the first feature is less than that of the second feature.

[0031] The technical solutions of the present application are further illustrated below in conjunction with the drawings and through specific embodiments.

[0032] As Figures 1 to 3As shown, the embodiment provides a tilting rotor mechanism of an electric vertical take-off and landing aircraft, which includes a plurality of tilting rotor units, the tilting rotor unit includes a nacelle assembly 1, a rotor assembly 2 integrated in the nacelle assembly 1, and a tilting drive assembly arranged in the wing 14, and the tilting drive assembly includes a driving member 3 and a tilting shaft 4, the output end of the driving member 3 is drivingly connected to the tilting shaft 4, the driving member 3 can drive the tilting shaft 4 to rotate, and the nacelle assembly 1 is fixedly connected to the tilting shaft 4. In this way, the tilting drive assembly is used to directly drive the tilting of the entire nacelle assembly 1, avoiding the introduction of complex connecting rods or gear sets and the like, further simplifying the overall structure assembly, reducing the processing and manufacturing difficulty, realizing lightweight design, and driving the entire nacelle assembly 1 through the core component of the tilting shaft 4, the force transmission path is clear and direct, ensuring the stability and control accuracy of the tilting movement, and finally realizing 360-degree omnidirectional vector thrust. At the same time, the tilting drive assembly is built into the wing 14, which maximizes the use of space and realizes the integration of the power transmission path and the movement structure, effectively improving the integration level of the overall structure.

[0033] It should be noted that the tilting shaft 4 can drive the nacelle assembly 1 to rotate within a range of 0 degrees to 360 degrees, and the aircraft can obtain thrust in any direction, greatly enhancing the maneuverability of the aircraft. Of course, the tilting range of the tilting rotor mechanism of the electric vertical take-off and landing aircraft of the embodiment is usually 0 degrees to 90 degrees in actual application.

[0034] Specifically, the embodiment exemplarily provides the following technical scheme: the tilting drive assembly further includes a first limiting plate 5, a first support rod 6, a second support rod 7, and a mounting plate 8, the first limiting plate 5 is fixedly arranged at one end of the wing 14, and a first through hole is formed in the first limiting plate 5, the tilting shaft 4 passes through the first through hole and is fixedly connected to the nacelle assembly 1. In this way, the first through hole formed in the first limiting plate 5 cooperates with the tilting shaft 4 to effectively limit the radial position of the tilting shaft 4, which constrains the unintended movement of the tilting shaft 4 in the plane perpendicular to its axis, and suppresses the radial jumping caused by load changes or vibrations, thereby enhancing the rigidity and operation stability of the entire transmission system.

[0035] Optionally, in order to improve the stability of the installation of the driving member 3 and ensure that the tilting shaft 4 is stably and reliably driven, the tilting drive assembly further includes a first support rod 6 and a second support rod 7 arranged opposite and spaced apart, and the first support rod 6 and the second support rod 7 are both fixedly connected to the first limiting plate 5, the mounting plate 8 is fixedly connected to the first support rod 6 and the second support rod 7, and the driving member 3 is fixedly installed to the mounting plate 8.

[0036] Optionally, the tilting driving assembly further comprises a second limiting plate 9, the first limiting plate 5 is arranged in a spaced manner with the second limiting plate 9, the second limiting plate 9 is fixedly connected to the first support rod 6 and the second support rod 7, and a second through hole is formed in the second limiting plate 9, the tilting shaft 4 is sequentially arranged in the second through hole, the first through hole and fixedly connected to the nacelle assembly 1.

[0037] Optionally, the tilting driving assembly further comprises a mounting seat 10 and a plurality of fasteners 11, the plurality of fasteners 11 are arranged in the mounting seat 10 to fix the driving part 3 between the mounting seat 10 and the mounting plate 8. Further, the fastener 11 is a bolt.

[0038] Optionally, the driving part 3 is mounted to the bottom of the mounting plate 8, the mounting seat 10 has a receiving groove, the driving part 3 is arranged in the receiving groove, the outer periphery of the receiving groove is provided with a plurality of mounting ears 101, the plurality of fasteners 11 are arranged in a one-to-one correspondence with the plurality of mounting ears 101, and the fastener 11 is arranged in the mounting ear 101 and fixedly connected to the mounting plate 8. In this way, the receiving groove can surround and limit the driving part 3, has good radial positioning and vibration suppression effect, and the design of a plurality of mounting points further realizes compact and stable installation of the driving part 3, and facilitates subsequent maintenance and disassembly.

[0039] In the embodiment, the number of mounting ears 101 is three. Of course, in other embodiments, the actual number of mounting ears 101 can also be arranged according to actual needs.

[0040] Optionally, in order to further improve the stability and reliability of power transmission of the driving part 3, the tilting driving assembly further comprises an output shaft 12, one end of the output shaft 12 is connected to the output end of the driving part 3, and the other end of the output shaft 12 is connected to the tilting shaft 4.

[0041] Optionally, the tilting shaft 4 is provided with a shaft hole, the other end of the output shaft 12 is inserted into the shaft hole, the tilting driving assembly further comprises a connecting piece 13, the connecting piece 13 is sequentially arranged in the outer peripheral wall of the tilting shaft 4 and the other end of the output shaft 12 in a radial direction, so as to circumferentially fix the tilting shaft 4 and the output shaft 12. Further, the connecting piece 13 is a bolt. In this way, the other end of the output shaft 12 is inserted into the tilting shaft 4, which can effectively improve the space utilization, ensure reliable connection between the two, and make the whole structure very compact.

[0042] Optionally, the driving part 3 is an electric motor. Of course, in other embodiments, the driving part 3 can also be a hydraulic cylinder, which is not limited here. Among them, the motor drive control is accurate, which is very suitable for flight control which needs to adjust the angle quickly and accurately, while the hydraulic can provide huge torque, which is suitable for large and heavy aircraft.

[0043] In the embodiment, the core components of at least one of the tilt-rotor units are made of light-weight materials to significantly reduce the moment of inertia and the overall weight, making the tilting action more rapid and energy-saving, and directly reducing the weight of the aircraft, improving the range and load capacity. Further, the light-weight materials can selectively use one or more of carbon fiber composite materials, titanium alloys or high-strength aluminum alloys.

[0044] Optionally, the electric vertical take-off and landing aircraft includes a fuselage body, and the plurality of tilt-rotor units are arranged in a distributed manner along the longitudinal and / or transverse direction of the fuselage body. In this way, the tilt-rotor mechanism adopts a distributed structure, avoiding thrust concentration, and through the plurality of independently controlled tilt-rotor units, the flight attitude can be more finely adjusted, improving flight stability and control redundancy. At the same time, the fault tolerance is improved, and when one of the tilt-rotor units fails, the remaining tilt-rotor units can be adjusted to compensate for the thrust, greatly enhancing the safety and reliability of flight.

[0045] Obviously, the above embodiments of the present application are only examples for the purpose of clear illustration, and are not intended to limit the embodiments of the present application. Based on the above description, those skilled in the art can make other different forms of changes or modifications. Here, it is not necessary and impossible to exhaust all the embodiments. Any modification, equivalent replacement and improvement made within the spirit and principle of the present application shall be included in the protection scope of the claims of the present application.

Claims

1. A tilt rotor mechanism for an electric vertical takeoff and landing aircraft, characterized in that, The system includes multiple tilt rotor units, each including a nacelle assembly (1), a rotor assembly (2), and a tilt drive assembly. The rotor assembly (2) is integrated into the nacelle assembly (1), and the tilt drive assembly is integrated into the wing (14). The tilt drive assembly includes a drive element (3) and a tilt shaft (4). The output end of the drive element (3) is connected to the tilt shaft (4), and the drive element (3) can drive the tilt shaft (4) to rotate. The nacelle assembly (1) is fixedly connected to the tilt shaft (4).

2. The tilt rotor mechanism of the electric vertical takeoff and landing aircraft according to claim 1, characterized in that, The tilt drive assembly also includes a first limiting plate (5), which is fixedly disposed at one end of the wing (14) and has a first through hole. The tilt shaft (4) passes through the first through hole and is fixedly connected to the nacelle assembly (1).

3. The tilt rotor mechanism of the electric vertical takeoff and landing aircraft according to claim 2, characterized in that, The tilt drive assembly further includes a first support rod (6), a second support rod (7), and a mounting plate (8). The first support rod (6) and the second support rod (7) are opposite to each other and spaced apart. The first support rod (6) and the second support rod (7) are both fixedly connected to the first limiting plate (5). The mounting plate (8) is fixedly connected to the first support rod (6) and the second support rod (7). The drive component (3) is fixedly installed on the mounting plate (8).

4. The tilt rotor mechanism of the electric vertical takeoff and landing aircraft according to claim 3, characterized in that, The tilt drive assembly also includes a second limiting plate (9), the first limiting plate (5) and the second limiting plate (9) are spaced apart, the second limiting plate (9) is fixedly connected to the first support rod (6) and the second support rod (7), and a second through hole is provided on the second limiting plate (9), the tilt shaft (4) passes through the second through hole and the first through hole in sequence and is fixedly connected to the nacelle assembly (1).

5. The tilt rotor mechanism of the electric vertical takeoff and landing aircraft according to claim 3, characterized in that, The tilt drive assembly also includes a mounting base (10) and a plurality of fasteners (11), the plurality of fasteners (11) passing through the mounting base (10) to fix the drive member (3) between the mounting base (10) and the mounting plate (8).

6. The tilt rotor mechanism of the electric vertical takeoff and landing aircraft according to claim 5, characterized in that, The mounting base (10) has a receiving groove, the driving member (3) is placed in the receiving groove, and a plurality of mounting ears (101) are protruding from the outer periphery of the receiving groove. A plurality of fasteners (11) are provided in correspondence with a plurality of mounting ears (101), and the fasteners (11) pass through the mounting ears (101) and are fixedly connected to the mounting plate (8).

7. The tilt rotor mechanism of the electric vertical takeoff and landing aircraft according to any one of claims 1-6, characterized in that, The tilt drive assembly also includes an output shaft (12), one end of which is connected to the output end of the drive unit (3), and the other end of which is connected to the tilt shaft (4).

8. The tilt rotor mechanism of the electric vertical takeoff and landing aircraft according to claim 7, characterized in that, The tilting shaft (4) is provided with a shaft hole, and the other end of the output shaft (12) is inserted into the shaft hole. The tilting drive assembly also includes a connector (13), which passes through the outer peripheral wall of the tilting shaft (4) and the other end of the output shaft (12) in a radial direction to fix the tilting shaft (4) and the output shaft (12) circumferentially.

9. The tilt rotor mechanism of the electric vertical takeoff and landing aircraft according to any one of claims 1-6, characterized in that, The driving component (3) is an electric motor.

10. The tilt rotor mechanism of the electric vertical takeoff and landing aircraft according to any one of claims 1-6, characterized in that, The electric vertical takeoff and landing aircraft includes a fuselage body, and a plurality of tiltrotor units are distributed along the longitudinal and / or lateral directions of the fuselage body.

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