Thrust assembly and aircraft

Abstract

The application discloses a kind of thrust assembly and aircraft, it is related to aircraft technical field.The electric motor of thrust assembly includes outer rotor and inner stator;Hub is fixedly connected with outer rotor, and the central axis of hub is collinear with the central axis of outer rotor;Linear drive assembly, the fixed end of linear drive assembly is arranged in hub and is fixedly connected with inner stator, and the output end of linear drive assembly extends to the outside of hub in the direction away from electric motor;Variable-pitch push disc is located on the side of hub away from electric motor, and is rotatably connected with output end by variable-pitch bearing, to reciprocate along the axial direction of hub under the driving of linear drive assembly;One end of connecting cable is connected with the connecting part of fixed end, and the other end of connecting cable passes through through hole and extends to inner stator and is connected with control module.The variable-pitch push disc of the application is placed on top of hub, so that its structural size is not limited by the size of hub and the structural strength of variable-pitch push disc can be improved.

Description

[0001] This invention is a divisional application of the patent application filed on December 5, 2024, with application number 202411775996.3 and title "Thrust Assembly and Aircraft". Technical Field

[0002] This invention relates to the field of aircraft technology, and particularly to thrust components and aircraft. Background Technology

[0003] For helicopters, rotorcraft, or tiltrotor-configured eVTOLs (electric vertical take-off and landing aircraft), the propeller in the thrust assembly is the component that ultimately generates thrust or lift, while the electric motor drives the propeller to rotate.

[0004] A variable-pitch propeller is a propeller whose blade angle can be changed during flight via a variable-pitch assembly. In related technologies, the variable-pitch assembly includes a variable-pitch pusher, which is mounted inside the propeller hub and moves vertically up and down along the propeller main shaft under the action of a variable-pitch motor. The variable-pitch pusher is connected to multiple blades via multiple links, so that as it moves up and down, it also drives the corresponding blades to oscillate relative to the propeller hub via the links.

[0005] However, due to the limited space inside the propeller hub, the size of the pitch changer is restricted, which affects its structural strength. This results in uneven stress on each pitch changer component, which in turn leads to the need to improve the consistency of the propeller blade pitch. Summary of the Invention

[0006] The main objective of this invention is to propose a thrust assembly and an aircraft that aims to solve the technical problem that the pitch consistency of the propeller blades needs to be improved due to the fact that the variable pitch thruster is set inside the propeller hub.

[0007] To achieve the above objectives, the present invention provides a thrust assembly comprising:

[0008] An electric motor, comprising an outer rotor and an inner stator, wherein the outer rotor has a through hole and the central axis of the through hole is collinear with the central axis of the thrust assembly, and a control module is installed inside the inner stator;

[0009] The rotor hub is fixedly connected to the outer rotor.

[0010] The linear drive assembly has a fixed end located inside the propeller hub and fixedly connected to the inner stator, and the output end of the linear drive assembly extends out of the propeller hub in a direction away from the electric motor.

[0011] A variable-pitch pusher, located on the side of the propeller hub facing away from the electric motor, and rotatably connected to the output end via a variable-pitch bearing, reciprocates axially along the propeller hub under the drive of a linear drive assembly; and

[0012] The connecting cable has one end connected to the connecting part of the fixed end, and the other end of the connecting cable passes through the through hole and extends into the inner stator to connect with the control module.

[0013] In one embodiment, the connecting portion passes through a through hole and is fixedly connected to the inner stator.

[0014] In one embodiment, the linear drive component includes:

[0015] A variable pitch motor, the body of which is disposed inside the propeller hub, the variable pitch motor mechanism forms a fixed end, and the variable pitch motor has a connecting part;

[0016] The lead screw extends axially along the hub. One end of the lead screw is connected to the output shaft of the variable pitch motor inside the hub, and the other end of the lead screw extends out of the hub in a direction away from the electric motor.

[0017] A moving part, which is threadedly connected to the portion of the lead screw extending beyond the propeller hub to form an output end; and

[0018] The telescopic component has one end fixedly connected to the body of the variable pitch motor and the other end fixedly connected to the moving component. The telescopic component is adapted to extend and retract along the axial direction of the propeller hub.

[0019] In one embodiment, the outer peripheral surface of the moving member near the hub has a radial protrusion, and the pitch bearing is disposed on the side of the radial protrusion away from the hub.

[0020] The thrust assembly also includes an end cap, which is located on the side of the pitch bearing opposite to the radial protrusion.

[0021] The variable pitch pusher is sleeved on the radial outer side of the variable pitch bearing, and the end cover is fixedly connected to the variable pitch pusher.

[0022] In one embodiment, the thrust assembly further includes:

[0023] At least two blades are rotatably connected to the circumferential wall of the hub about the blade pitch axis, and the at least two blades are evenly spaced along the circumferential direction of the hub.

[0024] At least two pitch transmission components are provided, each corresponding to one of the at least two blades. The pitch transmission components are connected to the pitch pusher and the blades respectively, so that the pitch pusher drives the blades to swing through the pitch transmission components.

[0025] In one embodiment, the blade includes:

[0026] The propeller handle is rotatably mounted on the propeller hub, and one end of the propeller handle extends radially out of the propeller hub.

[0027] The blade is fixedly connected to one end of the propeller handle, and the blade is spaced apart from the outer peripheral wall of the propeller hub so that part of the propeller handle is exposed.

[0028] The variable pitch transmission assembly is located radially outside the propeller hub, and one end of the variable pitch transmission assembly is connected to the exposed part of the propeller handle.

[0029] In one embodiment, the thrust assembly further includes:

[0030] At least two angle sensors, each corresponding to one of the at least two blades, and the angle sensors are located on the portion of the blades extending into the hub.

[0031] In one embodiment, the thrust assembly further includes:

[0032] At least two stabilizing components are provided, each stabilizing component being adapted to extend and retract along the axial direction of the propeller hub. One end of each stabilizing component is hinged to the outer edge of the pitch thruster, and the other end of each stabilizing component is hinged to the propeller hub. The at least two stabilizing components are evenly spaced along the circumferential direction of the pitch thruster.

[0033] In one embodiment, the number of stabilizing components is the same as the number of blades and they correspond one-to-one.

[0034] In the circumferential direction of the variable pitch push plate, the stabilizing component and the variable pitch transmission component are alternately arranged.

[0035] In one embodiment, the stabilizing component includes:

[0036] A first connecting arm, one end of which is hinged to the outer edge of the variable pitch push plate; and

[0037] A second connecting arm, one end of which is hinged to the other end of the first connecting arm, and the other end of which is hinged to the propeller hub, with an included angle between the first and second connecting arms; and

[0038] An elastic element is disposed between the first connecting arm and the second connecting arm;

[0039] The elastic element is a torsion spring, and the torsion spring is sleeved on the hinge shaft between the first connecting arm and the second connecting arm.

[0040] In one embodiment, the variable pitch transmission assembly includes a variable pitch link and a variable pitch pin. One end of the variable pitch link is hinged to a variable pitch push plate, and the other end of the variable pitch link is hinged to one end of the variable pitch pin. The other end of the variable pitch pin is fixedly connected to the blade to rotate about the variable pitch axis of the blade.

[0041] The pitch linkage includes:

[0042] A fixed section with openings at both ends along the axis, and a receiving cavity is defined within the fixed section that communicates with both openings;

[0043] The first movable section extends into the receiving cavity from one end opening of the fixed section and can move along the axial direction of the fixed section;

[0044] The second movable section, a portion of which extends into the receiving cavity from the other end of the fixed section, and is movable axially along the fixed section; and

[0045] The adjustable spacing structure is partially disposed within the receiving cavity and is connected to the first moving segment and the second moving segment respectively to adjust the spacing between the first moving segment and the second moving segment.

[0046] The locking element engages with both the fixed section and the adjusting structure to lock the adjusting structure.

[0047] In one embodiment, the electric motor further includes:

[0048] The rear cover is located on the side of the inner stator away from the propeller hub;

[0049] A cooling assembly is located on the side of the rear cover opposite to the inner stator.

[0050] An eccentric shaft is rotatably mounted in the central shaft hole of the inner stator about its own central axis. The central axis of the eccentric shaft is parallel to and spaced apart from the central axis of the central shaft hole. One end of the eccentric shaft is connected to the cooling assembly, and the other end is connected to the outer rotor, so that the outer rotor drives the cooling assembly through the eccentric shaft.

[0051] In one embodiment, the electric motor further includes:

[0052] An internal gear ring is fixedly connected to the end face of the outer rotor's shaft near the inner stator. The central axis of the internal gear ring is collinear with the central axis of the outer rotor. The shaft has a through hole.

[0053] The mating gear is fixedly sleeved on the other end of the eccentric shaft and meshes with the internal gear ring.

[0054] A support cover is provided in the through hole and fixedly connected to the inner stator. A portion of the surface of one end face of the support cover protrudes to form a protrusion. The protrusion has a wiring hole that passes through the support cover along the axial direction of the inner stator.

[0055] The protrusions are located radially outside the mating gear and are spaced apart from each other; the cross-section of the wiring hole is arc-shaped and partially surrounds the mating gear.

[0056] Furthermore, the present invention also provides an aircraft, the aircraft comprising:

[0057] Aircraft body; and

[0058] At least one thrust assembly as described above is located on the aircraft fuselage.

[0059] In one embodiment, the aircraft is an electric vertical takeoff and landing (EVTOL) aircraft.

[0060] One or more technical solutions proposed in this invention have at least the following technical effects:

[0061] Compared to the space-constrained approach of embedding the pitch pusher within the propeller hub, the pitch propeller technology of this invention places the linear drive assembly that drives the pitch pusher to reciprocate axially along the propeller hub within the hub. The pitch pusher is located on the side of the hub away from the electric motor, i.e., directly above the hub. This allows the structural dimensions of the pitch motor to be unrestricted by the dimensions of the hub, thereby improving the structural strength of the pitch pusher, enhancing its uniformity, and improving pitch consistency. Furthermore, the pitch motor is fixedly connected to the inner stator within the hub, and the pitch mechanism is stationary relative to the entire hub and blades. This allows the pitch motor to be directly connected to the control module within the inner stator via a connecting cable, ensuring a stable supply of electrical energy and / or control signals required for the operation of the pitch motor.

[0062] Furthermore, in this invention, the control module that provides electrical energy and transmits control signals to the variable-pitch motor is integrated into the inner stator, which facilitates the assembly of the thrust assembly, reduces assembly steps, and improves assembly efficiency. Additionally, integrating the variable-pitch motor control module and the electric motor controller into the inner stator simplifies system design and improves control efficiency through a unified control architecture, reducing development and maintenance costs while enhancing the maintainability of the thrust assembly. It also facilitates redundant configuration of both components, thereby improving safety. Moreover, arranging the variable-pitch motor control module within the inner stator allows for high integration within limited installation space and also enables better cooling through the electric motor's cooling components.

[0063] Furthermore, in this invention, the eccentric shaft in the thrust assembly is eccentrically arranged in the central shaft hole of the inner stator, thereby leaving sufficient space for the routing of connecting cables. Attached Figure Description

[0064] To more clearly illustrate the technical solutions in the embodiments of the present invention or the prior art, the drawings used in the description of the embodiments or the prior art will be briefly introduced below. Obviously, the drawings described below are only some embodiments of the present invention. For those skilled in the art, other drawings can be obtained based on the structures shown in these drawings without creative effort.

[0065] Figure 1 This is a schematic diagram of the thrust assembly provided by the present invention;

[0066] Figure 2 A schematic diagram of the structure of the electric motor with the thrust assembly provided by the present invention;

[0067] Figure 3 This is a schematic diagram showing the connection between the variable pitch push plate and the linear drive assembly provided by the present invention; the telescopic component is not shown.

[0068] Figure 4 A schematic diagram of the stabilizing component of the thrust assembly provided by the present invention;

[0069] Figure 5 A schematic diagram of the gain of the stabilizing component of the thrust assembly provided by the present invention;

[0070] Figure 6 A schematic diagram of the screw and nut structure of the thrust assembly provided by the present invention;

[0071] Figure 7 A schematic diagram of a structure of an embodiment of the variable pitch transmission assembly of the thrust assembly provided by the present invention;

[0072] Figure 8 A schematic diagram of the internal structure of the pitch linkage of the thrust assembly provided by the present invention;

[0073] Figure 9 A schematic diagram of the pitch adjustment structure of the thrust assembly provided by the present invention;

[0074] Figure 10 A schematic diagram of another embodiment of the variable pitch transmission assembly of the thrust assembly provided by the present invention;

[0075] Figure 11 A cross-sectional view of the support cover of the thrust assembly provided by the present invention;

[0076] Figure 12 An exploded view of the structure of the support cover of the thrust assembly provided by the present invention.

[0077] Explanation of icon numbers:

[0078] 100. Electric motor; 110. Outer rotor; 111. Through hole; 112. Shaft; 120. Inner stator; 130. Rear cover; 140. Cooling assembly; 150. Eccentric shaft; 161. Internal gear ring; 162. Matching gear; 171. Supporting lower cover; 1711. Lower protrusion; 172. Supporting upper cover; 1721. Upper protrusion; 173. Cable routing hole; 200. Propeller hub; 300. Pitch-changing push plate; 400. Linear drive assembly; 410. Pitch-changing motor; 420. Lead screw; 430. Moving part; 440. Telescopic part; 431. Equal diameter section; 432. Radial protrusion; 500. Pitch-changing transmission assembly; 510. Fixed section; 520. First moving section; 521. The... 522. First rod; 523. First elastic layer; 524. First protrusion; 531. Fourth rod; 532. Third rod; 533. Second elastic layer; 534. Second protrusion; 530. Second moving section; 540. Adjustable pitch structure; 541. Knob; 542. Fitting part; 5421. Cam groove; 550. Variable pitch pin; 560. Rotating component; 570. Locking component; 580. Connecting rod body; 600. Blade; 610. Blade handle; 620. Blade blade; 700. Stabilizing component; 710. First connecting arm; 720. Second connecting arm; 730. Elastic component; 800. Variable pitch bearing; 900. End cap; 910. Embedded part; 920. Outer edge of end cap.

[0079] The realization of the objective, functional features and advantages of the present invention will be further explained in conjunction with the embodiments and with reference to the accompanying drawings. Detailed Implementation

[0080] The technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only a part of the embodiments of the present invention, and not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those of ordinary skill in the art without creative effort are within the scope of protection of the present invention.

[0081] It should be noted that if the embodiments of the present invention involve directional indications (such as up, down, left, right, front, back, etc.), the directional indications are only used to explain the relative positional relationship and movement of the components in a specific posture. If the specific posture changes, the directional indications will also change accordingly.

[0082] Furthermore, if the embodiments of this invention involve descriptions such as "first" or "second," these descriptions are for descriptive purposes only and should not be construed as indicating or implying their relative importance or implicitly specifying the number of technical features indicated. Thus, a feature defined with "first" or "second" may explicitly or implicitly include at least one of those features. Additionally, the use of "and / or" or "and / or" throughout the text includes three parallel solutions. For example, "A and / or B" includes solution A, solution B, or a solution where both A and B are satisfied simultaneously. Furthermore, the technical solutions of the various embodiments can be combined with each other, but this must be based on the ability of those skilled in the art to implement them. When the combination of technical solutions is contradictory or impossible to implement, it should be considered that such a combination of technical solutions does not exist and is not within the scope of protection claimed by this invention.

[0083] For helicopters, rotorcraft, or tiltrotor-configured eVTOLs (electric vertical take-off and landing aircraft), the propeller in the thrust assembly is the final component that generates thrust or lift, while the electric motor drives the propeller to rotate. A variable-pitch propeller is a propeller whose blade angle can be changed during flight via a variable-pitch assembly. In related technologies, the variable-pitch assembly includes a variable-pitch pusher, which is mounted within the propeller hub and moves axially up and down along the propeller main shaft under the action of a variable-pitch motor. The variable-pitch pusher is connected to multiple blades via multiple links, so that during its up and down movement, it also drives the corresponding blades to oscillate relative to the propeller hub via the links.

[0084] In addition, when the pitch pusher is set inside the propeller hub, there is usually a linear guide rod on the pitch pusher to guide and stabilize the pitch pusher. However, due to the limited space inside the propeller hub, the stabilizing effect of the linear guide rod is greatly limited, making it difficult to ensure the stability of the pitch pusher's movement. The pitch pusher is very likely to tilt to one side, thus failing to ensure the consistency of the blade pitch.

[0085] To address this, the present invention provides a thrust assembly in which a linear drive assembly for driving the pitch-changing pusher to reciprocate along the axial direction of the propeller hub is placed inside the propeller hub, and the pitch-changing pusher is located on the side of the propeller hub away from the electric motor, that is, the pitch-changing pusher is positioned directly above the propeller hub. This allows the structural dimensions of the pitch-changing motor to be unrestricted by the dimensions of the propeller hub, thereby improving the structural strength of the pitch-changing pusher, improving the uniformity of the structural strength of the pitch-changing pusher, and enhancing pitch consistency.

[0086] Please see Figure 1 This embodiment proposes a thrust assembly, which includes an electric motor 100, a rotor hub 200, a variable pitch thruster 300, a linear drive assembly 400, and connecting cables.

[0087] The electric motor 100 includes an outer rotor 110 and an inner stator 120. The outer rotor 110 has a through hole 111, and the central axis of the through hole 111 is collinear with the central axis of the outer rotor 110. A control module is installed inside the inner stator 120. A propeller hub 200 is fixedly connected to the outer rotor 110, and the central axis of the propeller hub 200 is collinear with the central axis of the outer rotor 110. The fixed end of the linear drive assembly 400 is located inside the propeller hub 200 and fixedly connected to the inner stator 120. The output end of 00 extends out of the propeller hub 200 in a direction away from the electric motor 100; the variable pitch pusher 300 is located on the side of the propeller hub 200 away from the electric motor 100 and is rotatably connected to the output end via the variable pitch bearing 800 so as to reciprocate along the axial direction of the propeller hub 200 under the drive of the linear drive assembly 400; one end of the connecting cable (not shown) is connected to the connection part of the fixed end, and the other end of the connecting cable passes through the through hole 111 and extends into the inner stator 120 to connect with the control module (not shown).

[0088] Specifically, please refer to Figure 2 In this embodiment, the electric motor 100 is an external rotor motor. The rotor of the external rotor motor forms an external rotor 110, while the stator forms an inner stator 120. The inner stator 120 includes a stator housing, a stator core, and windings. The stator core is disposed within the stator housing, and the windings are embedded in the stator slots of the stator core. In this case, the shaft hole of the stator housing forms the central shaft hole of the inner stator 120, meaning the central axis of the central shaft hole is collinear with the central axis of the inner stator 120. It is understood that the central axis of the inner stator 120 and the central axis of the external rotor 110 are both collinear with the central axis of the thrust assembly. The inner stator 120 also contains a control module to output control signals and provide electrical energy.

[0089] The outer rotor 110 is generally constructed as a cylindrical member with an opening on one side, forming an open end for the inner stator 120 to be installed into the outer rotor 110 from this open end. Multiple magnetic poles are fixed on the inner circumferential surface of the outer rotor 110. It can be understood that the outer rotor 110 forms the front cover of the motor. Correspondingly, the other side of the outer rotor 110 is a mechanical connection end, used to connect with the propeller hub 200, thereby transmitting force, motion, and torque to the propeller hub 200. In this embodiment, the mechanical connection end is connected to the propeller hub 200 to transmit power, enabling the propeller to generate the lift and thrust required for flight. In this embodiment, the electric motor 100 can be considered to be located below the propeller hub 200.

[0090] The rotor hub 200 is the part where the individual rotor blades 600 are mounted and joined. Multiple rotor blades 600 are evenly mounted on the outer peripheral wall of the rotor hub 200. The rotor hub 200 itself is connected to the mechanical coupling end of the electric motor 100, thus, under the drive of the electric motor 100, the rotor hub 200 rotates around its own rotation axis. The rotation axis of the rotor hub 200 is the central axis (rotor axis) of the entire thrust assembly.

[0091] The rotor hub 200 is a hollow structure with an internal cavity. A linear drive assembly 400 is installed within this cavity. The output end of the linear drive assembly 400 extends upwards away from the electric motor 100 to the outside of the rotor hub 200. Understandably, the output end of the linear drive assembly 400 reciprocates axially around the rotor hub 200. A pitch shifter 300 is provided at the output end, so that the pitch shifter 300, located on the side of the rotor hub 200 away from the electric motor 100 (above the rotor hub 200), reciprocates axially around the rotor hub 200 under the drive of the output end, i.e., it moves closer to or further away from the rotor hub 200 above it. Since the pitch shifter 300 is connected to each rotor blade 600 via the pitch transmission assembly 500, and the central axis of the pitch shifter 300 is collinear with the central axis of the rotor hub 200, the reciprocating movement of the pitch shifter 300 can cause each rotor blade to oscillate around its own pitch axis.

[0092] Understandably, for aircraft, in order to reduce the overall weight, the electric motor 100 preferably adopts a single-bearing motor. Specifically, the outer rotor 110 includes a motor front cover and a shaft. A through hole is provided at the geometric center of the motor front cover. One axial end of the shaft is fixedly connected to the through hole of the motor front cover by a bolt group, and the other axial end of the shaft is rotatably connected to the end of the inner stator 120 facing the mechanical connection end by a bearing. Thus, the outer rotor 110 motor of the motor assembly provided in this embodiment is a single-bearing motor. It should be noted that the shaft hole is formed as a through hole 111, which connects the inner and outer spaces of the outer rotor 110, thereby also providing a channel for the fixed end to connect with the inner stator 120.

[0093] For the linear motion provided by the linear drive assembly 400, the fixed end is the stationary part, while the output end is the part that performs linear motion; that is, the output end performs linear motion relative to the fixed end. In this embodiment, the fixed end is fixedly connected to the inner stator 120, so the linear drive assembly 400 does not rotate with the propeller hub 200 within the hub 200. At this time, the variable pitch pusher 300 cooperates with the output end through a variable pitch bearing 800, so that while the variable pitch pusher 300 rotates with the propeller hub 200, the linear drive assembly 400 remains relatively stationary.

[0094] Understandably, since the linear drive assembly 400 is fixedly connected to the inner stator 120 and there is no relative movement between them, the fixed end and the control module can be connected via a connecting cable. Understandably, this connecting cable can be a power supply cable, a communication cable, or a combined power supply and communication cable; this embodiment is not limited to this.

[0095] It is easy to see that, compared to the space-constrained placement of the pitch pusher 300 within the propeller hub 200, the pitch propeller technology solution of this embodiment places the linear drive assembly 400 that drives the pitch pusher 300 to reciprocate along the axial direction of the propeller hub 200 within the propeller hub 200, while the pitch pusher 300 is located on the side of the propeller hub 200 away from the electric motor 100, that is, the pitch pusher 300 is positioned directly above the propeller hub 200. This allows the structural dimensions of the pitch motor 410 to be unrestricted by the dimensions of the propeller hub 200, thereby improving the structural strength of the pitch pusher 300, improving the uniformity of the structural strength of the pitch pusher 300, and enhancing the pitch consistency.

[0096] Furthermore, by placing the pitch changer push plate 300 on top, there is sufficient space around the pitch changer push plate 300 for installing other pitch changer auxiliary structures, which further improves the reliability of pitch change.

[0097] Furthermore, in this embodiment, the linear drive assembly 400 and the rotor hub 200 are separated by the variable pitch bearing 800. The linear drive assembly 400 can be directly electrically connected to the control module on the inner stator 120 of the electric motor 100 via a connecting cable, thereby achieving stable and reliable power supply and signal transmission.

[0098] Furthermore, in this embodiment, the control module that provides electrical energy and transmits control signals to the variable-pitch motor is integrated into the motor controller within the inner stator 120. This facilitates the assembly of the thrust assembly, reduces assembly steps, and improves assembly efficiency. Additionally, integrating the linear drive assembly 400 into the motor controller within the inner stator 120 simplifies system design and improves control efficiency through a unified control architecture, reducing development and maintenance costs while enhancing the maintainability of the thrust assembly. It also facilitates redundant configuration of both components, thereby improving safety. Moreover, arranging the control module of the linear drive assembly 400 within the inner stator allows for high integration within limited installation space and leverages the cooling components of the electric motor for better cooling.

[0099] Understandably, the fixed end can be entirely housed within the rotor hub 200, with additional components provided in the through hole 111 to securely connect the fixed end to the inner stator 120. Alternatively, in one embodiment, a portion of the fixed end structure, i.e., the connecting part, passes through the through hole 111 and is securely connected to the inner stator 120. In this case, part of the fixed end is located within the rotor hub 200, while the other part extends into the through hole 111, thereby securing it to the inner stator 120.

[0100] It is easy to see that in this embodiment, the size of the connection structure between the fixed end and the inner stator 120 can be reduced, thereby reducing the overall weight of the thrust assembly. Furthermore, the fact that part of the fixed end extends into the through hole 111 allows for more space within the rotor hub 200 for installing sensors and other components.

[0101] It is understood that the linear drive assembly 400 includes, but is not limited to, electric actuators, linear motors, cylinders, hydraulic cylinders, etc. Alternatively, in one embodiment, the linear drive assembly 400 includes a variable pitch motor 410, a lead screw 420, a moving member 430, and a telescopic member 440. The body of the variable pitch motor 410 is disposed within the propeller hub 200, the variable pitch motor 410 is configured as a fixed end, and the variable pitch motor 410 has a connecting portion; the lead screw 420 extends axially along the propeller hub 200, one end of the lead screw 420 is connected to the output shaft of the variable pitch motor 410 within the propeller hub 200, and the other end of the lead screw 420 extends out of the propeller hub 200 in a direction away from the electric motor 100; the moving member 430 is threadedly connected to the portion of the lead screw 420 extending out of the propeller hub 200 to form an output end. One end of the telescopic member 440 is connected to the body of the variable pitch motor 410, and the other end of the telescopic member 440 is connected to the moving member 430. The telescopic member 440 is adapted to extend and retract along the axial direction of the hub 200.

[0102] Specifically, please refer to Figure 1 and Figure 3 The movable component 430 and the portion of the lead screw 420 extending outside the propeller hub 200 are threadedly connected to form a lead screw nut structure. Therefore, in this embodiment, the linear drive assembly 400 is a combination of a motor and a lead screw nut structure. The lead screw nut structure converts the rotational motion of the motor's output shaft into linear motion, thereby driving the movable component 430 to move axially along the propeller hub 200 to move away from or towards the hub 200. It is understood that the lead screw nut structure is compact, provides smooth transmission, and has high positioning accuracy, making it suitable for propeller applications. The movable component 430 can be constructed as a lead screw nut.

[0103] Alternatively, in some embodiments, the variable-pitch motor 410 includes a first winding and a second winding, and the control module is connected to the first winding and the second winding respectively via connecting cables. This creates a dual-winding structure for the variable-pitch motor, resulting in a dual-redundancy configuration to improve safety. However, since the dual-winding design increases the size of the variable-pitch motor and the space within the rotor hub is limited, the control module corresponding to the variable-pitch motor can be placed within the inner stator 120 to accommodate it.

[0104] Of course, in order for the lead screw and nut structure to operate smoothly, the thrust assembly also needs to add a bracket in the lead screw and nut structure. That is, the moving part moves back and forth along the axis of the lead screw on the bracket, and the bracket restricts the moving part 430 to rotate with the lead screw 420. Since the variable pitch push plate 300 will rotate with the propeller hub 200, in this embodiment the bracket is adapted to be a telescopic part 440. One end of the telescopic part 440 extends into the propeller hub 200 and is connected to the body of the variable pitch motor 410, and the other end is connected to the moving part 430. Since the telescopic part 440 is constructed to extend and retract along the axis of the propeller hub 200, the moving part 430 will also only move back and forth along the axis of the propeller hub 200.

[0105] Understandably, the number of telescopic components 440 can be set to one or more. Of course, since the variable pitch pusher 300 is subject to the variable pitch load of each blade, it has a tendency to overturn and deflect. That is, the moving component 430 also has a tendency to overturn and deflect. Therefore, it is preferable to include multiple telescopic components 440, and the multiple telescopic components 440 are evenly arranged along the circumference of the moving component 430. This can better resist the overturning and deflection tendencies of the moving component 430 and ensure that the moving component 430 moves smoothly and linearly in the axial direction of the hub 200.

[0106] It is easy to see that the telescopic component 440 allows the screw-nut structure to be applied in scenarios where the propeller rotates at high speed around the rotor axis. It also fully utilizes the space within the propeller hub freed up by the top-mounted variable-pitch thruster, thereby improving the propeller's space utilization. Furthermore, when there are multiple telescopic components 440, the weight distribution of the thrust assembly can be made more uniform.

[0107] It is worth noting that the telescopic component 440 includes, but is not limited to, linear telescopic components such as telescopic cylinders, as well as hinge structures such as hinges or two-bar linkages. Please refer to [link / reference needed]. Figure 1 The telescopic component 440 is constructed as a two-link hinge structure, with the hinge axis of the two links perpendicular to the axial direction of the rotor hub 200, so that the length of the two links in the axial direction of the rotor hub 200 changes with the included angle of the two links.

[0108] In one embodiment, the outer peripheral surface of the movable member 430 near the hub 200 has a radial protrusion 432, and the pitch bearing 800 is disposed on the side of the radial protrusion 432 away from the hub 200; the thrust assembly also includes an end cap 900, which is disposed on the side of the pitch bearing 800 away from the radial protrusion 432; the pitch pusher 300 is sleeved on the radially outer side of the pitch bearing 800, and the end cap 900 is fixedly connected to the pitch pusher 300.

[0109] Specifically, please refer to Figure 3 After the movable member 430 is mounted onto the lead screw 420, its outer peripheral surface comprises two parts in the axial direction of the propeller hub 200: a radial protrusion 432 and a constant-diameter portion 431. The radial protrusion 432 is close to the propeller hub 200, while the constant-diameter portion 431 is away from the propeller hub 200. The outer contour of the constant-diameter portion 431 is circular to allow the variable-pitch bearing 800 to be fitted onto it. At least a portion of the radial protrusion 432 protrudes radially from the constant-diameter portion 431 of the movable member 430, thereby constraining and supporting the variable-pitch bearing 800 in the axial direction of the propeller hub 200. In one example, the radial protrusion 432 is constructed as an annular protrusion to uniformly constrain and support the variable-pitch bearing 800.

[0110] On the other side of the pitch bearing 800, it is constrained by an end cap 900. The insert 910 of the end cap 900 extends into the pitch pusher 300 and abuts against the side end face of the pitch bearing 800 opposite to the radial protrusion 432. In addition, the outer edge 920 of the end cap 900 is attached to the side end face of the pitch pusher 300 opposite to the propeller hub 200 and is fixedly connected to the pitch pusher 300 by fasteners such as bolts, so as to follow the movement of the pitch pusher 300.

[0111] Alternatively, the end cap 900 can be fixed to the equal diameter portion 431 of the moving member 430 by means of a locking nut or other structure, and move with the moving member 430. This embodiment does not limit this.

[0112] Of course, for the propeller, the thrust assembly also includes at least two blades 600 and at least two pitch transmission assemblies 500. The blades 600 are rotatably connected to the peripheral wall of the hub 200 around the pitch axis of the blades 600, and the at least two blades 600 are evenly spaced along the circumferential direction of the hub 200. The at least two pitch transmission assemblies 500 correspond one-to-one with the at least two blades 600, and the pitch transmission assemblies 500 are respectively connected to the pitch pusher 300 and the blades 600, so that the pitch pusher 300 drives the blades 600 to swing through the pitch transmission assemblies 500.

[0113] The blade 600 is not completely fixed within the hub 200, but is rotatably connected to the outer peripheral wall of the hub 200, with one end inserted into the hub 200 and capable of rotating around its own pitch axis, thereby changing the angle of attack of the blade 600. The pitch transmission assembly 500 converts the linear movement of the pitch pusher 300 into the rotational motion of the blade 600, thereby driving the blade 600 to oscillate as the pitch pusher 300 reciprocates.

[0114] The pitch transmission assembly 500 can be disposed inside the propeller hub 200, that is, one end of the pitch transmission assembly 500 is connected to one end of the propeller blade extending into the propeller hub 200, and the other end of the pitch transmission assembly 500 extends out of the propeller hub 200 in a direction away from the electric motor 100 until it is connected to the pitch push plate 300.

[0115] Alternatively, in another embodiment, the blade includes: a shank 610 and blades 620, the shank 610 being rotatably disposed on the hub 200, and one end of the shank 610 extending radially outward from the hub 200; the blades 620 being fixedly connected to one end of the shank 610, and the blades 620 being spaced apart from the outer peripheral wall of the hub 200 so that a portion of the shank 610 is exposed; wherein, the pitch transmission assembly 500 is located radially outward from the hub 200, and one end of the pitch transmission assembly 500 is connected to the exposed portion of the shank 610.

[0116] Specifically, please refer to Figure 1 The propeller shank 610 is a shaft-like component comprising a concealed section and an exposed section. The concealed section is inserted into the propeller hub 200 and rotates about its own central axis (i.e., the pitch axis of the propeller blade). The exposed section extends radially outward from the propeller hub 200 to be exposed. The propeller blade 620 is fixedly mounted to the exposed section and spaced apart from the outer peripheral wall of the propeller hub 200, thereby ensuring that at least a portion of the exposed section remains exposed. The pitch transmission assembly 500 is located radially outward from the propeller hub 200, with one end connected to the pitch pusher 300 and the other end connected to the exposed portion of the exposed section.

[0117] It is easy to see that, compared to installing the variable pitch transmission assembly 500 inside the propeller hub 200, placing the variable pitch transmission assembly 500 outside the propeller hub 200 means that the variable pitch transmission assembly 500 is not limited by the internal dimensions of the propeller hub 200, thus achieving higher structural strength through a larger size.

[0118] Furthermore, after the variable pitch thruster 300 is placed on top, due to the complexity of the flight environment and manufacturing errors, different blades 600 will generate different overturning moments on the variable pitch thruster 300. This makes it difficult for the variable pitch thruster 300 to maintain planar stability during rotation, and it may tilt towards some blades, thus affecting the pitch consistency of the blades 600. Therefore, in one embodiment, the thrust assembly further includes at least two stabilizing components 700. The stabilizing components 700 are adapted to extend and retract along the axial direction of the hub 200. One end of the stabilizing component 700 is hinged to the outer edge of the variable pitch thruster 300, and the other end of the stabilizing component 700 is hinged to the hub 200. The at least two stabilizing components 700 are evenly spaced along the circumferential direction of the variable pitch thruster 300.

[0119] Specifically, please refer to Figure 1 and Figure 4 The stabilizing assembly 700, relying on its own structural characteristics, has an adjustable dimension in the axial direction of the hub 200, thereby accommodating the reciprocating movement of the pitch pusher 300 in the axial direction of the hub 200. Furthermore, the stabilizing assembly 700, relying on its own structural characteristics, provides a stabilizing force in the radial direction of the pitch pusher 300, thus also providing a stabilizing torque to the pitch pusher 300. At least three stabilizing assemblies 700 are uniformly arranged along the circumference of the pitch pusher 300, so that when the pitch pusher 300 tilts to one side, at least some of the stabilizing assemblies 700 can provide a stabilizing force in the radial direction of the pitch pusher 300 based on their own structural stiffness, resisting the tilting deformation of the pitch pusher 300 and ensuring the planar stability of the pitch pusher 300 during rotation.

[0120] Understandably, since there are at least two blades, meaning there are at least two overturning moments applied to the pitch pusher 300, the number of stabilizing components 700 is at least two, thereby resisting the overturning deformation of the pitch pusher 300 and ensuring planar stability during rotation. Of course, since three points determine a plane, the number of stabilizing components 700 is preferably at least three. The three stabilizing components 700 working together can ensure the planar stability of the pitch pusher 300 during rotation. However, since some propellers have more than three blades, the number of stabilizing components 700 should be as large as possible to further improve the planar stability of the pitch pusher 300. For example, to balance the different overturning moments between different blades 600 as much as possible, in one embodiment, the number of stabilizing components 700 is the same as the number of blades 600 and they correspond one-to-one. That is, the number of stabilizing components 700 is the same as the number of blades 600, and each blade has a corresponding stabilizing component 700 to balance its overturning moment.

[0121] As can be seen, multiple pitch transmission assemblies 500 and multiple stabilizing assemblies 700 are connected to the outer edge of the pitch pusher 300. Since the pitch pusher 300 is positioned outside the propeller hub 200, the arrangement of the pitch transmission assemblies 500 and the stabilizing assemblies 700 will affect the aerodynamic shape of the pitch propeller. In one embodiment, at least three stabilizing assemblies 700 and at least two pitch transmission assemblies 500 are alternately arranged in the circumferential direction of the pitch pusher 300.

[0122] Specifically, since the pitch transmission assembly 500 is used to drive the blades to oscillate around their pitch axis, it is generally arranged eccentrically relative to the pitch axis of the blades. In this case, the stabilizing assembly 700 can be arranged directly opposite the pitch axis of the corresponding blade 600, thus allowing the pitch transmission assembly 500 and the stabilizing assembly 700 to be alternately arranged in the circumferential direction of the pitch pusher 300. That is, the pitch transmission assembly 500 and the stabilizing assembly 700 are staggered in the circumferential direction, avoiding radial interference between them and thus preventing an increase in the overall size of the propeller. This also facilitates the use of a small enclosure to completely enclose the pitch pusher 300, the pitch transmission assembly 500, and the stabilizing assembly 700, improving the aerodynamic shape of the pitch propeller.

[0123] The aforementioned stabilizing component 700 includes, but is not limited to, linear guide rods, telescopic cylinders, etc. Alternatively, in one embodiment, the stabilizing component 700 includes: a first connecting arm 710, a second connecting arm 720, and an elastic element 730. One end of the first connecting arm 710 is hinged to the variable pitch push plate 300; one end of the second connecting arm 720 is hinged to the other end of the first connecting arm 710, and the other end of the second connecting arm 720 is hinged to the propeller hub 200, with an included angle between the first connecting arm 710 and the second connecting arm 720; the elastic element 730 is disposed between the first connecting arm 710 and the second connecting arm 720.

[0124] Specifically, please refer to Figure 3 and Figure 4The first connecting arm 710 and the second connecting arm 720 are hinged together to form a "V"-shaped two-bar structure. When the pitch pusher 300 moves away from the rotor hub 200, the angle between the first connecting arm 710 and the second connecting arm 720 increases; conversely, when the pitch pusher 300 moves closer to the rotor hub 200, the angle between the first connecting arm 710 and the second connecting arm 720 decreases. This V-shaped structure, through the swing of the first connecting arm 710 relative to the pitch pusher 300, the swing of the second connecting arm 720 relative to the rotor hub 200, and the change in the angle between the first connecting arm 710 and the second connecting arm 720, can adequately accommodate the tensile and compressive loads on the pitch pusher 300 in its axial and radial directions. Furthermore, in this "V"-shaped two-link structure, as the pitch pusher 300 approaches or moves away from the propeller hub 200, the included angles of multiple two-link structures change simultaneously, collectively guiding the pitch pusher 300 and ensuring its axial reciprocating movement along the propeller hub 200. This V-shaped two-link structure forms a triangular unit, and by utilizing the stability principle of the triangular unit, the strength of the manufacturing materials of the first connecting arm 710 and the second connecting arm 720 is fully utilized in all included angle states.

[0125] In addition, an elastic element 730 is installed between the first connecting arm 710 and the second connecting arm 720. The elastic element 730 is used to provide a balancing torque by its own deformation when the variable pitch push plate 300 overturns and the included angle of the first connecting arm 710 and the second connecting arm 720 changes. Thus, the balancing torque provided by the elastic elements 730 of all stabilizing components 700 jointly resists the overturning torque of the variable pitch push plate 300, so as to maintain the stability of the variable pitch push plate 300.

[0126] Furthermore, the stabilizing component 700 can also reduce vibration and load through the elastic element 730. The elastic element 730 includes, but is not limited to, tension springs, compression springs, or torsion springs. In one embodiment, the elastic element 730 is a torsion spring, and the torsion spring is sleeved on the hinge shaft between the first connecting arm 710 and the second connecting arm 720. It should be noted that since the torsion spring is sleeved on the hinge shaft, compared to tension springs and compression springs, the torsion spring does not occupy space outside the first connecting arm 710 and the second connecting arm 720. This not only helps to make the aerodynamic shape of the variable pitch propeller simpler, but also avoids occupying space within the variable pitch pusher 300 and the hub 200 to affect the reciprocating movement of the variable pitch pusher 300.

[0127] It is worth mentioning that, compared to other configurations of the stabilizing component 700, the triangular structure is also suitable for dynamic load scenarios such as overturning moment. The combination of three or more "V"-shaped two-link structures with elastic element 730 gives the variable pitch pusher 300 a strong ability to resist overturning moment and ensures the consistency of the pitch of each blade.

[0128] In addition, in this embodiment, please refer to Figure 5 The diagram illustrates how the spring gain of the elastic element 730 and the motor load (torque value) of the electric motor 100 change with the aerodynamic pitch load during the transition from hovering to tilting conditions (where the elastic force of the elastic element 730 approximately conforms to Hooke's law, and its elastic force value changes with the length of the elastic element 730). The presence of the elastic element 730 reduces the average drive load of the pitch motor 410, and the integrated spring provides considerable power gain.

[0129] In addition, when the variable pitch propeller is subjected to unsteady variable pitch load fluctuations (such as gusts, diagonal currents, etc.), the elastic element 730 will also provide a balancing torque to rapidly reduce interference, thereby improving the anti-interference capability of the variable pitch pusher 300.

[0130] Understandably, as one option in this embodiment, the V-shaped structure formed by the first connecting arm 710 and the second connecting arm 720 is located in the lower inner region of the variable pitch push plate 300, that is, on the plane where the variable pitch push plate 300 is located, the projections of the first connecting arm 710 and the second connecting arm 720 are both located on the variable pitch push plate 300. Alternatively, as another option in this embodiment, on the plane where the variable pitch push plate 300 is located, the projections of the first connecting arm 710 and the second connecting arm 720 are both located radially outer of the variable pitch push plate 300.

[0131] It is easy to see that, compared to the V-shaped structure formed by the first connecting arm 710 and the second connecting arm 720 being located in the lower inner area of ​​the pitch pusher 300, the V-shaped structure formed by the first connecting arm 710 and the second connecting arm 720 being located on the outer side of the pitch pusher 300 will not occupy the space between the pitch pusher 300 and the hub 200 in the axial direction, thus avoiding increasing the distance between the pitch pusher 300 and the hub 200 and causing an increase in the overall axial dimension of the pitch propeller.

[0132] Additionally, please see Figure 6 The elastic element 730 also adds a preload to the pitch-changing push plate 300. The stabilizing component 700 provides the axial component of the preload in the hub 200, which can eliminate the clearance between the lead screw 420 and the moving component 430, improving pitch accuracy. When the preload provided by the stabilizing component 700 is a thrust, the teeth between the lead screw 420 and the moving component 430 are engaged on the upper surface, while when the preload provided by the elastic element is a tension, the teeth between the lead screw 420 and the moving component 430 are engaged on the lower surface.

[0133] It is worth mentioning that the stabilizing component 700 can also be constructed as an elastic damper, vibration damper, or other structures, thereby achieving the anti-overturning effect through structural stiffness while also providing the vibration reduction and load reduction functions of the aforementioned elastic components.

[0134] In one embodiment, the variable pitch transmission assembly 500 includes a variable pitch link and a variable pitch pin 550. One end of the variable pitch link is hinged to the variable pitch push plate 300, and the other end of the variable pitch link is hinged to one end of the variable pitch pin 550. The other end of the variable pitch pin 550 is fixedly connected to the blade 600 to rotate around the variable pitch axis of the blade 600, and the length of the variable pitch link is adjustable.

[0135] Specifically, the pitch pin 550 extends radially along the propeller shank 610, protruding from the circumferential wall of the blade 600, allowing the pitch pin 550 to pivot about the pitch axis of the blade 600. It is worth noting that when the pitch transmission assembly 500 is located inside the propeller hub 200, the pitch pin 550 can be fixed to the end face of the portion of the blade extending into the propeller hub 200, and extends radially along the propeller shank 610, protruding from the circumferential wall of the blade. Alternatively, when the pitch transmission assembly 500 is located outside the propeller hub 200, the pitch pin 550 can be fixed to the circumferential wall of the propeller shank 610.

[0136] The pitch control link extends roughly along the axial direction of the hub 200, with one end hinged to the pitch control pusher 300 above the hub 200 and the other end hinged to the pitch control pin 550 on the radial side of the hub 200. This allows the pitch control pusher 300, the pitch control link, and the pitch control pin 550 to form a crank-connecting rod structure, which can transmit the linear movement of the pitch control pusher 300 to the pitch control pin 550, thereby driving the blade to swing and adjusting the angle of attack of the blade.

[0137] After the blades are installed in the rotor hub 200, fine-tuning of the blade angle 600 can be achieved by adjusting the length of the pitch control link or the pitch pin 550. In this embodiment, the length of the pitch control link is adjustable, so after the blades are installed in the rotor hub 200, fine-tuning of the blade angle of attack can be achieved by adjusting the length of the pitch control link.

[0138] It is easy to understand that since the length of the pitch link is longer than the length of the pitch pin 550, and most of the pitch link is exposed compared to the pitch pin 550, it is easier for maintenance personnel to adjust the pitch of the pitch link, thereby achieving fine adjustment of the angle of attack.

[0139] As one option in this embodiment, the variable-pitch link includes: a fixed section 510 with openings at both ends along the axial direction, a first moving section 520, a second moving section 530, and an adjusting structure. The fixed section 510 defines a receiving cavity that communicates with both openings; a portion of the first moving section 520 extends into the receiving cavity from one end opening of the fixed section 510 and is movable along the axial direction of the fixed section 510; a portion of the second moving section 530 extends into the receiving cavity from the other end opening of the fixed section 510 and is movable along the axial direction of the fixed section 510; at least a portion of the adjusting structure 540 is disposed within the receiving cavity and is connected to both the first moving section 520 and the second moving section 530 to adjust the distance between them; a locking member (not shown) cooperates with both the fixed section 510 and the adjusting structure 540 to lock the adjusting structure.

[0140] Specifically, please refer to Figure 7 The variable pitch link generally consists of three parts: a fixed section 510, a first moving section 520, and a second moving section 530. The fixed section 510 is generally constructed as a hollow tubular structure with openings at both ends. This allows a portion of the first moving section 520 to extend into the fixed section 510 from one axial opening, and a portion of the second moving section 530 to extend into the fixed section 510 from the other axial opening. Both the first and second moving sections 520 and 530 can move axially within the fixed section 510, thereby changing the length of the portions of both sections exposed above the fixed section 510. This allows the overall length of the fixed section 510, the first moving section 520, and the second moving section 530 to be adjustable axially, meaning the length of the variable pitch link is adjustable.

[0141] It should be noted that the cross-sectional shape of the fixed segment 510 can be circular, polygonal, etc., and this embodiment is not limited in this respect. Furthermore, to prevent the first moving segment 520 and the second moving segment 530 from detaching from the fixed segment 510 during movement, both the first moving segment 520 and the second moving segment 530 are variable diameter structures. The outer diameter of the portion of the first moving segment 520 or the second moving segment 530 located inside the fixed segment 510 is larger than the outer diameter of the portion of the first moving segment 520 or the second moving segment 530 located outside the fixed segment 510. Additionally, the diameter of the openings at both axial ends of the fixed segment 510 matches the outer diameter of the portion of the first moving segment 520 or the second moving segment 530 located outside the fixed segment 510 and is smaller than the outer diameter of the portion of the first moving segment 520 or the second moving segment 530 located inside the fixed segment 510. In one example, please refer to... Figure 8 The portion of the first moving segment 520 or the second moving segment 530 located inside the fixed segment 510 is connected to the portion located outside the fixed segment 510 by a thread.

[0142] At least a portion of the adjusting structure 540 is disposed within the receiving cavity and is connected to the first moving segment 520 and the second moving segment 530 respectively, thereby adjusting the distance between the first moving segment 520 and the second moving segment 530 within the fixed segment 510.

[0143] The pitch adjustment structure 540 may include a knob and a cam fixedly connected to each other. The cam is rotatably disposed within a receiving cavity, while the knob is located outside the fixed section 510, and the cam can be forced to rotate by rotating the knob. The first moving section 520 and the second moving section 530 are located on opposite sides of the cam and both abut against the cam surface. As the cam rotates, the first moving section 520 and the second moving section 530 slide relative to the cam surface, thereby changing the pitch between the first moving section 520 and the second moving section 530.

[0144] Alternatively, in one embodiment, the adjusting structure 540 includes a knob portion 541 and a mating portion 542. The knob portion 541 is rotatably disposed on the outer peripheral wall of the fixed section 510; the mating portion 542 is disposed in the receiving cavity and fixedly connected to the knob portion 541, and a cam groove 5421 is formed on the side end face of the mating portion 542 opposite to the knob portion 541. The first moving section 520 includes a first protrusion 524, which extends into the cam groove 5421 and slidably engages with it; the second moving section 530 includes a second protrusion 534, which extends into the cam groove 5421 and slidably engages with it.

[0145] Specifically, the side wall of the fixed section 510 has a mounting hole communicating with the receiving cavity. The rotating post of the knob part 541 extends into the mounting hole, allowing the knob part 541 to rotate around the central axis of the mounting hole. The mating part 542 is located within the receiving cavity, and its end face facing the knob part 541 is fixedly connected to the rotating post of the knob part 541. Thus, when the knob part 541 is rotated, the mating part 542 can also be forced to rotate around the central axis of the mounting hole. A cam groove 5421 is provided on the end face of the mating part 542 away from the knob part 541. On the end face of the mating part 542 away from the knob part 541, the cam groove 5421 has a farthest point farthest from the central axis of the mounting hole and a closest point closest to the central axis of the mounting hole.

[0146] The first moving segment 520 has a first protrusion 524 that extends into and slides within the cam groove 5421. Similarly, the second moving segment 530 has a second protrusion 534 that extends into and slides within the cam groove 5421. It should be noted that the first moving segment 520, the mating portion 542, and the second moving segment 530 can be arranged sequentially along the axial direction of the fixed segment 510. Thus, the first protrusion 524 can protrude from the first moving segment 520 along the axial direction of the fixed segment 510 and bends and extends towards the mating portion 542, thereby extending into the cam groove 5421. Similarly, the second protrusion 534 can protrude from the second moving segment 530 along the axial direction of the fixed segment 510 and bends and extends towards the mating portion 542, thereby extending into the cam groove 5421. Alternatively, please refer to [link to relevant documentation]. Figure 9 The first moving segment 520 and the second moving segment 530 can be spaced apart from each other in the axial direction of the fixed segment 510, and the mating part 542 is located on the side of the first moving segment 520 and the second moving segment 530. A portion of the surface of the side wall of the first moving segment 520 near the mating part 542 protrudes into the cam groove 5421 to form a first protrusion 524, and a portion of the surface of the side wall of the second moving segment near the mating part 542 protrudes into the cam groove 5421 to form a second protrusion 534.

[0147] Therefore, when the maintenance personnel rotate the mating part 542 through the knob part 541, the cam groove 5421 on the end face of the mating part 542 is also forced to rotate. Since the first moving section 520 and the second moving section 530 are constrained by the fixed section 510, the first protrusion 524 and the second protrusion 534 can only move along the axial direction of the fixed section 510. As the first protrusion 524 and the second protrusion 534 slide in the cam groove 5421, the rotation of the cam groove 5421 will force the first protrusion 524 and the second protrusion 534 to move closer to or further away from each other, ultimately achieving the adjustment of the blade mounting angle.

[0148] Alternatively, in another embodiment, the mating portion 542 of the pitch adjustment structure 540 is constructed as an external gear, the first moving segment 520 has a first rack portion, the second moving segment 530 has a second rack portion, and the first rack portion and the second rack portion are respectively on opposite sides of the external gear and mesh with the mating portion 542.

[0149] Therefore, when the maintenance personnel rotate the mating part 542 through the knob part 541, since the first moving section 520 and the second moving section 530 are constrained by the fixed section 510, the first rack part and the second rack part can only move along the axial direction of the fixed section 510. In addition, since the first rack part and the second rack are located on opposite sides of the mating part 542, the rotation of the mating part 542 will force the first moving section 520 and the second moving section 530 to move closer to or further away from each other, ultimately achieving the adjustment of the blade mounting angle.

[0150] Of course, the adjustable pitch structure 540 is not limited to the above-described implementation method, and can still be achieved by converting rotary motion to linear motion through threaded pairs or other means.

[0151] In this embodiment, the locking component can be constructed as a locking pin or similar structure, which has a locking state. After the blade mounting angle is adjusted, the locking component switches to the locking state to lock the knob 541, preventing the knob 541 from rotating, thereby maintaining the current blade mounting angle. Of course, the locking component can also be constructed as other structures that can lock the knob and prevent the knob from rotating; this embodiment is not limited in this regard.

[0152] Alternatively, as another option in this embodiment, the variable pitch transmission assembly 500 further includes: a rotating member 560, a connecting rod body 580, and a locking member 570. The rotating member 560 is rotatably connected to the peripheral sidewall of the variable pitch push plate 300, and the rotation axis of the rotating member 560 extends radially along the variable pitch push plate 300. One end of the connecting rod body 580 is rotatably connected to the sidewall of the rotating member 560 opposite to the variable pitch push plate 300. The rotation axis between one end of the connecting rod body 580 and the rotating member 560 is parallel to and spaced apart from the rotation axis of the rotating member 560. The other end of the connecting rod body 580 is hinged to one end of the variable pitch pin 550. The locking member 570 cooperates with both the rotating member and the variable pitch push plate 300 to lock them.

[0153] Specifically, please refer to Figure 10 The rotating member 560 can be constructed in a cylindrical shape. The rotating member 560 and the connecting rod body 580 are arranged sequentially in the direction from the radial inner side to the radial outer side of the pitch-changing push plate 300. The rotating member 560 rotates relative to the pitch-changing push plate 300 around its central axis (parallel to the radial direction of the pitch-changing push plate 300). One end of the connecting rod body 580 is rotatably connected to the end face of the rotating member 560 facing away from the pitch-changing push plate 300. The axis of rotation between the end of the connecting rod body 580 and the rotating member 560 is parallel to and spaced apart from the axis of rotation of the rotating member 560, thus making the connecting rod body 580 eccentrically arranged relative to the rotating member 560. As a result, as the rotating component 560 rotates, the distance between one end of the connecting rod body 580 and the plane where the pitch pusher 300 is located also changes. That is, the distance between the hinge axis between the pitch pin 550 and the other end of the connecting rod body 580 and the plane where the pitch pusher 300 is located changes. When this distance changes, the pitch pin 550 drives the blade to swing, thereby changing the blade's installation angle.

[0154] Furthermore, the locking member 570 is used to lock the rotatable rotating member 560 to prevent it from rotating relative to the variable pitch push plate 300. Specifically, the circumferential sidewall of the rotating member 560 is threaded, and the locking member 570 can be constructed as a screw. In the axial direction of the screw, the screw has a threaded portion and a smooth portion, and the threaded portion and the rotating member 560 form a "worm gear" engagement relationship. In this way, the self-locking property of the "worm gear" is used to lock the rotating member 560, preventing it from rotating relative to the variable pitch push plate 300.

[0155] Of course, the locking component 570 can also be constructed as other structures that can lock the rotating component 560, which rotates around its own axis of rotation, such as a locking pin, etc., which will not be elaborated here.

[0156] It is easy to see that the blade installation angle can be adjusted at the pitch control link. Since the pitch control link is relatively long and generally exposed, it is convenient for maintenance personnel to operate. Furthermore, the blade installation angle can also be adjusted at the pitch pusher. In this embodiment, since the pitch pusher 300 is top-mounted, there is sufficient space for maintenance personnel to operate without needing to disassemble or reassemble the pitch propeller, thus improving maintenance efficiency and convenience.

[0157] Furthermore, during actual flight, inconsistent blade loads can sometimes occur, leading to a deviation in the actual flight direction. Therefore, in one embodiment, the first moving segment 520 further includes a first rod 521, a first elastic layer 523, and a second rod 522 sequentially connected along the axial direction of the fixed segment 510. The first rod 521 and / or the second rod 522 move within the fixed segment 510 along the axial direction of the fixed segment 510.

[0158] Specifically, please refer to Figure 9 The first moving segment 520 comprises three sequentially connected parts along the axial direction of the fixed segment 510. A first rod 521 is connected to the variable-pitch push plate 300. At least a portion of the second rod 522 extends into the fixed segment 510 and slides within it. The first rod 521 and the second rod 522 are connected by a first elastic layer 523. It should be noted that the first elastic layer 523 can be disposed within the fixed segment 510, in which case a portion of the first rod 521 extends into the fixed segment 510, and the entire second rod 522 is located within the fixed segment 510; alternatively, the first elastic layer 523 can be located outside the fixed segment 510, in which case the first rod 521 is located outside the fixed segment 510, and a portion of the second rod 522 extends into the fixed segment 510.

[0159] Alternatively, the second moving segment 530 may comprise three sequentially connected parts along the axial direction of the fixed segment 510: a third rod 532, a second elastic layer 533, and a fourth rod 531. At least a portion of the third rod 532 extends into the fixed segment 510 and slides within it. The fourth rod 531 is connected to the variable pitch pin 550, and the third rod 532 and the fourth rod 531 are connected via the second elastic layer 533. Similarly, the second elastic layer 533 may be disposed within the fixed segment 510, in which case a portion of the fourth rod 531 extends into the fixed segment 510, and the entire third rod 532 is located within the fixed segment 510; or, the second elastic layer 533 may be located outside the fixed segment 510, in which case the fourth rod 531 is located outside the fixed segment 510, and a portion of the third rod 532 extends into the fixed segment 510.

[0160] Of course, the first elastic layer 523 and the second elastic layer 533 can also be set at the same time, which will not be elaborated here.

[0161] Thus, when the tiltrotor undergoes a transition mode transition, resulting in inconsistent loads on the blades, the load is transferred to the pitch linkage. The first elastic layer 523 and / or the second elastic layer 533 can undergo elastic deformation, enabling the blade pitch angle to change in the direction of aerodynamic unloading, achieving adaptive adjustment of the pitch angle, thereby improving the uneven load on the hub 200 and the pitch pusher 300.

[0162] It is worth mentioning that the materials of the first elastic layer 523 and the second elastic layer 533 include, but are not limited to, rubber, elastomeric plastics, etc.

[0163] Additionally, please see Figure 9 The second rod 522 may have the aforementioned first protrusion 524, and the third rod 532 may have the aforementioned second protrusion 534. In one specific embodiment, the first protrusion 524 and the second protrusion 534 are both connected to the body (first rod 521 or fourth rod 531) of the first moving segment 520 or the second moving segment 530 through an elastic material (first elastic layer or second elastic layer).

[0164] As previously stated, in this embodiment, after the variable-pitch pusher 300 is positioned above the space within the propeller hub 200, in one embodiment, the variable-pitch propeller further includes at least two angle sensors. Each of the at least two angle sensors corresponds to one of the at least two propeller blades, and the angle sensors are located on the portions of the blades extending into the propeller hub 200. This allows for the addition of angle sensors within the propeller hub 200, matching the number of blades, thereby enabling the direct acquisition of the angle of attack of each blade and improving the accuracy of angle measurement.

[0165] Please see Figure 2In one embodiment, the electric motor 100 further includes a rear cover 130, a cooling assembly 140, and an eccentric shaft 150. The rear cover 130 is disposed on the side of the inner stator 120 opposite to the propeller hub 200; the cooling assembly 140 is disposed on the side of the rear cover 130 opposite to the inner stator 120; the eccentric shaft 150 is rotatably disposed in the central shaft hole of the inner stator 120 about its own central axis, the central axis of the eccentric shaft 150 is parallel to and spaced apart from the central axis of the central shaft hole, and one end of the eccentric shaft 150 is drivenly connected to the cooling assembly 140, and the other end of the eccentric shaft 150 is drivenly connected to the outer rotor 110, so that the outer rotor 110 drives the cooling assembly 140 through the eccentric shaft.

[0166] The cooling assembly 140 may include an air-cooled assembly (such as a cooling fan), a liquid-cooled assembly (such as a heat exchanger and a pumping assembly that pumps coolant into the motor so that the coolant flows through the motor), or a combination of an air-cooled assembly and a liquid-cooled assembly.

[0167] Since the central shaft hole inside the inner stator 120 connects the two axial ends of the inner stator 120, and the outer rotor 110 and the cooling assembly 140 are respectively located at the two axial ends of the inner stator 120, in this embodiment, part of the eccentric shaft 150 is arranged in the central shaft hole, with one end extending to the mechanical connection end and drivingly connected to the outer rotor 110, and the other end extending to the cooling assembly 140 and drivingly connected to the cooling assembly 140, thereby transmitting the rotational motion of the outer rotor 110 to the cooling assembly 140 to drive the air-cooled component and / or liquid-cooled component of the cooling assembly 140 to start operation.

[0168] It is easy to see that in this embodiment, an eccentric shaft 150 is added to the existing space in the inner stator 120 of the outer rotor 110 motor, that is, in the central shaft hole passing through the inner stator 120 along the axial direction of the inner stator 120. The eccentric shaft 150 drives the outer rotor 110 to the cooling assembly 140 that removes the heat generated during motor operation. Thus, the cooling assembly 140 is driven by the outer rotor 110 in the motor assembly, eliminating the need for a separate electric drive assembly and the required circuit wiring structure, thereby optimizing the overall weight of the motor assembly. In addition, the outer rotor 110 drives the cooling assembly 140 through the eccentric shaft with a mechanical transmission structure, which has higher reliability and safety compared to a separate electric drive assembly.

[0169] Furthermore, in this embodiment, most of the eccentric shaft is arranged in the central shaft hole within the inner stator 120, without changing the existing structure and layout of the motor and cooling assembly 140 in the motor assembly, thus facilitating its widespread use in existing products.

[0170] Furthermore, this embodiment eliminates the need for a separate electric drive assembly required for the cooling assembly 140, thereby avoiding the heat dissipation problems and risks associated with the separate drive motor.

[0171] Furthermore, since the eccentric shaft 150 rotates around its own central axis, and the central axis of the eccentric shaft 150 is offset from the central axis of the rotating shaft 112, a corresponding transmission structure is needed to connect the rotating shaft 112 and the eccentric shaft 150 to transmit the rotational motion of the rotating shaft 112 to the eccentric shaft 150. It is understood that the eccentric shaft 150 and the rotating shaft 112 are transmissions between different shafts, and therefore, a gear set or transmission belt can be used. However, transmission belts or similar structures may occupy space within the rotating shaft hole, thus affecting the laying of connecting cables. Therefore, in one embodiment, the electric motor also includes an internal gear ring 161 and a mating gear 162. The internal gear ring 161 is fixedly connected to the end face of the rotating shaft 112 of the outer rotor near the inner stator 120, and the central axis of the internal gear ring 161 is collinear with the central axis of the outer rotor 110; the mating gear 162 is fixedly sleeved on the other end of the eccentric shaft 150, and the mating gear 162 meshes with the internal gear ring 161.

[0172] Specifically, please refer to Figure 2 , Figure 11 and Figure 12 The internal gear ring 161 is fixed to the end face of the rotating shaft 112 near the inner stator 120 by fasteners such as screws or welding, and the central axis of the internal gear ring 161 is collinear with the central axis of the rotating shaft 112. A mating gear 162 meshes with the internal gear ring 161 inside the internal gear ring 161, and the mating gear 162 is fixedly sleeved on the end of the eccentric shaft 150 near the rotating shaft 112. Thus, when the rotating shaft 112 rotates, it also drives the internal gear ring 161 to rotate, and the rotation of the internal gear ring 161 will drive the mating gear 162 to rotate around the central axis of the eccentric shaft 150, that is, drive the eccentric shaft 150 to rotate around its own central axis.

[0173] It is easy to see that in this embodiment, since the internal gear ring 161 is an annular component and its interior is hollow, the internal gear ring 161 does not occupy the front and rear space in the axial direction of the shaft hole, thus leaving enough space for cable laying. In this way, the connecting cable can pass through the internal gear ring 161 and the through hole 111 in sequence and extend to the outside of the motor assembly.

[0174] It is worth mentioning that, in order to further avoid the internal gear ring 161 from affecting the cable laying, the inner diameter of the internal gear ring 161 can be larger than the inner diameter of the rotating shaft 112, that is, the inner edge of the projection of the internal gear ring 161 on the plane where the end face of the rotating shaft 112 is located is located radially outside the inner edge of the rotating shaft 112.

[0175] Understandably, when the motor is running, the mating gear 162 will rotate at high speed. If the cable touches the mating gear 162, it will be damaged. Therefore, in one embodiment, the thrust assembly further includes a support cover, which is disposed in the through hole 111 and fixedly connected to the inner stator 120. A portion of the surface of one end face of the support cover protrudes to form a protrusion, and the protrusion has a cable routing hole 173 that passes through the support cover along the axial direction of the inner stator 120. The protrusions are located radially outside the mating gear 162 and are spaced apart from each other.

[0176] Specifically, the support cover is located inside the shaft hole but is not fixedly connected to the shaft 112. Instead, it is fixedly connected to the inner stator 120. An eccentric shaft bearing is mounted on the support cover, which cooperates with the eccentric shaft 150 to allow the eccentric shaft 150 to rotate relative to the support cover. A portion of the surface of one end face of the support cover protrudes radially outward from the mating gear 162, forming a protrusion. A cable routing hole 173 is formed within the protrusion for the cable to pass through. The cable routing hole 173 provides a separate wiring space. Thus, when the connecting cable passes near the mating gear 162, it is constrained and protected by the wall of the cable routing hole 173, thereby preventing the connecting cable from being damaged by the high-speed rotating mating gear 162.

[0177] Please see Figure 11 and Figure 12The support cover includes an upper support cover 172 and a lower support cover 171. The lower support cover 171 is fixed to the end face of the inner stator 120 near the rotating shaft 112. A portion of the surface of the end face of the lower support cover 171 near the rotating shaft 112 protrudes in a direction away from the inner stator 120 to form a lower protrusion 1711. The upper support cover 172 is located inside the rotating shaft 112 and is not connected to the rotating shaft 112. A portion of the surface of the upper support cover 172 near the inner stator 120 protrudes in a direction close to the inner stator 120 to form an upper protrusion 1721. The upper protrusion 1721 abuts against the lower protrusion 1711 and is fixedly connected to each other to form a protrusion. At this time, the upper support cover 172 and the lower support cover 171 define a receiving space in which the gear 162 and the eccentric shaft bearing are located. It is easy to see that in this embodiment, the axial ends of the mating gear 162 are covered by the upper support cover 172 and the lower support cover 171, respectively. This further prevents foreign objects from entering the electric motor from the shaft hole, or prevents electronic components in the inner stator 120 from falling and moving to the mating gear 162 and affecting the meshing of the mating gear 162 and the internal gear ring 161, thereby improving the reliability of the mating between the mating gear 162 and the internal gear ring 161. In addition, the length of the connecting cable is always left when it is laid out. That is, the connecting cable is not a straight line in the motor assembly, but a curve. Therefore, covering the axial ends of the mating gear 162 with the upper support cover 172 and the lower support cover 171 respectively can protect the cable in the wiring hole 173 from the hole wall of the wiring hole 173, while the cable near the outside of the wiring hole 173 is protected by the upper support cover 172 and the lower support cover 171, thus preventing the cable from being damaged by the high-speed rotating mating gear 162.

[0178] The cross-sectional shape of the wiring hole 173 can be circular or other shapes. However, since the gear 162 already occupies a portion of the space defined by the shaft hole, in order to allow the wiring hole 173 to occupy more space in the remaining area to accommodate more cables, in one embodiment, please refer to... Figure 4 The cross-section of the wiring hole 173 is arc-shaped, and it partially surrounds the gear 162.

[0179] In addition, the present invention also provides an aircraft, the aircraft including an aircraft body; and at least one thrust assembly as described above, the thrust assembly being disposed on the aircraft body.

[0180] The specific structure of the thrust assembly is as described in the above embodiments. Since this aircraft adopts all the technical solutions of all the above embodiments, it has at least all the beneficial effects brought about by the technical solutions of the above embodiments, which will not be described in detail here.

[0181] The aircraft can be a drone or an electric vertical takeoff and landing (eVTOL) aircraft.

[0182] The above are merely exemplary embodiments of the present invention and do not limit the scope of the patent of the present invention. Any equivalent structural transformations made using the contents of the present invention specification and drawings under the technical concept of the present invention, or direct / indirect applications in other related technical fields, are included within the scope of patent protection of the present invention.

Claims

1. A thrust assembly, characterized in that, include: An electric motor, the electric motor including an outer rotor; The propeller hub is fixedly connected to the outer rotor; A variable pitch pusher, wherein the variable pitch pusher is located on the side of the propeller hub opposite to the electric motor; At least two blades are provided, the blades being rotatably connected to the peripheral wall of the hub about the blade pitch axis, and the at least two blades are spaced apart along the circumferential direction of the hub. as well as At least two pitch transmission assemblies are provided, and each of the at least two pitch transmission assemblies corresponds to one of the at least two blades. The pitch transmission assemblies are respectively connected to the pitch pusher and the blades, so that the pitch pusher drives the blades to swing through the pitch transmission assemblies. Each pitch transmission assembly includes a pitch pin, the other end of which is fixedly connected to the blade to rotate around the pitch axis of the blade. The distance between one end of the pitch pin and the plane where the pitch pusher is located is adjustable to achieve fine adjustment of the blade angle of attack. The thrust assembly also includes: At least two stabilizing components are provided, each stabilizing component being adapted to extend and retract along the axial direction of the propeller hub. One end of each stabilizing component is hinged to the pitch thruster, and the other end of each stabilizing component is hinged to the propeller hub. The at least two stabilizing components are spaced apart along the circumferential direction of the pitch thruster.

2. The thrust assembly as claimed in claim 1, characterized in that, The variable pitch transmission assembly also includes a variable pitch link, one end of which is hinged to the variable pitch push plate, and the other end of which is hinged to one end of the variable pitch pin, and the length of the variable pitch link is adjustable.

3. The thrust assembly as described in claim 2, characterized in that, The variable pitch link includes: A fixed section with openings at both ends along the axis, and the fixed section defines a receiving cavity that communicates with both openings; A first movable segment, a portion of which extends into the receiving cavity from one end opening of the fixed segment, and is movable along the axial direction of the fixed segment; The second movable segment extends into the receiving cavity from the other end of the fixed segment and is movable along the axial direction of the fixed segment; An adjustable spacing structure is provided, a portion of which is disposed within the receiving cavity and is connected to the first moving segment and the second moving segment respectively to adjust the spacing between the first moving segment and the second moving segment; A locking element, which cooperates with both the fixed section and the adjusting structure to lock the adjusting structure.

4. The thrust assembly as described in claim 3, characterized in that, The adjustment structure includes: A knob portion is rotatably disposed on the outer peripheral wall of the fixed section; The mating part is disposed in the receiving cavity and fixedly connected to the knob part, and a cam groove is provided on the side of the mating part away from the knob part. The first moving segment includes a first protrusion that extends into the cam groove and slidably engages with the cam groove, and the second moving segment includes a second protrusion that extends into the cam groove and slidably engages with the cam groove.

5. The thrust assembly as described in claim 3, characterized in that, The first movable segment further includes a first rod, a first elastic layer, and a second rod sequentially connected along the axial direction of the fixed segment, wherein the first rod and / or the second rod move within the fixed segment along the axial direction of the fixed segment; and / or The second moving segment further includes a third rod, a second elastic layer, and a fourth rod connected sequentially along the axial direction of the fixed segment, wherein the third rod and / or the fourth rod moves within the fixed segment along the axial direction of the fixed segment.

6. The thrust assembly as claimed in claim 1, characterized in that, The variable pitch transmission assembly also includes: A rotating component, which is rotatably connected to the peripheral sidewall of the pitch-changing push plate, and the axis of rotation of the rotating component extends radially along the pitch-changing push plate. The connecting rod body has one end rotatably connected to the side wall of the rotating member away from the pitch-changing push plate, and is arranged eccentrically relative to the rotating member. A locking element is provided to lock the rotating member to prevent it from rotating relative to the variable pitch push plate.

7. The thrust assembly as claimed in claim 6, characterized in that, The axial sidewall of the rotating component has threads, and the locking component includes a threaded portion that engages with the rotating component; or The rotating component and the locking component form a worm gear structure.

8. The thrust assembly as claimed in claim 1, characterized in that, One end of the stabilizing component is hinged to the outer edge of the pitch-changing push plate; and / or At least two of the stabilizing components are evenly spaced along the circumferential direction of the variable-pitch pusher; and / or The number of stabilizing components is the same as the number of propeller blades, and they correspond one-to-one.

9. The thrust assembly as claimed in claim 1, characterized in that, The stabilizing component includes: A first connecting arm, one end of which is hinged to the outer edge of the variable pitch push plate; and The second connecting arm has one end hinged to the other end of the first connecting arm, and the other end of the second connecting arm hinged to the propeller hub, with an included angle between the first connecting arm and the second connecting arm.

10. The thrust assembly as claimed in claim 9, characterized in that, The stabilizing component further includes an elastic element disposed between the first connecting arm and the second connecting arm.

11. An aircraft, characterized in that, The aircraft includes: Aircraft body; and At least one thrust assembly as described in any one of claims 1 to 10, the thrust assembly being disposed on the aircraft body, wherein the aircraft is an electric vertical takeoff and landing aircraft.

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