Tilting rotor wing structure with locking mechanism

Abstract

The utility model discloses a tiltable rotor structure with a locking mechanism, and belongs to the technical field of rotor aircrafts. In the tiltable rotor wing structure, a rotor wing power assembly comprises a cover body and a rotor wing installed at one end of the cover body; the tilting mechanism assembly is connected with a tilting shaft of the rotor power assembly and used for driving the rotor power assembly to rotate to a first working position and a second working position relative to the wings in the pitching direction of the aircraft. The tilting locking assembly can be operated to lock the rotor wing power assembly at the second working position when the rotor wing power assembly rotates to the second working position and eliminate the vacant position of the rotor wing power assembly at the second working position. According to the unmanned aerial vehicle, the clearance existing when the rotor wing is located at the working position is eliminated through the locking assembly, so that the rotor wing cannot shake due to the clearance in the flying process, abrasion between parts is reduced, the service life of a vehicle body is prolonged, and the flying quality and the flying stability are improved.

Description

Technical Field

[0001] The utility model belongs to the technical field of tiltrotor aircraft and relates to a tiltrotor structure with a locking mechanism. Background Art

[0002] The tilting mechanism of a tiltrotor aircraft uses gears or screws as a power transmission method, and relies on the self-locking properties of the gears, drive motors or screws to limit the position, or sets a stop mechanism for limiting the position. For example, in the worm gear rotor tilting structure disclosed in CN216102764U, the limit angle piece of the turbine cooperates with the limit bolts on the metal ribs of the wing to limit the tilt angle of the tiltrotor.

[0003] However, such locking or stopping methods cannot guarantee the locking gap amount. At the same time, due to the fact that the tilt-rotor aircraft is undergoing vertical take-off and landing and level flight cruising, the tilt-rotor drive structure will be subjected to large impact vibrations from the wing aerodynamics. Therefore, when it is used for a long time, the gap may become larger and generate noise and vibration, causing parts to collide back and forth or even get stuck, posing a major safety hazard. Utility Model Content

[0004] The utility model aims to provide a tiltable rotor structure with a locking mechanism, so that the rotor structure can achieve stable and reliable mechanical locking without relying on the self-locking of the rotary power device, thereby reducing the wear between parts.

[0005] To achieve the above purpose, the technical solution of the utility model is:

[0006] A tiltable rotor structure with a locking mechanism, comprising:

[0007] The rotor power assembly comprises a cover and a rotor mounted at one end of the cover, wherein a power assembly for driving the rotor is arranged in the cover, and the cover is mounted on the wing through a tilt shaft so that the rotor power assembly can rotate relative to the wing in the pitch direction of the aircraft;

[0008] A tilt mechanism assembly is connected to the tilt shaft of the rotor power assembly and is used to drive the rotor power assembly to rotate relative to the wing in the pitch direction of the aircraft to a first working position and a second working position; wherein, in the first working position, the rotor is in a vertical state relative to the wing to provide lift when the aircraft is ascending or descending; and in the second working position, the rotor is in a horizontal state relative to the wing to provide pulling force when the aircraft is in level flight and cruising;

[0009] The tilt lock assembly can be operated to lock the rotor power assembly in the second position when the rotor power assembly rotates to the second working position, and eliminate the virtual position existing in the rotor power assembly when the rotor power assembly is in the second working position.

[0010] In another example, the tilt locking assembly includes matching limit pins and limit locks, the limit pins are arranged on the side wall of the cover where the tilt axis is located, and the limit locks are installed on the wing component opposite to the side wall of the cover, and when the rotor power assembly rotates to the second working position, the limit locks are locked with the limit pins through a hydraulic or electric control mechanism.

[0011] In another example, a group of limit pins are respectively arranged on two opposite side walls of the cover body, each group of limit pins includes two limit pins that are symmetrical with respect to the center of the tilt axis, and a group of limit locks are respectively arranged on the wing parts opposite to the two side walls of the cover body, and each group of limit locks includes two limit locks that respectively cooperate with the two limit pins.

[0012] In another example, a line connecting two limit pins of the first group of limit pins and a line connecting two limit pins of the second group of limit pins are perpendicular to each other in space, and the two groups of limit locks are arranged correspondingly.

[0013] In another example, the limit lock has a hydraulic mode interface and an electric mode interface, and can be selected to work in a hydraulic mode or an electric mode.

[0014] In another example, the tilt mechanism assembly is disposed on a wing component near the cover, and includes a tilt motor for driving the tilt axis to rotate, the tilt motor having a self-locking function. When the rotor power assembly rotates to a first working position, and when the rotor power assembly rotates to a second working position and the limit lock and the limit pin are locked, the tilt motor activates the self-locking function.

[0015] In another example, the tilt axis includes a left tilt axis and a right tilt axis respectively fixed on two opposite side walls of the cover body, the left tilt axis and the right tilt axis are respectively installed on wing parts opposite to the two side walls of the cover body through bearings, and the tilt motor drives the left tilt axis to rotate through a gear drive mechanism.

[0016] In another example, the right tilt shaft is a hollow shaft, the pipeline channel tube is nested in the right tilt shaft and passes through the side wall of the cover body into the cover body, and the pipelines required by the power assembly enter the power assembly through the inner cavity of the pipeline channel tube.

[0017] In another example, the left tilt shaft and the right tilt shaft are respectively provided with axial limiting components on both sides of the wing component.

[0018] In another example, the outer surface of the cover is covered with a fairing skin so that the cover and the wing form an integrated shape when the rotor power assembly rotates to the first working position and the second working position.

[0019] The utility model eliminates the virtual position existing when the rotor is in the working position through the locking assembly, so that the rotor will not shake due to the virtual position during flight, thereby reducing wear between parts, extending the service life of the body, and improving the flight quality and flight stability.

[0020] In addition, the utility model adopts a rotor power assembly with an integral modular structure, and cooperates with a tilt mechanism assembly with a simple structure, which can realize a fast, stable and reliable tilt operation in a simple mechanism form. In addition, the tilt shaft with a hollow shaft structure simplifies the layout structure of the pipeline line, further improves the stability and reliability of the tilt rotor operation, and reduces the pipeline contact problem caused by vibration. BRIEF DESCRIPTION OF THE DRAWINGS

[0021] Figure 1 It is a schematic diagram of the axial structure of the tilt-rotor aircraft in a horizontal state (hiding part of the body structure not related to the present utility model);

[0022] Figure 2 It is a schematic diagram of the axial structure of the tilt-rotor aircraft in a vertical state (hiding part of the body structure not related to the present utility model);

[0023] Figure 3 for Figure 1 A schematic diagram of a partially enlarged structure of a mid-tilt rotor;

[0024] Figure 4 For Figure 3 Based on the above, the schematic diagram of the shaft side structure of the rotor tilting to the vertical state;

[0025] Figure 5 It is a schematic diagram of the structure of the tilt rotor in a horizontal state from a top view;

[0026] Figure 6 is a schematic diagram of the external structure of the rotor power assembly 200;

[0027] Figure 7 , Figure 8 It is a schematic diagram of the structure of the tilting mechanism assembly and the rotor power assembly when the tilting rotor is in a horizontal state;

[0028] Fig. 9 for Figure 5 Sectional view in the AA direction;

[0029] Fig.10 It is a schematic diagram of the shaft side structure of the right tilt shaft 108;

[0030] Fig.11 for Fig.10 Cross-sectional view in CC direction;

[0031] Fig.12for Figure 5 Cross-sectional view in the BB direction;

[0032] Fig.13 It is a schematic diagram of the axis side of the tilt rotor in a horizontal state;

[0033] Fig.14 For Fig.13 Based on the above, the schematic diagram of the shaft side structure of the rotor tilting to the vertical state;

[0034] Fig.15 for Fig.13 A partial enlarged schematic diagram of the mid-tilt locking assembly.

[0035] In the figure:

[0036] 100-tilt mechanism assembly; 101-driving cylindrical gear; 102-driven cylindrical gear; 103-tilt motor; 104-left tilt shaft; 105-left outer limiting ring; 106-left tilt bearing; 107-left inner limiting ring; 108-right tilt shaft; 109-right inner limiting ring; 110-right tilt bearing; 111-right outer limiting ring; 112-pipeline channel tube; 113-pipeline bearing; 114-pipeline;

[0037] 200-rotor power assembly; 201-engine (motor); 202-cover; 203-propeller shaft; 204-propeller blade; 205-rectifier skin;

[0038] 300-tilt locking assembly; 301-limiting pin; 302-limiting lock; 303-limiting lock connector;

[0039] 400-structural support assembly; 401-left side support rib; 402-right side support rib; 403-left front beam; 404-right front beam; 405-middle beam; 406-rear beam; DETAILED DESCRIPTION

[0040] The present invention is described in more detail below with reference to the accompanying drawings:

[0041] In this utility model, all Figure 1-15 The coordinate system is consistent with the coordinate system of the tilt-rotor aircraft, the X axis of the coordinate system is positive from the tail of the tilt-rotor aircraft to the nose (along the heading), the Y axis is positive from the root of the left wing (fixed wing) to the wing tip (span direction), and the Z axis is positive from the fuselage pointing directly upward. The three coordinate axes are orthogonal and meet the right-hand rule. At the same time, the left points to the +Y axis direction, the front points to the +X axis direction (that is, the forward direction of the tilt-rotor aircraft is forward), and the top points to the +Z axis direction.

[0042] In the present invention, it can be understood that the tilt-rotor aircraft with a tilt-rotor structure is symmetrical about the ZX plane, that is, the wing structures including the tilt-rotor structure on the left and right sides of the tilt-rotor aircraft are the same. Therefore, only the tilt-rotor structure arranged on one wing is described below, and the tilt-rotor structure arranged on the other wing is the same and is symmetrically arranged left and right.

[0043] In addition, it should be noted that for the sake of clarity of description, the present invention Figure 1-15 The fuselage structure that adopts conventional design, such as fuselage and wing skin, is hidden, and only part of the front and rear wing beams and wing ribs are displayed.

[0044] In one embodiment, referring to Figure 1-4 As shown, the tiltable rotor structure is arranged on the front side of the wing of the tiltrotor aircraft, and includes a tilt mechanism assembly 100 , a rotor power assembly 200 , a tilt locking assembly 300 and a structural support assembly 400 .

[0045] The rotor power assembly 200 adopts an independent module structure, including a cover body and a rotor installed at one end of the cover body, and a power assembly wing for driving the rotor is arranged in the shell.

[0046] The tilt mechanism assembly 100 is used to tilt the rotor power assembly 200 to a required working position.

[0047] The tilt lock assembly 300 is used to eliminate the virtual position that exists when the rotor is restricted to the working position, thereby preventing the rotor from shaking due to the virtual position during flight.

[0048] The structural support assembly 400 is used to provide structural support for the tilt mechanism assembly 100, the rotor power assembly 200, and the tilt lock assembly 300. As an example, the structural support assembly 400 adopts a structural integration design, and the front beam, the middle beam and the rib of the wing are used as the supporting structural parts in the structural support assembly 400 to reduce the structural weight. In other examples, the supporting structural parts in the structural support assembly 400 can also be designed as brackets, joints, etc. fixedly connected to the wing, thereby improving the flexibility of design, manufacturing and installation, and reducing the impact on the structure of the wing itself.

[0049] As an example, the structural support assembly 400 is formed with a mounting groove, the rotor power assembly 200 can be set in the mounting groove, and the tilt mechanism assembly 100 drives the power assembly 200 to tilt in the mounting groove along the pitch direction of the tilt rotor aircraft, so as to place the rotor in a horizontal working position used as a pulling propeller or a vertical working position providing lift. Specifically, for example, when the tilt rotor aircraft takes off and lands vertically, the tilt mechanism assembly 100 drives the power assembly 200 to tilt in the mounting groove as a whole, so as to place the rotor in a vertical working position providing lift, such as Figure 2 When the tilt-rotor aircraft takes off and reaches a certain speed, the tilt mechanism assembly 100 drives the power assembly 200 to tilt forward in the mounting slot as a whole, so as to place the rotor in a horizontal working position used as a pulling propeller, as shown in FIG. Figure 1 As shown, the tilt-rotor aircraft can now fly long distances at a higher speed like a wing aircraft.

[0050] Reference Figure 3-5 The power assembly of the rotor power assembly 200 includes an engine 201 installed in a cover 202, such as a drive motor. The rotor includes a propeller shaft 203 connected to the power output shaft of the engine 201 and blades 204 installed on the propeller shaft. The engine 201 drives the propeller shaft 203, thereby driving the blades 204 to rotate, providing traction or lift for the tilt-rotor aircraft.

[0051] In order to improve the aerodynamic performance of the tiltrotor aircraft and improve the stealth performance, the outer surface of the cover 202 is covered with a fairing skin 205 so that the cover and the wing form an integrated shape when the rotor is in the horizontal working position and the vertical working position.

[0052] The cover 202 is rotatably supported in the mounting groove via a tilt axis. The tilt mechanism assembly 100 is disposed on one side of the cover 202 and includes a tilt motor 103 which drives the tilt axis to rotate via a gear transmission mechanism, thereby driving the rotor power assembly 200 to tilt to a desired working position.

[0053] In one example, the gear transmission mechanism includes a driving cylindrical gear 102 connected to the tilt motor 103 and a driven cylindrical gear 101 meshing with the driving cylindrical gear 102 , wherein the driven cylindrical gear 102 is connected to the tilt axis.

[0054] When the tilt-rotor aircraft is performing vertical take-off and landing or level flight cruising, the tilt motor 103 drives the driving cylindrical gear 102 to rotate, and the driving cylindrical gear 102 drives the driven cylindrical gear 101 meshing therewith to rotate, and the driven cylindrical gear 101 drives the tilt shaft fixedly connected to the cover 202 to rotate, thereby driving the rotor power assembly 200 to tilt to the required working position.

[0055] Reference Figure 5 In one example, the structural support assembly 400 includes a left support rib 401 and a right support rib 402 fixedly installed between a left front beam 403, a right front beam 404 and a middle beam 405 of the wing, and the installation groove is formed between the left support rib 401 and the right support rib 402, that is, the rotor power assembly 200 is installed between the left support rib 401 and the right support rib 402.

[0056] The tilt motor 103 is fixedly mounted on one of the left side support ribs 401 and the right side support ribs 402, or on the middle beam 405 on the outside of one of the left side support ribs 401 and the right side support ribs 402, and its output shaft is connected to the driving cylindrical gear 102, and the driving cylindrical gear 102 is meshed with the driven cylindrical gear 101. In the example shown in the figure, the tilt motor 103 is fixedly mounted on the middle beam 405 on the outside of the corresponding left side support rib 401. The tilt shaft is mounted on the support rib on the side corresponding to the tilt motor 103 through a bearing, one end of which is nested and connected with the output shaft of the driven cylindrical gear 101, and the other end is fixedly connected to the cover 202.

[0057] Reference Fig. 9 In one example, the tilt axis includes a left tilt axis 104 and a right tilt axis 108. The outer periphery of the left tilt axis 104 is rotatably connected to the left support rib 401 through the left tilt bearing 106, one end of which is nested and connected to the output shaft of the driven cylindrical gear 101, and the other end is fixedly connected to the cover body 202. The right tilt axis 108 is fixedly connected to the cover body 202, and the outer periphery is rotatably connected to the right support rib 402 through the right tilt bearing 110. When the tilt motor 103 drives the driving cylindrical gear 102 to rotate, it will drive the driven cylindrical gear 101 and the left tilt axis 104 to rotate, so as to drive the rotor power assembly 200 to rotate around the left tilt axis 104 and the right tilt axis 108.

[0058] In one example, the right tilt shaft 108 is a hollow shaft with a sleeve structure, the pipeline channel tube 112 is nested in the right tilt shaft 108, and passes through the side wall of the cover 202 to enter the cover 202, and the pipelines 114 required by the engine 201 all enter the engine 201 through the inner cavity of the pipeline channel tube 112 to provide necessary protection for these pipelines and lines. The pipeline channel tube 112 is coaxially arranged with the right tilt shaft 108, and a pipeline bearing 113 is nested between the pipeline channel tube 112 and the right tilt shaft 108 to rotatably connect the two.

[0059] As the power input shaft, the left-leaning shaft 104 adopts a solid shaft to improve the mechanical strength. The output shaft of the driven cylindrical gear 101 is a cylinder. The end of the left-leaning shaft 104 penetrates into the cylinder to be nested and connected with the output shaft of the driven cylindrical gear 101.

[0060] In one example, the left-tilted shaft 104 and the right-tilted shaft 108 are fixedly connected to the cover body 202 through flange ends. In order to achieve axial stable positioning of each part, a stop ring 107 and a stop ring 109 are respectively provided between the flange end of the left-tilted shaft 104 and the inner wall of the left side support rib 401 (i.e., the side wall facing the rotor power assembly 200), and between the flange end of the right-tilted shaft 108 and the inner wall of the right side support rib 402 (i.e., the side wall facing the rotor power assembly 200). In addition, a stop ring 105 is also provided between the output shaft of the driven cylindrical gear 101 and the outer wall of the left side support rib 401, and a stop ring 111 is provided at the end of the right-tilted shaft 108 to press against the outer wall of the right side support rib 402.

[0061] like Fig. 9 As shown, the flange end of the right-leaning shaft 108 is provided with a boss structure, the pipeline line bearing 113 is installed on the inner side of the boss structure, and the limit ring 109 is installed between the axial side of the boss structure and the inner side wall of the right side support rib 402. The structural form of the left-leaning shaft 104 and the right-leaning shaft 108 is as follows Fig.10 and 11 shown.

[0062] According to an embodiment of the present utility model, the tilt locking assembly 300 includes a matching limit pin 301 and a limit lock 302. The limit lock 302 includes two groups, each group has two, the first group of limit locks 302 is arranged on the inner side wall of the left side support rib 401, and the second group of limit locks 302 is arranged on the inner side wall of the right side support rib 402, such as Fig.12 , 13 The limiting pins 301 include two groups, each group has two. The first group of limiting pins 301 is arranged on the side wall of the cover body 202 opposite to the inner side wall of the left side support rib 401, and the two limiting pins 301 are arranged symmetrically relative to the center of the left tilt shaft 104. The second group of limiting pins 301 is arranged on the side wall of the cover body 202 opposite to the inner side wall of the right side support rib 402, and the two limiting pins 301 are arranged symmetrically relative to the center of the right tilt shaft 108. Figure 6 shown.

[0063] When the tiltrotor aircraft is ready to start cruising flight, the tilt mechanism assembly 100 rotates the rotor power assembly 200 to a horizontal state (the rotor is in a horizontal working position). At this time, four pairs of symmetrical and diagonally arranged limit pins 301 are respectively embedded in four corresponding limit locks 302 and locked by a hydraulic or electric control mechanism. Such strong locking can eliminate the virtual position that exists when the rotor is restricted to the horizontal working position. Therefore, even if the aircraft is flying forward at high speed and is impacted by strong airflow, the rotor and wing will not shake, thereby improving the flight quality and flight stability. Fig.13 and 15 In addition, when the tilt-rotor aircraft is in a level flight cruising state, the tilt motor 103 starts a self-locking function.

[0064] When the tilt-rotor aircraft takes off and lands vertically, the four pairs of limit locks that are symmetrical on both sides are unlocked by hydraulic or electric control, and the tilt mechanism assembly 100 tilts the rotor power assembly 200 to a vertical state. At this time, since the tilt-rotor is less impacted by the airflow, the self-locking function of the tilt motor 103 can stabilize the rotor in a vertical working position. Fig.14 shown.

[0065] In another example, the line connecting the two limit pins of the first group of limit pins and the line connecting the two limit pins of the second group of limit pins are perpendicular to each other in space, and the two groups of limit locks are arranged correspondingly, so that in the locked state, the locking components on both sides of the rotor power component 200 are subjected to different forces, and the two are mutually constrained and cooperated, thereby further improving the locking stability.

[0066] In one example, the limit lock uses an operable lock hook to lock the embedded limit pin, and the locking and unlocking of the lock hook are controlled by a hydraulic or electric mechanism. In a preferred example, the limit lock has a hydraulic mode interface and an electric mode interface, so that it can be selected to work in a hydraulic mode or an electric mode, and the two working modes are backed up by each other.

[0067] In hydraulic mode, when the rotor is in a vertical state and the limit pin is not embedded in the limit lock, the hydraulic plunger pushes the crank under the drive of the hydraulic pressure and continuously maintains the unlocked position; when the rotor is in a horizontal state, two groups of symmetrical and diagonally arranged limit pins are respectively embedded in two corresponding limit locks and are ready to start cruising flight, the hydraulic plunger unloads the hydraulic pressure applied to the crank by controlling the switch, and at this time the spring-loaded lock hook rotates to the locked position under the action of the spring force.

[0068] In electric mode: the control process is the same as that in hydraulic mode, the difference is that the electric mode controls the electric actuator inside the lock through the control switch to control the worm gear mechanism connected to it to drive the crank to achieve locking and unlocking.

[0069] Exemplarily, the limit lock 302 includes a limit lock joint 303 , so as to be installed on the inner side walls of the left support rib 401 and the right support rib 402 through the limit lock joint 303 .

[0070] In the present invention, the tilt motor 103 may also be replaced by other actuators, such as hydraulic, pneumatic, electric, electromagnetic or other linear actuators.

[0071] The utility model has the advantages of direct force transmission, fast driving response, short wing attitude conversion time, simple wing tilting process, stability and reliability.

[0072] The above embodiments are only used to illustrate the technical solutions of the utility model, rather than to limit them. Although the utility model is described in detail with reference to the above embodiments, those skilled in the art should understand that the technical solutions described in the above embodiments can still be modified, or some or all of the technical features can be replaced by equivalents, and these modifications or replacements do not make the essence of the corresponding technical solutions deviate from the scope of the technical solutions of the embodiments of the utility model.

Claims

1. A tilting rotor structure with a locking mechanism, characterized in that: include: The rotor power assembly comprises a cover and a rotor mounted at one end of the cover, wherein a power assembly for driving the rotor is arranged in the cover, and the cover is mounted on the wing through a tilt shaft so that the rotor power assembly can rotate relative to the wing in the pitch direction of the aircraft; A tilt mechanism assembly is connected to the tilt shaft of the rotor power assembly and is used to drive the rotor power assembly to rotate relative to the wing in the pitch direction of the aircraft to a first working position and a second working position; wherein, in the first working position, the rotor is in a vertical state relative to the wing to provide lift when the aircraft is ascending or descending; and in the second working position, the rotor is in a horizontal state relative to the wing to provide pulling force when the aircraft is in level flight and cruising; The tilt lock assembly can be operated to lock the rotor power assembly in the second position when the rotor power assembly rotates to the second working position, and eliminate the virtual position existing in the rotor power assembly when the rotor power assembly is in the second working position.

2. The tilting rotor structure according to claim 1, characterized in that: The tilt locking assembly includes a matching limit pin and a limit lock. The limit pin is arranged on the side wall of the cover where the tilt axis is located, and the limit lock is installed on the wing component opposite to the side wall of the cover. When the rotor power assembly rotates to the second working position, the limit lock is locked with the limit pin through a hydraulic or electric control mechanism.

3. The tilting rotor structure according to claim 2, characterized in that: A group of limit pins are respectively arranged on the two opposite side walls of the cover body, and each group of limit pins includes two limit pins that are symmetrical with respect to the center of the tilt axis. A group of limit locks are respectively arranged on the wing parts opposite to the two side walls of the cover body, and each group of limit locks includes two limit locks that respectively cooperate with the two limit pins.

4. The tilting rotor structure according to claim 3, characterized in that: The connecting line between the two limiting pins of the first group of limiting pins and the connecting line between the two limiting pins of the second group of limiting pins are perpendicular to each other in space, and the two groups of limiting locks are arranged correspondingly.

5. The tilting rotor structure according to claim 2, characterized in that: The limit lock has a hydraulic mode interface and an electric mode interface, and can be selected to work in hydraulic mode or electric mode.

6. The tilting rotor structure according to claim 2, characterized in that: The tilt mechanism assembly is arranged on the wing component near the cover body, and includes a tilt motor for driving the tilt axis to rotate. The tilt motor has a self-locking function. When the rotor power assembly rotates to the first working position and when the rotor power assembly rotates to the second working position and the limit lock and the limit pin are locked, the tilt motor activates the self-locking function.

7. The tilting rotor structure according to claim 6, characterized in that: The tilt axis includes a left tilt axis and a right tilt axis respectively fixed on two opposite side walls of the cover body. The left tilt axis and the right tilt axis are respectively installed on wing components opposite to the two side walls of the cover body through bearings. The tilt motor drives the left tilt axis to rotate through a gear drive mechanism.

8. The tilting rotor structure according to claim 7, characterized in that: The right tilt shaft is a hollow shaft, the pipeline channel tube is nested in the right tilt shaft and passes through the side wall of the cover body into the cover body, and the pipelines required by the power assembly enter the power assembly through the inner cavity of the pipeline channel tube.

9. The tilting rotor structure according to claim 7, characterized in that: The left tilt shaft and the right tilt shaft are respectively provided with axial limiting components on both sides of the wing component.

10. The tilting rotor structure according to claim 1, characterized in that: The outer surface of the cover is covered with a fairing skin so that the cover and the wing form an integrated shape when the rotor power assembly rotates to the first working position and the second working position.

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