A self-rotating wing system and an aircraft assisted by a vertical axis fan

Abstract

The present invention relates to a vertical axis fan-assisted autogyro system and an aircraft, comprising: a propeller bin B, a first drive assembly, a rotor shaft, two main propeller rotor blades and a second drive assembly, wherein a lower seated self-aligning bearing is arranged in the propeller bin B, and an upper seated self-aligning bearing is installed on the top thereof; the first drive assembly is used to drive the lower seated self-aligning bearing to move; the rotor shaft is passed through the upper seated self-aligning bearing and the lower seated self-aligning bearing, and is fixed with the upper seated self-aligning bearing and the lower seated self-aligning bearing, and the other end of the rotor shaft is passed through the propeller hub bin A, and is fixed with the shaft top plate arranged in the propeller hub bin A; the main propeller rotor blade is connected to the propeller hub bin A, and a fan blade is arranged at the end thereof, and the second drive assembly is used to drive the main propeller rotor blade to rotate. The device assists the flight of the aircraft to reduce the energy consumption of the aircraft's own energy.

Description

Technical Field

[0001] The present invention relates to the field of aircraft rotor power design, and particularly to a self-rotor system and an aircraft assisted by a vertical-axis fan. Background Art

[0002] During flight, an aircraft often encounters gusts of air with unstable flow, which will inevitably cause changes in its own airspeed and energy, greatly affecting flight attitude stability and flight safety. To resist or counteract the disturbing effects brought by gusts, the aircraft requires additional energy consumption, while the energy carried by the aircraft itself, such as fuel or batteries, is limited, thus greatly affecting the flight time or range of the aircraft. Therefore, obtaining part of the energy required for flight in real time from the wind field in the flight environment is an innovative way to achieve safe and stable flight of the aircraft in the wind field.

[0003] Existing aircraft rely entirely on rotors to obtain energy from the wind field. However, the rotors of conventional rotorcraft can only capture energy from the wind field in a specific direction, so the captured energy is very limited. Furthermore, when the aircraft encounters an unstable wind field during flight, in order to adjust the flight attitude and ensure flight safety, the aircraft needs to use the carried energy for adjustment, which leads to additional energy consumption and thus greatly affects the range of the aircraft.

[0004] Therefore, it is necessary to provide a self-rotor system and an aircraft assisted by a vertical-axis fan to solve the above problems. Summary of the Invention

[0005] The present invention provides a self-rotor system and an aircraft assisted by a vertical-axis fan. By combining the fan blades and the main rotor blades, the main rotor blades are enabled to rotate relying on the energy captured by the fan blades, so as to solve the problem that when an existing aircraft is affected by an unstable wind field, it will lead to additional energy consumption and thus greatly affect the range of the aircraft.

[0006] A self-rotor system assisted by a vertical-axis fan according to the present invention adopts the following technical solutions: including:

[0007] A paddle wheel chamber, which is used to connect with the aircraft body, is internally provided with a lower pedestal spherical roller bearing, and an upper pedestal spherical roller bearing is installed on its top;

[0008] A first driving assembly, which is arranged in the paddle wheel chamber and is used to drive the lower pedestal spherical roller bearing to move in the paddle wheel chamber;

[0009] A rotor rotating shaft, one end of which passes through the upper pedestal spherical roller bearing and enters the paddle wheel chamber, is connected with the lower pedestal spherical roller bearing, and the other end passes through a hub chamber arranged on its top and is fixed to a rotating shaft top plate arranged in the hub chamber;

[0010] Two main propeller rotor blades are symmetrically arranged in the circumference of the hub compartment, one end of which is provided with a fan blade, and the two fan blades are arranged opposite to each other, and the other end is provided with a connecting shaft, which is inserted into the hub compartment and rotatably connected to the top plate of the rotating shaft, wherein the fan blade is a blade of a vertical axis fan;

[0011] The second drive assembly has an output end connected to the main rotor blades and is used to drive the two main rotor blades to rotate independently.

[0012] Preferably, it also includes a rotor brake assembly, which is arranged in the propeller disc bin. The rotor brake assembly includes: a plurality of linear drive assemblies, which are evenly distributed around the rotor shaft, and each linear drive assembly has a fixed end fixed to the inner wall of the propeller disc bin, and the output end of the linear drive assembly is connected to a brake chuck, which faces the rotor shaft.

[0013] Preferably, the chuck is an arc-shaped plate, and the inner arc surface of the arc-shaped plate faces the rotor shaft.

[0014] Preferably, it also includes an electromagnetic latch, which is arranged on the lower seat-aligning bearing, and a pin hole that cooperates with the electromagnetic latch is arranged on the rotor shaft.

[0015] Preferably, the first drive assembly includes four telescopic rods, which are evenly distributed around the lower seat-mounted self-aligning bearing, and the fixed end of each telescopic rod is hinged to the inner wall of the propeller disc bin, and the output end of each telescopic rod is hinged to the bearing seat of the lower seat-mounted self-aligning bearing.

[0016] Preferably, the bearing seat of the lower seat-aligning bearing is a square base, and each side surface of the square base is correspondingly hinged to the output end of a telescopic rod.

[0017] Preferably, the output end of the telescopic rod is ball-jointed to the bearing seat, and the fixed end of the telescopic rod is also ball-jointed to the inner wall of the propeller disc bin.

[0018] Preferably, the second drive assembly includes: two servos, both arranged at the bottom of the rotating shaft top plate, the output end of each servo is connected to a rocker arm, the end of the rocker arm facing away from the servo is connected to a connecting rod perpendicular to the rocker arm, the end of the connecting rod passes through a slot opened on the side wall of the hub compartment and is connected to a connecting rod, the end of the connecting rod facing away from the connecting rod is fixedly connected to the corresponding main propeller rotor blade; preferably, the slot is an arc-shaped slot.

[0019] Preferably, the cross-section of the fan blade is a wing airfoil, and the cross-section of the main rotor blade is an elliptical airfoil.

[0020] The invention discloses an aircraft, which comprises a vertical axis fan-assisted autogyro system. The top of the aircraft body is connected to the bottom of a propeller bin of the autogyro system.

[0021] The beneficial effects of the present invention are:

[0022] 1. By making full use of the self-rotating torque effect generated by the vertical-axis wind turbine in the wind field, the fan blades of the vertical-axis wind turbine are used as the driving force when the autorotor system is affected by the wind field. That is, fan blades are arranged on the main rotor blades. The fan blades are affected by the wind field to generate a driving force, which directly converts the driving force into the rotational kinetic energy of the main rotor blades, realizing the combination of the fan blades and the main rotor blades. Then, based on the utilization of the energy of the vertical-axis wind turbine in any wind field, the aircraft utilizes the energy captured by the fan blades from the omnidirectional and arbitrary wind field as an auxiliary energy source for the flight of the aircraft. That is, the lateral wind field that originally interfered with the flight of the aircraft can also be converted by the fan blades into additional driving force, thereby increasing the altitude or providing power for the aircraft. Therefore, the present invention realizes the operation of the main rotor blades capturing wind energy in the wind field, getting rid of the problem of the excessive proportion of the onboard energy consumption caused by the traditional power input method, and then reducing the energy consumption of the aircraft's own energy, increasing the flight range of the drone, and contributing to the development and progress of new aircraft.

[0023] 2. In the rotor mode, by means of the relative motion between the aircraft and the air, the fan blades are driven to drive the main rotor blades to rotate. Considering that the rotational speed of the main rotor blades is different under different composite speeds, the second driving component is used to adjust the collective pitch angle of the two main rotor blades, so as to generate a larger lift force, realizing the efficient acquisition and utilization of the wind field energy contacted during flight; in the fixed-wing mode, the two main rotor blades are fixed at the same installation angle, that is, the main rotor blades are changed from the rotor state to the fixed state to provide a certain lift force as a small fixed wing, thereby effectively reducing the structural dead weight (that is, the structural weight without flight benefit during flight), and assisting the aircraft to fly horizontally. BRIEF DESCRIPTION OF THE DRAWINGS

[0024] In order to more clearly illustrate the technical solutions in the embodiments of the present invention or the prior art, the following will briefly introduce the drawings required for the description of the embodiments or the prior art. Obviously, the following drawings are only some embodiments of the present invention. For those of ordinary skill in the art, without creative efforts, other drawings can be obtained based on these drawings.

[0025] Figure 1 It is a schematic diagram of the overall structure of an embodiment of an autorotor system assisted by a vertical-axis wind turbine according to the present invention;

[0026] Figure 2 It is a top view of the overall structure of an autorotor system assisted by a vertical-axis wind turbine according to the present invention;

[0027] Figure 3 It is a schematic diagram of the internal structure of the blade disc bin and the hub bin of an autorotor system assisted by a vertical-axis wind turbine according to the present invention;

[0028] Figure 4 Side view of the overall structure of a self-rotating wing system assisted by a vertical-axis wind turbine according to the present invention;

[0029] Figure 5 Side view of the hub bin of a self-rotating wing system assisted by a vertical-axis wind turbine according to the present invention;

[0030] Figure 6 Schematic diagram of the internal structure of the blade disc bin of a self-rotating wing system assisted by a vertical-axis wind turbine according to the present invention;

[0031] Figure 7 Partial schematic diagram of the braking assembly of a self-rotating wing system assisted by a vertical-axis wind turbine according to the present invention;

[0032] Figure 8 State diagram of two main blade rotor blades of a self-rotating wing system assisted by a vertical-axis wind turbine in rotor mode according to the present invention;

[0033] Figure 9 State diagram of two main blade rotor blades of a self-rotating wing system assisted by a vertical-axis wind turbine in fixed-wing mode according to the present invention;

[0034] Figure 10 Schematic diagram of the collective pitch angle of the main blade rotor blades of a self-rotating wing system assisted by a vertical-axis wind turbine in rotor mode according to the present invention;

[0035] Figure 11 Schematic diagram of the installation angle of the main blade rotor blades of a self-rotating wing system assisted by a vertical-axis wind turbine in fixed-wing mode according to the present invention;

[0036] In the figure: A, hub bin; A1, slot; B, blade disc bin; 1, first wind turbine blade; 2, second wind turbine blade; 3, first blade tip; 4, second blade tip; 5, first main blade rotor blade; 6, second main blade rotor blade; 7, rotor rotating shaft; 8, upper pedestal aligning bearing; 9, rotating shaft top disc; 10, first connecting shaft; 11, second connecting shaft; 12, electromagnetic plug; 13, lower pedestal aligning bearing; 14, linear drive assembly; 15, telescopic rod; 17, connecting rod; 18, rocker arm; 19, link; 20, pin hole; 22, rotor characteristic plane. Detailed implementation manners

[0037] Next, the technical solutions in the embodiments of the present invention will be clearly and completely described in conjunction with the accompanying drawings in the embodiments of the present invention. Obviously, the described embodiments are only a part of the embodiments of the present invention, rather than all the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those of ordinary skill in the art without creative efforts shall fall within the protection scope of the present invention.

[0038] Embodiment 1

[0039] An embodiment of a self-rotating wing system assisted by a vertical-axis wind turbine according to the present invention. Specifically, in the usage scenario, a self-rotating wing system is additionally provided on an aircraft to assist the aircraft in flight, such as Figure 3 shown, and specifically includes: a paddle disk chamber B, a first drive assembly, a rotor shaft 7, two main paddle rotor blades, and a second drive assembly. Among them, the paddle disk chamber B is used to connect to the aircraft body. A lower pedestal aligning bearing 13 is provided in the paddle disk chamber B, and an upper pedestal aligning bearing 8 is installed on the top of the paddle disk chamber B; a first drive assembly is further provided in the paddle disk chamber B, and the first drive assembly is used to drive the lower pedestal aligning bearing 13 to move in various different directions in the paddle disk chamber B; the outer ring of the upper pedestal aligning bearing 8 is fixed to the mounting hole opened at the top of the paddle disk chamber B, and the inner ring of the upper pedestal aligning bearing 8 is sleeved and fixed with a rotor shaft 7. One end of the rotor shaft 7 passes through the upper pedestal aligning bearing 8 and enters the paddle disk chamber B, and is sleeved and fixed with the lower pedestal aligning bearing 13. A hub chamber A is provided above the paddle disk chamber B. The other end of the rotor shaft 7 is disposed in the hub chamber A and is connected to a shaft top disk 9 fixed to the inner top of the hub chamber A; a first main paddle rotor blade 5 and a second main paddle rotor blade 6 are symmetrically arranged in the circumferential direction of the hub chamber A, and the two main paddle rotor blades are horizontally arranged. One end of each main paddle rotor blade facing away from the hub chamber A is provided with a wind turbine blade, and the two wind turbine blades are arranged oppositely (that is, as Figure 1 shown, the two wind turbine blades are both perpendicular to the top of the paddle disk chamber B. Specifically, the wind turbine blades are perpendicular to the rotor characteristic plane 22, and the rotor characteristic plane 22 is the plane swept by the main paddle rotor blade during rotation), specifically, as Figure 1 shown, a first wind turbine blade 1 is connected to a first blade tip 3 on the first main paddle rotor blade 5, and a second wind turbine blade 2 is connected to a second blade tip 4 on the second main paddle rotor blade 6. As Figure 3 shown, the other end of the first main paddle rotor blade 5 facing away from the first blade tip 3 is connected to a first connecting shaft 10. The end of the first connecting shaft 10 passes through the hub chamber A and is rotatably connected to the side end face of the shaft top disk 9. The other end of the second main paddle rotor blade 6 facing away from the second blade tip 4 is connected to a second connecting shaft 11. The end of the second connecting shaft 11 passes through the hub chamber A and is rotatably connected to the side end face of the shaft top disk 9; the second drive assembly is used to drive the two main paddle rotor blades to rotate independently.

[0040] It should be noted that wind-riding flight is an effective method to achieve long-term flight in a real wind field. One of its main means of realization is to directly capture the unknown and changeable wind field energy in the environment through a wind energy device, and convert it into flight power or altitude potential energy. This energy-harvesting flight method can adapt to any form of wind speed and gradient changes in the flight environment, and has little impact on the flight trajectory. Its realization depends on the design of an efficient wind energy capture or conversion device. A common wind energy capture device is a wind fan, among which a vertical axis wind fan utilizes a circumferential wind field to drive rotation to obtain energy. Its rotating shaft is perpendicular to the flow direction of the wind, and it does not need to face the wind to capture wind energy in almost any direction; a Darrieus vertical axis wind fan utilizes an airfoil to generate lift to work on the rotating shaft. It has been proven to be one of the most efficient wind energy conversion systems and is widely used in small wind turbines. At the same time, it is relatively simple in terms of mechanics and structure. The fan blades of the generator are used as a wind energy capture device, and torque can be output to the outside to perform work, thereby achieving efficient wind energy conversion. Therefore, this embodiment uses the fan blades of a vertical axis fan.

[0041] Specifically, Figure 3 and Figure 6 As shown, the first drive assembly includes four telescopic rods 15, which are evenly arranged around the lower seat self-aligning bearing 13, and the fixed end of each telescopic rod 15 is hinged to the inner wall of the propeller bin B, and the output end of each telescopic rod 15 is hinged to the bearing seat of the lower seat self-aligning bearing 13. The telescopic rod 15 of this example is an electric push rod, specifically, as shown in FIG. Figure 6 As shown, the bearing seat of the lower self-aligning bearing 13 with a seat is a square base, and each side of the square base is hinged to the output end of a telescopic rod 15, wherein the hinges between the telescopic rod 15 and the bearing seat and the inner wall of the propeller disc bin B are all ball hinges, so that when the bearing seat of the lower self-aligning bearing 13 with a seat is pushed or pulled by one of the telescopic rods 15, the other three telescopic rods will not affect the movement of the bearing seat of the lower self-aligning bearing 13; secondly, the angle between the axis of the telescopic rod 15 and the inner bottom surface of the propeller disc bin B is an acute angle.

[0042] Specifically, Figure 3 As shown, the second drive assembly includes: two steering gears, both arranged at the bottom of the rotating shaft top plate 9, the output end of each steering gear is connected to a rocker arm 18, and the end of the rocker arm 18 away from the steering gear is connected to a connecting rod 19 perpendicular to the rocker arm 18, as shown in FIG. Figure 5 As shown, the end of the connecting rod 19 passes through the slot A1 provided on the side wall of the hub compartment A and is connected to the connecting rod 17. Figure 3 and Figure 7 As shown, one end of the connecting rod 17 away from the connecting rod 19 is fixedly connected to the corresponding main propeller rotor blade. Since the rocker arm 18 rotates around the output shaft of the servo, the connecting rod 19 driven by the rocker arm 18 is an arc track when it rotates, as shown in FIG. Figure 5As shown, it is also possible to open a rectangular slot, but the width of the rectangular slot should satisfy the widest distance of the arc track for the rotation of the connecting rod 17. Therefore, in order to have a small width of the slot A1 (to prevent more wind from entering the hub bin A) and enable the slot A1 to meet the movement space during the rotation of the connecting rod 17, the slot A1 in this embodiment is preferably an arc-shaped slot.

[0043] Specifically, the cross-section of the fan blade is an airfoil profile. When the air incoming flow velocity is U, the self-rotation speed of the fan is ω, and the tangential velocity of the fan blade is Vt = ω × R (where R is the radius of the rotor). The air incoming flow velocity U, the tangential velocity Vt of the fan blade, and the relative velocity Vr between the fan blade and the air form a velocity triangle, thereby generating aerodynamic force. The magnitude and direction of the aerodynamic force are jointly determined by the specific airfoil profile of the cross-section of the fan blade and the magnitude and direction of the relative air velocity Vr. The aerodynamic force received by the fan blade forms a torque around the fan rotation axis in the tangential direction, which is the self-rotation driving torque of the fan blade. When the fan blade is used in this embodiment, the cross-section of the fan blade is also an airfoil profile, as Figure 1 shown. The fan blade is a straight blade without twist and without sweepback. The fan blade is perpendicular to the characteristic plane of the paddle disc bin B (the circular plane swept by the main paddle rotor blade). The fan blade is attached to and fixedly connected to the upper surface of the blade tip. Therefore, when the fan blade receives the air incoming flow, the fan blade will generate a self-rotation driving torque. When the self-rotation driving torque causes the fan blade to rotate, since the fan blade is fixedly connected to the main paddle rotor blade, ultimately this driving torque causes the main paddle rotor blade to rotate.

[0044] Specifically, the main paddle rotor blade is a rectangular blade, and its cross-section is a symmetric elliptical airfoil. The principle of generating lift by the main paddle rotor blade is as follows: Under the action of the self-rotation torque of the fan blade, the main paddle rotor blade rotates around the rotor main shaft, and its rotation speed is the same as the self-rotation speed ω of the fan blade, thereby generating a lift perpendicular to the rotor characteristic plane 22 (the rotor characteristic plane 22 is the plane swept by the main paddle rotor blade during rotation).

[0045] Embodiment 2

[0046] In order to brake the rotor shaft 7 to achieve the braking of the main paddle rotor blade, as Figure 6 shown, on the basis of Embodiment 1, this embodiment further includes a rotor braking assembly. The rotor braking assembly is arranged in the paddle disc bin B. The rotor braking assembly includes: two linear driving assemblies 14. The two linear driving assemblies 14 are evenly distributed around the rotor shaft 7, and the fixed end of each linear driving assembly 14 is fixed to the inner wall of the paddle disc bin B. The output end of the linear driving assembly 14 is connected with a braking chuck. The braking chuck faces the rotor shaft 7. Among them, the chuck is an arc-shaped plate, and the inner arc surface of the arc-shaped plate faces the rotor shaft 7.

[0047] Specifically, asFigure 6 and Figure 7 As shown in Figure 7 , it further includes an electromagnetic bolt 12, the electromagnetic bolt 12 is arranged on the lower pedestal self-aligning bearing 13, and a pin hole 20 cooperating with the electromagnetic bolt 12 is arranged on the rotor shaft 7.

[0048] An aircraft is provided with a self-rotating wing system assisted by a vertical axis fan. Specifically, the top of the aircraft body is connected to the bottom of the paddle disc bin of the self-rotating wing system.

[0049] Specific working principle

[0050] When specifically applied to an aircraft, the bottom of the paddle disc bin B is connected to the aircraft body. In the rotor mode (during the rotation of the main rotor blades), that is, as shown in

[0050] , when the aircraft is in a hover or vertical takeoff and landing stage, at this time, driven by the external wind field, the first fan blade 1 and the second fan blade 2 drive the main rotor blades to rotate, that is, the main rotor blades rotate, and the main rotor blades are controlled to rotate in the same direction by the same angle. That is, the servo drives the rocker arm 18 to rotate, the rocker arm 18 drives the connecting rod 19 to drive the connecting rod 17 to rotate through the connecting rod 19, and the connecting rod 17 thereby drives the corresponding main rotor blades to rotate in the same direction, so as to realize that the main rotor blades have the same collective pitch angle (the connection line between the end face of the main rotor blade and the main rotor blade, and the included angle between the connection line and the rotor characteristic plane). As shown in Figure 8 Figure 8 As shown, it should be noted that the collective pitch angle is the line-plane angle θ1 and θ2 formed by the chord line directions (the chord line direction is the connection line direction between the leading edge and the trailing edge of the main rotor blade) of the main rotor blades 5 and 6 in the rotor mode and the rotor characteristic plane 22 (the rotor characteristic plane 22 is the plane swept by the main rotor blade during rotation), and θ1 = θ2. Specifically, in this embodiment, according to the selected airfoil of the main rotor blade, according to the stall angle of attack of the selected rotor blade airfoil being α Figure 10 stall stall , then when the collective pitch angle of the main rotor blade is in the range of 0-α stall stall

[0051] range, the rotor can generate positive lift efficiency, thereby assisting the aircraft to rise. Secondly, in the rotor mode, the bearing seat of the lower pedestal self-aligning bearing 13 is controlled by four adjusting rods 15, and the bearing seat of the lower pedestal self-aligning bearing 13 can perform a small range of horizontal movement on the inner bottom surface of the paddle disc bin. That is, when the lower pedestal self-aligning bearing 13 moves, the relative position between the lower pedestal self-aligning bearing 13 and the upper pedestal self-aligning bearing 8 changes, and the two are not in the same vertical plane. That is, the movement of the lower pedestal self-aligning bearing 13 will cause the axis direction of the rotor shaft 7 to change, so that a certain horizontal component is generated in the rotor aerodynamic resultant force, providing a certain side force control ability for the stable flight of the aircraft in the rotor mode, that is, assisting in controlling the attitude or position of the aircraft, so as to ensure the stable flight of the assisted aircraft in the wind field.In the fixed-wing mode (the main rotor blades do not rotate), that is, as Figure 9 shown, when the aircraft is in the level flight state, the rotor shaft 7 is restricted and locked by the braking device, that is, the main rotor blades do not rotate. That is, the main rotor blades on the hub bin A connected to the rotor shaft 7 no longer rotate. And at this time, it is necessary to keep the fan blades perpendicular to the oncoming flow direction, and then transform the main rotor blades into small fixed wings. That is, the servo drives the rocker arm 18 to rotate. The rocker arm 18 drives the connecting rod 19 to drive the connecting rod 17 to rotate through the connecting rod 19. The connecting rod 17 thus drives the corresponding main rotor blades to rotate in the reverse direction, so as to ensure that the two main rotor blades are transformed into two fixed wings with the same installation angle, as Figure 11 shown. It should be noted that the installation angle is the line-plane angle β1, β2 formed by the chord line directions (the chord line direction is the connection direction of the leading edge and the trailing edge of the main rotor blade) of the main rotor blades 5, 6 in the rotor mode and the rotor characteristic plane 22 (the rotor characteristic plane 22 is the plane swept by the main rotor blade during rotation), and β1 = β2. In the fixed-wing mode, the two main rotor blades are fixed at the same installation angle, and the installation angle is within 0-α stall (the stall angle of attack of the selected rotor blade airfoil) range, the two rotor blades can provide partial lift for the main rotor blades in the fixed-wing mode, effectively reducing the dead weight of the mechanism, and then helping the aircraft to fly in the horizontal direction.

[0052] The braking process of the autogyro system is as follows: In the rotor mode, the electromagnetic plug 12 is in the energized retracted state. When transitioning from the rotor mode to the fixed-wing mode, the linear drive assembly 14 drives the brake chuck to clamp the rotor shaft 7 inward to decelerate it. When the rotational speed of the rotor shaft 7 drops to the preset critical speed ω0, the electromagnet of the electromagnetic plug 12 is de-energized to release the suction force on the plug. During the continued slow rotation of the rotor shaft 7, the electromagnetic plug 12 automatically pops out and aligns with the pin hole 20 on the rotor shaft 7 and inserts into it. At the same time, the brake chuck continues to advance inward to the maximum stroke position, and then locks the rotor shaft 7; when transitioning from the fixed-wing mode to the rotor mode, the electromagnetic plug 12 is energized and retracted, and the rotor brake chuck gradually actuates outward to release the lock on the rotor shaft, so that the rotor shaft returns to the free rotation state.

[0053] In summary, the autorotator system assisted by a vertical-axis wind turbine provided by the embodiments of the present invention makes full use of the autorotation torque effect generated by the vertical-axis wind turbine in the wind field, and uses the fan blades of the vertical-axis wind turbine as the driving force when the autorotator system is affected by the wind field. That is, fan blades are arranged on the main rotor blades. The fan blades generate a driving force under the action of the wind field, and thus directly convert the driving force into the rotational kinetic energy of the main rotor blades. It can not only realize the self-powered operation process in the rotor wind field and get rid of the problem of the excessive proportion of the airborne energy weight caused by the traditional power input method. Secondly, in the rotor mode, with the relative movement between the aircraft and the air, the fan blades are driven to drive the main rotor blades to rotate. Considering that the rotational speeds of the main rotor blades are different under different combined speeds, the second driving component is used to adjust the collective pitch angles of the two main rotor blades, so as to generate a large lift force and realize the efficient acquisition and utilization of the wind field energy contacted during flight; in the fixed-wing mode, the two main rotor blades are fixed at the same installation angle, that is, the main rotor blades are changed from the rotor state to the fixed state to provide a certain lift force as a small fixed wing, thereby effectively reducing the dead weight of the mechanism (that is, the structural weight without flight benefit during flight) and assisting the aircraft to fly in the horizontal direction. The present invention promotes the use of the omnidirectional arbitrary wind field as the flight energy source by the aircraft, reduces the energy consumption level of the aircraft, and helps to promote the development and progress of new aircraft.

[0054] The foregoing are only the preferred embodiments of the present invention and are not intended to limit the present invention. Any modifications, equivalent replacements, improvements, etc. made within the spirit and principle of the present invention shall be included in the protection scope of the present invention.

Claims

1. A self-rotor system assisted by a vertical-axis wind turbine, characterized in that, include: The propeller disc compartment has a lower self-aligning bearing with a seat arranged inside and an upper self-aligning bearing with a seat installed on the top; A first driving assembly is disposed in the propeller disc compartment and is used to drive the lower seated self-aligning bearing to move horizontally in the propeller disc compartment; The rotor shaft, one end of which passes through the upper seat self-aligning bearing and enters the propeller disc compartment, and is connected to the lower seat self-aligning bearing, and the other end of which passes through the propeller hub compartment set on the top and is fixed to the shaft top plate set in the propeller hub compartment; Two main propeller rotor blades are symmetrically arranged in the circumference of the hub compartment, one end of which is provided with a fan blade, and the two fan blades are arranged opposite to each other, and the other end is provided with a connecting shaft, and the connecting shaft is inserted into the hub compartment and rotatably connected to the top plate of the rotating shaft, wherein the fan blade is a blade of a vertical axis fan; The second drive assembly has an output end connected to the main rotor blades and is used to drive the two main rotor blades to rotate independently.

2. The autorotator system assisted by a vertical-axis wind turbine according to claim 1, wherein, It also includes a rotor brake assembly, which is arranged in the propeller disc bin. The rotor brake assembly includes: a plurality of linear drive assemblies, which are evenly distributed around the rotor shaft, and each linear drive assembly has a fixed end fixed to the inner wall of the propeller disc bin, and an output end of the linear drive assembly is connected to a brake chuck, which faces the rotor shaft.

3. The autorotator system assisted by a vertical-axis wind turbine according to claim 2, wherein The chuck is an arc-shaped plate, and the inner arc surface of the arc-shaped plate faces the rotor shaft.

4. The autorotator system assisted by a vertical-axis wind turbine according to claim 3, characterized in that, It also includes an electromagnetic latch, which is arranged on the lower seat-aligning bearing, and the rotor shaft is provided with a pin hole that cooperates with the electromagnetic latch.

5. A self-rotating wing system assisted by a vertical-axis fan according to claim 1, characterized in that, The first driving assembly includes four telescopic rods, which are evenly distributed around the lower seat-aligning bearing, and the fixed end of each telescopic rod is hinged to the inner wall of the propeller disc bin, and the output end of each telescopic rod is hinged to the bearing seat of the lower seat-aligning bearing.

6. The autorotating wing system assisted by a vertical-axis wind turbine according to claim 5, characterized in that, The bearing seat of the lower seated self-aligning bearing is a square base, and each side surface of the square base is correspondingly hinged to the output end of a telescopic rod.

7. A self-rotating wing system assisted by a vertical-axis wind turbine according to claim 5, characterized in that, The output end of the telescopic rod is ball-jointed with the bearing seat, and the fixed end of the telescopic rod is also ball-jointed with the inner wall of the propeller disc bin.

8. A self-rotating wing system assisted by a vertical-axis fan according to claim 1, characterized in that, The second drive assembly includes: two servos, both of which are arranged at the bottom of the rotating shaft top plate, the output end of each servo is connected to a rocker arm, the end of the rocker arm facing away from the servo is connected to a connecting rod perpendicular to the rocker arm, the end of the connecting rod passes through a slot opened on the side wall of the hub bin and is connected to a connecting rod, the end of the connecting rod facing away from the connecting rod is fixedly connected to the corresponding main propeller rotor blade, wherein the slot is an arc-shaped slot.

9. The autorotator system assisted by a vertical-axis wind turbine according to claim 1, wherein, The cross section of the fan blade is a wing airfoil, and the cross section of the main rotor blade is an elliptical airfoil.

10. An aircraft, characterized in that, The aircraft comprises a vertical axis fan-assisted autogyro system as described in any one of claims 1 to 9, wherein the top of the aircraft body is connected to the bottom of the propeller compartment of the autogyro system.

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