CN112623210A - Rotor assembly and aircraft - Google Patents

Abstract

The application discloses rotor subassembly and aircraft, wherein this rotor subassembly includes: the paddle base, a first inertia transmission assembly connected with the paddle base, a first paddle connected with the first inertia transmission assembly, a second inertia transmission assembly connected with the paddle base and a second paddle connected with the second inertia transmission assembly; when the paddle seat rotates around the rotation axis of the paddle seat, the first paddle can be driven to rotate through the first inertia transmission assembly, and the second paddle is driven to rotate through the second inertia transmission assembly; when the paddle seat has acceleration, the first inertia transmission assembly can drive the first paddle to rotate under the inertia effect so as to increase the attack angle of the first paddle, and the second inertia transmission assembly can drive the second paddle to rotate under the inertia effect so as to reduce the attack angle of the second paddle, so that the traditional tilting disk is not depended on, the effect of the variable pitch of an aircraft rotor system is achieved, and the rotor assembly is simple in structure and high in reliability.

Description

Rotor assembly and aircraft

Technical Field

The present application relates to the field of aircraft, and more particularly, to an inertia control rotor assembly and an aircraft having the same.

Background

The tilting disk is a special device used for operating the total pitch of a rotor wing and the periodic pitch variation of blades in most of the current aircraft operating systems so as to realize the lifting, the front-back and the left-right movement of the aircraft.

The swashplate in a conventional aircraft, such as a helicopter, is used to adjust the pitch of the rotor of the helicopter, thereby creating a difference in lift in different quadrants on the plane of rotation of the helicopter, with which the direction of flight of the helicopter is changed.

Therefore, the conventional aircraft rotor system needs to use a tilting disk to realize the pitch change of the rotor system, and the tilting disk usually occupies a large space and is complex in structure. If the difficulty and the cost of maintenance are higher after the fault occurs, the stability of the structure is difficult to guarantee.

In summary, there is still a need for a rotor assembly that is simpler in structure, lower in cost than a swashplate, and more stable in structure, that replaces a conventional swashplate of an aircraft, and that also achieves control of the direction of flight of the aircraft.

Disclosure of Invention

The invention provides a rotor wing assembly which can achieve the effect of pitch changing of a helicopter rotor wing system without depending on a traditional tilting disk.

To solve the technical problem, the present application provides a rotor assembly, comprising:

a paddle seat;

the first inertia transmission assembly is connected with the paddle seat;

the first blade is connected with the first inertia transmission assembly;

the second inertia transmission assembly is connected with the paddle seat;

the second blade is connected with the second inertia transmission assembly;

when the paddle seat rotates around the rotation axis of the paddle seat, the first paddle can be driven to rotate by the first inertia transmission assembly, and the second paddle is driven to rotate by the second inertia transmission assembly; when the paddle base is accelerated after being decelerated, the first inertia transmission assembly can drive the first paddle to rotate under the inertia effect so as to reduce the attack angle of the first paddle, and the second inertia transmission assembly can drive the second paddle to rotate under the inertia effect so as to increase the attack angle of the second paddle.

The invention also provides an aircraft which comprises an aircraft body, a receiver, a controller, a brushless motor, an angle sensor and the rotor wing assembly provided by the invention; the rotor wing assembly is connected with the brushless motor;

wherein the brushless motor drives the rotor assembly to rotate; the angle sensor detects the rotation angle of the brushless motor and sends the rotation angle information to the controller; the receiver receives a control signal and sends the control signal to the controller; the controller controls the brake position and brake period of the brushless motor according to the control signal and the rotation angle information, and the rotor wing assembly is periodically changed in distance.

The beneficial effect of this application is: when the paddle seat rotates around the rotation axis of the paddle seat, the first paddle and the second paddle can be driven to rotate by the first inertia transmission assembly and the second inertia transmission assembly; when the paddle seat has acceleration, the first inertia transmission assembly and the second inertia transmission assembly can drive the first paddle and the second paddle to rotate under the inertia effect so as to change the attack angle of the first paddle and the attack angle of the second paddle, so that the traditional tilting disk is not depended, the variable pitch effect of a helicopter rotor system is achieved, and the rotor assembly is simple in structure and high in reliability.

Drawings

In order to more clearly illustrate the technical solutions in the embodiments of the present application, the drawings needed to be used in the description of the embodiments are briefly introduced below, it is obvious that the drawings in the following description are only some embodiments of the present application, and other drawings can be obtained by those skilled in the art without inventive efforts, wherein:

figure 1 is a front view of one embodiment of a rotor assembly of the present invention;

FIG. 2 is a block diagram of an inertial drive assembly of one embodiment of a rotor assembly of the present invention;

FIG. 3 is a schematic structural connection of a first inertia transmission assembly of an embodiment of a rotor assembly of the present invention;

FIG. 4 is a schematic structural connection of a second inertia drive assembly of an embodiment of a rotor assembly of the present invention;

FIG. 5 is a schematic pitch change for one embodiment of a rotor assembly of the present invention in a certain motion;

figure 6 is a block diagram of a rotor assembly according to an embodiment of the present invention;

figure 7 is a front view of another embodiment of a rotor assembly of the present invention;

figure 8 is a perspective view of a region i of one embodiment of a rotor assembly of the present invention;

FIG. 9 is a front view of the aircraft of the present invention;

FIG. 10 is a block diagram of the airframe removal of the present invention.

Reference numerals: 10 a first inertia transmission assembly, 20 a second inertia transmission assembly, 30 a first blade, 40 a second blade, 50 a paddle mount, 60 a first mount, 70 a second mount, 80 a first inertia element, 81 a first lever, 90 a second inertia element, 91 a second lever, 11 a first hinge mount, 21 a second hinge mount, 12 a first paddle clip, 22 a second paddle clip, alpha a first included angle, beta a second included angle beta, 101 a first connecting portion, 102 a second connecting portion, 201 a third connecting portion, 204 a fourth connecting portion, 51 a fixed mount, 52 a connecting plate, 121 a first clamping portion, 221 a second clamping portion, 131 a third clamping portion, 231 a fourth clamping portion, 300 a first gear transmission assembly, 400 a second gear transmission assembly, 301 a first driving gear, 302 a first driven gear, 401 a second driving gear, 402 a second driven gear, 130 a first rotating shaft, 140 a second rotating shaft, 230 a third rotating shaft, 240 a fourth rotating shaft, 01 organism, 02 rotor subassembly, 03 brushless motor, 04 control module.

Detailed Description

The technical solutions in the embodiments of the present application will be clearly and completely described below with reference to the drawings in the embodiments of the present application, and it is obvious that the described embodiments are only a part of the embodiments of the present application, and not all of the embodiments. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present application.

The terms "first" and "second" in this application are used for descriptive purposes only and are not to be construed as indicating or implying relative importance or implicitly indicating the number of technical features indicated. Thus, a feature defined as "first" or "second" may explicitly or implicitly include at least one such feature. Furthermore, the terms "include" and "have," as well as any variations thereof, are intended to cover non-exclusive inclusions.

Reference herein to "an embodiment" means that a particular feature, structure, or characteristic described in connection with the embodiment can be included in at least one embodiment of the application. The appearances of the phrase in various places in the specification are not necessarily all referring to the same embodiment, nor are separate or alternative embodiments mutually exclusive of other embodiments. It is explicitly and implicitly understood by one skilled in the art that the embodiments described herein can be combined with other embodiments.

As shown in fig. 1, embodiments of the present invention provide a rotor assembly that may include a paddle mount 50, a first inertia drive assembly 10, a first blade 30, a second inertia drive assembly 20, and a second blade 40. It is understood that the number of linear transmission assemblies and blades of the rotor assembly provided by the invention is not limited to two, and can be three or four, etc. In the present embodiment, two inertia transmission assemblies and two blades are exemplified for explanation.

The first inertia transmission assembly 10 is connected with the paddle seat 50, the first paddle 30 is connected with the first inertia transmission assembly 10, the second inertia transmission assembly 20 is connected with the paddle seat 50, and the second paddle 40 is connected with the second inertia transmission assembly 20.

When the paddle holder 50 rotates around its rotation axis, the first paddle 30 can be rotated by the first inertia drive assembly 10, and the second paddle 40 can be rotated by the second inertia drive assembly 20.

When the paddle mount 50 rotates around its rotation axis at a certain initial speed, the first inertia drive assembly 10, the first blade 30, the second inertia drive assembly 20, and the second blade 40 all rotate around the axis of the paddle mount 50.

At this moment, a deceleration is given to the paddle seat 50, the first inertia transmission assembly 10 can drive the first paddle 30 to rotate under the inertia effect so as to increase the attack angle of the first paddle 30, and the second inertia transmission assembly 20 can drive the second paddle 40 to rotate under the inertia effect so as to decrease the attack angle of the second paddle 40. The magnitude of the increase in the angle of attack of the first blade 30 and the magnitude of the decrease in the angle of attack of the second blade 40 are related to the magnitude of the initial speed and deceleration of the paddle mount 50, as well as to the configuration of the blade itself and the configuration of the inertia about assembly, and the degree of change in the angle of attack is not limited here.

The magnitude of the change in the angle of attack of first blade 30 and second blade 40 may be controlled by controlling the magnitude of the initial velocity and deceleration.

The attack angle of the first blade 30 is increased, and the lift force borne by the blade surface of the first blade 30 is increased; the angle of attack of the second blade 40 decreases and the lift experienced by the airfoil of the second blade 40 decreases, at which point the rotor assembly as a whole tilts towards the first blade 30.

Similarly, the angle of inclination is related to the magnitude of the change in angle of attack; similarly, the magnitude of the initial velocity and deceleration can be controlled to control the degree of tilt of the rotor assembly.

After the speed of the paddle base 50 is reduced, the first paddle 30 rotates relative to the first inertia transmission assembly 10, the second paddle 40 rotates relative to the second inertia transmission assembly 20, the paddle base 50 is accelerated again at the moment, the first inertia transmission assembly 10 can drive the first paddle 30 to rotate under the inertia effect so as to reduce the attack angle of the first paddle 30, and the second inertia transmission assembly 20 can drive the second paddle 40 to rotate under the inertia effect so as to increase the attack angle of the second paddle 40.

The attack angle of the first blade 30 is reduced, and the lift force received by the blade surface of the first blade 30 is reduced; the angle of attack of second blade 40 increases and the lift experienced by the airfoil of second blade 40 decreases, at which point the rotor assembly as a whole tilts towards second blade 40.

Because the paddle housing 50 decelerates, the rotor assembly as a whole tilts toward the first blade 30, and after acceleration, the rotor assembly tilts toward the second blade 40, i.e., the rotor assembly returns to its original flight state.

If an instantaneous deceleration is periodically applied to the paddle base 50 at the same rotation position of the paddle base 50 rotating at a constant speed, the entire rotor assembly can be tilted in a certain direction, and the initial motion state can be rapidly recovered after the tilting until the paddle base 50 rotates to a corresponding position and the rotor assembly tilts in the same direction.

As shown in fig. 2 to 4, in some embodiments, the first inertia transfer assembly 10 may include a first hinge base 11 and a first paddle clip 12, and the second inertia transfer assembly 20 includes a second hinge base 21 and a second paddle clip 22.

Referring to fig. 3 and 4, the first hinge base 11 is connected to the paddle base 50, one end of the first paddle catch 12 is connected to the first hinge base 11 through the first inclined shaft 110, the second hinge base 21 is connected to the paddle base 50, and one end of the second paddle catch 22 is connected to the second hinge base 11 through the second inclined shaft 210.

When the paddle holder 50 decelerates, the first paddle clamp 12 and the first paddle 30 rotate around the first inclined shaft 110 in the initial speed direction due to the inertia force, so as to increase the attack angle of the first paddle 30; thereafter, the paddle holder 50 is accelerated, and the first paddle holder 12 and the first paddle 30 rotate in the lagging direction around the rotation shaft of the first inclined shaft 110 due to the inertia force, thereby reducing the attack angle of the first paddle 30.

When the paddle holder 50 decelerates, the second paddle clip 22 and the second paddle 40 rotate around the second inclined shaft 210 in the initial speed direction due to the inertia force, thereby reducing the attack angle of the second paddle 40; thereafter, the paddle holder 50 is accelerated, and the second paddle holder 22 and the second paddle 40 rotate in the lagging direction around the rotation shaft of the second tilt shaft 210 due to the inertia force, thereby increasing the attack angle of the second paddle 40.

In some embodiments, with continued reference to fig. 3 and 4, the first hinge base 11 includes a first connecting portion 101 and a second connecting portion 102, one end of the first connecting portion 101 is rigidly connected to one end of the second connecting portion 102, and a first included angle α is formed between the first connecting portion 101 and the second connecting portion 102; the second hinge base 21 includes a third connecting portion 201 and a fourth connecting portion 202, one end of the third connecting portion 201 is rigidly connected to one end of the fourth connecting portion 202, and a second included angle β is formed between the third connecting portion 201 and the fourth connecting portion 202.

The first included angle α is greater than 90 ° and less than 180 °, preferably 120 ° to 150 °, for example 130 °, 145 ° or 150 °.

The second angle beta is greater than 90 deg. and less than 180 deg., preferably 120 deg. -150 deg., such as 130 deg., 145 deg., or 150 deg., and the magnitude of the first angle alpha is equal to the magnitude of the second angle beta.

The first connecting portion 101 and the third connecting portion 201 are located on the same straight line and located in the rotation plane of the first blade 30 and the second blade 40, the second connecting portion 102 is bent toward the direction close to the blade base 50, the fourth connecting portion 202 is bent toward the direction away from the blade base 50, and the second connecting portion 102 is parallel to the fourth connecting portion 202, that is, the first included angle α and the second included angle β are in a diagonal relationship.

The first inclined shaft 110 is vertically disposed on the second connecting portion 102, the second inclined shaft 210 is vertically disposed on the fourth connecting portion 202, and the first inclined shaft 110 is parallel to the second inclined shaft 210 and is not parallel to the rotation plane of the paddle holder 50 or the rotation planes of the first and second paddles 30 and 40. An angle between a plane of rotation of the first blade 30 and the second blade 40 and the first oblique axis 110 may be 30 ° or more and 60 ° or less. In one embodiment, the plane of rotation of the first and second paddles 30, 40 is at a 45 ° angle to the first oblique axis 110.

Because the first inclined shaft 110 is parallel to the second inclined shaft 210 and is not parallel to the rotation surface of the paddle holder 50, after the paddle holder 50 is decelerated, the first paddle clamp 12 and the first paddle 30 can rotate around the first inclined shaft 110 in the initial speed direction by the action of inertia force, so that the attack angle of the first paddle 30 is increased; the second blade clamp 22 and the second blade 40 can rotate around the second inclined shaft 210 in the initial speed direction by the inertia force, so that the attack angle of the second blade 40 is reduced.

Because the first inclined shaft 110 is parallel to the second inclined shaft 210 and is not parallel to the rotating surface of the paddle holder 50, when the paddle holder 50 accelerates after decelerating, the first paddle clamp 12 and the first paddle 30 can rotate around the rotating shaft of the first inclined shaft 110 in the lagging direction by the action of inertia force, so as to reduce the attack angle of the first paddle 30; the second blade holder 22 and the second blade 40 rotate in the lagging direction around the second inclined shaft 210 due to the inertia force, thereby increasing the attack angle of the second blade 40.

The first included angle α is smaller than the second included angle β, and the second connection portion 102 is bent toward the direction close to the paddle seat 50, and the fourth connection portion 202 is bent toward the direction away from the paddle seat 50, which means that the second connection portion 102 and the fourth connection portion 202 may be parallel to each other.

The first connecting portion 101 and the third connecting portion 201 are parallel to the rotation surface of the paddle holder 50, and when the paddle holder 50 rotates around the axis thereof, the rotation surfaces of the first connecting portion 101 and the third connecting portion 201 are parallel to the rotation surface of the paddle holder 50.

In some embodiments, referring to fig. 2 to 4, the first paddle clip 12 further includes a first clamping portion 121, and the second paddle clip 22 further includes a second clamping portion 221. The first clamping portion 121 clamps the second connecting portion 102, and two clamped ends are respectively located at two ends of the first rotating shaft 110; the second clamping portion 221 clamps the fourth connecting portion 202, and two clamped ends are respectively located at two ends of the second rotating shaft 210. It is understood that a clamping portion may be provided on the second connecting portion 102 and the fourth connecting portion 202 to clamp the ends of the first blade clamp 12 and the second blade clamp 22. Alternatively, both the paddle clamp and the connecting portion are provided with a clamp.

In some embodiments, with continued reference to fig. 5, the first hinge mount 11 is rotationally connected to the paddle mount 50 through a rotational axis, and the second hinge mount 21 is rotationally connected to the paddle mount 50 through a rotational axis, such that the first hinge mount 11 can rotate in a plane of rotation perpendicular to the paddle mount 50, the second hinge mount 21 can rotate in a plane of rotation perpendicular to the paddle mount 50, and the directions of rotation of the first hinge mount 11 and the second hinge mount 21 in the plane of rotation perpendicular to the paddle mount 50 are the same.

Figure 5 is a state diagram of a rotor assembly after an instantaneous deceleration has been applied to the paddle mount 50 rotating at a constant speed in some embodiments. Because the attack angle of the first blade 30 is increased, the lift force received by the first blade is increased, and the first hinge base 11 rotates in the direction of increasing the lift force in the rotating plane which is vertical to the blade base 50; the second blade 40 receives a reduced lift force when the angle of attack is reduced, and the second hinge base 21 rotates in a direction in which the lift force is reduced in a rotation plane perpendicular to the blade base 50.

The rotating amplitude of the first hinge base 11 and the second hinge base 21 is controllable, and the rotating amplitude of the first hinge base 11 and the second hinge base 21 can be changed by controlling the change of the attack angle of the first blade 30 and the second blade 40.

When the instantaneous deceleration disappears and the initial speed is recovered, the attack angle of the first blade 30 is reduced, the applied lift force is reduced, and the first hinge base 11 rotates in the direction of reducing the lift force in the rotating plane vertical to the blade base 50; the attack angle of the second blade 40 is increased, the lift force received by the second blade is increased, and the second hinge base 21 rotates in the direction of increasing the lift force in the plane perpendicular to the rotation plane of the blade base 50 until the initial motion state is recovered.

In some embodiments, referring to fig. 6, the paddle socket 50 further includes a fixed socket 51 and a connecting plate 52 connected to the fixed socket 51, the first connecting portion 101 further includes a third clamping portion 131, and the third clamping portion 201 forms a first connecting portion connected to the paddle socket 50 by clamping the connecting plate 52; the third connecting portion 201 further includes a fourth clamping portion 231, and the fourth clamping portion 231 clamps the connecting plate 52 to form the third connecting portion 201 to be connected with the paddle seat 50. It is understood that the clamping portion may be provided on the connecting plate 52, or both the connecting plate 52 and the connecting portion.

When the first hinge base 11 and the paddle base 50 are rotatably connected by the rotating shaft, the third clamping portion 131 may clamp both ends of the connecting plate 52 as both ends of the rotating shaft, so that the first hinge base 11 can rotate in a rotating plane perpendicular to the paddle base 50. When the second hinge base 21 is rotatably connected to the paddle base 50 via the rotation shaft, the fourth clamping portion 231 may clamp both ends of the connecting plate 52 as both ends of the rotation shaft, so that the second hinge base 21 can rotate in a rotation plane perpendicular to the paddle base 50.

In other embodiments, referring to fig. 7 and 8, fig. 8 is a perspective view of the area of fig. 7 i, and the first inertia track assembly 10 includes a first mounting base 60, a first gear assembly 300, a first paddle holder 12 and a first inertia member 80. The first gear assembly 300 is disposed on the first mounting base 60, one end of the first paddle clamp 12 is connected to the first gear assembly 300, the other end is connected to the first paddle 30, and the first inertia member 80 is connected to the first gear assembly 300. The second inertia track assembly 20 includes a second mount 70, a second gear assembly 400, a second paddle holder 22, and a second inertia member 90. The second gear assembly 300 is disposed on the second mounting base 70, one end of the second paddle clamp 22 is connected to the second gear assembly 400, the other end is connected to the second blade 40, and the second inertia member 90 is connected to the second gear assembly 400.

When the paddle holder 50 rotates around the axis thereof, the first mounting seat 60, the first gear transmission assembly 300, the first paddle clip 12, the first paddle 30, the first inertia member 80, the second mounting seat 70, the second gear transmission assembly 400, the second paddle clip 22, the second paddle 40, and the second inertia assembly 90 can be driven to rotate together.

When the paddle seat 50 decelerates, the first inertial member 80 continues to rotate under the action of the inertial force, so as to drive the first gear transmission assembly 300 to rotate, and the first gear transmission assembly 300 drives the first paddle clamp 12 and the first paddle 30 to rotate, so as to increase the attack angle of the first paddle 30; the second inertia member 90 continues to rotate under the action of the inertia force, so as to drive the second gear transmission assembly 400 to rotate, and the second gear transmission assembly 400 drives the second paddle clip 22 and the second paddle 40 to rotate, thereby reducing the attack angle of the second paddle 40.

The attack angle of the first blade 30 is increased, and the lift force borne by the blade surface of the first blade 30 is increased; the angle of attack of the second blade 40 decreases and the lift experienced by the airfoil of the second blade 40 decreases, at which point the rotor assembly as a whole tilts towards the first blade 30.

When the paddle seat 50 is accelerated after being decelerated, the first inertial member 80 drives the first gear transmission assembly 300 to rotate under the action of the inertial force, and the first gear transmission assembly 300 drives the first paddle clamp 12 and the first paddle 30 to rotate, so that the attack angle of the first paddle 30 is reduced; the second inertia member 90 drives the second gear transmission assembly 400 to rotate under the action of the inertia force, and the second gear transmission assembly 400 drives the second paddle clamp 22 and the second paddle 40 to rotate, so as to increase the attack angle of the second paddle 40.

The attack angle of the first blade 30 is reduced, and the lift force received by the blade surface of the first blade 30 is reduced; the angle of attack of the second blade 40 is increased, the lift force applied to the blade surface of the second blade 40 is reduced, and at this time, the rotor assembly is wholly inclined towards the direction of the second blade 40, and the rotor assembly is restored to the original flight state.

In some embodiments, referring to fig. 7 and 8, the first gear assembly 300 includes a first shaft 130, a first driving gear 301, a second shaft 140, and a first driven gear 302. The first rotating shaft 130 is rotatably connected to the first mounting base 60, a first end of the first rotating shaft 130 is connected to the first inertia element 80 through the first lever 81, and a second end is connected to the first driving gear 301. The second rotating shaft 140 is rotatably connected to the first mounting base 60 and is perpendicular to the first rotating shaft 130, a first end of the second rotating shaft 140 is fixedly connected to the first paddle holder 12, a second end of the second rotating shaft is rigidly connected to the first driven gear 302, and the first driving gear 301 is engaged with the first driven gear 302. The second gear assembly 400 includes a third shaft 230, a second driving gear 401, a fourth shaft 240 and a second driven gear 402. The third shaft 230 is rotatably connected to the second mounting base 70, a first end of the third shaft 230 is connected to the second inertia element 90 through a second lever 91, and a second end of the third shaft is connected to the second driving gear 401. The fourth rotating shaft 240 is rotatably connected to the second mounting base 70 and is perpendicular to the third rotating shaft 230, a first end of the fourth rotating shaft 240 is fixedly connected to the second paddle holder 22, a second end of the fourth rotating shaft 240 is rigidly connected to the second driven gear 402, and the second driving gear 401 is engaged with the second driven gear 402.

When the first inertia element 80 moves under the action of the inertia force, the first lever 81 can drive the first rotating shaft 130 to rotate, the first rotating shaft 130 drives the first driving gear 301 to rotate, the first driving gear 301 drives the first driven gear 302 to rotate, so that the second rotating shaft 140 rotates, and the second rotating shaft 140 rotates to drive the first paddle clamp 12 and the first paddle 30 to rotate, so as to finally change the angle of attack of the first paddle 30.

When the second inertia element 90 moves under the action of the inertia force, the second lever 91 can drive the third rotating shaft 230 to rotate, the third rotating shaft 230 drives the second driving gear 401 to rotate, the second driving gear 401 drives the second driven gear 402 to rotate, so that the fourth rotating shaft 240 rotates, and the fourth rotating shaft 240 rotates to drive the second paddle clamp 22 and the second paddle 40 to rotate, so as to finally change the angle of attack of the second paddle 40.

In some embodiments, the second rotating shaft 140 and the fourth rotating shaft 240 are parallel to the rotation plane of the paddle socket 50, when the paddle socket 50 drives the second rotating shaft 140 and the fourth rotating shaft 240 to rotate, the rotation plane of the second rotating shaft 140 around the rotation axis of the paddle socket 50 and the rotation plane of the fourth rotating shaft 240 around the rotation axis of the paddle socket 50 are parallel to each other two by two, and the rotation plane of the second rotating shaft 140 may also be located on the same plane as the rotation plane of the fourth rotating shaft 240.

In some embodiments, the first shaft 130 and the second shaft 140 are in the same plane, which is perpendicular to the plane of rotation of the paddle mount 50.

In some embodiments, the third shaft 230 and the fourth shaft 240 are located in the same plane, which is perpendicular to the rotation plane of the paddle mount 50.

Alternatively, the first rotating shaft 130, the second rotating shaft 140, the third rotating shaft 230, and the fourth rotating shaft 240 may be located on the same plane, which is perpendicular to the rotation plane of the paddle holder 50.

In some embodiments, the first shaft 130 is located on a side of the second shaft 140 away from the paddle mount, and the third shaft 230 is located on a side of the fourth shaft 240 away from the paddle mount 50. First inertia member 80 is located on a side of first blade 30 remote from paddle mount 50 and second inertia member 90 is located on a side of second blade 40 remote from the paddle mount.

In some embodiments, the first rotating shaft 130 is spaced apart from the first inertia element 80, and the third rotating shaft 230 is spaced apart from the second inertia element 90.

Optionally, the distance between the first rotating shaft 130 and the first inertia element 80 can be adjusted by the length of the first lever 81, and the distance between the third rotating shaft 230 and the second inertia element 90 can be adjusted by the length of the second lever 91, where the distance can enable the first inertia element 80 and the second inertia element 90 to generate inertial motion when the paddle base 50 decelerates.

Alternatively, the first and second inertia members 80 and 90 may be pendulum assemblies, or other assemblies having a mass.

The greater the distance between the first rotation axis 130 and the first inertia member 80, the greater the inertial force obtained by the first inertia member 80 when the paddle mount 50 decelerates; according to the principle, the larger the distance between the second rotating shaft 230 and the second inertia member 90 is, the larger the inertia force obtained by the second inertia member 90 when the paddle mount 50 decelerates, the larger the inertia force obtained by the inertia member can be, by controlling the distance between the rotating shaft and the inertia member, the magnitude of the inertia force obtained by the inertia member can be controlled, and finally, the degree of the change of the pitch angle of the blade can be controlled.

Alternatively, the first lever 81 and the second lever 91 may be provided in a structure with adjustable length, and the degree of change in the blade attack angle may be changed by adjusting the lengths of the first lever 81 and the second lever 91.

The present invention also provides an aircraft that, in some embodiments, may include a body 01, a rotor assembly 02, a brushless motor 03, and a control module 04, see fig. 9 and 10. Rotor assembly 02 is the rotor assembly provided by the present invention described above. Rotor assembly 02 is mounted on airframe 01. Body 01 is capable of flying by the power provided by rotor assembly 02. Brushless motor 03 is connected with rotor subassembly 02 to it is rotatory to drive rotor subassembly 02. A receiver, a controller and an angle sensor are arranged in the control module 04, and the control module 04 is electrically connected to the brushless motor 03.

Referring to fig. 10, the brushless motor 03 may be connected to the paddle socket 50 and disposed in the paddle socket 50. The brushless motor 03 drives the rotor assembly 02 to rotate; an angle sensor in the control module 04 detects a rotation angle of the brushless motor 03 and transmits rotation angle information to a controller in the control module 04; the receiver receives control signals, e.g., attitude control signals from a remote control, and sends the control signals to the controller.

The controller may be further configured to control a rotation speed of the brushless motor 03 and a rotation angle position of the brushless motor 03, and the controller controls a brake position and a brake cycle of the brushless motor 03 according to the control signal and the rotation angle information.

When the brushless motor 03 stops periodically at the same rotation angle, the rotor assemblies 02 are periodically shifted in the same direction, and the aircraft can advance in a specific direction.

The above are embodiments of the present application only, and not intended to limit the scope of the present application, and all equivalent changes of structures or other structures that rely on inertia transmission assemblies to cause a change in the angle of attack of a blade, or that are directly or indirectly applied to other related technical fields, are also included in the scope of the present application.

Claims (10)

1. A rotor assembly, comprising:

a paddle seat;

the first inertia transmission assembly is connected with the paddle seat;

the first blade is connected with the first inertia transmission assembly;

the second inertia transmission assembly is connected with the paddle seat;

the second blade is connected with the second inertia transmission assembly;

when the paddle seat rotates around the rotation axis of the paddle seat, the first paddle can be driven to rotate by the first inertia transmission assembly, and the second paddle is driven to rotate by the second inertia transmission assembly; when the paddle base decelerates, the first inertial transmission component can drive the first paddle to rotate under the action of inertia so as to increase the attack angle of the first paddle, and the second inertial transmission component can drive the second paddle to rotate under the action of inertia so as to decrease the attack angle of the second paddle; when the paddle base is accelerated after being decelerated, the first inertia transmission assembly can drive the first paddle to rotate under the inertia effect so as to reduce the attack angle of the first paddle, and the second inertia transmission assembly can drive the second paddle to rotate under the inertia effect so as to increase the attack angle of the second paddle.

2. A rotor assembly according to claim 1, wherein the first inertia drive assembly comprises:

the first hinge base is connected with the paddle base;

one end of the first paddle clamp is connected with the first hinge base through a first inclined shaft, and the other end of the first paddle clamp is rigidly connected with the first paddle; when the paddle base decelerates, the first paddle and the first paddle clamp rotate around the first inclined shaft under the action of inertia force, and therefore the attack angle of the first paddle is increased;

the second inertia drive assembly includes:

the second hinge base is connected with the paddle base;

one end of the second paddle clamp is connected with the second hinge base through a second inclined shaft, and the other end of the second paddle clamp is rigidly connected with the second paddle; when the paddle base decelerates, the second paddle and the second paddle clamp rotate around the second inclined shaft under the action of inertia force, and therefore the attack angle of the second paddle is reduced.

3. A rotor assembly according to claim 2, wherein the first hinge mount comprises: the first connecting part is connected with the paddle seat, and the second connecting part is rigidly connected with the first connecting part; a first included angle is formed between the second connecting part and the first connecting part; the first inclined shaft is vertically arranged on the second connecting part, and the second connecting part is bent towards the direction close to the paddle seat;

the second hinge base comprises a third connecting part connected with the paddle base and a fourth connecting part rigidly connected with the third connecting part; a second included angle is formed between the fourth connecting part and the third connecting part; the second inclined shaft is vertically arranged on the fourth connecting part, and the fourth connecting part is bent away from the paddle seat;

the first included angle is larger than 90 degrees and smaller than 180 degrees, and the size of the first included angle is equal to that of the second included angle; the included angle between the rotating planes of the first paddle and the second paddle and the first inclined shaft is more than or equal to 120 degrees and less than or equal to 150 degrees.

4. A rotor assembly according to claim 3, wherein the first connection is parallel to the plane of rotation of the paddle mount, and the second connection is perpendicular to the plane of rotation of the paddle mount; the size of the first included angle is 120-150 degrees; one end of the first paddle clamp connected with the first hinge seat is provided with a first clamping part for clamping the second connecting part;

the third connecting part is parallel to the rotating surface of the paddle seat, and the plane where the fourth connecting part and the third connecting part are located is perpendicular to the rotating surface of the paddle seat; the size of the second included angle is 120-150 degrees; and one end of the second paddle clamp connected with the second hinge seat is provided with a second clamping part for clamping the fourth connecting part.

5. A rotor assembly according to claim 4, wherein the rotational connection between the first hinge mount and the paddle mount enables the first hinge mount to rotate in a plane perpendicular to a plane of rotation of the paddle mount;

the second hinge seat is connected with the paddle seat in a rotating mode, so that the second hinge seat can rotate in a plane perpendicular to the rotating surface of the paddle seat;

the first hinge seat and the second hinge seat have the same rotation direction in a plane perpendicular to the rotation surface of the paddle seat.

6. A rotor assembly according to claim 5, wherein the paddle mount includes a fixed mount and a web connected to the fixed mount; one end of the first connecting part, which is connected with the paddle seat, is provided with a third clamping part for clamping the connecting plate; one end of the third connecting part, which is connected with the paddle seat, is provided with a fourth clamping part for clamping the connecting plate.

7. A rotor assembly according to claim 1, wherein the first inertia drive assembly comprises:

a first mounting seat;

the first gear transmission assembly is arranged on the first mounting seat;

one end of the first paddle clamp is connected with the first gear transmission assembly, and the other end of the first paddle clamp is connected with the first paddle;

the first inertia piece is connected with the first gear transmission assembly; when the paddle seat decelerates, the first inertia part continues to rotate under the action of inertia force, and the first gear transmission assembly drives the first paddle clamp to rotate, so that the attack angle of the first paddle is increased;

the second inertia drive assembly includes:

a second mounting seat;

the second gear transmission assembly is arranged on the second mounting seat;

one end of the second paddle clamp is connected with the second gear transmission assembly, and the other end of the second paddle clamp is connected with the second paddle;

the second inertia piece is connected with the second gear transmission assembly; when the paddle base decelerates, the second inertia part continues to rotate under the action of inertia force, and the second gear transmission assembly drives the second paddle clamp to rotate, so that the attack angle of the second paddle is reduced.

8. A rotor assembly according to claim 7, wherein the first gear assembly comprises:

the first end of the first rotating shaft is connected with the first inertia part through a first lever, and the first inertia part drives the first rotating shaft to rotate under the action of inertia force;

the first driving gear is rigidly connected with the second end of the first rotating shaft;

the second rotating shaft is rotatably connected with the first mounting seat and is perpendicular to the first rotating shaft, and a first end of the second rotating shaft is fixedly connected with the first paddle clamp;

the first driven gear is rigidly connected with the second end of the second rotating shaft and is meshed with the first driving gear to convert the rotation of the first rotating shaft into the rotation of the second rotating shaft;

the second gear assembly includes:

the first end of the third rotating shaft is connected with the second inertia part through a second lever, and the second inertia part drives the third rotating shaft to rotate under the action of inertia force;

the second driving gear is rigidly connected with the second end of the third rotating shaft;

the fourth rotating shaft is rotatably connected with the second mounting seat and is perpendicular to the third rotating shaft, and a first end of the fourth rotating shaft is fixedly connected with the first paddle clamp;

and the second driven gear is rigidly connected with the second end of the fourth rotating shaft, is meshed with the second driving gear, and converts the rotation of the third rotating shaft into the rotation of the fourth rotating shaft.

9. A rotor assembly according to claim 8, wherein the second axis of rotation is parallel to a plane of rotation of the paddle mount; the plane where the first rotating shaft and the second rotating shaft are located is perpendicular to the rotating surface of the paddle seat; the first rotating shaft is positioned on one side, away from the paddle seat, of the second rotating shaft; the first inertia piece is positioned on one side of the first blade far away from the blade seat;

the fourth rotating shaft is parallel to the rotating surface of the paddle seat; the plane where the third rotating shaft and the fourth rotating shaft are located is perpendicular to the rotating surface of the paddle seat; the third rotating shaft is positioned on one side of the fourth rotating shaft, which is far away from the paddle seat; the second inertia member is positioned on one side of the second paddle remote from the paddle seat.

10. An aircraft, comprising a fuselage, a receiver, a controller, a brushless motor, an angle sensor, and a rotor assembly; the rotor assembly is connected with the brushless motor and is the rotor assembly according to any one of claims 1-9;

wherein the brushless motor drives the rotor assembly to rotate; the angle sensor detects the rotation angle of the brushless motor and sends the rotation angle information to the controller; the receiver receives a control signal and sends the control signal to the controller; the controller controls the brake position and brake period of the brushless motor according to the control signal and the rotation angle information, and the rotor wing assembly is periodically changed in distance.

Images