CN117734933A - An aircraft power system - Google Patents

Abstract

An aircraft power system relates to the field of aircraft, comprising: the device comprises a main shaft and a variable-pitch component, wherein one end of the main shaft is movably connected with a first propeller component, the other end of the main shaft is movably connected with a second propeller component, and the central axis of the main shaft is coincident with the rotation axis of the first propeller component; the main shaft is movably connected with the first screw member along the rotation direction of the first screw member, and is movably connected with the rotating shaft of the second screw member along the rotation direction of the second screw member; the variable-pitch component is arranged on the main shaft and used for adjusting the synchronous change of the blade angle of the first propeller component and the blade angle of the second propeller component. The power system structure can be simplified, meanwhile, the whole occupied space of the power system is greatly reduced, the whole weight is reduced, and the aircraft is lighter and convenient to control.

Description

An aircraft power system

Technical field

The present invention relates to the field of aircraft, and in particular, to an aircraft power system.

Background technique

At present, the power systems of existing aircraft such as double-propeller drones/helicopters are relatively complex, which not only places extremely high requirements on the flight control system, but also takes up a large space and affects the overall weight of the aircraft.

In view of this, this application is filed.

Contents of the invention

The purpose of the present invention is to provide an aircraft power system that can simplify the structure of the power system while greatly reducing the space occupied by the entire power system and reducing the overall weight, making the aircraft lighter and easier to control.

The embodiment of the present invention is implemented as follows:

An aircraft power system, including: a main shaft and a variable pitch member. One end of the main shaft is movably connected to a first propeller member, and the other end is movably connected to a second propeller member. The central axis of the main shaft coincides with the rotation axis of the first propeller member. ; Along the rotation direction of the first propeller member, the main shaft is movably connected with the first propeller member, and along the rotation direction of the second propeller member, the main shaft is movably connected with the rotating shaft of the second propeller member;

The pitch changing member is provided on the main shaft and is used to adjust the blade angle of the first propeller member and the blade angle of the second propeller member to change synchronously.

Further, the variable pitch component includes: a first swash plate assembly, a second swash plate assembly and a synchronization assembly;

The first swash plate assembly and the second swash plate assembly are both arranged on the main shaft, and the first swash plate assembly is connected to the first propeller member, and the second swash plate assembly is connected to the second propeller member; along the axial direction of the main shaft, the first tilt Both the plate assembly and the second tilt plate assembly are movably connected to the main shaft;

One end of the synchronization assembly is connected to the first swash plate assembly, and the other end is connected to the second swash plate assembly; so that the first swash plate assembly and the second swash plate assembly can tilt synchronously and/or move axially along their respective central axes. , synchronously adjusting the blade angles of the first propeller component and the second propeller component.

Further, the first swash plate assembly includes: a first spherical bearing, a first transmission part, a first transmission arm and a second transmission arm; along the circumferential direction of the first spherical bearing, the first transmission part is connected with the outer surface of the first spherical bearing. circle activity connection;

The first transmission arm and the second transmission arm are respectively rotatably connected with the outer ring of the first spherical bearing, and the ends of the first transmission arm and the second transmission arm away from the first spherical bearing are respectively rotatably connected with the two propellers of the first propeller member. rotationally connected;

The second swash plate assembly includes: a second spherical bearing, a second transmission part, a third transmission arm and a fourth transmission arm; along the circumferential direction of the second spherical bearing, the second transmission part is movably connected to the outer ring of the second spherical bearing. ;

The third transmission arm and the fourth transmission arm are respectively rotatably connected with the outer ring of the second spherical bearing, and the ends of the third transmission arm and the fourth transmission arm away from the second spherical bearing are respectively rotatably connected with the two propellers of the second propeller member. rotationally connected;

One end of the synchronization component is connected to the second transmission part, and the other end is connected to the first transmission part, and at least three synchronization components are evenly distributed along the circumferential direction of the first swash plate assembly.

Further, the variable pitch component also includes a power component, which is used to drive the first swash plate assembly or the second swash plate assembly to tilt with its central axis as an axis, and/or drive the first swash plate assembly or the second swash plate assembly. Reciprocating movement along its central axis;

The power assembly includes: a support member and a drive member; the drive member is located on the support member, and the drive member is connected to the first swash plate assembly or the second swash plate assembly to drive the first swash plate assembly or the second swash plate assembly to its central axis tilt the axis, and/or drive the first swash plate assembly or the second swash plate assembly to move in the direction of its central axis.

Further, the central axis of the support member coincides with the central axis of the first swash plate assembly or the second swash plate assembly; the driving member includes at least three driving assemblies evenly arranged along the circumferential direction of the supporting member.

Further, the driving assembly includes: a steering gear, a driving arm and a connecting arm. The steering gear is located on the support member. One end of the driving arm is connected to the output shaft of the steering gear, and the other end is rotatably connected to the connecting arm. The connecting arm is away from the end of the driving arm. It is rotatably connected with the first transmission part or the second transmission part.

Further, the variable pitch component also includes a limiting component; along the central axis direction of the first propeller component or the second propeller component, the limiting component is movably connected with the first swash plate assembly and/or the second swash plate assembly; to limit the third a swash plate assembly and/or a second swash plate assembly;

The limiting component includes: a limiting part, a first limiting rod and a second limiting rod. The limiting part is connected with the main shaft. A first strip hole and a second strip hole are respectively provided at both ends of the limiting part; The central axes of the first strip hole and the second strip hole coincide with each other, and the central axes of the first strip hole and the second strip hole are respectively parallel to the central axis of the main shaft;

One end of the first limiting rod is connected to the first transmission part, and the other end is placed in the first strip hole and can reciprocate along the axial direction of the first strip hole; one end of the second limiting rod is connected to the second transmission part, and the other end is connected to the first strip hole. One end is placed in the second strip hole and can reciprocate along the axial direction of the second strip hole.

Further, the first propeller component includes: a first motor and a first blade assembly, the first blade assembly is connected with the rotating part of the first motor;

The second propeller component includes: a second motor and a second blade assembly, the second blade assembly is connected to the rotating part of the second motor;

Along the circumferential direction of the rotation axis of the first motor, one end of the main shaft is movably connected with the first motor; along the circumferential direction of the rotation axis of the second motor, one end of the main shaft away from the first motor is movably connected with the second motor.

Further, the first motor includes: a first stator, a first rotor housing and a first connecting component, the central axis of the first connecting component coincides with the rotation axis of the first rotor housing;

The first connection component includes a first connection part and a second connection part coaxially arranged. The first connection part is connected to the first rotor shell; the first rotor shell is provided with a first center hole matching the second connection part, and the second connection part is connected to the first rotor shell. One end of the connecting part away from the first connecting part passes through the first central hole and is placed in the shaft hole of the first stator; along the circumferential direction of the second connecting part, the second connecting part is movably connected with the first stator;

The second motor includes: a second stator, a second rotor housing and a second connecting component, the central axis of the second connecting component coincides with the rotation axis of the second rotor housing;

The second connection component includes a third connection part and a fourth connection part coaxially arranged. The third connection part is connected with the second rotor shell; the second rotor shell is provided with a second center hole matching the fourth connection part. One end of the connecting part away from the third connecting part passes through the second central hole and is placed in the shaft hole of the second stator; along the circumferential direction of the fourth connecting part, the fourth connecting part is movably connected with the second stator.

Further, the first blade assembly includes a first fixed connection part, a first rotating connection part and a first propeller blade. The first fixed connection part is detachably connected to the first connection component; along the circumferential direction of the first fixed connection part, The first fixed connection part is movably connected with the first rotary connection part; the first propeller blade is connected with the first rotary connection part; at least two first propeller components are symmetrically provided on the first connection component;

The second blade assembly includes a second fixed connection part, a second rotating connection part and a second propeller blade. The second fixed connection part is detachably connected to the second connection component; along the circumferential direction of the second fixed connection part, the second fixed connection part The connecting part is movably connected with the second rotating connecting part; the second propeller blade is connected with the second rotating connecting part; at least two second propeller components are symmetrically arranged on the second connecting component.

The beneficial effects of the embodiments of the present invention are:

The aircraft power system provided by the embodiment of the present invention can use the main shaft to connect the first propeller component and the second propeller component and provide a certain supporting force. In addition, installing the variable pitch component on the main shaft can reduce the stress of the variable pitch component. Dedicated space, and the blade angles of the first propeller component and the second propeller component are synchronously adjusted through a variable pitch component, which greatly saves the occupied space, reduces the weight of the power system, and ensures that the first propeller component and the second propeller component are The blade angles of the two propeller components are always synchronized during the adjustment process to improve flight stability.

Generally speaking, the aircraft power system provided by embodiments of the present invention can simplify the structure of the power system, greatly reduce the space occupied by the entire power system, and reduce the overall weight, making the aircraft lighter and easier to control.

Description of drawings

In order to explain the technical solutions of the embodiments of the present invention more clearly, the drawings required to be used in the embodiments will be briefly introduced below. It should be understood that the following drawings only show some embodiments of the present invention and therefore do not It should be regarded as a limitation of the scope. For those of ordinary skill in the art, other relevant drawings can be obtained based on these drawings without exerting creative efforts.

Figure 1 is a perspective view of a power system provided by an embodiment of the present invention;

Figure 2 is a front view of the power system provided by the embodiment of the present invention;

Figure 3 is a cross-sectional view of the power system provided by the embodiment of the present invention;

Figure 4 is a perspective view of the variable distance component provided by the embodiment of the present invention;

Figure 5 is a front view of the variable pitch component provided by the embodiment of the present invention;

Figure 6 is a schematic structural diagram of the first swash plate assembly provided by an embodiment of the present invention;

Figure 7 is a top view of the first swash plate assembly provided by the embodiment of the present invention;

Figure 8 is a cross-sectional view along line A-A in Figure 7;

Figure 9 is a schematic structural diagram of a second swash plate assembly provided by an embodiment of the present invention;

Figure 10 is a top view of the second swash plate assembly provided by the embodiment of the present invention;

Figure 11 is a front view of the power assembly provided by the embodiment of the present invention;

Figure 12 is a schematic structural diagram of a power assembly provided by an embodiment of the present invention;

Figure 13 is a schematic structural diagram of a limiting component provided by an embodiment of the present invention;

Figure 14 is a schematic diagram of the working state of the first propeller component provided by the embodiment of the present invention;

Figure 15 is a schematic diagram of the first propeller component in a static state according to an embodiment of the present invention;

Figure 16 is a cross-sectional view of the first motor provided by the embodiment of the present invention;

Figure 17 is a perspective view of the first motor provided by the embodiment of the present invention;

Figure 18 is a schematic structural diagram of the first rotor housing provided by the embodiment of the present invention;

Figure 19 is a schematic structural diagram of the first connection component provided by an embodiment of the present invention;

Figure 20 is a partial structural schematic diagram of the first blade assembly provided by an embodiment of the present invention;

Figure 21 is an exploded view of a partial structure of the first blade assembly provided by the embodiment of the present invention;

Figure 22 is a schematic structural diagram of the first blade assembly provided by an embodiment of the present invention;

Figure 23 is a schematic diagram of the working state of the second propeller component provided by the embodiment of the present invention;

Figure 24 is a schematic diagram of the second propeller component in a static state according to an embodiment of the present invention;

Figure 25 is a cross-sectional view of the second motor provided by the embodiment of the present invention;

Figure 26 is a perspective view of the second motor provided by the embodiment of the present invention;

Figure 27 is a schematic structural diagram of the second rotor housing provided by the embodiment of the present invention;

Figure 28 is a schematic structural diagram of the second connection component provided by the embodiment of the present invention;

Figure 29 is a partial structural schematic diagram of the second blade assembly provided by the embodiment of the present invention;

Figure 30 is an exploded view of a partial structure of the second blade assembly provided by the embodiment of the present invention;

Figure 31 is a schematic structural diagram of a second blade assembly provided by an embodiment of the present invention.

Icon: 1000-spindle;

2000-variable pitch member;

100-first swash plate assembly, 110-first spherical bearing, 120-first transmission part, 130-first transmission arm, 140-second transmission arm;

200-second swash plate assembly, 210-second spherical bearing, 220-second transmission part, 230-third transmission arm, 240-fourth transmission arm;

300-synchronization component;

400-power component, 410-support member, 420-drive component, 421-server, 422-drive arm, 423-connecting arm;

500-limiting component, 510-limiting part, 520-first limiting rod, 530-second limiting rod, 540-first strip hole, 550-second strip hole;

3000-first propeller component;

600-first motor, 700-first blade assembly;

610-first connection component, 611-first connection part, 612-second connection part, 620-first bearing part, 630-first receiving part, 640-first rotor housing, 641-first center hole, 642 -The first receiving groove, 650-the first stator;

710-first fixed connection part, 720-first rotating connection part, 730-first transition connection part, 740-first propeller blade; 741-first blade, 742-second blade, 750-first auxiliary blade Connection part, 760-second auxiliary connection part;

4000-Second propeller component;

800-second motor, 900-second propeller assembly;

810-Second connection component, 811-Third connection part, 812-Fourth connection part, 820-Second bearing part, 830-Second receiving part, 840-Second rotor shell, 841-Second center hole, 842 -The second receiving groove, 850-the second stator;

910-second fixed connection part, 920-second rotating connection part, 930-second transition connection part, 940-second propeller blade; 941-third blade, 942-fourth blade, 950-third auxiliary blade Connection part, 960-the fourth auxiliary connection part.

Detailed ways

In order to make the purpose, technical solutions and advantages of the embodiments of the present invention clearer, the technical solutions in the embodiments of the present invention will be clearly and completely described below in conjunction with the drawings in the embodiments of the present invention. Obviously, the described embodiments These are some embodiments of the present invention, rather than all embodiments. The components of the embodiments of the invention generally described and illustrated in the figures herein may be arranged and designed in a variety of different configurations.

Therefore, the following detailed description of the embodiments of the invention provided in the appended drawings is not intended to limit the scope of the claimed invention, but rather to represent selected embodiments of the invention. Based on the embodiments of the present invention, all other embodiments obtained by those of ordinary skill in the art without making creative efforts fall within the scope of protection of the present invention.

Example

Please refer to Figures 1-31. This embodiment provides an aircraft power system, including: a main shaft 1000, a pitch variable component 2000, a first propeller component 3000 and a second propeller component 4000.

Among them, one end of the main shaft 1000 is movably connected with the first propeller member 3000, and the other end is movably connected with the second propeller member 4000, and the central axis of the main shaft 1000 coincides with the rotation axis of the first propeller member 3000; along the first propeller member 3000 Along the rotation direction of the second propeller member 4000, the main shaft 1000 is movably connected with the first propeller member 3000; along the rotation direction of the second propeller member 4000, the main shaft 1000 is movably connected with the rotating shaft of the second propeller member 4000;

The variable pitch component 2000 is provided on the main shaft 1000 and is used to adjust the blade angle of the first propeller component 3000 and the blade angle of the second propeller component 4000 to change synchronously.

It should be noted that in this embodiment, during the respective rotations of the first propeller component 3000 and the second propeller component 4000, the main shaft 1000 always remains stationary.

Another thing that needs to be noted is that during actual operation, the rotation directions of the first propeller member 3000 and the second propeller member 4000 are opposite to offset the torsion. This is a conventional prior art and will not be described again here.

During operation, the aircraft is powered by the rotation of the first propeller component 3000 and the second propeller component 4000. In addition, the aircraft heading can be adjusted through different rotational speeds of the first propeller component 3000 and the second propeller component 4000.

In addition, the pitch changing member 2000 is used to adjust the blade angles of the first propeller member 3000 and the second propeller member 4000, thereby realizing the lifting and turning of the aircraft.

Through the above design, the main shaft 1000 can be used to connect the first propeller member 3000 and the second propeller member 4000 and provide a certain supporting force. In addition, installing the pitch variable member 2000 on the main shaft 1000 can reduce the stress of the pitch variable member 2000. Dedicated space, and the blade angles of the first propeller component 3000 and the second propeller component 4000 are synchronously adjusted through a variable pitch component 2000, which greatly saves the occupied space, reduces the weight of the power system, and ensures that the first propeller component The blade angles of the component 3000 and the second propeller component 4000 are always synchronized during the adjustment process, thereby improving flight stability.

Generally speaking, the aircraft power system provided by embodiments of the present invention can simplify the structure of the power system, greatly reduce the space occupied by the entire power system, and reduce the overall weight, making the aircraft lighter and easier to control.

Please refer to Figures 14-24. In this embodiment, the first propeller component 3000 includes: a first motor 600 and a first blade assembly 700. The first blade assembly 700 is connected to the rotating part of the first motor 600; The propeller component 4000 includes: a second motor 800 and a second blade assembly 900. The second blade assembly 900 is connected to the rotating part of the second motor 800;

Along the circumferential direction of the rotation axis of the first motor 600, one end of the main shaft 1000 is movably connected with the first motor 600; along the circumferential direction of the rotation axis of the second motor 800, one end of the main shaft 1000 away from the first motor 600 is connected with the second motor 600. Two motors with 800 active connections.

Specifically, the first motor 600 includes: a first stator 650, a first rotor housing 640, a first connection component 610, a first bearing part 620 and a first receiving part 630, wherein the first connection component 610 is the same as the first rotor. The shell 640 is connected, and the central axis of the first connection component 610 coincides with the rotation axis of the first rotor shell 640;

The first receiving portion 630 is connected to an end of the first connecting component 610 away from the first rotor housing 640 , and the central axis of the first bearing portion 620 and the central axis of the first connecting component 610 have an included angle.

In this embodiment, the angle between the central axis of the first receiving portion 630 and the central axis of the first connecting component 610 is preferably 90°.

It should be noted that during actual implementation, the number of first receiving portions 630 can be set accordingly according to the number of actuators that need to be connected; however, in order to ensure that the first rotor housing 640 drives the actuators to maintain stable rotation when rotating. , when there are multiple actuators that need to be connected, and thus there are multiple first receiving parts 630 , the plurality of first receiving parts 630 need to be distributed in an array along the circumferential direction of the first connecting component 610 to ensure force bearing during rotation. Evenly.

Through the above design, the first connection component 610 can be directly disposed on the first rotor housing 640, thereby facilitating the direct connection of the actuator, ensuring the stability of the motor during rotation to a great extent, and improving the applicable scope of the motor.

The first connection component 610 includes a first connection part 611 and a second connection part 612 arranged coaxially. The first connection part 611 is connected to the first rotor shell 640; the first rotor shell 640 is provided with a matching second connection part 612. The first central hole 641 and the end of the second connecting portion 612 away from the first connecting portion 611 pass through the first central hole 641 and are placed in the shaft hole of the first stator 650 .

Specifically, along the circumferential direction of the second connecting portion 612, the second connecting portion 612 is movably connected to the first stator 650.

It should be noted that the first stator 650 of the external rotor motor is provided with a shaft hole, which is a conventional technical means, and its purpose is to facilitate the connection between the first stator 650 and an external fixture for installation.

Another thing that needs to be explained is that the central axis of the first central hole 641 coincides with the central axis of the shaft hole of the first stator 650, that is, the first central hole 641 is coaxial with the shaft hole of the first stator 650; in addition, Since the first connecting component 610 is connected to the first rotor housing 640, the second connecting portion 612 and the first central hole 641 may have an interference fit, a clearance fit, or no fit.

In this embodiment, in order to ensure that the first stator 650 can provide certain support to the first connection component 610, a plurality of bearings are installed on the outside of the second connection part 612, and the outer ring of the bearing is in contact with the inner wall of the shaft hole of the first stator 650. .

In this way, the first connecting part 611 can be used to connect to the first rotor housing 640, and the second connecting part 612 can be movably connected to the first stator 650 along the circumferential direction of the rotation axis of the first rotor housing 640, thereby further ensuring This improves the rotational stability of the first rotor housing 640 and ensures the stability of the first connecting component 610 when rotating with the first rotor housing 640, thereby preventing the first connecting component 610 from swinging in the horizontal direction and affecting the actual use effect.

In this embodiment, in order to ensure the stability of the connection between the first connection component 610 and the first rotor housing 640, a first load-bearing part 620 is specially added. The first load-bearing part 620 is provided on the outer wall of the first connection part 611. A plurality of first load-bearing parts 620 are The bearing portions 620 are evenly distributed along the circumferential direction of the first connecting component 610, and the plurality of first bearing portions 620 are detachably connected to the first rotor housing 640.

Specifically, the detachable connection method between the first bearing part 620 and the first rotor housing 640 may adopt one of bolt connection, screw connection, buckle connection, etc., or other detachable connection methods in the conventional art. , in this embodiment, it is preferable to adopt a bolt connection method, by opening a through hole in the first bearing part 620 and a threaded hole in the first rotor housing 640, and then connecting through bolts.

The first rotor housing 640 is provided with a first receiving groove 642 for accommodating a plurality of first bearing parts 620. The central axis of the first receiving groove 642 coincides with the rotation axis of the first rotor housing 640. Moreover, the distance from the end of the first bearing portion 620 to the central axis of the first connecting portion 611 is smaller than the radius of the first receiving groove 642 , ensuring that the first bearing portion 620 can be placed in the first receiving groove 642 .

Specifically, the first blade assembly 700 includes a first fixed connection part 710, a first rotating connection part 720, a first transition connection part 730 and a first propeller blade 740. The first fixed connection part 710 can be connected with the first receiving part 630. Detachable connection; along the circumferential direction of the first receiving part 630, the first fixed connection part 710 is movably connected with the first rotating connection part 720; the first propeller blade 740 is connected with the first rotating connection part 720.

Specifically, the first receiving part 630 has a threaded hole along its axial direction, and one end of the first fixed connection part 710 is processed with threads that engage with the threaded hole. In this way, the first fixed connection part 710 and the first receiving part 630 are connected. Connection.

In addition, the first rotating connection part 720 is provided with a fitting hole along its axial direction, and the end of the first fixed connection part 710 away from the first receiving part 630 can be placed in the fitting hole, and the first fixed connection part 710 is connected to the first fixed connection part 710 through a bearing. The rotary connection part 720 is connected, so that the first rotary connection part 720 can rotate about the central axis of the first fixed connection part 710 as an axis.

In this embodiment, one side of the first transitional connection part 730 is connected to the first propeller blade 740, and the other end is rotatably connected to the first rotating connection part 720; the rotational axis line of the first transitional connection part 730 is connected to the first receiving part The central axis of 630 is located on the same plane, and there is an included angle between the rotation axis of the first transition connection part 730 and the central axis of the first receiving part 630 .

Specifically, in this embodiment, the included angle between the rotation axis of the first transition connection part 730 and the central axis of the first receiving part 630 is 90°.

It should be noted that in this embodiment, when the motor is not rotating, the first propeller blade 740 drives the first transition connection portion 730 to rotate under the action of its gravity. At this time, the central axis of the first propeller blade 740 is the same as the first propeller blade 740 . There is an included angle of 90° between the central axes of the receiving portion 630; when the motor starts to rotate, the first rotor housing 640 drives the first blade assembly 700 to rotate, and under the action of centrifugal force, the first transition connection portion 730 and the first blade assembly 700 rotate. A rotary connection part 720 rotates relatively, and at this time, the central axis of the first propeller blade 740 coincides with the central axis of the first receiving part 630 .

In addition, in this embodiment, at least two first receiving parts 630 are evenly arranged along the circumferential direction of the first connecting component 610, and each first receiving part 630 is connected to the first blade assembly 700; when the first blade assembly When 700 is not less than three, the plurality of first blade assemblies 700 are distributed in an annular array with the central axis of the first connecting assembly 610 as the axis, thereby ensuring stability during rotation.

Please refer to Figures 25-31. Specifically, the second motor 800 includes: a second stator 850, a second rotor housing 840, a second connection component 810, a second bearing part 820 and a second receiving part 830, wherein the second The connecting component 810 is connected to the second rotor housing 840, and the central axis of the second connecting component 810 coincides with the rotation axis of the second rotor housing 840;

The second receiving portion 830 is connected to an end of the second connecting component 810 away from the second rotor housing 840 , and the central axis of the second bearing portion 820 and the central axis of the second connecting component 810 have an included angle.

In this embodiment, the angle between the central axis of the second receiving portion 830 and the central axis of the second connecting component 810 is preferably 90°.

It should be noted that during actual implementation, the number of the second receiving portion 830 can be set accordingly according to the number of actuators that need to be connected; however, in order to ensure that the second rotor housing 840 drives the actuators to maintain stable rotation when rotating. , when there are multiple actuators that need to be connected, and thus there are multiple second receiving parts 830 , the plurality of second receiving parts 830 need to be distributed in an array along the circumferential direction of the second connecting component 810 to ensure force bearing during rotation. Evenly.

Through the above design, the second connection component 810 can be directly arranged on the second rotor housing 840, thereby facilitating the direct connection of the actuator, and ensuring the stability of the second motor 800 during rotation to a great extent, improving the second The scope of application of motor 800.

The second connection component 810 includes a coaxially arranged third connection part 811 and a fourth connection part 812. The third connection part 811 is connected to the second rotor housing 840; the second rotor housing 840 is provided with a matching fourth connection part 812. The end of the fourth connecting portion 812 away from the third connecting portion 811 passes through the second central hole 841 and is placed in the shaft hole of the second stator 850 .

Specifically, along the circumferential direction of the fourth connecting portion 812 , the fourth connecting portion 812 is movably connected with the second stator 850 .

It should be noted that the second stator 850 of the second outer rotor motor 800 is provided with a shaft hole, which is a conventional technical means, and its purpose is to facilitate the connection of the second stator 850 with an external fixture for installation.

Another thing that needs to be explained is that the central axis of the second central hole 841 coincides with the central axis of the shaft hole of the second stator 850, that is, the second central hole 841 is coaxial with the shaft hole of the second stator 850; in addition, since the second central hole 841 is coaxial with the shaft hole of the second stator 850, The second connecting component 810 is connected to the second rotor housing 840. Therefore, the fourth connecting part 812 and the second central hole 841 may have an interference fit, a clearance fit, or no fit.

In this embodiment, in order to ensure that the second stator 850 can provide certain support to the second connection component 810, a plurality of bearings are installed on the outside of the fourth connection part 812, and the outer rings of the bearings are in contact with the inner wall of the shaft hole of the second stator 850.

In this way, the third connecting part 811 can be used to connect to the second rotor housing 840, and the fourth connecting part 812 can be movably connected to the second stator 850 along the circumferential direction of the rotation axis of the second rotor housing 840, thereby further ensuring that The stability of the rotation of the second rotor housing 840 is ensured, and the stability of the second connection component 810 when rotating with the second rotor housing 840 is ensured, thereby preventing the second connection component 810 from swinging in the horizontal direction and affecting the actual use effect.

In this embodiment, in order to ensure the stability of the connection between the second connecting component 810 and the second rotor housing 840, a second bearing part 820 is specially added. The second bearing part 820 is provided on the outer wall of the third connecting part 811. A plurality of second bearing parts 820 are provided on the outer wall of the third connecting part 811. The bearing portions 820 are evenly distributed along the circumferential direction of the second connecting component 810, and the plurality of second bearing portions 820 are detachably connected to the second rotor housing 840.

Specifically, the detachable connection method between the second bearing part 820 and the second rotor housing 840 may adopt one of bolt connection, screw connection, buckle connection, etc., or other detachable connection methods in the conventional art. , in this embodiment, it is preferable to adopt a bolt connection method, by opening a through hole in the second bearing part 820 and a threaded hole in the second rotor housing 840, and then connecting through bolts.

The second rotor housing 840 is provided with a second receiving groove 842 for accommodating a plurality of second bearing portions 820 . The central axis of the second receiving groove 842 coincides with the rotation axis of the second rotor housing 840 . Moreover, the distance from the end of the second bearing portion 820 to the central axis of the third connecting portion 811 is smaller than the radius of the second receiving groove 842 , ensuring that the second bearing portion 820 can be placed in the second receiving groove 842 .

Specifically, the second blade assembly 900 includes a second fixed connection part 910, a second rotating connection part 920, a second transition connection part 930 and a second propeller blade 940. The second fixed connection part 910 can be connected with the second receiving part 830. Detachable connection; along the circumferential direction of the second receiving portion 830, the second fixed connection portion 910 is movably connected to the second rotary connection portion 920; the second propeller blade 940 is connected to the second rotary connection portion 920.

Specifically, the second receiving part 830 has a threaded hole along its axial direction, and one end of the second fixed connection part 910 is processed with threads that engage with the threaded hole. In this way, the second fixed connection part 910 and the second receiving part 830 are connected. Connection.

In addition, the second rotating connection part 920 is provided with a fitting hole along its axial direction, and one end of the second fixed connection part 910 away from the second receiving part 830 can be placed in the fitting hole, and the second fixed connection part 910 is connected to the second fixed connection part 910 through a bearing. The rotary connection part 920 is connected, so that the second rotary connection part 920 can rotate about the central axis of the second fixed connection part 910 as an axis.

In this embodiment, one side of the second transitional connection part 930 is connected to the second propeller blade 940, and the other end is rotatably connected to the second rotating connection part 920; the rotational axis line of the second transitional connection part 930 is connected to the second receiving part The central axis of 830 is located on the same plane, and there is an included angle between the rotation axis of the second transition connection part 930 and the central axis of the second receiving part 830 .

Specifically, in this embodiment, the included angle between the rotation axis of the second transition connection part 930 and the central axis of the second receiving part 830 is 90°.

It should be noted that in this embodiment, when the second motor 800 is not rotating, the second propeller blade 940 drives the second transition connection portion 930 to rotate under the action of its gravity. At this time, the center of the second propeller blade 940 There is an included angle of 90° between the axis and the central axis of the second receiving part 830; when the second motor 800 starts to rotate, it rotates from the housing to drive the second blade assembly 900 to rotate. Under the action of centrifugal force, the second transition connection part 930 rotates relative to the second rotary connection part 920. At this time, the central axis of the second propeller blade 940 coincides with the central axis of the second receiving part 830.

In addition, in this embodiment, at least two second receiving parts 830 are evenly arranged along the circumferential direction of the second connecting component 810, and each second receiving part 830 is connected to the second blade assembly 900; when the second blade assembly When 900 is not less than three, the plurality of second blade assemblies 900 are distributed in an annular array with the central axis of the second connecting assembly 810 as the axis, thereby ensuring stability during rotation.

It should be noted that the first motor 600 and the second motor 800 proposed in this embodiment are both external rotor motors, which have a fixed stator and a rotor housing that rotates with the stator as an axis. This is a conventional structure of an external rotor motor. , will not be described in detail here.

Please refer to Figures 4-13. Further, the variable pitch member 2000 includes: a first swash plate assembly 100, a second swash plate assembly 200 and a synchronization assembly 300; wherein the first swash plate assembly 100 is connected to the first propeller member 3000. ; The second swash plate assembly 200 is connected to the second propeller member 4000, and the central axis of the second swash plate assembly 200 coincides with the central axis of the first swash plate assembly 100; one end of the synchronization assembly 300 is connected to the first swash plate assembly 100, The other end is connected to the second swash plate assembly 200; so that the first swash plate assembly 100 and the second swash plate assembly 200 can synchronously tilt and/or synchronously move axially along their respective central axes, and synchronously adjust the first propeller member 3000. and the blade angle of the second propeller member 4000.

It should be noted that the first swash plate assembly 100 and the second swash plate assembly 200 themselves can tilt with their central axis as the axis under the action of external force, thereby controlling the size of the propeller component blade angle through the size of the tilt angle. It is a conventional prior art in this field and will not be described in detail here.

Another thing that needs to be explained is that there are three modes for adjusting the blade angle of the two propeller components during actual movement; one is that the first swash plate assembly 100 and the second swash plate assembly 200 tilt simultaneously (at this time, the first tilt The plane where the plate assembly 100 is located and the plane where the second swash plate assembly 200 is located are always parallel); second, the first swash plate assembly 100 and the second swash plate assembly 200 move synchronously along the directions of their respective central axes for a certain distance; third, the first tilt The plate assembly 100 and the second swash plate assembly 200 tilt synchronously, and at the same time, the first swash plate assembly 100 and the second swash plate assembly 200 move a certain distance in the direction of their respective central axes synchronously. During the actual flight, you can choose any mode or switch between the three modes as needed.

Through the synchronization assembly 300, the first swash plate assembly 100 and the second swash plate assembly 200 are always synchronized whether they are tilting or moving along their respective central axes, thereby greatly reducing the control difficulty and effectively reducing the length of the variable pitch system. The space volume reduces the overall weight of the variable pitch system, and the structure is simpler and the stability is stronger.

In this embodiment, the first propeller blade 740 includes a first blade 741 and a second blade 742; the second propeller blade 940 includes a third blade 941 and a fourth blade 942 arranged coaxially.

Specifically, please refer to Figures 6-8. In this embodiment, the first swash plate assembly 100 includes a first spherical bearing 110, a first transmission part 120, a first transmission arm 130 and a second transmission arm 140; wherein, The first spherical bearing 110 is provided on the main shaft 1000. Along the circumferential direction of the first spherical bearing 110, the first transmission part 120 is movably connected with the outer ring of the first spherical bearing 110;

The first transmission arm 130 and the second transmission arm 140 are rotatably connected to the outer ring of the first spherical bearing 110 respectively, and the ends of the first transmission arm 130 and the second transmission arm 140 away from the first spherical bearing 110 are respectively connected to the first propeller. The first blade 741 and the second blade 742 of the member 3000 are rotatably connected.

Please refer to Figures 9 and 10. The second swash plate assembly 200: includes a second spherical bearing 210, a second transmission part 220, a third transmission arm 230 and a fourth transmission arm 240; the second spherical bearing 210 is provided on the main shaft 1000; Along the circumferential direction of the second spherical bearing 210, the second transmission part 220 is movably connected with the outer ring of the second spherical bearing 210;

The third transmission arm 230 and the fourth transmission arm 240 are rotatably connected to the outer ring of the second spherical bearing 210 respectively, and the ends of the third transmission arm 230 and the fourth transmission arm 240 away from the second spherical bearing 210 are respectively connected to the second propeller. The third blade 941 and the fourth blade 942 of the member 4000 are rotatably connected.

One end of the synchronization component 300 is connected to the second transmission part 220 , and the other end is connected to the first transmission part 120 . Specifically, since the first swash plate assembly 100 and the second swash plate assembly 200 are tilted in all directions of their circumference, in order to ensure synchronization in all directions, in this embodiment, at least three synchronization assemblies are provided 300, three synchronization assemblies 300 are evenly distributed along the circumferential direction of the first swash plate assembly 100.

It should be noted that the first transmission part 120 and the second transmission part 220 are sleeved on the outer rings of the first spherical bearing 110 and the second spherical bearing 210 through bearings.

Another thing that needs to be explained is that in order to ensure the stability of the propeller pitch changing system, the first transmission arm 130 and the second transmission arm 140 are symmetrically arranged on the first transmission part 120 with the central axis of the first spherical bearing 110 as the axis. On both sides; furthermore, when the ends of the first transmission arm 130 and the second transmission arm 140 away from the first spherical bearing 110 are connected to the first blade 741 and the second blade 742 respectively, their connection points are also located on the first blade 741 and the second blade 742 is asymmetrical on both sides. Similarly, the third transmission arm 230 and the fourth transmission arm 240 are symmetrically arranged on both sides of the second transmission part 220 with the central axis of the second spherical bearing 210 as the axis; furthermore, between the third transmission arm 230 and the fourth transmission arm 240 When the end far away from the second spherical bearing 210 is connected to the third blade 941 and the fourth blade 942 respectively, the connection points are also located on asymmetrical sides of the third blade 941 and the fourth blade 942 .

In addition, considering that the two propeller components need to drive their blades to rotate when adjusting their blade angles, however, when the first swash plate assembly 100 and the second swash plate assembly 200 tilt and/or move axially along the main shaft 1000, so The force generated is in the vertical direction, and when the blade rotates, it will also drive the first transmission arm 130, the second transmission arm 140, the third transmission arm 230 and the fourth transmission arm 240 to produce a certain horizontal displacement; however, the Both ends of the first transmission arm 130 , the second transmission arm 140 , the third transmission arm 230 and the fourth transmission arm 240 are all rotatably connected, so displacement in the horizontal direction can be eliminated.

On the other hand, the first blade 741 and the second blade 742 are respectively provided with a first auxiliary connection part 750 and a second auxiliary connection part 760 connected to the first transmission arm 130 and the second transmission arm 140, wherein the first The end of the transmission arm 130 away from the spherical bearing is rotatably connected to the first auxiliary connection part 750, and the end of the second transmission arm 140 away from the spherical bearing is rotatably connected to the second auxiliary connection part 760;

The third blade 941 and the fourth blade 942 are respectively provided with a third auxiliary connection part 950 and a fourth auxiliary connection part 960 that are rotatably connected to the third transmission arm 230 and the fourth transmission arm 240, wherein the third transmission arm The end of 230 away from the spherical bearing is rotatably connected to the third auxiliary connection part 950, and the end of the fourth transmission arm 240 away from the spherical plain bearing is rotatably connected to the fourth auxiliary connection part 960; in this process of overcoming the rotation There are many solutions to the horizontal displacement method in the prior art. In addition, this problem is a common problem in the technical field and can be easily thought of by those skilled in the art.

In this embodiment, the power assembly 400 is used to drive the first swash plate assembly 100 or the second swash plate assembly 200 to tilt with the central axis of the main shaft 1000 as the axis, and/or drive the first swash plate assembly 100 or the second swash plate assembly 200 reciprocates along the axial direction of the main shaft 1000.

Specifically, please refer to Figures 11 and 12. The power assembly 400 includes: a support member 410 and a driving member; the support member 410 is provided on the main shaft 1000, and the support member 410 is located between the first swash plate assembly 100 and the second swash plate assembly 200. between;

The driving member is provided on the supporting member 410 and is connected with the first swash plate assembly 100 or the second swash plate assembly 200 to drive the first swash plate assembly 100 or the second swash plate assembly 200 to tilt with the central axis of the main shaft 1000 as the axis. , and/or drive the first swash plate assembly 100 or the second swash plate assembly 200 to move along the axial direction of the main shaft 1000 .

In addition, the central axis of the supporting member 410 coincides with the central axis of the main shaft 1000; the driving member includes at least three driving assemblies 420 evenly arranged along the circumferential direction of the supporting member 410.

The driving assembly 420 includes: a steering gear 421, a driving arm 422 and a connecting arm 423. The steering gear 421 is provided on the support member 410. One end of the driving arm 422 is connected to the output shaft of the steering gear 421, and the other end is rotatably connected to the connecting arm 423. The end of the arm 423 away from the driving arm 422 is rotatably connected to the first transmission part 120 or the second transmission part 220 .

It should be noted that since the steering gear 421 drives the driving arm 422 to rotate to drive the connecting arm 423 to produce a certain displacement, in order to overcome the horizontal displacement, on the one hand, the length of the driving arm 422 is shorter than the length of the connecting arm 423. On the other hand, both ends of the connecting arm 423 are rotatably connected to the driving arm 422 and the first swash plate assembly 100 or the second swash plate assembly 200 respectively, which is sufficient to overcome the horizontal displacement of the driving arm 422 during rotation. .

Another thing that needs to be noted is that the end of the connecting arm 423 away from the driving arm 422 is rotatably connected to the first transmission part 120 or the second transmission part 220 . The connection points between at least three connecting arms 423 and the first transmission part 120 or the second transmission part 220 are evenly distributed along the circumferential direction of the first transmission part 120 or the second transmission part 220 to ensure stability.

Since the support member 410 is fixedly connected to the main shaft 1000, the first spherical bearing 110 and the second spherical bearing 210 are also disposed on the main shaft 1000. However, along the circumferential direction of the first spherical bearing 110, the first transmission part 120 and the first spherical bearing 120 are The outer ring of 110 is movably connected; along the circumferential direction of the second spherical bearing 210, the second transmission part 220 is movably connected with the outer ring of the second spherical bearing 210. During operation, the first propeller member 3000 and the second propeller member 4000 rotate, but the main shaft 1000 remains stationary, because the first transmission arm 130, the second transmission arm 140, the third transmission arm 230 and the fourth transmission arm 240 will As the first propeller member 3000 and the second propeller member 4000 rotate, the outer rings of the first spherical bearing 110 and the second spherical bearing 210 are driven to rotate.

During the actual movement, the controller controls each of the three servos 421 to rotate at a certain angle, and the driving arm 422 in the three driving components 420 rotates at a certain angle to drive the connecting arm 423 to produce different displacements, thereby transmitting the force to the third A transmission part 120 or a second transmission part 220 drives the first spherical bearing 110 or the second spherical bearing 210 to move, thereby causing the first swash plate assembly 100 and the second swash plate assembly 200 to tilt at a certain angle and/or make the The first swash plate assembly 100 and the second swash plate assembly 200 generate a certain displacement along the axial direction of the main axis 1000. Due to the action of the synchronization assembly 300, during the above process, the first swash plate and the second swash plate are always tilted or moved. is to maintain synchronization; at the same time, under the action of the first transmission arm 130, the second transmission arm 140, the third transmission arm 230 and the fourth transmission arm 240, the force is further transmitted to the first propeller component 3000 and the second propeller component 4000, thereby causing the first blade 741 and the second blade 742 and the third blade 941 and the fourth blade 942 to rotate at a certain angle to achieve adjustment of the blade angle.

It should be noted that the rotation angles of the three servos 421 are calculated and controlled by the controller according to different operations during flight. This is a conventional prior art and will not be described in detail here.

Further, in order to avoid that when the rotation of the first propeller member 3000 and the second propeller member 4000 drives the outer rings of the first spherical bearing 110 and the second spherical bearing 210 to rotate, the first transmission part 120 and the second transmission part 120 may be caused by friction. The part 220 rotates, and a limiting component 500 is specially added in this embodiment;

Please refer to Figure 13. The limit assembly 500 includes: a limit part 510, a first limit rod 520 and a second limit rod 530. The limit part 510 is connected with the main shaft 1000. The limit part 510 is provided with a third limit rod at both ends. The strip hole 540 and the second strip hole 550; the central axes of the first strip hole 540 and the second strip hole 550 coincide, and the central axes of the first strip hole 540 and the second strip hole 550 are respectively the same. The central axis of the spindle 1000 is parallel;

One end of the first limiting rod 520 is connected to the first tilt plate assembly 100, and the other end is placed in the first strip hole 540 and can reciprocate along the axial direction of the first strip hole 540; one end of the second limiting rod 530 is connected to the first strip hole 540. The two tilt plate assemblies 200 are connected, and the other end is placed in the second strip hole 550 and can reciprocate along the axial direction of the second strip hole 550 .

Specifically, in this embodiment, the limiting part 510 is fixedly connected to the supporting member 410, and the first limiting rod 520 and the second limiting rod 530 are fixedly connected to the first transmission part 120 and the second transmission part 220 respectively; when the third When the first swash plate and the second swash plate move along the axial direction of the main shaft 1000, the first limit rod 520 and the second limit rod 530 move in the first strip hole 540 and the second strip hole 550 respectively.

In addition, in this embodiment, the main shaft 1000 adopts a hollow structure, which facilitates the circuit of the first propeller component 3000 to pass through and then be connected to the power supply and control system of the fuselage.

The working principle of an aircraft power system is:

When neither the first motor 600 nor the second motor 800 rotates, the first propeller blade 740 and the second propeller blade 940 drive the first transition connection part 730 and the second transition connection part 930 to rotate under the action of their gravity. When , the central axes of the first propeller blade 740 and the second propeller respectively have an included angle of 90° with the central axes of the first receiving portion 630 and the second receiving portion 830;

When the first motor 600 and the second motor 800 start to rotate simultaneously, the first rotation of the self-casing drives the first connection component 610 to rotate, and the second rotation of the self-casing drives the second connection component 810 to rotate, thereby driving the third connection component 610 through the first receiving part 630. One blade 741 assembly 700 rotates, and the second receiving part 830 drives the second blade 742 assembly to rotate. Under the action of centrifugal force, the first transition connection part 730 and the first rotation connection part 720 rotate relatively, and the second transition connection part 930 and The second rotary connection part 920 rotates relatively. At this time, the central axis of the first propeller blade 740 coincides with the central axis of the first receiving part 630, and the central axis of the second propeller blade 940 coincides with the central axis of the second receiving part 830;

When the blade angle needs to be adjusted during flight, first, the controller calculates the rotation amount of the three servos 421 as needed, and then controls the three servos 421 to rotate a certain angle, and the drive arms in the three drive assemblies 420 422 rotates at a certain angle to drive the connecting arm 423 to produce different displacements, thereby transmitting the force to the first transmission part 120 or the second transmission part 220, thereby driving the first spherical bearing 110 or the second spherical bearing 210 to move, thereby causing the first The swash plate assembly 100 and the second swash plate assembly 200 produce a certain angle of inclination and/or cause the first swash plate assembly 100 and the second swash plate assembly 200 to produce a certain displacement along the axial direction of the main shaft 1000 due to the action of the synchronization assembly 300 , during the above process, the first swash plate assembly 100 and the second swash plate assembly 200 are always synchronized regardless of tilt or movement; at the same time, during the first transmission arm 130, the second transmission arm 140, the third transmission arm 230 and the third Under the action of the four transmission arms 240, the force is further transmitted to the first propeller member 3000 and the second propeller member 4000, thereby making the first blade 741 and the second blade 742 and the third blade 941 and the fourth blade 942 rotates at a certain angle to adjust the blade angle.

In summary, the present invention can simplify the structure of the power system while greatly reducing the space occupied by the entire power system and reducing the overall weight, making the aircraft lighter and easier to control.

The above descriptions are only preferred embodiments of the present invention and are not intended to limit the present invention. For those skilled in the art, the present invention may have various modifications and changes. Any modifications, equivalent substitutions, improvements, etc. made within the spirit and principles of the present invention shall be included in the protection scope of the present invention.

Claims (10)

1. An aircraft power system, characterized by including: Main shaft, one end of the main shaft is movably connected with the first propeller member, the other end is movably connected with the second propeller member, and the central axis of the main shaft coincides with the rotation axis of the first propeller member; along the first propeller member Along the rotation direction of the propeller member, the main shaft is movably connected with the first propeller member, and along the rotation direction of the second propeller member, the main shaft is movably connected with the rotating shaft of the second propeller member; A pitch changing member, which is provided on the main shaft and is used to adjust the blade angle of the first propeller member and the blade angle of the second propeller member to change synchronously. 2. The aircraft power system according to claim 1, wherein the pitch variable component includes: a first swash plate assembly, a second swash plate assembly and a synchronization assembly; The first swash plate assembly and the second swash plate assembly are both provided on the main shaft, and the first swash plate assembly is connected to the first propeller member, and the second swash plate assembly is connected to the first propeller member. The two propeller components are connected; along the axial direction of the main shaft, the first swash plate assembly and the second swash plate assembly are movably connected to the main shaft; One end of the synchronization component is connected to the first swash plate assembly, and the other end is connected to the second swash plate assembly; so that the first swash plate assembly and the second swash plate assembly can tilt synchronously and/or The blade angles of the first propeller component and the second propeller component are synchronously adjusted by synchronously moving axially along respective central axis directions. 3. The aircraft power system according to claim 2, wherein the first swash plate assembly includes: a first spherical bearing, a first transmission part, a first transmission arm and a second transmission arm; In the circumferential direction of a spherical bearing, the first transmission part is movably connected with the outer ring of the first spherical bearing; The first transmission arm and the second transmission arm are rotatably connected to the outer ring of the first spherical bearing respectively, and the first transmission arm and the second transmission arm are away from the first spherical bearing. One end is rotatably connected to the two propellers of the first propeller member respectively; The second swash plate assembly includes: a second spherical bearing, a second transmission part, a third transmission arm and a fourth transmission arm; along the circumferential direction of the second spherical bearing, the second transmission part is the same as the third transmission arm. The outer rings of the two joint bearings are movablely connected; The third transmission arm and the fourth transmission arm are rotatably connected to the outer ring of the second spherical bearing respectively, and the third transmission arm and the fourth transmission arm are away from the second spherical bearing. One end is rotatably connected to the two propellers of the second propeller member respectively; One end of the synchronization component is connected to the second transmission part, and the other end is connected to the first transmission part, and at least three synchronization components are evenly distributed along the circumferential direction of the first swash plate assembly. 4. The aircraft power system according to claim 3, wherein the pitch variable component further includes a power assembly for driving the first swash plate assembly or the second swash plate assembly to its center The axis is an axis tilt, and/or drives the first swash plate assembly or the second swash plate assembly to reciprocate in the direction of its central axis; The power assembly includes: a support member and a drive member; the drive member is provided on the support member, and the drive member is connected with the first swash plate assembly or the second swash plate assembly to drive the third swash plate assembly. A swash plate assembly or a second swash plate assembly tilts with its central axis as its axis, and/or drives the first swash plate assembly or the second swash plate assembly to move along its central axis. 5. The aircraft power system according to claim 4, wherein the central axis of the support member coincides with the central axis of the first swash plate assembly or the second swash plate assembly; the driving member includes at least three A driving assembly is evenly arranged along the circumferential direction of the support member. 6. The aircraft power system according to claim 4, wherein the driving assembly includes: a steering gear, a driving arm and a connecting arm, the steering gear is arranged on the support member, and one end of the driving arm is connected to the connecting arm. The output shaft of the steering gear is connected, and the other end is rotatably connected to the connecting arm, and the end of the connecting arm away from the driving arm is rotatably connected to the first transmission part or the second transmission part. 7. The aircraft power system according to claim 3, wherein the pitch variable component further includes a limiting component; along the direction of the central axis of the first propeller component or the second propeller component, the limiting component The bit assembly is movably connected with the first swash plate assembly and/or the second swash plate assembly; to limit the first swash plate assembly and/or the second swash plate assembly; The limiting component includes: a limiting part, a first limiting rod and a second limiting rod. The limiting part is connected with the main shaft. First strip holes are respectively opened at both ends of the limiting part. and a second strip hole; the central axes of the first strip hole and the second strip hole coincide with each other, and the central axes of the first strip hole and the second strip hole are respectively the same as the The central axis of the spindle is parallel; One end of the first limiting rod is connected to the first transmission part, and the other end is placed in the first strip hole and can reciprocate along the axial direction of the first strip hole; the second limiting rod One end of the rod is connected to the second transmission part, and the other end is placed in the second strip hole and can reciprocate along the axial direction of the second strip hole. 8. The aircraft power system according to claim 3, wherein the first propeller component includes: a first motor and a first blade assembly, and the first blade assembly rotates with the first motor. external connection; The second propeller component includes: a second motor and a second blade assembly, the second blade assembly is connected to the rotating part of the second motor; Along the circumferential direction of the rotation axis of the first motor, one end of the main shaft is movably connected with the first motor; along the circumferential direction of the rotation axis of the second motor, the main shaft is away from the third motor. One end of a motor is movably connected to the second motor. 9. The aircraft power system according to claim 8, characterized in that, The first motor includes: a first stator, a first rotor housing and a first connecting component, the central axis of the first connecting component coincides with the rotation axis of the first rotor housing; The first connection component includes a first connection part and a second connection part arranged coaxially. The first connection part is connected with the first rotor shell; the first rotor shell is provided with a second connection part. The end of the second connecting part away from the first connecting part passes through the first central hole and is placed in the shaft hole of the first stator; along the second connecting part in the circumferential direction, the second connecting portion is movably connected to the first stator; The second motor includes: a second stator, a second rotor housing and a second connecting component, the central axis of the second connecting component coincides with the rotation axis of the second rotor housing; The second connection component includes a third connection part and a fourth connection part arranged coaxially. The third connection part is connected with the second rotor shell; the second rotor shell is provided with a connection with the fourth connection part. The end of the fourth connection part away from the third connection part passes through the second center hole and is placed in the shaft hole of the second stator; along the fourth connection part The fourth connecting portion is movably connected with the second stator in the circumferential direction of the stator. 10. The aircraft power system according to claim 9, characterized in that: The first blade assembly includes a first fixed connection part, a first rotating connection part and a first propeller blade. The first fixed connection part is detachably connected to the first connection component; along the first fixed connection The first fixed connection part is movably connected to the first rotary connection part; the first propeller blade is connected to the first rotary connection part; at least two of the first propeller assemblies are symmetrically arranged to the first connecting component; The second blade assembly includes a second fixed connection part, a second rotating connection part and a second propeller blade. The second fixed connection part is detachably connected to the second connection component; along the second fixed connection part The second fixed connection part is movably connected to the second rotary connection part; the second propeller blade is connected to the second rotary connection part; at least two second propeller assemblies are symmetrically arranged to the second connecting component.