CN218368270U

CN218368270U - Birotor motor and aircraft comprising same

Info

Publication number: CN218368270U
Application number: CN202222325294.8U
Authority: CN
Inventors: 薛松柏; 徐大勇; 李清; 易礼杰; 王武先
Original assignee: Zhejiang Geely Holding Group Co Ltd; Aerofugia Technology Chengdu Co Ltd
Current assignee: Chengdu Wofeitianyu Technology Co ltd; Zhejiang Geely Holding Group Co Ltd
Priority date: 2022-08-30
Filing date: 2022-08-30
Publication date: 2023-01-24
Anticipated expiration: 2032-08-30

Abstract

The utility model provides a birotor motor and aircraft that contains this birotor motor, this birotor motor includes: the motor comprises a shell, a stator bracket, a first winding and a second winding; the stator bracket is rotatably arranged in the shell; the first winding comprises a first stator winding and a first rotor winding, and the first stator winding is fixedly arranged on the stator bracket; the first rotor winding is fixedly arranged on the shell outside the first stator winding and is coaxially arranged with the first stator winding, and a first torque output end is arranged on the first rotor winding; the second winding comprises a second stator winding and a second rotor winding, and the second stator winding is fixedly arranged on the stator bracket; the second rotor winding is rotatably arranged on the stator support and/or the shell and is coaxial with the second stator winding, and a second torque output end is arranged on the second rotor winding. The problem that a rotor wing device and a pitch changing mechanism of an aircraft cannot be driven by the same driving device in the prior art can be solved through the double-rotor motor.

Description

Birotor motor and aircraft comprising same

Technical Field

The utility model relates to an aircraft technical field, concretely relates to birotor motor and contain aircraft of this birotor motor.

Background

The propeller is a device which rotates in fluid (such as air or water) by means of blades and converts the rotation kinetic energy of an engine or a motor into thrust (tensile force or lift force), has a very wide application range, is used as an important power mechanism in an aircraft, and is widely applied to the technical field of the aircraft; the method is also widely applied to the fields of ships, submarines and the like. The conventional propeller is a fixed-distance propeller, and even if a variable-pitch propeller is also provided, the variable-pitch propeller needs to adopt a steering engine or a hydraulic mechanism to control the pitch of the propeller additionally. It is therefore desirable to provide a dual rotor motor and an aircraft including the dual rotor motor, which can achieve the pitch-varying driving of the rotor device and the blades by the same motor.

SUMMERY OF THE UTILITY MODEL

In view of the shortcomings of the prior art above, the utility model provides a birotor motor and contain aircraft of this birotor motor to rotor device and the unable same drive arrangement driven problem of adopting of displacement mechanism of aircraft among the improvement prior art.

In order to achieve the above and other related objects, the present invention provides a dual rotor motor, comprising: the motor comprises a shell, a stator bracket, a first winding and a second winding; the stator bracket is rotatably arranged in the shell; the first winding comprises a first stator winding and a first rotor winding, and the first stator winding is fixedly arranged on the stator bracket; the first rotor winding is fixedly arranged on the shell outside the first stator winding and is coaxially arranged with the first stator winding, and a first torque output end is arranged on the first rotor winding; the second winding comprises a second stator winding and a second rotor winding, and the second stator winding is fixedly arranged on the stator bracket; the second rotor winding is rotatably installed on the stator support and/or the shell and is coaxial with the second stator winding, and a second torque output end is arranged on the second rotor winding.

In an embodiment of the dual-rotor motor of the present invention, the housing includes a first cover and/or a second cover, and the first cover is disposed on one side of the stator bracket close to the second torque output end and is fixedly connected to the housing; the second cover body is arranged on one side, deviating from the second torque output end, of the stator support and is fixedly connected with the shell.

The utility model discloses in an embodiment of birotor motor, first lid and/or be provided with on the second lid can be right the forced air cooling structure of birotor motor cooling of blowing.

In an embodiment of the present invention, the housing is provided with a cooling channel inside, the first cover and/or the second cover are provided with an airflow generating device capable of generating a cooling airflow during rotation, and the cooling airflow enters from one end of the cooling channel and is discharged from the other end of the cooling channel.

In an embodiment of the dual-rotor motor of the present invention, the cooling channel includes a plurality of through holes disposed on the stator bracket and located between the first stator winding and the second stator winding; the through holes are uniformly distributed along the circumferential direction of the stator support.

In an embodiment of the present invention, the stator frame is provided with a plurality of cooling fins.

In an embodiment of the dual-rotor motor of the present invention, the plurality of fins are disposed in the through hole, and a gap through which a cooling airflow passes is formed between two adjacent fins.

In an embodiment of the dual-rotor motor of the present invention, the airflow generating device includes a plurality of air inlets disposed on a side wall of the first cover or the second cover and a plurality of fan blades correspondingly disposed on a side of the first cover or the second cover close to the stator frame; the fan blades are uniformly distributed on the first cover body or the second cover body along the circumferential direction.

The utility model discloses in an embodiment of the birotor motor, the birotor motor still includes right the rotational speed or the rotary displacement of first rotor winding and/or second rotor winding carry out the sensor of feeding back, the sensor with the wired or wireless communication of control system of birotor motor is connected.

The utility model also provides an aircraft, which comprises a fuselage, a propeller arranged on the fuselage and a blade pitch varying mechanism for driving the pitch varying of the propeller blades, wherein the aircraft also comprises any one of the double-rotor motors; the stator support of the double-rotor motor is fixed on a body of the aircraft, and a first torque output end of the double-rotor motor is connected with the mounting frame of the propeller so as to drive the propeller to rotate; and a second torque output end of the double-rotor motor is connected with an input end of the blade pitch-changing mechanism so as to drive the blades of the propeller to change pitch.

The utility model discloses birotor motor has first torque output and the second torque output that can independent action simultaneously, and first torque output and second torque output can independent action simultaneously, can drive different subassemblies respectively and move, and the utility model discloses birotor motor installs the stator of two windings on same stator support, structurally optimizes more on the one hand, and on the other hand has reduced the volume of whole motor, has reduced the weight of motor. The utility model discloses the aircraft that contains this birotor motor adopts the utility model discloses the birotor motor can drive the screw respectively through first moment of torsion output, the second moment of torsion output of birotor motor and rotate and the displacement, has reduced the volume of aircraft, has reduced the whole weight of aircraft.

Drawings

In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings used in the description of the embodiments or the prior art will be briefly described below, it is obvious that the drawings in the following description are only some embodiments of the present invention, and for those skilled in the art, other drawings can be obtained according to these drawings without creative efforts.

Fig. 1 is a three-dimensional schematic view of a rotor device to which an embodiment of the dual-rotor motor of the present invention is applied;

fig. 2 is a plan sectional view of a rotor device to which an embodiment of the dual rotor motor of the present invention is applied;

fig. 3 is a half sectional axial view of a rotor device to which an embodiment of the dual rotor motor of the present invention is applied;

fig. 4 is an exploded view of a pitch varying mechanism connected to an embodiment of the dual-rotor motor according to the present invention;

fig. 5 is an exploded view of a dual-rotor motor according to an embodiment of the present invention;

fig. 6 is a partial view of a planetary gear and a sun gear connected to an embodiment of the dual-rotor motor according to the present invention;

FIG. 7 is an enlarged view of area I of FIG. 6;

fig. 8 is a schematic diagram illustrating the engagement of the bevel gear set connected to the dual-rotor motor according to an embodiment of the present invention;

fig. 9 is a front view of a stator frame in an embodiment of the dual-rotor motor of the present invention;

fig. 10 is a half sectional axial view of a stator frame according to an embodiment of the dual rotor motor of the present invention;

fig. 11 is a three-dimensional axial view of the first cover in an embodiment of the dual-rotor motor of the present invention;

fig. 12 is a three-dimensional axial view of a second cover in an embodiment of the dual-rotor motor of the present invention;

fig. 13 is a half sectional view of the second cover in an embodiment of the dual-rotor motor of the present invention.

Description of the element reference numerals

10. A paddle; 110. a rotating support; 20. a blade mount; 210. a gear case; 211. a first cylindrical recess; 212. mounting a through hole; 220. a housing; 221. a second cylindrical groove; 222. a first bevel gear mounting hole; 30. a pitch-changing mechanism; 310. a planetary gear set; 311. a sun gear; 312. a planet wheel; 313. a ring gear; 320. a bevel gear set; 321. a first bevel gear; 322. a second bevel gear; 323. a first bevel gear mounting shaft; 324. a fifth bearing; 40. a dual rotor motor; 410. a first winding; 411. a first rotor winding; 412. a first stator winding; 413. a first torque output; 420. a second winding; 421. a second rotor winding; 422. a second stator winding; 423. a second torque output; 430. a housing; 41. a fourth bearing; 42. a barrel; 43. a stator support; 431. a through hole; 432. a fin group; 433. a third bearing mounting cavity; 434. connecting ribs; 435. a first stator mounting base; 436. a second stator mounting seat; 437. a connecting portion; 44. a first cover body; 441. a second bearing mounting cavity; 442. a vent hole; 45. a second cover body; 451. an air inlet; 452. a fan blade; 453. a first bearing mounting cavity; 454. a rotor slot; 46. a first bearing; 47. a second bearing; 48. a third bearing; 49. a sensor.

Detailed Description

The following description of the embodiments of the present invention is provided for illustrative purposes, and other advantages and effects of the present invention will be readily apparent to those skilled in the art from the disclosure herein. The present invention can also be implemented or applied through other different specific embodiments, and various details in the present specification can be modified or changed based on different viewpoints and applications without departing from the spirit of the present invention. It is to be noted that the features in the following embodiments and examples may be combined with each other without conflict. It is also to be understood that the terminology used in the examples of the present invention is for the purpose of describing particular embodiments only, and is not intended to limit the scope of the present invention. Test methods in which specific conditions are not specified in the following examples are generally carried out under conventional conditions or under conditions recommended by the respective manufacturers.

When numerical ranges are given in the examples, it is understood that both endpoints of each of the numerical ranges and any number between the endpoints are optional unless the utility model discloses otherwise. Unless defined otherwise, all technical and scientific terms used herein have the same meaning as commonly understood by one of ordinary skill in the art to which this invention belongs and are intended to describe the same, and all methods, apparatus and materials similar or equivalent to those described herein may be used in the practice of this invention.

It should be understood that the terms "upper", "lower", "left", "right", "middle" and "one" used herein are used for descriptive purposes only and are not intended to limit the scope of the present invention, and that changes and modifications in the relative relationship may be made without substantial technical changes and modifications.

Please refer to fig. 1 to 13, the utility model provides a birotor motor and aircraft that contains this birotor motor, this birotor motor have first torque output and the second torque output that can independent action simultaneously, and first torque output and second torque output can independent action simultaneously, can drive different subassemblies respectively and act in order to improve the birotor motor of aircraft among the prior art and the unable same drive arrangement driven problem that adopts of displacement mechanism.

Referring to fig. 2 to 3, and fig. 5 and 10, in an embodiment of the dual-rotor motor of the present invention, the dual-rotor motor 40 includes: housing 430, stator support 43, first winding 410, and second winding 420; the stator bracket 43 is rotatably mounted in the housing 430; the first winding 410 comprises a first stator winding 412 and a first rotor winding 411, the second winding 420 comprises a second stator winding 422 and a second rotor winding 421, the stator support 43 is provided with an annular first stator mounting seat 435 and an annular second stator mounting seat 436, and the first stator mounting seat 435 and the second stator mounting seat 436 are coaxially arranged; the first stator winding 412 is mounted on the first stator mounting seat 435, the second stator winding 422 is fixedly mounted on the second stator mounting seat 436, and the first stator winding 412 is coaxially arranged on the outer ring of the second stator winding 422; the first rotor winding 411 is coaxially and fixedly installed on the housing 430 at the outer ring of the first stator winding 412, and the first torque output end 413 is connected with the housing 430; the second rotor winding 421 is coaxially and rotatably mounted in the inner ring of the second stator winding 422, and the second torque output end 423 is connected to the second rotor winding 421. In an embodiment of the dual-rotor motor of the present invention, for reducing weight and increasing heat dissipation, the inner ring and the outer ring of the stator support 43 are fixedly connected by a plurality of connecting ribs 434. It should be noted that, the utility model discloses in the wire winding mode of first stator winding, first rotor winding, second stator winding and second rotor winding, can refer to the conventional wire winding form of current birotor motor, specifically no longer give consideration to.

Referring to fig. 2 and 5, in an embodiment of the dual-rotor motor of the present invention, the housing 430 includes a cylinder 42, a first cover 44 and a second cover 45, the first cover 44 is located on a side of the stator support 43 departing from the second torque output end 423, and is fixedly connected to an end of the cylinder 42; the second cover 45 is located on one side of the stator bracket 43 facing the second torque output end 423 and is fixedly connected with the end of the other side of the cylinder 42; the second cover 45 is provided with a rotor clamping groove 454, and the rotor clamping groove 454 can be clamped into the first rotor winding 411, so that a stable matching state with the first rotor winding 411 is maintained. Second bearing 47 is installed to the one side that deviates from displacement mechanism 30 of stator support 43, is provided with second bearing installation cavity 441 on the first lid 44, and the outer lane of second bearing 47 is fixed in second bearing installation cavity 441, thereby makes stator support 43 rotates through second bearing 47 and installs on first lid 44, is provided with third bearing installation cavity 433 on stator support 43, and third bearing 48 is installed to the output shaft one end of second rotor winding 421, and the outer lane fixed mounting of third bearing 48 is in third bearing installation cavity 433, so that second rotor winding 421 rotates through third bearing 48 and installs on stator support 43, and the one side that second rotor winding 421 output shaft deviates from third bearing 48 rotates through first bearing 46 and installs on first lid 44. First bearing 46 is installed on the output shaft of second rotor winding 421, first bearing installation cavity 453 is provided on second lid 45, and installation of first bearing 46 is in first bearing installation cavity 453 to make second rotor winding 421 have more stable operating condition. The first cover 44 and/or the second cover 45 are provided with an airflow generating structure that can generate airflow to cool the dual-rotor motor 40.

It should be noted that, the housing 430 in the present invention may also only have the first cover 44 or the second cover 45, for example, in another embodiment of the present invention, one end of the cylinder 42 facing the second torque output end 423 is closed and has a through hole 431 for the second torque output end 423 to penetrate out, one end of the cylinder 42 facing away from the second torque output end 423 has an opening, the opening is installed with the first cover 44 capable of being detached and fixedly connected, and the first cover 44 is provided with the airflow generating structure (not shown). The utility model discloses in another embodiment, one side that the stator support deviates from second moment of torsion output 423 is provided with the connecting portion 437 that is used for being connected with the fuselage, and the one end that deviates from second moment of torsion output 423 of barrel 42 is sealed and has the through-hole that supplies stator support 43 to expose, and the one end of orientation second moment of torsion output 423 of barrel 42 has the opening, installs the second lid 45 that can dismantle fixed connection on the opening, is provided with on the second lid 45 the air current takes place the structure.

In an embodiment of the present invention, the cooling channel is disposed inside the casing 430 of the dual-rotor motor 40, and the specific configuration of the cooling channel is not limited, as long as the cooling air generated by the air flow generating structure can pass through the first winding 410 and the second winding 420 for cooling. In order to obtain a better cooling effect, in an embodiment of the present invention, the cooling channel includes a plurality of through holes 431 disposed on the stator bracket 43 and penetrating along the axial direction, and the positions of the first cover 44 corresponding to the plurality of through holes 431 are provided with ventilation holes 442. The cooling airflow generated by the airflow generation structure passes through the plurality of through holes 431, can directly cool the stator support 43, and further cools the first stator winding 412 and the second stator winding 422 through the stator support 43. The arrangement of the plurality of through holes 431 may not be limited, and may be uniformly or non-uniformly distributed on the stator frame 43, for example. In an embodiment of the dual-rotor motor of the present invention, the through holes 431 are uniformly distributed on the stator support 43 between the first stator winding 412 and the second stator winding 422 along the circumferential direction.

Referring to fig. 11 to 13, in an embodiment of the dual-rotor motor of the present invention, the airflow generating structure includes a plurality of air inlets 451 disposed on a side wall of the first cover 44 or the second cover 45, and a plurality of fan blades 452 correspondingly disposed on a side of the first cover 44 or the second cover 45 close to the stator bracket 43; the fan blades 452 are uniformly distributed on the first cover 44 or the second cover 45 along the circumferential direction. When the first cover 44 or the second cover 45 rotates, the air flow enters from the air inlet 451, is guided by the fan blade 452 to flow out from the first cover 44 or the second cover 45 toward the center side, and flows out toward the stator bracket 43 along the axial direction, then enters the cooling channel, and is discharged to the outside of the housing 430 through the opening of the cooling channel on the other side. It should be noted that, in the present invention, the corresponding airflow generating structures may be provided on the first cover 44 and the second cover 45 at the same time, as long as the airflow generated by the two is consistent and not conflicted. Of course, different cooling channels may be provided in the stator frame 43, so that the air flow generated by the air flow generating structure on the first cover 44 and the air flow generated by the air flow generating structure on the second cover 45 can pass through different cooling channels independently.

Referring to fig. 9 and 10, in order to obtain better heat dissipation efficiency, in an embodiment of the dual-rotor motor of the present invention, the dual-rotor motor 40 further includes a fin group 432 disposed in at least one of the through holes 431. Each of the fin groups 432 includes a plurality of parallel fins, and a gap for cooling airflow to pass through is formed between adjacent fins, so that the heat dissipation efficiency of the first winding 410 and the second winding 420 can be greatly improved by the fin groups 432.

Referring to fig. 5, in an embodiment of the dual-rotor motor of the present invention, the dual-rotor motor further includes a sensor 49 for feeding back the rotation speed or the rotation displacement of the first rotor winding 411 and/or the second rotor winding 421, and the sensor 49 is connected to the control system of the dual-rotor motor or the rotor device in a wired or wireless communication manner. The type of the sensor 49 is not limited as long as the sensor 49 can accurately feed back the rotation speed or the rotation displacement of the first rotor winding 411 and/or the second rotor winding 421, and may be, for example, a hall sensor 49 commonly used in an existing aviation motor, in this embodiment, the hall sensor 49 is installed on the stator bracket 43 and is used to detect the rotation angle displacement of the second rotor winding 421 so as to feed back the rotation angle displacement to a corresponding control system, so as to control the rotation angle of the blade 10.

The utility model also provides an aircraft, which comprises a fuselage, a propeller and the double-rotor motor; wherein, the pedestal fixed mounting of birotor motor 40 can drive the screw rotatory on the fuselage of aircraft, also can drive the paddle rotation in the screw and carry out the displacement, the birotor motor does the aircraft provides the power of navigation. Wherein the double-rotor motor 40 includes: housing 430, stator support 43, first winding 410, and second winding 420; the stator bracket 43 is rotatably mounted in the housing 430 and connected to the body; the first winding 410 comprises a first stator winding 412 and a first rotor winding 411, the second winding 420 comprises a second stator winding 422 and a second rotor winding 421, the stator support 43 is provided with an annular first stator mounting seat 435 and an annular second stator mounting seat 436, and the first stator mounting seat 435 and the second stator mounting seat 436 are coaxially arranged; the first stator winding 412 is mounted on the first stator mounting seat 435, the second stator winding 422 is fixedly mounted on the second stator mounting seat 436, and the first stator winding 412 is coaxially arranged on the outer ring of the second stator winding 422; the first rotor winding 411 is coaxially and fixedly installed on the housing 430 at the outer ring of the first stator winding 412, and the first torque output end 413 is connected with the housing 430; the second rotor winding 421 is coaxially and rotatably mounted in the inner ring of the second stator winding 422, and the second torque output end 423 is connected to the second rotor winding 421.

The propeller includes: a blade mounting bracket 20, a pitch change mechanism 30, a dual-rotor motor 40 and at least one blade 10; the root of each blade 10 is rotatably mounted on the blade mounting bracket 20 and extends out along the radial direction of the blade mounting bracket 20, and each blade 10 can rotate around its own rotating shaft; the pitch-variable mechanism 30 is installed in the blade mount 20 and drives at least one blade 10 to rotate so as to rotate around its rotation axis by a set angle relative to the blade mount 20; the rotating shafts of the first torque output end 413 and the second torque output end 423 are on the same straight line and both extend out towards the blade mounting rack 20, wherein the first torque output end 413 is fixedly connected with the blade mounting rack 20 so as to drive the blade mounting rack 20 to rotate when rotating, so that the blade mounting rack 20 drives the blade 10 to revolve around the central line of the blade mounting rack 20 to generate sailing power; the second torque output end 423 is circumferentially and fixedly connected with the input end of the pitch varying mechanism 30 to drive the pitch varying mechanism 30 to act, so as to drive the corresponding blade 10 to rotate around the rotation shaft thereof by a set angle, thereby adjusting the pitch of the blade 10.

Referring to fig. 2 to 3, the structure and shape of the blade mount 20 can be selected according to the needs, preferably, a rotation-type structure with low resistance can be selected, and in this embodiment, the blade mount 20 is a rotation-type structure similar to a rocket head. The number of the blades 10 may be one, two or more, in this embodiment, the number of the blades 10 is three, three blades 10 are uniformly arranged along the circumference of the blade mounting rack 20, the root of each blade 10 is rotatably mounted on the blade mounting rack 20 and extends out along the radial direction of the blade mounting rack 20, and each blade 10 can rotate around its own rotating shaft; the pitch-variable mechanism 30 is installed in the blade installation frame 20 and drives at least one blade 10 to rotate, so that the corresponding blade rotates around a rotating shaft of the corresponding blade relative to the blade installation frame 20 by a set angle; the number of the blades 10 driven by the pitch varying mechanism 30 can be set according to requirements, for example, only part of the blades 10 can be driven to rotate for pitch variation, or all the blades 10 can be driven simultaneously to realize pitch variation synchronously; the dual rotor motor 40 has independently acting first and second torque outputs 413, 423; the first torque output end 413 and the second torque output end 423 both extend towards the blade mounting bracket 20 and have rotating shafts on the same straight line, wherein the first torque output end 413 is fixedly connected with the blade mounting bracket 20 so as to drive the blade mounting bracket 20 to rotate when rotating, so that the blade mounting bracket 20 drives the blade 10 to revolve and generate sailing power; the second torque output end 423 is connected to the input end of the pitch varying mechanism 30 to drive the pitch varying mechanism 30 to act, so as to drive the corresponding blade 10 to rotate around its own rotation axis by a set angle, thereby adjusting the pitch of the blade 10.

Referring to fig. 3 to 4 and 7 to 8, in an embodiment of the propeller of the aircraft of the present invention, the pitch change mechanism 30 includes a planetary gear set 310 and a bevel gear set 320; a planetary gear set 310 is mounted within the blade mount 20, the planetary gear set 310 comprising a sun gear 311, at least one planet gear 312 and a ring gear 313, the ring gear 313 being an annulus gear; the second torque output end 423 is connected with the sun gear 311 and drives the sun gear 311 to rotate; the gear ring 313 is coaxially arranged outside the sun gear 311, the number of the planet gears 312 can be set according to requirements, and preferably, in this embodiment, there are three planet gears 312, three planet gears 312 are rotatably installed on the blade mounting bracket 20, and are uniformly arranged between the sun gear 311 and the gear ring 313 along the circumferential direction of the sun gear 311, and all three planet gears 312 are engaged with the sun gear 311 and the gear ring 313; the sun gear 311 is driven by the second torque output end 423 to drive the three planet gears 312 to rotate, and the three planet gears 312 drive the ring gear 313 to rotate. The bevel gear set 320 comprises a first bevel gear 321 and second bevel gears 322 which are equal to the number of the blades 10 to be pitch-changed; the gear ring 313 drives the first bevel gear 321 to coaxially rotate; the second bevel gears 322 are installed at the root of the corresponding blade 10 in a stopping manner along the circumferential direction and are driven by the first bevel gears 321 to rotate. The utility model provides a displacement actuating mechanism, through planetary gear set 310 and bevel gear set 320's combination, not only improved the reduction ratio but also can make displacement actuating mechanism keep comparatively compact overall arrangement and higher stability when overcoming great dynamic displacement resistance.

Referring to fig. 2, 4 and 6, in an embodiment of the propeller of the aircraft of the present invention, the blade mounting bracket 20 includes a gear box 210 and a housing 220 connected to the gear box 210, a first cylindrical groove 211 penetrating in a radial direction is disposed on a mating surface of the gear box 210 and the housing 220, a second cylindrical groove 221 penetrating in the radial direction is disposed on a mating surface of the housing 220 and the gear box 210, positions of the first cylindrical groove 211 and the second cylindrical groove 221 correspond, and a rotary support member 110 is mounted at a root of the blade 10; the first cylindrical groove 211 and the second cylindrical groove 221 clamp and fix the outer ring of the rotary support 110 from both sides of the blade 10, so that the corresponding blade 10 is rotatably mounted on the blade mounting bracket 20. The gear box 210 is provided with an installation through hole 212 for the second torque output end 423 to extend into, and the second torque output end 423 extends into the installation through hole 212 and is in key connection with the sun gear 311 so as to drive the sun gear 311 to rotate. A second torque output end support hole (not shown) is provided at a side of the first bevel gear 321 toward the planetary gear set 310; a first bevel gear mounting shaft 323 is arranged on one side of the first bevel gear 321, which is far away from the planetary gear 312; a fifth bearing 324 is mounted on the first bevel gear mounting shaft 323, and a first bevel gear mounting hole 222 for mounting the fifth bearing 324 is formed in the housing 220; the first bevel gear mounting shaft 323 is rotatably mounted in the first bevel gear mounting hole 222 through a fifth bearing 324; the second torque output end 423 is provided with a fourth bearing 41, and an outer ring of the fourth bearing 41 is fixedly arranged in the second torque output end supporting hole. By means of the arrangement mode, on one hand, a more compact layout can be obtained, on the other hand, the requirement for relative rotation of the first bevel gear 321 and the second torque output end 423 can be met through the supporting effect of the first bevel gear 321 and the second torque output end 423, and the supporting effect of the first bevel gear mounting shaft 323 and the first bevel gear mounting hole 222 on the two sides of the bevel gear, and the stability of the first bevel gear 321, the second torque output end 423 and the sun gear 311 are improved.

Referring to fig. 4, in an embodiment of the pitch-variable driving mechanism of the aircraft of the present invention, the gear ring 313 and the first bevel gear 321 are of an integral structure, and the gear ring 313 and the first bevel gear 321 are respectively disposed on two sides of the same gear along the axis extending direction and are integrally processed, so that the coaxiality of the gear ring 313 and the first bevel gear 321 can be effectively ensured. It will be appreciated by those skilled in the art that the ring gear 313 and the first bevel gear 321 may be separately provided and then detachably and coaxially fixed.

To sum up, the utility model discloses the birotor motor has first torque output and the second torque output that can independent action simultaneously, and first torque output and second torque output can independent action simultaneously, can drive different subassemblies respectively and move, and the utility model discloses the birotor motor is installed the stator of two windings on same stator support, structurally optimizes more on the one hand, and on the other hand has reduced the volume of whole motor, has reduced the weight of motor. The utility model discloses the aircraft that contains this birotor motor adopts the utility model discloses the birotor motor can drive the screw respectively through first moment of torsion output, the second moment of torsion output of birotor motor and rotate and the displacement, has reduced the volume of aircraft, has reduced the whole weight of aircraft. Therefore, the utility model discloses thereby effectively overcome some practical problems among the prior art and had very high use value and use meaning. The above embodiments are merely illustrative of the principles and effects of the present invention, and are not to be construed as limiting the invention. Modifications and variations can be made to the above-described embodiments by those skilled in the art without departing from the spirit and scope of the present invention. Accordingly, it is intended that all equivalent modifications or changes which may be made by those skilled in the art without departing from the spirit and technical spirit of the present invention be covered by the claims of the present invention.

Claims

1. A dual rotor motor, comprising:

a housing;

the stator bracket is rotatably arranged in the shell;

the first winding comprises a first stator winding and a first rotor winding, and the first stator winding is fixedly arranged on the stator bracket; the first rotor winding is fixedly arranged on the shell outside the first stator winding and is coaxially arranged with the first stator winding, and a first torque output end is arranged on the first rotor winding;

the second winding comprises a second stator winding and a second rotor winding, and the second stator winding is fixedly arranged on the stator bracket; the second rotor winding is rotatably arranged on the stator support and/or the shell and is coaxial with the second stator winding, and a second torque output end is arranged on the second rotor winding.

2. The dual-rotor motor as claimed in claim 1, wherein the housing includes a first cover and/or a second cover, the first cover being disposed on a side of the stator bracket adjacent to the second torque output end and fixedly connected to the housing; the second cover body is arranged on one side, deviating from the second torque output end, of the stator support and is fixedly connected with the shell.

3. The dual-rotor motor as claimed in claim 2, wherein an air cooling structure is disposed on the first cover and/or the second cover for cooling the dual-rotor motor.

4. The dual-rotor motor as claimed in claim 2, wherein a cooling channel is formed inside the housing, and the first cover and/or the second cover are provided with an airflow generating device for generating a cooling airflow during rotation, the cooling airflow entering from one end of the cooling channel and being discharged from the other end of the cooling channel.

5. The dual-rotor motor as claimed in claim 4, wherein the cooling passage includes a plurality of through holes provided on a stator frame between the first stator winding and the second stator winding;

the through holes are uniformly distributed along the circumferential direction of the stator support.

6. The dual rotor motor as claimed in claim 5, wherein a plurality of heat radiating fins are provided on said stator frame.

7. The pair-rotor motor according to claim 6, wherein a plurality of the heat radiating fins are provided in the through-hole, and a gap through which a cooling airflow passes is provided between adjacent two of the heat radiating fins.

8. The dual-rotor motor as claimed in claim 4, wherein the airflow generating device includes a plurality of air inlets disposed on a side wall of the first cover or the second cover and a plurality of fan blades correspondingly disposed on a side of the first cover or the second cover close to the stator frame; the fan blades are uniformly distributed on the first cover body or the second cover body along the circumferential direction.

9. The dual-rotor motor of claim 1, further comprising a sensor for feeding back a rotational speed or a rotational displacement of said first rotor winding and/or said second rotor winding, said sensor being in wired or wireless communication with a control system of said dual-rotor motor.

10. An aircraft comprising a fuselage and a propeller mounted on the fuselage, and a blade pitch mechanism for driving the propeller blades to pitch, characterized by further comprising a dual-rotor motor as claimed in any one of claims 1 to 9; the stator support of the double-rotor motor is fixed on a body of the aircraft, and a first torque output end of the double-rotor motor is connected with the mounting frame of the propeller so as to drive the propeller to rotate; and a second torque output end of the double-rotor motor is connected with an input end of the blade pitch-changing mechanism so as to drive the blades of the propeller to change the pitch.