CN214799249U - Coaxial reverse axial magnetic motor for electric aircraft - Google Patents
Coaxial reverse axial magnetic motor for electric aircraft Download PDFInfo
- Publication number
- CN214799249U CN214799249U CN202120779343.8U CN202120779343U CN214799249U CN 214799249 U CN214799249 U CN 214799249U CN 202120779343 U CN202120779343 U CN 202120779343U CN 214799249 U CN214799249 U CN 214799249U
- Authority
- CN
- China
- Prior art keywords
- rotor
- reverse
- iron core
- stator support
- motor
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Active
Links
Images
Landscapes
- Connection Of Motors, Electrical Generators, Mechanical Devices, And The Like (AREA)
Abstract
The utility model discloses an electric aircraft is with coaxial reversal axial magnetic flux electric machine, including reverse rotation rotor mechanism, forward rotation rotor mechanism and stator mechanism. The reverse rotation rotor mechanism and the forward rotation rotor mechanism of the utility model are both arranged on the stator mechanism and are of a coaxial structure, so that the requirements of reverse output and torque offset of the motor can be realized, an additional torque offset device is not required to be added on the body of the electric airplane, the flying stability of the airplane is greatly improved, the flying control of the airplane structure is simplified, the electric quantity of the battery carried by the electric airplane is saved, and the comprehensive performance of the airplane is further improved; the utility model discloses an axial magnetic flux theory of operation, greatly increased the power density of motor, moment of torsion weight ratio, reduce the motor loss, the utility model discloses coaxial reversal axial magnetic flux motor can be applied to on the large-scale electronic unmanned aerial vehicle.
Description
Technical Field
The utility model relates to a brushless DC motor technical field specifically is an electric aircraft is with coaxial reversal axial magnetic flux motor.
Background
At present, common electric airplanes, such as electric unmanned helicopters and electric autorotation gyroplanes, are basically powered by a single-shaft motor and a single propeller, and have the defect that the rotation of the single-shaft motor and the single propeller can generate large reverse torque to directly act on airplane bodies, thereby seriously affecting the flight stability of the airplanes. In order to offset the large reverse torque generated by the rotation of the single-shaft motor and the single propeller, an additional device is often required to be added to the airplane, for example, a tail rotor is usually arranged at the tail of the helicopter in order to offset the reverse torque, so that the cost and the difficulty of airplane design, production and flight control are greatly increased, and the electric quantity of a battery carried on the airplane is additionally wasted.
In addition, the existing coaxial reversing motor for the electric unmanned aerial vehicle is mostly a single-shaft radial flux motor, a gear transmission structure is adopted to realize reversing operation, the structure is simple, the power density is low, each performance index is poor, the coaxial reversing motor is mostly used for a model airplane, and the use requirement of a large unmanned/manned electric aircraft cannot be met.
SUMMERY OF THE UTILITY MODEL
The to-be-solved technical problem of the utility model is to provide an electric aircraft is with coaxial reversal axial flux motor, solved the problem that uses the electronic flight of unipolar motor + single oar in the past needs to increase extra moment of torsion on the organism and offset the device, and satisfied large-scale electronic unmanned/manned aircraft and possessed the requirement of characteristics such as power density height, moment of torsion weight ratio, motor loss are little to its use motor needs.
The technical scheme of the utility model is that:
a coaxial reverse rotation axial magnetic flux motor for an electric airplane comprises a reverse rotation rotor mechanism, a forward rotation rotor mechanism and a stator mechanism;
the reverse rotation rotor mechanism comprises a motor shell, a reverse rotor upper cover fixed in the motor shell and reverse rotor magnetic steel fixed on the lower end surface of the reverse rotor upper cover and the inner bottom surface of the motor shell, and the reverse rotor upper cover divides the interior of the motor shell into a positive chamber and a negative chamber from top to bottom;
the forward rotating rotor mechanism comprises a forward rotor shell, forward rotor magnetic steel fixed on the inner top surface and the inner bottom surface of the forward rotor shell, and a forward rotating shaft with a forward output end penetrating out of the forward rotor shell, wherein the forward rotor shell is arranged in a forward cavity of the motor shell and is not in contact with the motor shell, the forward rotating shaft is fixedly connected with the forward rotor shell, and the forward output end of the forward rotating shaft extends out of the motor shell;
stator mechanism including stator support and suit and be fixed in the positive direction winding iron core and the reverse winding iron core on the stator support, the top and the bottom of stator support be connected with motor housing through the bearing that corresponds respectively for realize that reverse rotation rotor mechanism rotates for stator support, positive direction winding iron core be located the inside of positive direction rotor housing, positive direction winding iron core respectively with positive direction rotor housing, positive direction rotor magnet steel all contactless, positive direction rotation axis penetrate stator support in and positive direction rotation axis and stator support are coaxial, be connected with the bearing between positive direction rotation axis and the stator support for realize the rotation of positive direction rotation rotor mechanism for stator support, reverse winding iron core be located the negative cavity, reverse winding iron core respectively with motor housing, reverse rotor magnet steel all contactless.
The lower end face of the upper cover of the reverse rotor, the inner bottom face of the motor shell, the inner top face and the inner bottom face of the forward rotor shell are respectively fixed with a magnetic conduction plate, and the magnetic steel of the reverse rotor and the magnetic steel of the forward rotor are fixed on the corresponding magnetic conduction plates.
The motor is characterized in that a rotating shaft mounting hole which is through up and down is formed in the stator support, a forward rotating shaft penetrates into the rotating shaft mounting hole from top to bottom, bearings are connected in the rotating shaft mounting hole of the stator support and adjacent to the bottom end and the top end, the forward rotating shaft is connected and positioned with the stator support through the two bearings, and a forward output end of the forward rotating shaft extends to the outside of the motor shell.
The bottom of stator support stretch out to motor housing's outside, stator support's bottom fixedly connected with motor mount.
And a forward driving piece fixing disc is fixedly connected to the forward output end of the forward rotating shaft.
And the bottom end of the stator support is provided with a three-phase outgoing line connector led out of the motor shell, and the winding of the forward winding iron core and the winding of the reverse winding iron core are connected with the three-phase outgoing line connector.
The stator support on be provided with the cooling pipeline, the bottom of stator support is provided with and connects in the water inlet pipe joint and the outlet pipe joint on the cooling pipeline both ends respectively, water inlet pipe joint and outlet pipe joint all extend to the outside of motor housing.
The electronic shell and the forward rotor shell are both composed of an upper cover, a lower cover and a housing connected between the upper cover and the lower cover.
The forward winding iron core and the reverse winding iron core respectively comprise an iron core winding fixing frame and an iron core winding which are integrally molded by encapsulation, the iron core winding iron is fixed on the iron core winding fixing frame, and the iron core winding fixing frame is fixed on the stator support.
The utility model has the advantages that:
the reverse rotation rotor mechanism and the forward rotation rotor mechanism of the utility model are both arranged on the stator mechanism and are of a coaxial structure, so that the requirements of reverse output and torque offset of the motor can be realized, an additional torque offset device is not required to be added on the body of the electric airplane, the flying stability of the airplane is greatly improved, the flying control of the airplane structure is simplified, the electric quantity of the battery carried by the electric airplane is saved, and the comprehensive performance of the airplane is further improved; the utility model discloses an axial magnetic flux theory of operation, greatly increased the power density of motor, moment of torsion weight ratio, reduce the motor loss, the utility model discloses coaxial reversal axial magnetic flux motor can be applied to on the large-scale electronic unmanned aerial vehicle.
Drawings
Fig. 1 is a front view of the present invention.
Fig. 2 is a cross-sectional view of the present invention.
Fig. 3 is a sectional view of the counter-rotating rotor mechanism of the present invention.
Fig. 4 is a cross-sectional view of the forward rotary rotor mechanism of the present invention.
Fig. 5 is a schematic structural diagram of the stator mechanism of the present invention.
Detailed Description
The technical solutions in the embodiments of the present invention will be described clearly and completely with reference to the accompanying drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only some embodiments of the present invention, not all embodiments. Based on the embodiments in the present invention, all other embodiments obtained by a person skilled in the art without creative work belong to the protection scope of the present invention.
Referring to fig. 1 to 5, a coaxial reverse rotation axial flux motor for an electric aircraft comprises a reverse rotation rotor mechanism, a forward rotation rotor mechanism and a stator mechanism;
the reverse rotation rotor mechanism comprises a motor shell 1, a reverse rotor upper cover 2 fixed inside the motor shell 1 and reverse rotor magnetic steel 3 fixed on the lower end surface of the reverse rotor upper cover 2 and the inner bottom surface of the motor shell 1, the reverse rotor upper cover 2 divides the inside of the motor shell 1 into a positive chamber and a negative chamber from top to bottom, and the top end of the motor shell 1 is fixedly connected with a reverse propeller or a reverse rotation rotor;
the forward rotating rotor mechanism comprises a forward rotor shell 4, forward rotor magnetic steel 5 fixed on the inner top surface and the inner bottom surface of the forward rotor shell 4 and a forward rotating shaft 6 with a forward output end penetrating out of the forward rotor shell 4, the forward rotor shell 4 is arranged in a forward cavity of the motor shell 1 and is not contacted with the motor shell 1, the forward rotating shaft 6 is fixedly connected with the forward rotor shell 4, the forward output end of the forward rotating shaft 6 extends upwards to the outside of the motor shell 1, a forward driving piece fixing disc 7 is fixedly connected to the forward output end of the forward rotating shaft 6, and the forward driving piece fixing disc 7 is used for fixedly connecting a forward propeller or a forward rotating rotor;
the stator mechanism comprises a stator support 8, a forward winding iron core 9 and a reverse winding iron core 10 which are sleeved and fixed on the stator support 8, the bottom end of the stator support 8 extends out of a motor shell 1, the top and the bottom of the stator support 8 are respectively connected with the motor shell 1 through corresponding bearings 11 and are used for realizing the rotation of the reverse rotating rotor mechanism relative to the stator support 8, the bottom end of the stator support 8 is fixedly connected with a motor fixing frame 12, the bottom end of the stator support 8 is provided with a three-phase outgoing line connector 13 led out of the motor shell 1, the winding of the forward winding iron core 9 and the winding of the reverse winding iron core 10 are both connected with the three-phase outgoing line connector 13, the stator support 8 is provided with a cooling pipeline, the bottom end of the stator support 8 is provided with a water inlet pipe connector 14 and a water outlet pipe connector 15 which are respectively connected with two ends of the cooling pipeline, the forward winding iron core 9 is positioned inside the forward rotor shell 4, forward winding iron core 4 respectively with forward rotor shell 4, forward rotor magnet steel 5 all contactless, the rotation axis mounting hole that link up from top to bottom has been seted up on stator support 8, forward rotation axis 6 is from last down penetrating in the rotation axis mounting hole and forward rotation axis 6 and stator support 8 are coaxial, just neighbouring bottom and top all are connected with bearing 11 in stator support 8's the rotation axis mounting hole, forward rotation axis 6 is connected the location through two bearings and stator support 8, a rotation for realizing forward rotation rotor mechanism for stator support, reverse winding iron core 10 is located motor shell 1's negative cavity, reverse winding iron core 10 respectively with motor shell 1, reverse rotor magnet steel 3 all contactless.
Magnetic conductive plates 16 are fixed on the lower end face of the reverse rotor upper cover 2, the inner bottom face of the motor shell 1, the inner top face and the inner bottom face of the forward rotor shell 4, the reverse rotor magnetic steel 3 and the forward rotor magnetic steel 5 are fixed on the corresponding magnetic conductive plates 16, magnetic field conduction between the reverse rotor magnetic steels 3 or between the forward rotor magnetic steels 5 on each positioning face is realized, and the influence of the magnetic steel field on the outside is simultaneously cut off; the electronic shell 1 and the forward rotor shell 4 are both composed of an upper cover, a lower cover and a housing connected between the upper cover and the lower cover, so that the assembly and the connection of the reverse rotating rotor mechanism, the forward rotating rotor mechanism and the stator mechanism are facilitated; the forward winding iron core 9 and the reverse winding iron core 10 both comprise an iron core winding fixing frame and an iron core winding which are integrally molded by encapsulation, the iron core winding iron is fixed on the iron core winding fixing frame, and the iron core winding fixing frame is fixed on the stator support 8.
When the motor is used, the forward winding iron core 9 and the reverse winding iron core 10 are electrified to respectively drive the reverse rotating rotor mechanism and the forward rotating rotor mechanism to rotate coaxially and reversely around the stator support 8.
Although embodiments of the present invention have been shown and described, it will be appreciated by those skilled in the art that changes, modifications, substitutions and alterations can be made in these embodiments without departing from the principles and spirit of the invention, the scope of which is defined in the appended claims and their equivalents.
Claims (9)
1. The utility model provides an electric aircraft is with coaxial reversal axial magnetic flux machine which characterized in that: comprises a reverse rotating rotor mechanism, a forward rotating rotor mechanism and a stator mechanism;
the reverse rotation rotor mechanism comprises a motor shell, a reverse rotor upper cover fixed in the motor shell and reverse rotor magnetic steel fixed on the lower end surface of the reverse rotor upper cover and the inner bottom surface of the motor shell, and the reverse rotor upper cover divides the interior of the motor shell into a positive chamber and a negative chamber from top to bottom;
the forward rotating rotor mechanism comprises a forward rotor shell, forward rotor magnetic steel fixed on the inner top surface and the inner bottom surface of the forward rotor shell, and a forward rotating shaft with a forward output end penetrating out of the forward rotor shell, wherein the forward rotor shell is arranged in a forward cavity of the motor shell and is not in contact with the motor shell, the forward rotating shaft is fixedly connected with the forward rotor shell, and the forward output end of the forward rotating shaft extends out of the motor shell;
stator mechanism including stator support and suit and be fixed in the positive direction winding iron core and the reverse winding iron core on the stator support, the top and the bottom of stator support be connected with motor housing through the bearing that corresponds respectively for realize that reverse rotation rotor mechanism rotates for stator support, positive direction winding iron core be located the inside of positive direction rotor housing, positive direction winding iron core respectively with positive direction rotor housing, positive direction rotor magnet steel all contactless, positive direction rotation axis penetrate stator support in and positive direction rotation axis and stator support are coaxial, be connected with the bearing between positive direction rotation axis and the stator support for realize the rotation of positive direction rotation rotor mechanism for stator support, reverse winding iron core be located the negative cavity, reverse winding iron core respectively with motor housing, reverse rotor magnet steel all contactless.
2. A coaxial contra-rotating axial flux machine for an electric aircraft as claimed in claim 1, wherein: the lower end face of the upper cover of the reverse rotor, the inner bottom face of the motor shell, the inner top face and the inner bottom face of the forward rotor shell are respectively fixed with a magnetic conduction plate, and the magnetic steel of the reverse rotor and the magnetic steel of the forward rotor are fixed on the corresponding magnetic conduction plates.
3. A coaxial contra-rotating axial flux machine for an electric aircraft as claimed in claim 1, wherein: the motor is characterized in that a rotating shaft mounting hole which is through up and down is formed in the stator support, a forward rotating shaft penetrates into the rotating shaft mounting hole from top to bottom, bearings are connected in the rotating shaft mounting hole of the stator support and adjacent to the bottom end and the top end, the forward rotating shaft is connected and positioned with the stator support through the two bearings, and a forward output end of the forward rotating shaft extends to the outside of the motor shell.
4. A coaxial contra-rotating axial flux machine for an electric aircraft as claimed in claim 1, wherein: the bottom of stator support stretch out to motor housing's outside, stator support's bottom fixedly connected with motor mount.
5. A coaxial contra-rotating axial flux machine for an electric aircraft as claimed in claim 1, wherein: and a forward driving piece fixing disc is fixedly connected to the forward output end of the forward rotating shaft.
6. A coaxial contra-rotating axial flux machine for an electric aircraft as claimed in claim 1, wherein: and the bottom end of the stator support is provided with a three-phase outgoing line connector led out of the motor shell, and the winding of the forward winding iron core and the winding of the reverse winding iron core are connected with the three-phase outgoing line connector.
7. A coaxial contra-rotating axial flux machine for an electric aircraft as claimed in claim 1, wherein: the stator support on be provided with the cooling pipeline, the bottom of stator support is provided with and connects in the water inlet pipe joint and the outlet pipe joint on the cooling pipeline both ends respectively, water inlet pipe joint and outlet pipe joint all extend to the outside of motor housing.
8. A coaxial contra-rotating axial flux machine for an electric aircraft as claimed in claim 1, wherein: the motor shell and the positive rotor shell are both composed of an upper cover, a lower cover and a housing connected between the upper cover and the lower cover.
9. A coaxial contra-rotating axial flux machine for an electric aircraft as claimed in claim 1, wherein: the forward winding iron core and the reverse winding iron core respectively comprise an iron core winding fixing frame and an iron core winding which are integrally molded by encapsulation, the iron core winding iron is fixed on the iron core winding fixing frame, and the iron core winding fixing frame is fixed on the stator support.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202120779343.8U CN214799249U (en) | 2021-04-15 | 2021-04-15 | Coaxial reverse axial magnetic motor for electric aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202120779343.8U CN214799249U (en) | 2021-04-15 | 2021-04-15 | Coaxial reverse axial magnetic motor for electric aircraft |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN214799249U true CN214799249U (en) | 2021-11-19 |
Family
ID=78687239
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202120779343.8U Active CN214799249U (en) | 2021-04-15 | 2021-04-15 | Coaxial reverse axial magnetic motor for electric aircraft |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN214799249U (en) |
-
2021
- 2021-04-15 CN CN202120779343.8U patent/CN214799249U/en active Active
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| US11383850B2 (en) | Integrated electric propulsion assembly | |
| US11679891B2 (en) | Integrated electric propulsion assembly | |
| CN205060011U (en) | Oil moves four rotor unmanned aerial vehicle rotor - control system of displacement | |
| CN210592390U (en) | Permanent magnet motor contrarotating pod propeller | |
| CN106672186B (en) | A kind of full open model binary is to turning underwater propulsion system | |
| CN105270619A (en) | Oil-drive variable-pitch quad-rotor unmanned aerial vehicle | |
| CN112406434B (en) | Electric water-air dual-purpose propeller | |
| EP4070434A1 (en) | An integrated electric propulsion assembly | |
| CN101820209A (en) | Coaxial double-output brushless motor | |
| CN212667652U (en) | Tandem type electric double-rotor helicopter | |
| CN104753271A (en) | Full-rotor hub motor | |
| CN214799249U (en) | Coaxial reverse axial magnetic motor for electric aircraft | |
| CN114726177A (en) | Permanent magnet contra-rotating propulsion motor and aircraft | |
| CN113078787A (en) | Coaxial reverse axial magnetic motor for electric aircraft | |
| CN218229372U (en) | Propeller and water area movable equipment | |
| CN212099307U (en) | Coaxial propeller power system, coaxial double-propeller underwater propeller and aircraft | |
| CN109956028B (en) | Driving system based on coaxial double-rotor aircraft | |
| CN206654193U (en) | A kind of new unmanned vehicle drive device | |
| CN221852181U (en) | Electronically controlled rotor wing, helicopter and unmanned aerial vehicle of coaxial layout brushless motor | |
| CN220054114U (en) | Double-deck screw propeller | |
| CN110667859A (en) | Hybrid power driving system for aircraft and unmanned aerial vehicle aircraft | |
| CN112960094A (en) | Full-rotation propeller with double propellers directly driven by double-layer permanent magnet motor | |
| CN219856776U (en) | Split type driving unit, electric vehicle and aircraft | |
| CN219927951U (en) | Driving structure of two-stage propeller | |
| CN219790503U (en) | Propeller and coaxial double-oar structure thereof |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| GR01 | Patent grant | ||
| GR01 | Patent grant |