CN117277649A - Lightweight aero-motor - Google Patents
Lightweight aero-motor Download PDFInfo
- Publication number
- CN117277649A CN117277649A CN202311550200.XA CN202311550200A CN117277649A CN 117277649 A CN117277649 A CN 117277649A CN 202311550200 A CN202311550200 A CN 202311550200A CN 117277649 A CN117277649 A CN 117277649A
- Authority
- CN
- China
- Prior art keywords
- dovetails
- stator
- motor
- lightweight
- dovetail
- 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.)
- Pending
Links
- 229910000831 Steel Inorganic materials 0.000 claims abstract description 7
- XAGFODPZIPBFFR-UHFFFAOYSA-N aluminium Chemical compound [Al] XAGFODPZIPBFFR-UHFFFAOYSA-N 0.000 claims abstract description 7
- 229910052782 aluminium Inorganic materials 0.000 claims abstract description 7
- 239000010959 steel Substances 0.000 claims abstract description 7
- 229910000976 Electrical steel Inorganic materials 0.000 claims description 4
- 229910000838 Al alloy Inorganic materials 0.000 claims description 3
- 239000000956 alloy Substances 0.000 claims description 3
- 239000004411 aluminium Substances 0.000 claims 1
- 239000000919 ceramic Substances 0.000 description 4
- PMHQVHHXPFUNSP-UHFFFAOYSA-M copper(1+);methylsulfanylmethane;bromide Chemical compound Br[Cu].CSC PMHQVHHXPFUNSP-UHFFFAOYSA-M 0.000 description 2
- 239000000463 material Substances 0.000 description 2
- 239000013585 weight reducing agent Substances 0.000 description 2
- RYGMFSIKBFXOCR-UHFFFAOYSA-N Copper Chemical compound [Cu] RYGMFSIKBFXOCR-UHFFFAOYSA-N 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000001816 cooling Methods 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 230000017525 heat dissipation Effects 0.000 description 1
- 238000004804 winding Methods 0.000 description 1
Classifications
-
- H—ELECTRICITY
- H02—GENERATION; CONVERSION OR DISTRIBUTION OF ELECTRIC POWER
- H02K—DYNAMO-ELECTRIC MACHINES
- H02K1/00—Details of the magnetic circuit
- H02K1/06—Details of the magnetic circuit characterised by the shape, form or construction
- H02K1/22—Rotating parts of the magnetic circuit
- H02K1/27—Rotor cores with permanent magnets
- H02K1/2786—Outer rotors
- H02K1/2787—Outer rotors the magnetisation axis of the magnets being perpendicular to the rotor axis
- H02K1/2789—Outer rotors the magnetisation axis of the magnets being perpendicular to the rotor axis the rotor consisting of two or more circumferentially positioned magnets
- H02K1/2791—Surface mounted magnets; Inset magnets
- H02K1/2792—Surface mounted magnets; Inset magnets with magnets arranged in Halbach arrays
-
- H—ELECTRICITY
- H02—GENERATION; CONVERSION OR DISTRIBUTION OF ELECTRIC POWER
- H02K—DYNAMO-ELECTRIC MACHINES
- H02K1/00—Details of the magnetic circuit
- H02K1/06—Details of the magnetic circuit characterised by the shape, form or construction
- H02K1/12—Stationary parts of the magnetic circuit
- H02K1/14—Stator cores with salient poles
- H02K1/146—Stator cores with salient poles consisting of a generally annular yoke with salient poles
-
- H—ELECTRICITY
- H02—GENERATION; CONVERSION OR DISTRIBUTION OF ELECTRIC POWER
- H02K—DYNAMO-ELECTRIC MACHINES
- H02K11/00—Structural association of dynamo-electric machines with electric components or with devices for shielding, monitoring or protection
- H02K11/20—Structural association of dynamo-electric machines with electric components or with devices for shielding, monitoring or protection for measuring, monitoring, testing, protecting or switching
- H02K11/21—Devices for sensing speed or position, or actuated thereby
- H02K11/215—Magnetic effect devices, e.g. Hall-effect or magneto-resistive elements
-
- H—ELECTRICITY
- H02—GENERATION; CONVERSION OR DISTRIBUTION OF ELECTRIC POWER
- H02K—DYNAMO-ELECTRIC MACHINES
- H02K3/00—Details of windings
- H02K3/04—Windings characterised by the conductor shape, form or construction, e.g. with bar conductors
- H02K3/18—Windings for salient poles
Landscapes
- Engineering & Computer Science (AREA)
- Power Engineering (AREA)
- Microelectronics & Electronic Packaging (AREA)
- Iron Core Of Rotating Electric Machines (AREA)
- Motor Or Generator Cooling System (AREA)
Abstract
The utility model provides a lightweight aero motor, includes outer rotor subassembly and the interior stator subassembly of coaxial setting, interior stator subassembly includes stator support and stator core, and stator core includes a plurality of dovetails tooth and a plurality of dovetailed yoke, and dovetailed tooth and dovetailed yoke mortise and tenon nest each other. The dovetail teeth are provided with coils. The outer rotor component comprises a shell and an end cover, and the inner wall of the shell is provided with a Harbarg magnetic steel display. According to the lightweight aviation motor, the Harbark magnetic steel display structure is adopted, an outer rotor magnetic yoke is completely omitted, the weight of the motor is greatly reduced, and heat generated by eddy currents in permanent magnets is directly led out through strong convection air flow outside an outer rotor shell. The aluminum coil is adopted to further reduce the weight, and the formed flat coil is adopted to improve the slot filling rate of the inner stator. The inner stator is formed by mutually nesting and combining the dovetail teeth and the dovetail yokes, so that the stator teeth can be conveniently provided with flat coils, torque can be radially transmitted, an inner stator core can be circumferentially fixed, and the using amount of the yoke core is reduced.
Description
Technical Field
The invention relates to the technical field of motors, in particular to a lightweight aviation motor.
Background
The maximum weight reduction has important significance for the aviation motor, and with the advent of new electrical materials, some structures in the traditional motor can be replaced or redesigned by using the new electrical materials so as to further reduce the weight of the motor.
Disclosure of Invention
The invention aims to provide a lightweight aero-motor.
In order to achieve the above purpose, the technical scheme of the invention is as follows: the utility model provides a lightweight aero motor, including the outer rotor subassembly and the interior stator subassembly of coaxial setting, interior stator subassembly includes stator support and stator core, stator core includes a plurality of dovetails tooth and a plurality of dovetails yoke, have the coil on the dovetails tooth, the dovetails yoke is two dovetails structure, the dovetails yoke includes first dovetails portion and second dovetails portion, have a plurality of first dovetails on the stator support, the first dovetails portion of dovetails yoke splice in first dovetails portion, constitute the second dovetails portion between the second dovetails portion of two adjacent dovetails, the dovetails tooth splice in the second dovetails portion, adjacent dovetails tooth constitutes the stator groove; the outer rotor assembly comprises a shell and an end cover, and the inner wall of the shell is provided with a Harbarg magnetic steel array.
Furthermore, the stator support and the shell are made of aluminum alloy materials.
Furthermore, the coil is an aluminum coil, and the dovetail teeth and the dovetail yoke are formed by splicing oriented silicon steel sheets.
Further, the coil is a formed flat coil, two heat conducting strips are arranged on the inner side of the formed flat coil and radially arranged on two sides of the dovetail teeth along the stator, and the heat conducting strips are simultaneously attached to the formed flat coil and the dovetail teeth.
Further, one end of the heat conducting strip is flush with the dovetail teeth, and the other end of the heat conducting strip is propped against the stator support.
Further, the heat conducting strip also comprises a Hall sensor, wherein the Hall sensor is fixed at one end of the heat conducting strip.
Furthermore, a slot wedge is arranged between two formed flat coils in the same stator slot.
Furthermore, the heat conducting strips and the slot wedges are both made of aluminum nitride ceramics.
Compared with the prior art, the invention has the beneficial technical effects that: according to the lightweight aviation motor, the Harbarker magnet steel array structure is adopted, an outer rotor magnet yoke is completely omitted, the weight of the motor is greatly reduced, and heat generated by eddy currents in the permanent magnets is directly led out through strong convection air flow outside an outer rotor shell. The aluminum coil is adopted to further reduce weight, the formed flat coil is adopted to improve the slot filling rate of the inner stator, and the defect of the aluminum wire compared with a copper wire is comprehensively made up through a tooth yoke made of oriented silicon steel. The ceramic slot wedge is used for fastening the formed flat wire in the inner stator slot, and meanwhile, the heat conduction from the formed flat wire to the heat dissipation channel of the inner stator core is increased. The inner stator is formed by mutually nesting and combining the dovetail teeth and the dovetail yokes, so that the stator teeth can be conveniently provided with flat coils, torque can be radially transmitted, an inner stator core can be circumferentially fixed, and the using amount of the yoke core is reduced. The ceramic heat conducting strip is closely contacted with the aluminum bracket of the inner stator, so that the temperature difference between the inside of the motor and the cooling surface can be further reduced. The Hall sensor is ingeniously arranged on the heat conducting strip to serve as a position sensor, and weight reduction is realized by replacing the rotary transformer.
Drawings
Fig. 1 is a schematic view of the overall structure of a lightweight aero-motor according to embodiment 1 of the present invention.
Fig. 2 is a schematic view of a stator assembly splicing structure in embodiment 1 of the present invention.
Fig. 3 is a schematic view showing the overall structure of a stator assembly in embodiment 1 of the present invention.
Fig. 4 is a schematic diagram showing the relative positions of the shaped flat coil, the heat conducting strip, the hall sensor and the slot wedge on the stator assembly in the embodiment 1 of the invention.
In the above figures 1-4, the stator frame-1; a first dovetail groove-101; dovetail tooth-2; dovetail yoke-3; first dovetail-301; a second dovetail-302; a second dovetail groove-303; forming a flat coil-4; a heat conducting strip-5; hall sensor-6; slot wedge-7; a housing-8; harbarg magnetic steel array-9.
Detailed Description
The technical scheme of the present invention will be clearly and completely described below with reference to the accompanying drawings and specific embodiments.
Example 1
As shown in fig. 1-3, a lightweight aero-motor comprises an outer rotor assembly and an inner stator assembly which are coaxially arranged, wherein the inner stator assembly comprises a stator bracket 1 and a stator core, and the stator core is fixed on the stator bracket 1. The stator core is formed by mutually mortise and tenon nesting of dovetail teeth 2 and dovetail yokes 3, stator grooves are formed between adjacent dovetail teeth 2, and coils are arranged on the dovetail teeth 2. The dovetail yokes 3 comprise first dovetail parts 301 and second dovetail parts 302, the stator bracket 1 is provided with first dovetail grooves 101, the first dovetail parts 301 of the dovetail yokes 3 are spliced in the first dovetail grooves 101, second dovetail grooves 303 are formed between the second dovetail parts 302 of two adjacent dovetail yokes 3, and the dovetail teeth 2 are spliced in the second dovetail grooves 303. The dovetail teeth (2) and the dovetail yoke (3) are formed by splicing oriented silicon steel sheets. The outer rotor assembly comprises a shell 8 and an end cover, and the inner wall of the shell is provided with a Harbarg magnetic steel array 9. The stator bracket 1 and the shell 8 are made of aluminum alloy materials.
As shown in fig. 4, the coil is a shaped flat coil 4 formed by winding an aluminum flat wire, two heat conducting strips 5 are arranged on the inner side of the shaped flat coil 4, the two heat conducting strips 5 are radially arranged on two sides of the dovetail teeth 2 along the stator, and the heat conducting strips 5 are simultaneously attached to the shaped flat coil 4 and the dovetail teeth 2. One end of the heat conducting strip 5 is flush with the dovetail teeth 2, and the other end of the heat conducting strip 5 is propped against the stator bracket 1. A hall sensor 6 is fixed to one end of the heat conducting strip 5. A slot wedge 7 is also arranged between the two formed flat coils 4 in the stator slot, and the heat conducting strip 5 and the slot wedge 7 are both made of aluminum nitride ceramics.
Claims (7)
1. The utility model provides a lightweight aero motor, including coaxial external rotor subassembly and the interior stator subassembly that sets up, a serial communication port, interior stator subassembly includes stator support (1) and stator core, stator core includes a plurality of dovetails (2) and a plurality of dovetails yoke (3), coil has on dovetails (2), dovetails yoke (3) include first dovetails (301) and second dovetails (302), stator support (1) is last to have a plurality of first dovetails (101), first dovetails (301) of dovetails (3) splice in first dovetails (101), constitute second dovetails (303) between second dovetails (302) of two adjacent dovetails (3), dovetails (2) splice in second dovetails (303), constitute the stator groove between adjacent dovetails (2); the outer rotor component comprises a shell (8) and an end cover, and the inner wall of the shell is provided with a Harbarg magnetic steel array (9).
2. A lightweight aero-motor as claimed in claim 1, wherein the stator support (1) and the housing (8) are both of aluminium alloy material.
3. A lightweight aero-motor as claimed in claim 1, wherein said coil is an aluminium coil, and said dovetail teeth (2) and dovetail yoke (3) are formed by stacking oriented silicon steel sheets.
4. The lightweight aero-motor according to claim 1, wherein the coil is a shaped flat coil (4), two heat conducting strips (5) are arranged on the inner side of the shaped flat coil (4), the two heat conducting strips (5) are radially arranged on two sides of the dovetail teeth (2) along the stator, and the heat conducting strips (5) are simultaneously attached to the shaped flat coil (4) and the dovetail teeth (2).
5. A lightweight aero-motor as claimed in claim 4, wherein one end of the heat conducting strip (5) is flush with the dovetail teeth (2), and the other end of the heat conducting strip (5) is propped against the stator frame (1).
6. A lightweight aero-motor as claimed in claim 5, further comprising a hall sensor (6), the hall sensor (6) being fixed to one end of the heat conducting strip (5).
7. A lightweight aero-motor as claimed in claim 1, wherein a slot wedge (7) is also provided between two shaped flat coils (4) in the same stator slot.
Priority Applications (3)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202311550200.XA CN117277649A (en) | 2023-11-21 | 2023-11-21 | Lightweight aero-motor |
| CN202410740458.4A CN118713385A (en) | 2023-11-21 | 2024-06-08 | Cooling structure of totally-enclosed external rotor motor |
| CN202410740460.1A CN118713386A (en) | 2023-11-21 | 2024-06-08 | Internal cooling method of totally-enclosed external rotor motor |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202311550200.XA CN117277649A (en) | 2023-11-21 | 2023-11-21 | Lightweight aero-motor |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN117277649A true CN117277649A (en) | 2023-12-22 |
Family
ID=89212778
Family Applications (3)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202311550200.XA Pending CN117277649A (en) | 2023-11-21 | 2023-11-21 | Lightweight aero-motor |
| CN202410740460.1A Pending CN118713386A (en) | 2023-11-21 | 2024-06-08 | Internal cooling method of totally-enclosed external rotor motor |
| CN202410740458.4A Pending CN118713385A (en) | 2023-11-21 | 2024-06-08 | Cooling structure of totally-enclosed external rotor motor |
Family Applications After (2)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202410740460.1A Pending CN118713386A (en) | 2023-11-21 | 2024-06-08 | Internal cooling method of totally-enclosed external rotor motor |
| CN202410740458.4A Pending CN118713385A (en) | 2023-11-21 | 2024-06-08 | Cooling structure of totally-enclosed external rotor motor |
Country Status (1)
| Country | Link |
|---|---|
| CN (3) | CN117277649A (en) |
Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN201365175Y (en) * | 2009-02-19 | 2009-12-16 | 宁波北斗科技有限公司 | Motor inner stator |
| CN201839179U (en) * | 2010-10-28 | 2011-05-18 | 陕西航空电气有限责任公司 | Rotor structure of aircraft generator |
| JP2015073358A (en) * | 2013-10-02 | 2015-04-16 | 日産自動車株式会社 | Stator |
| CN105720788A (en) * | 2016-04-25 | 2016-06-29 | 江苏磁谷科技股份有限公司 | High-power winding type permanent-magnet coupler |
| CN111917203A (en) * | 2019-05-08 | 2020-11-10 | 劳斯莱斯有限公司 | Electric machine |
| FR3132990A1 (en) * | 2022-02-24 | 2023-08-25 | Renault S.A.S | Stator for an axial flux electric machine, machine, vehicle and associated method |
| CN116722674A (en) * | 2023-05-30 | 2023-09-08 | 雷厉 | Motor with cooling structure at axial end |
-
2023
- 2023-11-21 CN CN202311550200.XA patent/CN117277649A/en active Pending
-
2024
- 2024-06-08 CN CN202410740460.1A patent/CN118713386A/en active Pending
- 2024-06-08 CN CN202410740458.4A patent/CN118713385A/en active Pending
Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN201365175Y (en) * | 2009-02-19 | 2009-12-16 | 宁波北斗科技有限公司 | Motor inner stator |
| CN201839179U (en) * | 2010-10-28 | 2011-05-18 | 陕西航空电气有限责任公司 | Rotor structure of aircraft generator |
| JP2015073358A (en) * | 2013-10-02 | 2015-04-16 | 日産自動車株式会社 | Stator |
| CN105720788A (en) * | 2016-04-25 | 2016-06-29 | 江苏磁谷科技股份有限公司 | High-power winding type permanent-magnet coupler |
| CN111917203A (en) * | 2019-05-08 | 2020-11-10 | 劳斯莱斯有限公司 | Electric machine |
| FR3132990A1 (en) * | 2022-02-24 | 2023-08-25 | Renault S.A.S | Stator for an axial flux electric machine, machine, vehicle and associated method |
| CN116722674A (en) * | 2023-05-30 | 2023-09-08 | 雷厉 | Motor with cooling structure at axial end |
Also Published As
| Publication number | Publication date |
|---|---|
| CN118713386A (en) | 2024-09-27 |
| CN118713385A (en) | 2024-09-27 |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| WD01 | Invention patent application deemed withdrawn after publication | ||
| WD01 | Invention patent application deemed withdrawn after publication |
Application publication date: 20231222 |