CN218456380U - External rotor electric machine suitable for aircraft, aircraft horn - Google Patents
External rotor electric machine suitable for aircraft, aircraft horn Download PDFInfo
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- CN218456380U CN218456380U CN202222428094.5U CN202222428094U CN218456380U CN 218456380 U CN218456380 U CN 218456380U CN 202222428094 U CN202222428094 U CN 202222428094U CN 218456380 U CN218456380 U CN 218456380U
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Abstract
The utility model provides an external rotor electric machine and aircraft horn suitable for aircraft, this external rotor electric machine includes: the middle shaft body, the outer rotor, the inner stator, the outer ring piece, the inner ring piece and the electric brush plate; wherein: the middle shaft body is arranged at the center of the inner stator and can rotate relative to the inner stator; the outer rotor is fixedly connected with the middle shaft body; the first end of the inner ring piece is fixedly connected to the middle shaft body; the outer wall of the inner ring piece is provided with an electric brush wire surface; the outer ring member is rotatably mounted at the second end of the inner ring member; the electric brush plate is fixed on the outer ring piece and can be in contact with the electric brush wire surface. This aircraft horn includes: the outer rotor motor suitable for the aircraft comprises a horn main body and the outer rotor motor suitable for the aircraft, wherein the horn main body is fixedly connected to an inner stator of the outer rotor motor suitable for the aircraft. The utility model discloses can effectively prevent the harm of thunder and lightning and static to the motor. The structure of the outer rotor motor can meet the operation mode of an aircraft, so that the electric protection of the aircraft is more reliable.
Description
Technical Field
The utility model relates to an aircraft technical field especially relates to an external rotor electric machine, aircraft horn suitable for aircraft.
Background
For a typical motor, the rotor of which is mounted in a cylindrical stator, to protect the motor from static electricity or lightning, the stator (or motor housing) of the motor is merely connected to the fuselage of the aircraft by a cable to discharge static electricity or lightning from the motor.
However, with the increasing development of new energy airplanes, the structure of the airplane motor is greatly different from that of the traditional airplane engine, and the traditional electrostatic protection and lightning protection cannot meet the requirement of the airplane motor part. For example, the electric machine of aircraft EH216 is an outer rotor electric machine, and in this case, it is not possible to conduct static electricity away by direct electrical bonding on the outer rotor, and it is more difficult to achieve lightning protection fixing bonding.
SUMMERY OF THE UTILITY MODEL
The features and advantages of the present invention are set forth in part in the description which follows, or may be obvious from the description, or may be learned by practice of the invention.
For overcoming prior art's problem, the utility model provides an external rotor electric machine suitable for aircraft, include: the electric brush comprises a middle shaft body, an outer rotor, an inner stator, an outer ring piece, an inner ring piece and an electric brush plate; wherein:
the middle shaft body is arranged at the center of the inner stator and can rotate relative to the inner stator; the outer rotor is fixedly connected with the middle shaft body;
the first end of the inner ring piece is fixedly connected to the middle shaft body; the outer wall of the inner ring piece is provided with an electric brush wire surface;
the outer ring member is rotatably mounted at the second end of the inner ring member;
the electric brush plate is fixed on the outer ring piece and can be in contact with the electric brush wire surface.
In one embodiment of the present application, the cross-sectional area of the brush plate is 1.8 to 2.2cm 2 。
In one embodiment of the present application, the brush plate is fixed to the outer ring member by a fixing plate; the central line of the fixing plate is parallel to the axial central line of the inner ring piece.
In one embodiment of the present application, the brush plate is plural and arranged on the fixing plate along a center line of the fixing plate.
In an embodiment of this application, the center of inner stator is equipped with the first chamber and the second chamber that holds that communicate with each other, well axis body rotates to be connected on the first inner wall that holds the chamber, just the first end of well axis body stretches into the second holds the intracavity.
In an embodiment of the present application, the inner ring member is located in the second accommodating cavity and is fixedly connected to the first end of the middle shaft body.
In one embodiment of the present application, the inner wall of the second receiving chamber is rotatably connected to the inner ring member.
In one embodiment of the present application, the electric vehicle further includes a first cable connected to the outer ring member and a second cable connected to the inner ring member, and the second cable is electrically connected to the outer rotor.
The utility model also provides an aircraft horn, include: the outer rotor motor applicable to the aircraft comprises a horn main body and the outer rotor motor applicable to the aircraft, wherein the horn main body is fixedly connected to an inner stator of the outer rotor motor applicable to the aircraft.
In one embodiment of the present application, the second cable of the external rotor motor for an aircraft is connected to the horn body.
The utility model provides an external rotor electric machine suitable for aircraft can effectively prevent the harm of thunder and lightning and static to the motor. The structure of the outer rotor motor can meet the operation mode of an aircraft, so that the electric protection of the aircraft is more reliable.
The features and content of these solutions will be better understood by those skilled in the art from reading the present description.
Drawings
The advantages and mode of realisation of the invention will become more apparent hereinafter by describing in detail the invention with reference to the attached drawings, wherein the content shown in the drawings is only for explaining the invention, without constituting any limitation to the meaning of the invention, in which:
fig. 1 is a cross-sectional view of the outer rotor motor suitable for aircraft according to the embodiment of the present invention.
Fig. 2 is a schematic structural view of an outer rotor motor of the outer rotor motor for an aircraft shown in fig. 1.
Fig. 3 is a cross-sectional view of an embodiment of the present invention, adapted for use in an aircraft horn.
Reference numerals:
10. a middle shaft body; 20. an inner stator; 30. an outer rotor; 41. an inner ring member; 42. an outer ring member; 43. A brush plate; 44. a fixing plate; 45. a wire surface of the electric brush; 46. a first cable; 47. a second cable; 50. A horn body; 51. and (4) screws.
Detailed Description
In the description of the present invention, "a plurality" means two or more unless otherwise specified; the terms "upper", "lower", "inner", "outer", "top", "bottom", and the like refer to orientations or positional relationships based on orientations or positional relationships illustrated in the drawings, merely for convenience in describing the present invention and to simplify the description, and do not indicate or imply that the device or element referred to must have a particular orientation, be constructed and operated in a particular orientation, and therefore should not be construed as limiting the invention. Furthermore, the terms "first," "second," and the like are used for descriptive purposes only and are not to be construed as indicating or implying relative importance.
In the description of the present invention, it is to be noted that, unless otherwise explicitly specified or limited, the terms "connected" and "connected" are to be interpreted broadly, and may be, for example, fixedly connected, detachably connected, or integrally connected; can be mechanically or electrically connected; may be directly connected or indirectly connected through an intermediate. The specific meaning of the above terms in the present invention can be understood according to specific situations by those skilled in the art.
To facilitate an understanding of the present application, the present application will now be described more fully with reference to the accompanying drawings. Preferred embodiments of the present application are given in the accompanying drawings. This application may, however, be embodied in many different forms and should not be construed as limited to the embodiments set forth herein. Rather, these embodiments are provided so that this disclosure will be thorough and complete.
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 application belongs. The terminology used herein in the description of the present application is for the purpose of describing particular embodiments only and is not intended to be limiting of the application.
Example 1
As shown in fig. 1 and fig. 2, the present embodiment provides an external rotor motor suitable for an aircraft, including: the motor comprises a middle shaft body 10, an inner stator 20, an outer rotor 30, an inner ring element 41, an outer ring element 42 and a brush plate 43.
Wherein, the inner stator 20 is cylindrical, the middle shaft 10 is arranged at the center of the inner stator 20 and can rotate relative to the inner stator 20; the outer rotor 30 is disposed outside the inner stator 20 and is fixedly connected to the middle shaft 10, that is, the outer rotor 30 and the middle shaft 10 are relatively fixed.
The first end of the inner ring member 41 is fixedly connected to the middle shaft body 10; in an embodiment, the inner ring member 41 and the middle shaft 10 may be directly connected or may be connected through a connecting member to fix the inner ring member 41 and the middle shaft 10 relative to each other, and when the outer rotor 30 rotates relative to the inner stator 20, the inner ring member 41 will follow the middle shaft 10 to rotate together with the outer rotor 30.
The outer ring member 42 is rotatably mounted at the second end of the inner ring member 41; the outer wall of the inner ring piece 10 is provided with an electric brush wire surface 45; the brush plate 43 is fixed to the outer ring member 42, and the brush plate 43 can be in contact with the brush wire surface 45. In practical implementation, the brush plate 43 is fixed on the outer ring 10 through the fixing plate 44, and a center line of the fixing plate 44 is parallel to an axial center line of the inner ring and is fixed on the outer ring 10 through welding or the like, or is integrally formed with the outer ring 10. One end of the brush plate 43 is fixed to the fixing plate 44, and the other end is in contact with the brush wire surface 45.
The inner ring member 41, the outer ring member 42, and the brush plate 43 constitute an electrical slip ring. The embodiment aims at static electricity and lightning, and an electric slip ring is added in the outer rotor motor so as to effectively conduct away the static electricity.
Example 2
As shown in fig. 1 and 2, the present embodiment provides an external rotor motor suitable for an aircraft, including: the electric brush comprises a middle shaft body 10, an inner stator 20, an outer rotor 30, an inner ring member 41, an outer ring member 42 and a brush plate 43.
In this embodiment, the center of the inner stator 20 is provided with a first accommodating cavity and a second accommodating cavity which are communicated with each other, and the diameter of the second accommodating cavity is larger than that of the first accommodating cavity. The well axis body 10 rotates to be connected on the inner wall that the first chamber that holds, and the first end of well axis body 10 stretches into the second and holds the intracavity.
The inner ring member 41 is located in the second accommodating cavity and is fixedly connected with the first end of the middle shaft body 10. The inner ring member 41 and the middle shaft body 10 may be directly connected or may be connected through a connecting member to fix the inner ring member 41 and the middle shaft body 10 relative to each other. The inner wall of the second accommodating cavity is rotationally connected with the inner ring member 41, so that the inner ring member 41 can rotate along with the middle shaft body 10.
The outer ring member 42 is rotatably mounted at the second end of the inner ring member 41; the outer wall of the inner ring piece 10 is provided with an electric brush wire surface 45; the brush plate 43 is fixed to the outer ring member 42, and the brush plate 43 can be in contact with the brush wire surface 45.
In specific implementation, the brush plate 43 is fixed on the outer ring 10 by the fixing plate 44, and the center line of the fixing plate 44 is parallel to the axial center line of the inner ring and fixed on the bottom of the fixing plate 11 by welding or the like, or is integrally formed with the outer ring 10. One end of the brush plate 43 is fixed to the fixing plate 44, and the other end is in contact with the brush wire surface 45. At this time, the inner stator 20 is further provided with a brush wire groove for accommodating the fixing plate and the brush plate, and the brush wire groove is communicated with the second accommodating chamber, so that the brush plate located in the brush wire groove can contact the inner ring member 41 located in the second accommodating chamber.
The outer rotor 30 is disposed outside the inner stator 20, and is fixedly connected to the middle shaft 10 and can rotate together with the middle shaft 10. In this embodiment, the axial height of the inner stator 41 is greater than the axial height of the outer rotor 30.
Example 3
In addition to the above embodiment 1 or embodiment 2, the brush wire area of the brush plate and the brush wire surface is further increased, in this case, the brush plate 30 in this embodiment is a whole metal, and the cross-sectional area of the brush plate is 1.8-2.2 cm 2 For example 2cm 2 . The electric slip ring with the enlarged brush wire area can bear the current of 30KA, and the current of lightning is usually about 20KA-30KA, so the damage of the lightning and static electricity to the motor can be effectively prevented by enlarging the brush wire area.
In another embodiment of the present application, the brush plate 43 may be plural and arranged on the fixing plate 44 along a center line of the fixing plate 44.
In addition, the outer rotor motor further includes a first cable 46 and a second cable 47. One end of the first cable 46 is fixedly connected to the inner ring member 41, and the other end is connected to the outer rotor 30 of the outer rotor motor, specifically, a metal hole is formed at the end of the first cable 46, a corresponding connection hole is formed in the outer rotor, and the metal hole and the connection hole are connected through a screw. One end of the second cable 47 is fixedly connected to the outer ring member, and the other end is used for being connected with the arm main body.
Example 4
As shown in fig. 3, the present application further provides an aircraft horn, which includes a horn main body 50 and the external rotor motor for an aircraft provided in any of the above embodiments, where the horn main body 50 is fixedly connected to the inner stator 20 of the external rotor motor for an aircraft. In specific implementation, the axial height of the inner stator 20 is greater than the axial height of the outer rotor 30, the first end of the inner stator 20 protrudes from the outer rotor 30, the first end of the inner stator 20 is provided with a plurality of mounting holes, the housing of the horn main body 50 is provided with connecting holes matched with the mounting holes, and the horn main body 50 is connected with the inner stator 20 through screws 51. In this embodiment, the end face of the outer ring 42 is fixed to the arm body by a fastener such as a screw or a bolt. The second cable 47 of the external rotor motor is connected to the arm body 50. Specifically, the second cable 47 has a metal hole at the end of the cable, and the arm body 50 has a corresponding connecting hole, and the metal hole and the connecting hole are connected by a screw.
The utility model provides a pair of external rotor electric machine suitable for aircraft can effectively prevent the harm of thunder and lightning and static to the motor, satisfies aircraft electrostatic protection and lightning protection's demand, makes aircraft electric protection more reliable.
The preferred embodiments of the present invention have been described with reference to the accompanying drawings, and those skilled in the art can implement the present invention in various modifications without departing from the scope and spirit of the present invention. For instance, features illustrated or described as part of one embodiment, can be used with another embodiment to yield a still further embodiment. The above description is only a preferred and practical embodiment of the present invention, and not intended to limit the scope of the present invention, and all equivalent changes made by using the contents of the specification and the drawings of the present invention are included in the scope of the present invention.
Claims (10)
1. An external rotor electric machine suitable for an aircraft, comprising: the electric brush comprises a middle shaft body, an outer rotor, an inner stator, an outer ring piece, an inner ring piece and an electric brush plate; wherein:
the middle shaft body is arranged at the center of the inner stator and can rotate relative to the inner stator; the outer rotor is fixedly connected with the middle shaft body;
the first end of the inner ring piece is fixedly connected to the middle shaft body; the outer wall of the inner ring piece is provided with an electric brush wire surface;
the outer ring member is rotatably mounted at the second end of the inner ring member;
the electric brush plate is fixed on the outer ring piece and can be in contact with the electric brush wire surface.
2. The external rotor electric machine for aircraft according to claim 1, wherein the cross-sectional area of the brush plate is 1.8-2.2 cm 2 。
3. The external rotor electric machine for aircraft according to claim 1, wherein the brush plate is fixed to the outer ring member by a fixing plate; the central line of the fixing plate is parallel to the axial central line of the inner ring piece.
4. The external rotor electric machine for aircraft according to claim 3, wherein the brush plate is plural and arranged on the fixing plate along a center line of the fixing plate.
5. The external rotor motor for the aircraft according to claim 1, wherein the center of the internal stator is provided with a first receiving cavity and a second receiving cavity which are communicated with each other, the middle shaft body is rotatably connected to an inner wall of the first receiving cavity, and a first end of the middle shaft body extends into the second receiving cavity.
6. The external rotor electric machine for aircraft according to claim 5, wherein the inner ring member is located in the second accommodating cavity and is fixedly connected with the first end of the middle shaft body.
7. The external rotor electric machine for aircraft according to claim 5, wherein an inner wall of the second receiving chamber is rotatably connected to the inner ring member.
8. The external rotor electric machine for aircraft according to claim 5, further comprising a first cable connected to the outer ring member and a second cable connected to the inner ring member, the second cable being electrically connected to the external rotor.
9. An aircraft horn, comprising: an outer rotor motor for an aircraft according to any one of claims 1 to 8, and a horn body fixedly attached to an inner stator of the outer rotor motor for an aircraft.
10. The aircraft horn of claim 9 wherein said second cable of said external rotor electric machine for an aircraft is connected to said horn body.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202222428094.5U CN218456380U (en) | 2022-09-14 | 2022-09-14 | External rotor electric machine suitable for aircraft, aircraft horn |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202222428094.5U CN218456380U (en) | 2022-09-14 | 2022-09-14 | External rotor electric machine suitable for aircraft, aircraft horn |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN218456380U true CN218456380U (en) | 2023-02-07 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202222428094.5U Active CN218456380U (en) | 2022-09-14 | 2022-09-14 | External rotor electric machine suitable for aircraft, aircraft horn |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN218456380U (en) |
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2022
- 2022-09-14 CN CN202222428094.5U patent/CN218456380U/en active Active
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