CN203722421U - Shielding structure of aviation-used permanent magnet motor - Google Patents
Shielding structure of aviation-used permanent magnet motor Download PDFInfo
- Publication number
- CN203722421U CN203722421U CN201420014723.2U CN201420014723U CN203722421U CN 203722421 U CN203722421 U CN 203722421U CN 201420014723 U CN201420014723 U CN 201420014723U CN 203722421 U CN203722421 U CN 203722421U
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- China
- Prior art keywords
- lead
- out wire
- aviation
- shielding
- shielding construction
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Abstract
The utility model belongs to the technical field of motors and relates to a shielding structure of an aviation-used permanent magnet motor. According to the shielding structure, a contact end of a position sensor lead-out wire and an electric connecting socket is provided with a lead-out wire shielding sleeve which is made of an aluminum alloy material. When the shielding structure is assembled, at first, the position sensor lead-out wire is sleeved with a metal wave-proof sleeve, and passes through the lead-out wire shielding sleeve so as to be welded on the electric connecting socket, and then, an end portion of the metal wave-proof sleeve is bonded at one end of the lead-out wire shielding sleeve, and the other end of the lead-out wire shielding sleeve abuts against the bottom surface of the electric connecting socket; and the outer circumferential surface of the lead-out wire shielding sleeve closely contacts with a casing. The shielding structure is simple in operation. With the shielding structure adopted, full shielding of the signals of the position sensor lead-out wire can be realized, and the reliability of the operation of an aviation-used high-power permanent magnet motor can be improved, and a risk coefficient can be reduced.
Description
Technical field
The utility model relates to technical field of motors, especially a kind of aviation magneto shielding construction.
Background technology
Aviation with magneto shielding construction all require to have that power output is high, compact conformation, Electro Magnetic Compatibility is good, reliability is high feature, therefore, its built-in field environment complexity very.In the prior art, aviation adopts brushless revolver as position transducer with magneto shielding construction great majority, gather again the positional information of rotor by position transducer, and then offer controller, so, the reliability of the position signalling of the rotor of magneto shielding construction for aviation, directly affects aviation electric power system operating safety factor; And aviation need to have the features such as lightweight, volume is little with magneto shielding construction, motor and position transducer can not independently be installed, therefore position transducer lead-out wire and motor winding leading-out wire can only be drawn in same casing cavity, like this, make motor winding form a kind of inevitable technical problem to the interference of position transducer lead-out wire.
At present, for the lead-out wire of aviation machine and the lead-out wire of position transducer, what conventionally adopt is that the shielding of anti-ripple cover is disturbed, this technical scheme has certain technique effect for anti-tampering, but the interference of shield electric machine winding to position transducer completely, particularly in position transducer lead-out wire and socket junction, this place's antijamming capability extreme difference, the problem that motor winding is disturbed is difficult to solve, can not realize the full-shield of position transducer lead-out wire signal, and then affect the reliability of the position signalling of the rotor of aviation magneto shielding construction, reliability while reducing machine operation, promote the danger coefficient that aviation is used.
For this reason, for aviation machine shield technology, we are badly in need of proposing a kind of new approaches.
Utility model content
In order to solve the technical problem existing in above-mentioned prior art, it is a kind of on the basis of original aviation magneto shielding construction that the utility model provides, carry out the reliability design on position transducer lead-out wire shielding construction, realize the shielding completely of position transducer lead-out wire signal, improve the aviation magneto shielding construction of aviation high-power permanent magnet motor functional reliability.
Concrete is achieved by the following technical programs:
A kind of aviation magneto shielding construction, comprise arbor, be through rotor on arbor, around the casing of the motor winding on stator, parcel stator, arrange in one end of rotor revolve change, also include lead-out wire shielding construction, the lead-out wire that has prevented position transducer lead-out wire and motor winding forms after electromagnetic field, phase mutual interference, and then the reliability of magneto shielding construction for raising aviation, reduce danger coefficient.
Further, draw the shielding completely of signal in order more effectively to realize position transducer, described lead-out wire shielding construction by with revolve the anti-ripple cover of the covert lead-out wire being connected, metal and anti-metal ripple cover be bundled in to the binding strap of lead-out wire, and the lead-out wire housing that is arranged on lead-out wire and socket contact jaw forms.
Further, one end of the anti-ripple cover of described metal is connected with one end of housing.
Further, one end of the anti-ripple cover of described metal is that colligation is connected with one end of housing.
Further, described lead-out wire is through housing.
Further, described lead-out wire housing is aluminium alloy.
Further, described lead-out wire housing is connected with casing.
Technique effect of the present utility model is embodied in: use the lead-out wire of magneto shielding construction to carry out shielding construction setting by aviation, the lead-out wire of position transducer and the lead-out wire of motor winding can separatedly be opened, further realize the shielding completely of position transducer lead-out wire signal, improve the reliability of aviation high-power permanent magnet motor in the time of work, reduce coefficient of safety; Meanwhile, this structure simple to operate, production cost is low.
Brief description of the drawings
Fig. 1 is the overall schematic of aviation of the present utility model magneto shielding construction.
Fig. 2 is the lead-in wire shielding construction partial enlarged drawing of aviation of the present utility model magneto shielding construction.
1-lead-out wire shielding construction 2-motor winding 3-revolves and becomes the anti-ripple cover of 4-rotor 5-casing 6-stator 7-arbor 8-lead-out wire 9-binding strap 10-housing 11-socket 12-metal.
Embodiment
Below in conjunction with accompanying drawing and concrete execution mode, the technical solution of the utility model is further elaborated, but claimed scope is not only confined to done description.
Embodiment mono-
As depicted in figs. 1 and 2, a kind of aviation magneto shielding construction, comprise arbor 7, be through rotor 4 on arbor 7, become 3 around the casing 5 of the motor winding 2 on stator 6, parcel stator 6, revolving of arranging in one end of arbor 7, also include lead-in wire shielding construction 1; The lead-out wire that has prevented position transducer lead-out wire and motor winding forms after electromagnetic field, and phase mutual interference, and then the reliability of magneto shielding construction for raising aviation, reduced danger coefficient; Lead-in wire shielding construction 1 by with revolve the binding strap 9 that becomes the anti-ripple cover 12 of 3 lead-out wires that are connected 8, metal and anti-metal ripple cover 12 is bundled in to lead-out wire housing 10; The more effective shielding completely that realizes position transducer and draw signal.
Embodiment bis-
According to embodiment mono-, one end of the anti-ripple cover 12 of metal is that colligation is connected with one end of lead-out wire housing 10; Lead-out wire 8 is through aluminium alloy lead-out wire housing 10; Lead-out wire housing 10 is closely connected with casing 5.
Embodiment tri-
As depicted in figs. 1 and 2, a kind of aviation magneto shielding construction, its structure is, at position transducer lead-out wire 8 and the contact jaw of electric-connected socket 11, a lead-out wire housing 10 is installed, these lead-out wire housing 10 materials are aluminium alloy; In the time of assembling, first the anti-ripple cover 12 of position transducer lead-out wire 8 use metal being set up and pass lead-out wire housing 10 is welded on electric-connected socket 11, again anti-metal ripple is overlapped to 12 end bandings one end at lead-out wire housing 10, the other end of lead-out wire housing 10 is by electric-connected socket 11 bottom surfaces, lead-out wire housing 10 cylindricals and casing 5 close contacts, meanwhile, on casing 5, designing a step retrains entirely to lead-out wire housing 10; This structure operation is simple, has realized the signal full-shield of position transducer lead-out wire 8, improves aviation high-power permanent magnet motor functional reliability, has reduced danger coefficient.
Claims (7)
1. an aviation magneto shielding construction, comprise arbor (7), be through rotor (4) on arbor (7), around the casing (5) of the motor winding (2) of stator (6) outside, parcel stator (6), arrange in one end of arbor (7) revolve changes (3), it is characterized in that: also include the shielding construction (1) that goes between.
2. aviation as claimed in claim 1 magneto shielding construction, it is characterized in that: described lead-in wire shielding construction (1) by with revolve the anti-ripple cover of lead-out wire (8), metal (12) that change (3) is connected and the binding strap (9) that anti-metal ripple cover (12) is bundled in to lead-out wire housing (10), and be arranged on lead-out wire housing (10) composition of lead-out wire (8) and socket (11) contact jaw.
3. aviation as claimed in claim 2 magneto shielding construction, is characterized in that: one end of the anti-ripple cover of described metal (12) is connected with one end of lead-out wire housing (10).
4. aviation as claimed in claim 3 magneto shielding construction, is characterized in that: one end of the anti-ripple cover of described metal (12) is that colligation is connected with one end of lead-out wire housing (10).
5. the aviation magneto shielding construction as described in claim 2,3,4, is characterized in that: described lead-out wire (8) is through lead-out wire housing (10).
6. the aviation magneto shielding construction as described in claim 2,3,4 or 5, is characterized in that: described lead-out wire housing (10) is aluminium alloy.
7. the aviation magneto shielding construction as described in claim 2,3,4 or 6, is characterized in that: described lead-out wire housing (10) is connected with casing (5).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201420014723.2U CN203722421U (en) | 2014-01-09 | 2014-01-09 | Shielding structure of aviation-used permanent magnet motor |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201420014723.2U CN203722421U (en) | 2014-01-09 | 2014-01-09 | Shielding structure of aviation-used permanent magnet motor |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN203722421U true CN203722421U (en) | 2014-07-16 |
Family
ID=51161544
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201420014723.2U Expired - Fee Related CN203722421U (en) | 2014-01-09 | 2014-01-09 | Shielding structure of aviation-used permanent magnet motor |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN203722421U (en) |
-
2014
- 2014-01-09 CN CN201420014723.2U patent/CN203722421U/en not_active Expired - Fee Related
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20140716 Termination date: 20220109 |