CN220857850U - Aviation direct current brush micro-motor rotor winding transition line structure - Google Patents
Aviation direct current brush micro-motor rotor winding transition line structure Download PDFInfo
- Publication number
- CN220857850U CN220857850U CN202322318256.4U CN202322318256U CN220857850U CN 220857850 U CN220857850 U CN 220857850U CN 202322318256 U CN202322318256 U CN 202322318256U CN 220857850 U CN220857850 U CN 220857850U
- Authority
- CN
- China
- Prior art keywords
- rotor winding
- transition line
- wire
- transition
- direct current
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Links
- 238000004804 winding Methods 0.000 title claims abstract description 47
- 230000007704 transition Effects 0.000 title claims abstract description 46
- 238000003466 welding Methods 0.000 claims abstract description 14
- XEEYBQQBJWHFJM-UHFFFAOYSA-N Iron Chemical compound [Fe] XEEYBQQBJWHFJM-UHFFFAOYSA-N 0.000 claims description 8
- ATJFFYVFTNAWJD-UHFFFAOYSA-N Tin Chemical compound [Sn] ATJFFYVFTNAWJD-UHFFFAOYSA-N 0.000 claims description 4
- 229910052742 iron Inorganic materials 0.000 claims description 4
- 238000005476 soldering Methods 0.000 claims description 4
- 229920000742 Cotton Polymers 0.000 claims description 3
- -1 polytetrafluoroethylene Polymers 0.000 claims description 3
- 229920001343 polytetrafluoroethylene Polymers 0.000 claims description 3
- 239000004810 polytetrafluoroethylene Substances 0.000 claims description 3
- 239000000463 material Substances 0.000 claims description 2
- 238000009413 insulation Methods 0.000 claims 1
- 241001391944 Commicarpus scandens Species 0.000 description 1
- 239000004593 Epoxy Substances 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 238000007598 dipping method Methods 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 239000003973 paint Substances 0.000 description 1
- 239000002904 solvent Substances 0.000 description 1
Landscapes
- Motor Or Generator Current Collectors (AREA)
Abstract
The utility model belongs to the technical field of aviation motor design, and relates to an aviation direct-current brush micro-motor rotor winding transition line structure. The commutator comprises commutator lifting pieces (2), transition wires (3), rotor winding end parts (4), binding wires (5), slot wedges (6), rotor core slots (7), winding wires (8) and insulating sleeves (9); the utility model adopts the measure of increasing a transition line (3) with larger cross section area at the welding position of the end part of a rotor winding wire of the avionic direct current brush micro motor and a commutator lifting piece (2), and improves the connection reliability of the rotor winding wire (8) and the commutator (1).
Description
Technical Field
The utility model belongs to the technical field of aviation motor design, and relates to an aviation direct-current brush micro-motor rotor winding transition line structure.
Technical Field
Because the aviation direct current brushed micro-motor is small in required size and small in diameter of a motor rotor winding wire, two ends of each winding are welded with lifting pieces of a commutator, the more the number of the commutator pieces is, the more the welding parts are, the more the number of virtual grooves is, the more the welding parts are, if electrical double redundancy is required, the welding parts are doubled, and when the working vibration amplitude of the micro-motor is large, the welding parts of the winding wire ends and the lifting pieces of the commutator are easy to break, therefore, measures are required to improve the connection reliability of the rotor winding ends and the commutator.
Disclosure of Invention
The purpose of the utility model is that: and a measure of adding a transition line with larger cross section area between the end part of the rotor winding wire of the avionic direct current brush micro motor and the welding part of the commutator lifting piece is adopted, so that the reliability of the connection between the rotor winding wire and the commutator is improved.
The technical scheme of the utility model is as follows: the transition line structure of the rotor winding of the aviation direct current brush micro-motor comprises a lifting piece 2 of a commutator 1, a transition line 3, a rotor winding end 4, a binding line 5, a slot wedge 6, a rotor core slot 7, a winding wire 8 and an insulating sleeve 9; one end of the transition wire 3 is welded with the commutator lifting piece 2 by tin, the other end of the transition wire 3 is welded with the end part of the rotor winding wire 8, an insulating sleeve 9 is sleeved at the welding part and then is placed into the rotor core slot 7, the rotor core slot is pressed by the slot wedge 6, and the rotor winding end part 4 and the transition wire 3 are bound and fixed by the binding wire 5.
The transition line 3 is a polytetrafluoroethylene line.
The cross section area of the transition line 3 is 5-25 times of the cross section area of the winding wire 8.
The length of the transition line 3 is 2-3 times of the distance from the end face of the rotor core 10 to the commutator segment 2.
The two ends of the transition line 3 are respectively stripped of insulating skins by 5mm.
And the soldering iron power used when the transition wire 3 is welded with the commutator lifting piece 2 and the end part of the transition wire 3 is welded with the end part of the rotor winding wire 8 is 30 watts.
The binding thread 5 is made of cotton thread.
The utility model has the beneficial effects that: the utility model adopts the measure of increasing the transition line with larger sectional area between the end part of the rotor winding wire of the avionic direct current brush micro motor and the welding part of the commutator lifting piece, thereby improving the connection reliability of the rotor winding wire and the commutator.
Drawings
FIG. 1 is a schematic diagram of a rotor winding structure of an aviation DC brush micro-motor
Wherein: 1-commutator, 2-lifting piece, 3-transition wire, 4-rotor winding end, 5-binding wire, 6-slot wedge, 7-rotor core slot, 8-winding wire, 9-insulating sleeve and 10-rotor core
The specific embodiment is as follows:
the utility model is described in further detail below with reference to the accompanying drawings.
As shown in fig. 1, the transition line structure of the rotor winding of the aviation direct current brush micro-motor comprises a lifting piece 2 of a commutator 1, a transition line 3, a rotor winding end 4, a binding line 5, a slot wedge 6, a rotor core slot 7, a winding wire 8 and an insulating sleeve 9; one end of the transition wire 3 is welded with the commutator lifting piece 2 by tin, the other end of the transition wire 3 is welded with the end part of the rotor winding wire 8, an insulating sleeve 9 is sleeved at the welding part and then is placed into the rotor core slot 7, the rotor core slot is pressed by the slot wedge 6, and the rotor winding end part 4 and the transition wire 3 are bound and fixed by the binding wire 5.
Polytetrafluoroethylene wire AFR-250 is selected as transition wire 3, the sectional area of which is 5-25 times of the sectional area of winding wire 8, the length of which is about 2-3 times of the distance from the end face of rotor core 10 to commutator lifter plate 2, and insulating skins at two ends of transition wire 3 are removed by 5mm respectively. One end of the transition wire 3 is welded with the commutator lifting piece 2 by tin, the other end of the transition wire 3 is welded with the end of the rotor winding wire 8, and the soldering iron power used in the welding process is 30 watts, so that the wire is damaged due to the fact that the soldering iron power is high, and the welding is not performed. The welding part is sleeved with an insulating sleeve 9 and then is placed in a rotor core groove 7, then is pressed by a slot wedge 6, the rotor winding end 4 comprises a transition wire 3, the material of the binding wire 5 is cotton wire binding and fixing, and the rotor is subjected to vacuum epoxy dipping without solvent paint, so that the strength of the welding part is greatly improved, and the use requirement is met.
Claims (7)
1. The transition line structure of the rotor winding of the aviation direct current brush micro-motor is characterized by comprising a lifting piece (2), a transition line (3), a rotor winding end (4), a binding line (5), a slot wedge (6), a rotor core slot (7), a winding wire (8) and an insulating sleeve (9) in a commutator (1); one end of the transition wire (3) is welded with the lifting piece (2) by tin, the other end of the transition wire (3) is welded with the end part of the rotor winding wire (8), an insulating sleeve (9) is sleeved at the welding part and then is placed into the rotor core slot (7), the rotor core slot is pressed by the slot wedge (6), and the rotor winding end part (4) and the transition wire (3) are bound and fixed by the binding wire (5).
2. The aviation direct current brush micro-machine rotor winding transition line structure according to claim 1, characterized in that the transition line (3) is selected from polytetrafluoroethylene lines.
3. The transition line structure of the rotor winding of the aviation direct current brush micro-motor according to claim 1, wherein the cross section area of the transition line (3) is 5-25 times of the cross section area of the winding wire (8).
4. The transition line structure of the rotor winding of the aviation direct current brush micro-motor according to claim 1, wherein the length of the transition line (3) is 2-3 times of the distance from the end face of the rotor core (10) to the lifting sheet (2).
5. The transition line structure of the rotor winding of the aviation direct current brush micro-motor according to claim 1, wherein insulation covers are removed by 5mm at two ends of the transition line (3).
6. The transition line structure of the rotor winding of the aviation direct current brush micro-motor according to claim 1, wherein the soldering iron power used when the transition line (3) is welded with the lifting piece (2) and the transition line (3) is welded with the end part of the rotor winding wire (8) is 30 watts.
7. The aviation direct current brush micro-motor rotor winding transition line structure according to claim 1, wherein the binding line (5) material is cotton thread.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202322318256.4U CN220857850U (en) | 2023-08-28 | 2023-08-28 | Aviation direct current brush micro-motor rotor winding transition line structure |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202322318256.4U CN220857850U (en) | 2023-08-28 | 2023-08-28 | Aviation direct current brush micro-motor rotor winding transition line structure |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN220857850U true CN220857850U (en) | 2024-04-26 |
Family
ID=90747151
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202322318256.4U Active CN220857850U (en) | 2023-08-28 | 2023-08-28 | Aviation direct current brush micro-motor rotor winding transition line structure |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN220857850U (en) |
-
2023
- 2023-08-28 CN CN202322318256.4U patent/CN220857850U/en active Active
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