CN102857060A - Slotless and brushless permanent magnet direct-current motor for aviation - Google Patents

Abstract

The invention belongs to the field of direct-current motors and aims to provide a slotless and brushless permanent magnet direct-current motor for aviation. The motor comprises a stator, a rotor, an enclosure, a front end cover and a back end cover and is of an inner rotor integrated structure. The rotor comprises a magnet yoke in a circular structure; and a slot structure is arranged in the inner circle of the circular structure. By adopting the slotless and brushless permanent magnet direct-current motor for aviation provided by the invention, the structure of the motor is greatly simplified, the power/volume ratio s greatly improved, and the overload capacity of the motor is improved; and the weight of the rotor of the motor is reduced and the rotational inertia is decreased so that the rotational speed and the rapid startup or shutdown capacity of the motor are obviously improved.

Description

A kind of aviation brushless slotless permanent magnet DC motor

Technical field

The present invention relates to the direct current machine field, refer to especially a kind of aviation brushless slotless permanent magnet DC motor.

Background technology

Application number is 201120556470.8 to disclose a kind of high-speed permanent magnetic brushless slotless DC motor, it is a kind of direct current machine of brushless slotless, it is not enough because of the torque pulsation that the stator tooth slot structure brings to have overcome existing permanent-magnet brushless DC electric machine, cause the generation of jerk phenomenon when having avoided motor to run up because of the rotor part unbalance dynamic, the present invention is the improvement of these innovation and creation, improve the power-weight ratio of motor, improve the frequency response speed of motor, to satisfy field of aerospace to the requirement of power of motor, frequency response and stability.

Summary of the invention

A kind of aviation brushless slotless permanent magnet DC motor provided by the invention, the motor frequency response is high, operate steadily, and power-weight ratio is large.

Technical scheme of the present invention is achieved in that a kind of aviation brushless slotless permanent magnet DC motor, comprises stator, rotor, casing, front end housing and rear end cap, is the internal rotor integral structure, and described rotor comprises yoke, and described yoke is loop configuration; Annular yoke inner ring is provided with trench structure.

Described rotor is armature spindle, yoke, magnet steel, retaining ring from inside to outside successively; Stator is stator core, insulation film, stator winding from outside to inside successively; Stator core forms by silicon steel sheet is stacking.

Described motor also has dynamic balancing adjustment block, bearing, transducer magnet steel seat and transducer magnet steel; The transducer magnet steel seat is positioned at the dynamic balancing adjustment block outside; Fit in first multidiameter surface of end face of transducer magnet steel seat and rotating shaft one side, the transducer magnet steel is consistent with magnet steel in a circumferential direction; Bearing holder (housing, cover) is located on the armature spindle, is positioned at the transducer magnet steel seat outside.

The level of ring and vertical both direction are provided with 4 grooveds in the described yoke.

Described stator winding is the tubular winding.

Described retaining ring is sheathed on the magnet steel periphery, with the magnet steel interference fit.

The thickness of described retaining ring is 0.5-0.8mm.

Optimize, described transducer magnet steel seat is made by nylon material.

A kind of aviation brushless slotless permanent magnet DC motor provided by the invention is simplified electric machine structure greatly, and power, volume ratio are improved greatly, improves the motor overload ability; Rotor weight saving, moment of inertia diminishes, and obviously improves rotating speed and the rapid starting/stopping ability of motor.

Description of drawings

In order to be illustrated more clearly in the embodiment of the invention or technical scheme of the prior art, the below will do to introduce simply to the accompanying drawing of required use in embodiment or the description of the Prior Art, apparently, accompanying drawing in the following describes only is some embodiments of the present invention, for those of ordinary skills, under the prerequisite of not paying creative work, can also obtain according to these accompanying drawings other accompanying drawing.

Fig. 1: structural representation of the present invention.

Fig. 2: magnetic yoke structure schematic diagram of the present invention.

Wherein: 1-armature spindle, 2-yoke, 3-magnet steel, 4-retaining ring, 5-stator core, 6-tubular winding, 7-dynamic balancing adjustment block, 8-bearing, 9-transducer magnet steel seat, 10-transducer magnet steel.

Embodiment

Below in conjunction with the accompanying drawing in the embodiment of the invention, the technical scheme in the embodiment of the invention is clearly and completely described, obviously, described embodiment only is the present invention's part embodiment, rather than whole embodiment.Based on the embodiment among the present invention, those of ordinary skills belong to the scope of protection of the invention not making the every other embodiment that obtains under the creative work prerequisite.

A kind of aviation brushless slotless permanent magnet DC motor provided by the invention comprises stator, rotor, casing, front end housing and rear end cap, is the internal rotor integral structure, and described rotor comprises yoke 2, and described yoke 2 is loop configuration; Annular yoke 2 inner rings are provided with trench structure.Described rotor is armature spindle 1, yoke 2, magnet steel 3, retaining ring 4 from inside to outside successively; Stator is stator core 5, insulation film, stator winding from outside to inside successively; Stator core 5 forms by silicon steel sheet is stacking.Described motor also has dynamic balancing adjustment block 7, bearing 8, transducer magnet steel seat 9 and transducer magnet steel 10; Transducer magnet steel seat 9 is positioned at dynamic balancing adjustment block 7 outsides; Fit in first multidiameter surface of end face of transducer magnet steel seat 9 and rotating shaft 1 one sides, transducer magnet steel 10 is consistent with magnet steel 3 in a circumferential direction; Bearing 8 is sheathed on the armature spindle 1, is positioned at transducer magnet steel seat 9 outsides.The level of described yoke 2 interior rings and vertical both direction are provided with 4 grooveds.Described stator winding is tubular winding 6.Described retaining ring 4 is sheathed on magnet steel 3 peripheries, with magnet steel 3 interference fit.The thickness of described retaining ring 4 is 0.5-0.8mm.Optimize, described transducer magnet steel seat 9 is made by nylon material.

Described yoke 2 and armature spindle 1 interference fit, magnet steel 3 Surface Mounts are in yoke 2, and retaining ring 4 is sheathed on magnet steel 3 peripheries, with magnet steel 3 interference fit; Described stator core 5 is slotless annulus, and tubular winding 6 is wound on the stator core 5, and the external diameter of tubular winding 6 and stator core 5 internal diameters are fitted.Be provided with dynamic balancing adjustment block 7 on the armature spindle 1, adjacent with yoke 2.Motor one end also is provided with transducer magnet steel seat 9 and transducer magnet steel 10; Transducer magnet steel seat 9 is between bearing 8 and dynamic balancing adjustment block 7; Fit in first multidiameter surface of end face of transducer magnet steel seat 9 and rotating shaft 1 one sides, transducer magnet steel 10 is consistent with magnet steel 3 in a circumferential direction.Bearing 8 is sheathed on the armature spindle 1, is positioned at transducer magnet steel seat 9 outsides.Stator core 5 forms by silicon steel sheet is stacking.Tubular winding 6 is two layer winding.The thickness of described retaining ring 4 is 0.5-0.8mm.Stator core 5 inwalls are provided with insulation film.Stator core 5 is DW310-35; Retaining ring rust steel 1Cr18Ni9Ti.

The present embodiment following table is every carries out calculation Design for parameter objectives:

Table 1 major parameter table

Electromagnetic structure design part:

One, key dimension is determined:

1. the efficient of looking ahead, no-load speed:

η′＝0.75 n ₀＝24000r/m

2. rated output, the motor long-term work:

$P^{\′}=\frac{1+2{\mathrm{\η}}^{\′}}{3{\mathrm{\η}}^{\′}}{P}_N=\frac{1+2\×0.75}{3\×0.75}\×2100=2333W$

3. prefetched lines is loaded:

A＝80A/cm＝8000A/m

4. the gap density of looking ahead:

B _δ＝0.65T

5. because this motor adopts watt shape rubidium iron boron magnet steel, so the effective pole arc coefficients of looking ahead is:

α _i＝0.9

6. the external diameter of determining rotor according to rated power and the rated speed of motor

D＝42mm

Get motor length:

L＝80mm

Its draw ratio then:

$\mathrm{\λ}=\frac{L}{D}=\frac{80}{42}\≈1.9$

7. because motor speed is higher, corresponding number of pole-pairs will be lacked.So get number of pole-pairs:

2P＝6

8. calculation stage distance:

$\mathrm{\τ}=\frac{\mathrm{\πD}}{2P}=\frac{3.14\×4.2}{2\×3}=2.198\mathrm{cm}$

9. determine magnet steel 3 sizes:

According to rotor structure and length thereof, adopt tile-shaped magnet steel in conjunction with Experience Design.Magnet steel 3 internal diameters are consistent with rotor diameter to be 42mm, and thickness is 4mm, and namely external diameter is 50mm.

10. the retaining ring size is definite:

Retaining ring 4 internal diameters are consistent with magnet steel 3 external diameters to be 50mm, for guarantee in the situation of its rigidity magnetic resistance again as much as possible little its thickness of getting be 1mm, then retaining ring 4 external diameters are 52mm.Retaining ring 4 adopts the stainless steel 1Cr18Ni9Ti of non-magnet material.

11. magnetic circuit calculates:

Magnet steel 3 producible total magnetic flux are:

ψ＝πDB _rLα _i×10 ^-4＝6.172×10 ^-3Wb

This motor adopts the mode of operation of three-phase six states, so its two-phase (conducting) magnetic flux is:

ψ ₂＝4.114656×10 ^-3Wb

12. number of conductors calculates:

Two phase conductors sum:

$N=\frac{60U_N(2\sqrt{\mathrm{\η}}-\mathrm{\η})}{{\mathrm{\ψ}}_2{n}_0}=\frac{60\×110\×(2\sqrt{0.75}-0.75)}{0.004114656\×24000}=65.63\≈66$

Then single-phasely be about 33.Consider the loop construction mode with virtual 18 grooves, then every phase coil will take 6 virtual grooves.Be that each virtual groove includes 5 wires.

13. conductor size is determined:

Get AJ=900 (A/cm) (A/mm ²), can obtain line current by specific electric load A=80A/cm:

J＝11.25A/mm ²

Estimate sectional area of wire:

$S_c=\frac{P_N}{U_N\mathrm{\ηJ}}=\frac{2100}{110\×0.75\×11.25\×{10}^6}=2.26{\mathrm{mm}}^2$

Calculating its diameter is: d=1.7mm.Obviously wire diameter is thicker, the coil winding difficulty.Be formed in parallel in order to overcome the generation of this situation, can adopt 15 wire diameters the thin wire that is 0.45mm.

14. determining of stator core size:

Determine that according to the external diameter of the number of turn of conductor coils and diameter and retaining ring 4, air gap etc. are comprehensive the internal diameter of stator core is 68mm, external diameter is 85mm.

As shown in Figure 1, rotor is made of armature spindle 1, yoke 2, magnet steel 3, retaining ring 4, bearing 8, transducer magnet steel seat 9, transducer magnet steel 10.Yoke 2 is annular; Surface-mount type is adopted in the installation of magnet steel 3, and situation about magnet steel 3 being thrown away when the high rotation speed operation of rotor occurring adds non-magnetic retaining ring 4 in the periphery of magnet steel 3, and material is stainless steel; The internal diameter of retaining ring 4 is slightly less than magnet steel 3 external diameters, and it cooperates is interference fit, the length of retaining ring 4 and magnet steel 3 equal in length; Because retaining ring 4 can produce magnetic resistance to magnetic flux, so its thickness is as much as possible little in the situation that does not affect rigidity, generally gets 0.5-0.8mm.

Described yoke 2 is loop configuration; Level and the vertical both direction of annular yoke inner ring are provided with 4 trench structures, and the notch cross sectional shape is identical with the spline grooved.Alleviate the weight of rotor, greatly improved the power of motor weight ratio, improved the frequency response of motor.

During installation, yoke 2 is pressed into rotating shaft 1, until till yoke 2 end faces and the applying of rotating shaft 1 shaft shoulder.Being pressed into rear rotating shaft 1 and yoke 2 is solidified as a whole.Magnet steel 3 is pasted on behind yoke 2 surfaces uniformly retaining ring 4 is sheathed on its outside.Fit in first multidiameter surface of the left side of transducer magnet steel seat 9 and rotating shaft 1 right side, being arranged on the circumferencial direction of transducer magnet steel 10 is consistent with magnet steel 3, and magnet steel seat 9 adopts the further weight reduction of nylon material of lightweight.Bearing 8 is sheathed on the armature spindle 1.

Stator core 5 usefulness silicon steel sheets are stacked into circular.Stator core 5 inwalls add insulation film makes motor integral body will reach the higher class of insulation.Tubular winding 6 adopts the virtual winding method that the groove motor is arranged.Its external diameter and stator core 5 internal diameters are fitted after the coiling; Internal diameter determines according to retaining ring 4 external diameters and size of gaps.Generally get tubular winding 6 internal diameters than retaining ring 4 external diameter 1mm-2mm.

A kind of aviation brushless slotless permanent magnet DC motor provided by the invention is simplified electric machine structure greatly, and power, volume ratio are improved greatly, improves the motor overload ability; Rotor weight saving, moment of inertia diminishes, and obviously improves rotating speed and the rapid starting/stopping ability of motor.

Certainly; in the situation that does not deviate from spirit of the present invention and essence thereof; those of ordinary skill in the art should make according to the present invention various corresponding changes and distortion, but these corresponding changes and distortion all should belong to the protection range of the appended claim of the present invention.

Claims (8)

1. an aviation brushless slotless permanent magnet DC motor comprises stator, rotor, casing, front end housing and rear end cap, is the internal rotor integral structure, and described rotor comprises yoke (2), it is characterized in that: described yoke (2) is loop configuration; Annular yoke (2) inner ring is provided with trench structure.

2. a kind of aviation brushless slotless permanent magnet DC motor according to claim 1, it is characterized in that: described rotor is armature spindle (1), yoke (2), magnet steel (3), retaining ring (4) from inside to outside successively; Stator is stator core (5), insulation film, stator winding from outside to inside successively; Stator core (5) forms by silicon steel sheet is stacking.

3. a kind of aviation brushless slotless permanent magnet DC motor according to claim 1, it is characterized in that: described motor also has dynamic balancing adjustment block (7), bearing (8), transducer magnet steel seat (9) and transducer magnet steel (10); Transducer magnet steel seat (9) is positioned at dynamic balancing adjustment block (7) outside; Fit in first multidiameter surface of end face of transducer magnet steel seat (9) and rotating shaft (1) one side, transducer magnet steel (10) is consistent with magnet steel (3) in a circumferential direction; Bearing (8) is sheathed on the armature spindle (1), is positioned at transducer magnet steel seat (9) outside.

4. a kind of aviation brushless slotless permanent magnet DC motor according to claim 1 is characterized in that: in the described yoke (2) level of ring and vertically both direction be provided with 4 grooveds.

5. a kind of aviation brushless slotless permanent magnet DC motor according to claim 2, it is characterized in that: described stator winding is tubular winding (6).

6. a kind of aviation brushless slotless permanent magnet DC motor according to claim 2, it is characterized in that: described retaining ring (4) is sheathed on magnet steel (3) periphery, with magnet steel (3) interference fit.

7. a kind of aviation brushless slotless permanent magnet DC motor according to claim 2, it is characterized in that: the thickness of described retaining ring (4) is 0.5-0.8mm.

8. a kind of aviation brushless slotless permanent magnet DC motor according to claim 3, it is characterized in that: described transducer magnet steel seat (9) is made by nylon material.

Images