CN105281465A - Variable-electrode-distance long primary bilateral linear induction motor - Google Patents
Variable-electrode-distance long primary bilateral linear induction motor Download PDFInfo
- Publication number
- CN105281465A CN105281465A CN201510738358.9A CN201510738358A CN105281465A CN 105281465 A CN105281465 A CN 105281465A CN 201510738358 A CN201510738358 A CN 201510738358A CN 105281465 A CN105281465 A CN 105281465A
- Authority
- CN
- China
- Prior art keywords
- launch
- electrode
- motor
- elementary
- line inductance
- 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.)
- Granted
Links
Landscapes
- Linear Motors (AREA)
- Control Of Ac Motors In General (AREA)
Abstract
The invention discloses a variable-electrode-distance long primary bilateral linear induction motor, which is applied to electromagnetic launch of a carrier-borne aircraft and serves as a driving power source. In the early-state design and manufacturing of the motor, electrode distances of the motor are made different at different launch displacement positions, an electrode distance continuous changing method can be adopted, an electrode distance segmented changing method can be adopted, and the motor can be machined by adopting a numerically-controlled machine tool in the manufacturing process. According to the variable-electrode-distance long primary bilateral linear induction motor, the launch speed or launch displacement does not need to be detected in the launch process of the carrier-borne aircraft, the current frequency and magnitude of a primary coil winding remain unchanged, and the launch control method is optimized. By adopting the structure of the variable-electrode-distance long primary bilateral linear induction motor, the problem of limited frequency of an inverter can be solved, the linear motor loss in the launch process of the carrier-borne aircraft can be reduced, the linear motor efficiency can be improved, and the linear motor control method can be simplified.
Description
Technical field
The present invention relates to carrier-borne aircraft electromagnetic launch technical field, be specifically related to long elementary bilateral line inductance electromotor and be used as linear drive system.
Background technology
At present, domestic and international electromagnetic launch drives linear electric motors mainly to adopt long elementary bilateral line inductance electromotor.Its electric machine structure is simple, and secondary mass is little, manufacture and operating cost low, safe and reliable to operation, inverter high-power switch device switching frequency is lower, can be applicable to preferably among carrier-borne aircraft electromagnetic ejection system.
But be permanent pole span linear electric motors for electromagnetic launch driving line inductance electromotor, by changing primary winding current frequency, change electromagnetic push size, and then control ejection speed.But in actual carrier-borne aircraft ejection process, the time is of short duration, continuous detection position and velocity magnitude, whole system is comparatively complicated.Actual ejection process is by the object of 25 tons, and the ejection orbit that 100m is long accelerates to 100m/s from static, used time 2s.Simplified analysis process, ignore air drag and outer friction power, ignore the traction power that aircraft self produces, suppose that the electromagnetic push that the tractive effort of ejection process is only produced by linear electric motors provides, and suppose that whole process is in permanent accelerator, namely ensure that electromagnetic push is invariable.The electromagnetic push then needing linear electric motors to produce is 1.25MN, linear electric motors energy supply 125MJ, power 62.5MW.
Traditional method of determining pole span bilateral line inductance electromotor employing change coil windings power frequency controls electromagnetic push and exports, control to adopt closed loop feedback to control, to constantly detect ejection speed or launch displacement, and extremely shortly only there is 2S the whole ejection process used time, control difficulty can be increased undoubtedly.Moreover along with the continuous increase of ejection speed, tradition determines power frequency needed for the long elementary bilateral line inductance electromotor of pole span constantly to be increased, and inevitable inverter frequency will be restricted, and during high speed, the increase of power frequency causes the loss of electric machine to increase.
Summary of the invention
In view of the shortcoming of prior art, the object of the invention is to design the elementary bilateral line inductance electromotor of a kind of pole-changing distance, make it the shortcoming overcoming prior art.
The object of the invention is by following method realize.
The elementary bilateral line inductance electromotor of pole-changing distance, primarily of being applied to aircraft carrier electromagnetic launch as the power source driven, bilateral line inductance electromotor is primarily of secondary aluminium sheet 1 and the elementary formation of length being symmetrically placed in the upper and lower both sides of aluminium sheet, length is elementary to be made up of elementary iron core and the multiple coil windings be entrenched in elementary iron core, the direction of motion of level aluminium sheet successively, i.e. long ejection orbit direction, adjacent two coil windings are that polar distance is arranged.
Further, described polar distance is arranged can adopt pole span continuous transformation mode, can also adopt pole span segmentation variation pattern.
Described pole span is continuous, namely refers to, in the direction of motion of level aluminium sheet successively, the pole span between each coil windings increases continuously; Described pole span segmentation change, namely refers to, in the direction of motion of level aluminium sheet successively, adjacent two or more coil windings has pole span A and forms one group, and adjacent two or more coil windings has pole span B and forms another group in addition.
Adopt such structure, the elementary bilateral line inductance electromotor of pole-changing distance for aircraft carrier electromagnetic launch is at the diverse location place of 100 meters of long ejection orbits, the pole span of bilateral line inductance electromotor is unequal, pole span continuous transformation mode can be adopted, pole span segmentation variation pattern can also be adopted, whole carrier-borne aircraft ejection process, size of current, the frequency of primary coil winding all remain unchanged.
Adopt structure of the present invention, manufacture also relatively easy, only need when the design processing and manufacturing of motor initial stage, different displacement place, manufactures motor pole span different, and motor pole span can consecutive variations, also sectional change, and manufacture process can adopt that Digit Control Machine Tool is convenient to be processed.Adopt the bilateral line inductance electromotor of polar distance as launching driving, without the need to detecting ejection speed and displacement, primary winding current size, power frequency are constant, then along with the continuous increase of ejection speed, inverter frequency restriction can not be subject to, also can not increase the loss of electric machine, because power frequency is constant, launch control mode and to be optimized and easier.
From the above mentioned, under rational design condition, adopt structure of the present invention, namely can meet aircraft carrier carrier-borne aircraft and launch requirement, can also optimize and launch control mode.Power frequency can be fixed on a suitable value by ejection process, and then avoids the loss of electric machine to increase.
Accompanying drawing is described as follows:
Accompanying drawing 1 is long elementary bilateral line inductance electromotor structure chart.
Accompanying drawing 2 is determined pole span for prior art and is grown elementary bilateral line inductance electromotor longitdinal cross-section diagram.
Accompanying drawing 3 is the elementary bilateral line inductance electromotor longitdinal cross-section diagram of pole-changing distance of the present invention.
Accompanying drawing 4 is determined pole span for prior art and is grown elementary bilateral line inductance electromotor primary structure figure.
Accompanying drawing 5 is the elementary bilateral line inductance electromotor primary structure figure of pole-changing distance of the present invention.
Accompanying drawing 6 determines the long elementary bilateral line inductance electromotor of pole span and the simulation analysis figure launching displacement and power frequency relation corresponding to the elementary bilateral line inductance electromotor of pole-changing distance.
Accompanying drawing 7 be determine the long elementary bilateral line inductance electromotor of pole span and the elementary bilateral line inductance electromotor of pole-changing distance corresponding launch displacement and the simulation analysis figure launching displacement relation.
Fig. 8 is the elementary bilateral line inductance electromotor design parameter of pole-changing distance.
Fig. 9 be the elementary bilateral line inductance electromotor of pole-changing distance surely frequently 200Hz time, the motor pole span value corresponding to different ejection seat, speed.
Embodiment
Below in conjunction with accompanying drawing, the present invention is described in further detail.
Fig. 1 is line inductance electromotor part-structure figure.Line inductance electromotor all adopts slotless Winding Design, and can effectively reduce volume and eliminate the slot ripples impact of air-gap field, secondary plate adopts aluminum, and quality is light, is beneficial to and launches requirement.
Two kinds of dissimilar line inductance electromotor structural representations are respectively shown in Fig. 2 and Fig. 3.Determine pole span line inductance electromotor winding spacing constant, polar distance line inductance electromotor winding spacing consecutive variations; Stator takes sectional power supply mode to put forward high-tension utilance; Shown in Fig. 8.Demand is launched according to actual carrier-borne aircraft, and ignore the traction power of carrier-borne aircraft self and extraneous frictional resistance, the tractive effort hypothesis of process need only has line inductance electromotor to provide, and think that electromagnetic push is constant, for 1.25MN, then can derive the elementary bilateral line inductance electromotor parameter of structure design of pole-changing distance.
Adopt the method derivation line inductance electromotor electromagnetic push expression formula of equivalent electric circuit.
In formula, m
1for the armature winding number of phases; I
1, I
2be respectively elementary phase current and secondary conversion to elementary phase current; k
αfor the proportionality coefficient of secondary and first level length; S is slip, s=(V
s-V
x)/V
s, V
sand V
xbe respectively primary electrical fluid layer and secondary along x-axis translational speed, V
s=2 τ f, f are Rated motor frequency; R'
2for secondary conversion is to elementary resistance; x
mfor excitation reactance.
In formula, d
1for elementary interferric width 1/2; k
ωfor armature winding coefficient, be the product of breadth coefficient and chording factor, value k
ω=1; ω
1for armature winding is in series the number of turn; σ
sfor secondary conductor surface conductivity, σ
s=σ d
2, σ and d
2be respectively secondary conductor bulk conductivity and secondary conductor thickness 1/2, σ value 3.53 × 10
7s/m; P is motor number of pole-pairs; τ is motor pole span, and pole span changes; μ
0for permeability of vacuum, value 4 π × 10
-7h/m; δ
efor the effective electromagnetism air gap of motor, δ
e=k
μk
δδ, k
μand k
δbe respectively iron core cutter coefficient and Carter's coefficient, δ is electromechanics air gap.Fig. 4, Fig. 5 sets forth the tangent plane structure of determining the long elementary bilateral line inductance electromotor of pole span and the elementary bilateral line inductance electromotor primary part of pole-changing distance.
Shown in Fig. 9.According to theory analysis modeling, simulation analysis proof theory calculates validity, and provides guarantee primary winding current size 340A, and power frequency 200Hz is constant, when electromagnetic push 1.25MN is constant, and the motor pole span value corresponding to different ejection seat.Experimental verification pole-changing distance preliminary linear induction motor is as the motor-driven feasibility of carrier-borne aircraft.
Shown in Fig. 6.Launch needs to meet carrier-borne aircraft, assuming that the electromagnetic push that motor provides is constant, during for 1.25MN, pole span is fixing to be changed with pole span, the power frequency relation needed for different displacement friction speed.When pole span is constant, ejection process adopts and controls power frequency control electromagnetic push, and pole span is constant is 0.30m, and ejection process power frequency constantly increases.1m displacement place, namely during speed 10m/s, power frequency 98Hz; 10m displacement place, namely during speed 31.62m/s, power frequency 134.0Hz; When speed is increased to 100m/s, i.e. 100m carrier-borne aircraft takeoff setting place, power frequency is increased to 248.0Hz.Whole ejection process slip-frequency is constant is about 81.3Hz, and revolutional slip s is reduced to 0.33 successively by 0.83.
Shown in Fig. 7.When adopting the bilateral line inductance electromotor of polar distance to launch, control power frequency 200Hz and fix, same guarantee 1.25MN is constant, adopting different displacement place motor pole span different designs scheme, completing carrier-borne aircraft and launching when designing motor.1m displacement place, namely during speed 10m/s, pole span value 0.231m; 10m displacement place, namely during speed 31.62m/s, pole span value 0.252m; 100m carrier-borne aircraft takeoff setting, during speed 100m/s, pole span value 0.343m.Whole ejection process slip-frequency is reduced to 54.23Hz successively by 178.35Hz, and revolutional slip s is reduced to 0.23 successively by 0.89.
With the present invention and existingly determine the long elementary bilateral line inductance electromotor of pole span and carry out emulation experiment and contrast for launching driving and can find out, polar distance line inductance electromotor ejection process power frequency remains unchanged, and at high speed stage, required power frequency is less than tradition to be determined pole span line inductance electromotor ejection and needs frequency values.
In sum, the elementary bilateral line inductance electromotor of pole-changing distance of the present invention can reduce the loss of electric machine, optimizes Electric Machine Control, practicable.Carrier-borne aircraft electromagnetic launch task can be completed well.
The above-mentioned specific descriptions for preferred embodiment; those of ordinary skill in the art will appreciate that; embodiment described here is to help reader understanding's principle of the present invention, should be understood to that the protection range invented is not limited to so special statement and embodiment.Everyly make various possible equivalent replacement or change according to foregoing description, be all considered to belong to the protection range of claim of the present invention.
Claims (2)
1. the elementary bilateral line inductance electromotor of pole-changing distance, primarily of being applied to aircraft carrier electromagnetic launch as the power source driven, bilateral line inductance electromotor is primarily of secondary aluminium sheet 1 and the elementary formation of length being symmetrically placed in the upper and lower both sides of aluminium sheet, length is elementary to be become with the multiple coil windings be entrenched in elementary iron core by elementary iron core, it is characterized in that, the direction of motion of level aluminium sheet successively, i.e. long ejection orbit direction, adjacent two coil windings are that polar distance is arranged.
2. the elementary bilateral line inductance electromotor of pole-changing distance according to claim 1, is characterized in that, described polar distance is arranged can adopt pole span continuous transformation mode, can also adopt pole span segmentation variation pattern.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510738358.9A CN105281465B (en) | 2015-11-03 | 2015-11-03 | The primary bilateral line inductance electromotor of pole-changing distance |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510738358.9A CN105281465B (en) | 2015-11-03 | 2015-11-03 | The primary bilateral line inductance electromotor of pole-changing distance |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN105281465A true CN105281465A (en) | 2016-01-27 |
| CN105281465B CN105281465B (en) | 2018-10-30 |
Family
ID=55149984
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201510738358.9A Expired - Fee Related CN105281465B (en) | 2015-11-03 | 2015-11-03 | The primary bilateral line inductance electromotor of pole-changing distance |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN105281465B (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105915018A (en) * | 2016-05-20 | 2016-08-31 | 南京航空航天大学 | Composite phase belt winding structure for two-armature cylinder-type permanent magnet synchronous linear motor |
| CN110190726A (en) * | 2019-05-30 | 2019-08-30 | 西南交通大学 | Mover, pole spans formula double-fed linear motor and its design method such as not |
| CN111208457A (en) * | 2019-12-18 | 2020-05-29 | 清华大学 | Novel magnetostriction measurement method and device |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN203698673U (en) * | 2013-12-04 | 2014-07-09 | 中国科学院宁波材料技术与工程研究所 | Permanent magnet linear ejection device |
| CN104691776A (en) * | 2013-12-04 | 2015-06-10 | 中国科学院宁波材料技术与工程研究所 | Permanent magnet linear launch device |
| CN205429917U (en) * | 2015-11-03 | 2016-08-03 | 西南交通大学 | Pole change is apart from growing elementary bilateral linear induction motor |
| EP3076533A1 (en) * | 2014-03-12 | 2016-10-05 | National Institute of Technology | Linear motor |
-
2015
- 2015-11-03 CN CN201510738358.9A patent/CN105281465B/en not_active Expired - Fee Related
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN203698673U (en) * | 2013-12-04 | 2014-07-09 | 中国科学院宁波材料技术与工程研究所 | Permanent magnet linear ejection device |
| CN104691776A (en) * | 2013-12-04 | 2015-06-10 | 中国科学院宁波材料技术与工程研究所 | Permanent magnet linear launch device |
| EP3076533A1 (en) * | 2014-03-12 | 2016-10-05 | National Institute of Technology | Linear motor |
| CN205429917U (en) * | 2015-11-03 | 2016-08-03 | 西南交通大学 | Pole change is apart from growing elementary bilateral linear induction motor |
Non-Patent Citations (1)
| Title |
|---|
| 张昆仑，刘希军，张文龙: "长初级双边直线感应电机推力输出研究", 《铁道工程学报》 * |
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105915018A (en) * | 2016-05-20 | 2016-08-31 | 南京航空航天大学 | Composite phase belt winding structure for two-armature cylinder-type permanent magnet synchronous linear motor |
| CN105915018B (en) * | 2016-05-20 | 2018-06-01 | 南京航空航天大学 | A kind of compound phase band winding construction of double armature cylindrical permanent linear synchronous motor |
| CN110190726A (en) * | 2019-05-30 | 2019-08-30 | 西南交通大学 | Mover, pole spans formula double-fed linear motor and its design method such as not |
| CN111208457A (en) * | 2019-12-18 | 2020-05-29 | 清华大学 | Novel magnetostriction measurement method and device |
| CN111208457B (en) * | 2019-12-18 | 2021-05-18 | 大连理工大学 | Novel magnetostriction measurement method and device |
Also Published As
| Publication number | Publication date |
|---|---|
| CN105281465B (en) | 2018-10-30 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN205429917U (en) | Pole change is apart from growing elementary bilateral linear induction motor | |
| EP2999652B1 (en) | Self-propelled elevator with wireless power supply | |
| Sulaiman et al. | Design study and experimental analysis of wound field flux switching motor for HEV applications | |
| EP3151396B1 (en) | Rotary electric machine controller and system | |
| US20140167894A1 (en) | Electric machine having a low-mass design in magnetically active parts | |
| CN105281465A (en) | Variable-electrode-distance long primary bilateral linear induction motor | |
| CN103762821B (en) | electromagnetic brake linear motor system and control method thereof | |
| CN101478272A (en) | Linear induction repelling float motor | |
| CN103236774A (en) | Bilateral flat-plate type linear motor | |
| Lu et al. | Performance analysis of linear induction motor for electromagnetic catapult | |
| Sun et al. | DSSRM design with multiple pole arcs optimization for high torque and low torque ripple applications | |
| CN115333323A (en) | Double-side-length stator segmented parallel power supply asynchronous linear motor driving structure and power supply method | |
| Sulaiman et al. | Field-excited flux switching motor design, optimization and analysis for future hybrid electric vehicle using finite element analysis | |
| Aydin et al. | Comparing various PM synchronous generators: a feasible solution for high-power, off-highway, series hybrid, electric traction applications | |
| CN103248312A (en) | Control method based on linear servo motor | |
| Eastham | Iron-cored linear synchronous machines | |
| Samimi et al. | Investigation of multi-layer secondary concept of an electromagnetic launcher | |
| CN201336640Y (en) | Linear induction suspending-repelling electric motor | |
| CN202076918U (en) | Low positioning force high thrust linear switch magnetic flux permanent magnet motor | |
| Hirayama et al. | Study on transfer system with both long-distance driving and high positioning accuracy using linear switched reluctance motor | |
| Sampath et al. | Design, development and electromagnetic analysis of a linear induction motor | |
| Suryawanshi et al. | Analysis of linear induction motor for Aircraft Launch System considering end-effects | |
| Chirkov et al. | Improving the efficiency of an electric drive with a cylindrical linear alternating current electronic engine | |
| Ganesh Sampath et al. | Design, Development and Electromagnetic Analysis of a Linear Induction Motor | |
| CN111884476B (en) | Linear homopolar motor and control method |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20181030 Termination date: 20201103 |
|
| CF01 | Termination of patent right due to non-payment of annual fee |