CN110912464A - Aircraft engine starting controller with active filtering function and starting/electric energy quality control system formed by aircraft engine starting controller - Google Patents
Aircraft engine starting controller with active filtering function and starting/electric energy quality control system formed by aircraft engine starting controller Download PDFInfo
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- CN110912464A CN110912464A CN201911246734.7A CN201911246734A CN110912464A CN 110912464 A CN110912464 A CN 110912464A CN 201911246734 A CN201911246734 A CN 201911246734A CN 110912464 A CN110912464 A CN 110912464A
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- H—ELECTRICITY
- H02—GENERATION; CONVERSION OR DISTRIBUTION OF ELECTRIC POWER
- H02P—CONTROL OR REGULATION OF ELECTRIC MOTORS, ELECTRIC GENERATORS OR DYNAMO-ELECTRIC CONVERTERS; CONTROLLING TRANSFORMERS, REACTORS OR CHOKE COILS
- H02P1/00—Arrangements for starting electric motors or dynamo-electric converters
- H02P1/16—Arrangements for starting electric motors or dynamo-electric converters for starting dynamo-electric motors or dynamo-electric converters
- H02P1/26—Arrangements for starting electric motors or dynamo-electric converters for starting dynamo-electric motors or dynamo-electric converters for starting an individual polyphase induction motor
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- H—ELECTRICITY
- H02—GENERATION; CONVERSION OR DISTRIBUTION OF ELECTRIC POWER
- H02J—CIRCUIT ARRANGEMENTS OR SYSTEMS FOR SUPPLYING OR DISTRIBUTING ELECTRIC POWER; SYSTEMS FOR STORING ELECTRIC ENERGY
- H02J3/00—Circuit arrangements for ac mains or ac distribution networks
- H02J3/01—Arrangements for reducing harmonics or ripples
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- H—ELECTRICITY
- H02—GENERATION; CONVERSION OR DISTRIBUTION OF ELECTRIC POWER
- H02J—CIRCUIT ARRANGEMENTS OR SYSTEMS FOR SUPPLYING OR DISTRIBUTING ELECTRIC POWER; SYSTEMS FOR STORING ELECTRIC ENERGY
- H02J3/00—Circuit arrangements for ac mains or ac distribution networks
- H02J3/18—Arrangements for adjusting, eliminating or compensating reactive power in networks
- H02J3/1821—Arrangements for adjusting, eliminating or compensating reactive power in networks using shunt compensators
- H02J3/1835—Arrangements for adjusting, eliminating or compensating reactive power in networks using shunt compensators with stepless control
- H02J3/1842—Arrangements for adjusting, eliminating or compensating reactive power in networks using shunt compensators with stepless control wherein at least one reactive element is actively controlled by a bridge converter, e.g. active filters
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02E—REDUCTION OF GREENHOUSE GAS [GHG] EMISSIONS, RELATED TO ENERGY GENERATION, TRANSMISSION OR DISTRIBUTION
- Y02E40/00—Technologies for an efficient electrical power generation, transmission or distribution
- Y02E40/30—Reactive power compensation
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02E—REDUCTION OF GREENHOUSE GAS [GHG] EMISSIONS, RELATED TO ENERGY GENERATION, TRANSMISSION OR DISTRIBUTION
- Y02E40/00—Technologies for an efficient electrical power generation, transmission or distribution
- Y02E40/40—Arrangements for reducing harmonics
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- Engineering & Computer Science (AREA)
- Power Engineering (AREA)
- Motor And Converter Starters (AREA)
- Supply And Distribution Of Alternating Current (AREA)
- Control Of Eletrric Generators (AREA)
Abstract
The invention provides an aircraft engine starting controller with an active filtering function and a starting/electric energy quality control system formed by the aircraft engine starting controller, wherein when the controller works in a starting mode, an aircraft provides a direct-current power supply for the controller, the controller inverts the direct-current power supply into three-phase variable-frequency alternating current to be output to a main generator stator winding of a three-level synchronous motor, and the three-level synchronous motor drives an aircraft engine to complete starting; after starting, the controller works in an active filtering mode, and the output of the controller passes through an alternating current bus bar on a filter inductor access machine; the controller calculates to obtain harmonic components by detecting the voltage and current of the onboard power grid and generates compensation current with the same size and the opposite direction of the harmonic, so that the aim of harmonic suppression is fulfilled, and comprehensive centralized compensation of harmonic, reactive and unbalanced of the onboard power grid is realized.
Description
Technical Field
The invention relates to the technical field of aviation power supplies, in particular to an aircraft engine starting controller with an active filtering function and a starting/electric energy quality control system formed by the same.
Background
Currently, in an aircraft power system, an engine ac starting system has gradually replaced an engine dc starting system. After the starting of the ac starting controller is completed, the controller is generally left idle, or as a controller for the motor of other actuating equipment with smaller capacity, the capacity of the engine starting controller cannot be fully utilized.
On the other hand, with the development of 'multi-electric aircraft' and 'full-electric aircraft', airborne electronic equipment is more and more, and harmonic waves, reactive power, unbalance and other components pollute an aircraft alternating current power grid, affect the aircraft power supply quality, reduce the performance of electric equipment and the service life of the equipment, seriously even endanger the safety of a power supply system, and cause flight accidents. For the harmonic pollution of an airplane Power grid, the conventional airplane mostly achieves the purpose of harmonic suppression by an LC passive filtering scheme, a multi-pulse rectification scheme and an additional Power Factor Correction (PFC) device at the front stage of an AC/DC Power supply, but the methods have respective defects. The passive filter has heavy weight and is difficult to optimize and design, and the application of the technology is greatly limited along with the continuous development of an aviation variable-frequency alternating-current system; the transformer in the multi-pulse rectification technology has large volume and weight, and the number of the phase-shifting transformers which need to be connected in parallel is continuously increased when a better filtering effect is achieved; PFC only corrects power for a single powered device.
Disclosure of Invention
The Active Power Filters (APF) can accurately compensate harmonic current, reactive Power, unbalanced current and the like of a Power grid and control the Power quality of the Power grid.
The AC starting controller and the APF are essentially voltage source type three-phase inverters, and if the working state of the aircraft can be combined and the power circuit and the control circuit of the AC starting controller and the APF are shared, the power supply quality of an AC power grid of the aircraft can be improved and the weight of a power supply can be reduced under the condition of complicated electric equipment.
Based on the thought, the invention provides an aircraft engine starting controller with an active filtering function and a starting/power quality control system formed by the aircraft engine starting controller, wherein the starting controller is called as a multifunctional controller, the multifunctional controller works in a starting mode in the starting process to drive a three-stage synchronous motor to rotate so as to provide power for starting an engine, after the starting is completed and is switched into a power generation mode, the controller output is connected to an aircraft alternating current bus bar through line switching, and the multifunctional controller works in an APF mode to perform comprehensive harmonic wave, reactive power and unbalance compensation on the aircraft alternating current bus bar.
The technical scheme of the invention is as follows:
the aircraft engine starting controller with the active filtering function is characterized in that:
when the controller works in a starting mode, the airplane provides a direct-current power supply for the controller, the controller inverts the direct-current power supply into three-phase variable-frequency alternating current and outputs the three-phase variable-frequency alternating current to a main generator stator winding of a three-level synchronous motor in an airborne aviation power supply system, and the three-level synchronous motor drives an airplane engine to complete starting;
when the starting is finished, the starting power supply is disconnected, the three-stage synchronous motor works in a power generation mode to generate three-phase alternating current, the controller works in an active filtering mode, and the output of the controller is connected to an alternating current bus bar on the motor through a filter inductor; the controller calculates to obtain harmonic components by detecting the voltage and current of the onboard power grid, and generates compensation current with the same size and the opposite direction of the harmonic, so that the aim of harmonic suppression is fulfilled, and comprehensive centralized compensation of harmonic, reactive and unbalanced of the onboard power grid is realized.
In a further preferred aspect, the aircraft engine starting controller with an active filtering function is characterized in that: the three-phase inverter comprises a three-phase inverter power circuit, a sampling circuit, a control circuit and a driving circuit;
in a starting mode, a controller sampling circuit monitors input direct-current bus voltage, three-phase current output by inversion and three-level synchronous motor rotating speed signals, obtains a driving control signal in a control circuit according to a vector control method, drives a three-phase inversion power circuit through a driving circuit and outputs three-phase variable-frequency alternating current, so that the starting and fault detection protection functions are realized;
after the three-stage synchronous motor is started, the controller sampling circuit monitors three-phase alternating current voltage, three-phase load current and direct current bus voltage output by the three-stage synchronous motor, active filtering reference current is calculated in the control circuit, feedback signals of the reference current and the active filtering compensation current are controlled through hysteresis current to obtain PWM driving signals, and the PWM driving signals control a switching tube in the three-stage inversion power circuit through the driving circuit, so that harmonic current compensation is realized, and the power quality of a power grid is improved.
The starting/power quality control system with the controller is characterized in that: the system comprises a controller, an aircraft engine, a three-stage synchronous motor and an electricity load;
an external power contactor EPC is arranged between a direct current power supply on the airplane and the controller, a starting excitation contactor SEC and a starting contactor SC are arranged between the controller and the three-stage synchronous motor, a power generation contactor GC is arranged between the three-stage synchronous motor and an electric load, and an active filter contactor APFC is arranged between the controller and the electric load;
when the controller works in a starting mode, the outer power supply contactor EPC, the starting excitation contactor SEC and the starting contactor SC are switched on, the airplane provides a direct-current power supply for the controller, the controller inverts the direct-current power supply into three-phase variable-frequency alternating current and outputs the three-phase variable-frequency alternating current to a main generator stator winding of the three-level synchronous motor, and the three-level synchronous motor drives an airplane engine to complete starting;
after starting, a starting excitation contactor SEC and a starting contactor SC are disconnected, a power generation contactor GC and an active filter contactor APFC are connected, the three-stage synchronous motor works in a power generation mode to generate three-phase alternating current, the controller works in an active filter mode, and the output of the controller passes through an alternating current bus bar on a filter inductor access machine; the controller calculates to obtain harmonic components by detecting the voltage and current of the onboard power grid and generates compensation current with the same size and the opposite direction of the harmonic, so that the aim of harmonic suppression is fulfilled, and comprehensive centralized compensation of harmonic, reactive and unbalanced of the onboard power grid is realized.
Advantageous effects
The invention realizes the integrated design of starting/airplane power grid electric energy quality control, the system can not only complete the starting function of the aircraft engine, when the multifunctional controller works in an active filtering mode, the formed system can realize the concentrated accurate compensation of the harmonic wave, the reactive power and the unbalanced component of the airplane power grid, and the whole airplane power supply quality is reduced.
Additional aspects and advantages of the invention will be set forth in part in the description which follows and, in part, will be obvious from the description, or may be learned by practice of the invention.
Drawings
The above and/or additional aspects and advantages of the present invention will become apparent and readily appreciated from the following description of the embodiments, taken in conjunction with the accompanying drawings of which:
FIG. 1 is a block diagram of a start/power quality control system employing a multi-function controller having an APF function and an aircraft engine start function;
FIG. 2 is an electrical schematic of the start-up state, APF state; (the excitation circuit during start-up is not shown in fig. 2, and this part may employ either a two-phase excitation or a three-phase excitation scheme).
Detailed Description
The following detailed description of embodiments of the invention is intended to be illustrative, and not to be construed as limiting the invention.
In the present embodiment, a 115V/400Hz ac power source is taken as an example, and fig. 1 illustrates a block diagram of a starting/power quality control system using a multifunctional controller having an APF function and an aircraft engine starting function, including the multifunctional controller, an aircraft engine, a three-stage synchronous motor, and a power load.
An outer power supply contactor EPC is arranged between a direct current power supply and a multifunctional controller on the airplane, a starting excitation contactor SEC and a starting contactor SC are arranged between the multifunctional controller and a three-stage synchronous motor, a power generation contactor GC is arranged between the three-stage synchronous motor and an electric load, and an active filter contactor APFC is arranged between the multifunctional controller and the electric load.
The contactor status is shown in table 1:
TABLE 1 starting and active Filter mode contactor states
When the multifunctional controller works in a starting mode, the outer power supply contactor EPC, the starting excitation contactor SEC and the starting contactor SC are connected, the airplane provides a 270V direct-current power supply for the multifunctional controller, the multifunctional controller inverts 270VDC into three-phase variable-frequency alternating current to be output to a main generator stator winding of the three-level synchronous motor, and the three-level synchronous motor drives an airplane engine to complete starting. In a static state of the three-stage synchronous motor, alternating current introduced into an exciter exciting winding forms a rotating magnetic field in an exciter air gap, an exciter rotor armature winding cuts the rotating magnetic field to generate induction current, and the induction current flows through a rotating rectifier to be rectified to supply power for the main generator in an exciting way. The main generator stator winding adjusts armature current through a response vector control strategy, so that the rotating speed of the motor is controlled, and the starting function of the aero-engine is realized.
When the starting is finished, the starting excitation contactor SEC and the starting contactor SC are disconnected, the power generation contactor GC and the active filter contactor APFC are connected, the three-stage synchronous motor works in a power generation mode to generate three-phase alternating current, the working mode is switched into the active filter mode by the multifunctional controller, and the output of the multifunctional controller passes through an alternating current bus bar on the filter inductor access machine; the multifunctional controller calculates to obtain harmonic components by detecting the voltage and current of the onboard power grid and generates compensation current with the same size and the opposite direction of the harmonic, so that the aim of harmonic suppression is fulfilled, and comprehensive centralized compensation of harmonic, reactive and unbalanced of the onboard power grid is realized.
Fig. 2 depicts an electrical schematic diagram of a starting state (an excitation control part is not marked in the diagram) and an APF state, and mainly comprises a three-phase inverter power circuit, a sampling circuit, a control circuit and a driving circuit. The energy in the starting and active filtering modes is single-phase flow and is from the direct current side to the alternating current side, and the two modes share a main power part, a driving circuit and a control circuit; but the voltage monitoring point, the current monitoring point, the control algorithm, the motor working state and the like in the two modes are different.
In a starting mode, the sampling circuit of the multifunctional controller monitors input direct-current bus voltage, three-phase current output by inversion and three-level synchronous motor rotating speed signals, obtains a driving control signal in the control circuit according to a vector control method, drives a three-phase inversion power circuit through the driving circuit, and outputs three-phase variable-frequency alternating current, so that the starting and fault detection protection functions are realized.
After the start is finished, the starting excitation contactor SEC and the starting contactor SC are disconnected, the power generation contactor GC and the active filter contactor APFC are connected, the three-stage synchronous motor works in a power generation mode and emits 115V/400Hz three-phase alternating current, and the multifunctional controller switches the working mode to be the active filter mode. The controller sampling circuit monitors three-phase alternating current voltage, three-phase load current and direct current bus voltage output by the three-level synchronous motor, active filtering reference current is calculated in the control circuit, feedback signals of the reference current and the active filtering compensation current are subjected to hysteresis current control to obtain PWM driving signals, and the PWM driving signals control 6 switching tubes in the three-phase inversion power circuit through the driving circuit, so that harmonic current compensation is realized, and the power quality of a power grid is improved.
Although embodiments of the present invention have been shown and described above, it is understood that the above embodiments are exemplary and should not be construed as limiting the present invention, and that variations, modifications, substitutions and alterations can be made in the above embodiments by those of ordinary skill in the art without departing from the principle and spirit of the present invention.
Claims (3)
1. An aeroengine starts controller with active filtering function which characterized in that:
when the controller works in a starting mode, the airplane provides a direct-current power supply for the controller, the controller inverts the direct-current power supply into three-phase variable-frequency alternating current and outputs the three-phase variable-frequency alternating current to a main generator stator winding of a three-level synchronous motor in an airborne aviation power supply system, and the three-level synchronous motor drives an airplane engine to complete starting;
when the starting is finished, the starting power supply is disconnected, the three-stage synchronous motor works in a power generation mode to generate three-phase alternating current, the controller works in an active filtering mode, and the output of the controller is connected to an alternating current bus bar on the motor through a filter inductor; the controller calculates to obtain harmonic components by detecting the voltage and current of the onboard power grid, and generates compensation current with the same size and the opposite direction of the harmonic, so that the aim of harmonic suppression is fulfilled, and comprehensive centralized compensation of harmonic, reactive and unbalanced of the onboard power grid is realized.
2. An aircraft engine start controller with active filtering as claimed in claim 1, wherein: the three-phase inverter comprises a three-phase inverter power circuit, a sampling circuit, a control circuit and a driving circuit;
in a starting mode, a controller sampling circuit monitors input direct-current bus voltage, three-phase current output by inversion and three-level synchronous motor rotating speed signals, obtains a driving control signal in a control circuit according to a vector control method, drives a three-phase inversion power circuit through a driving circuit and outputs three-phase variable-frequency alternating current, so that the starting and fault detection protection functions are realized;
after the three-stage synchronous motor is started, the controller sampling circuit monitors three-phase alternating current voltage, three-phase load current and direct current bus voltage output by the three-stage synchronous motor, active filtering reference current is calculated in the control circuit, feedback signals of the reference current and the active filtering compensation current are controlled through hysteresis current to obtain PWM driving signals, and the PWM driving signals control a switching tube in the three-stage inversion power circuit through the driving circuit, so that harmonic current compensation is realized, and the power quality of a power grid is improved.
3. A start/power quality control system having the controller of claim 1, wherein: the system comprises a controller, an aircraft engine, a three-stage synchronous motor and an electricity load;
an external power contactor EPC is arranged between a direct current power supply on the airplane and the controller, a starting excitation contactor SEC and a starting contactor SC are arranged between the controller and the three-stage synchronous motor, a power generation contactor GC is arranged between the three-stage synchronous motor and an electric load, and an active filter contactor APFC is arranged between the controller and the electric load;
when the controller works in a starting mode, the outer power supply contactor EPC, the starting excitation contactor SEC and the starting contactor SC are switched on, the airplane provides a direct-current power supply for the controller, the controller inverts the direct-current power supply into three-phase variable-frequency alternating current and outputs the three-phase variable-frequency alternating current to a main generator stator winding of the three-level synchronous motor, and the three-level synchronous motor drives an airplane engine to complete starting;
after starting, a starting excitation contactor SEC and a starting contactor SC are disconnected, a power generation contactor GC and an active filter contactor APFC are connected, the three-stage synchronous motor works in a power generation mode to generate three-phase alternating current, the controller works in an active filter mode, and the output of the controller passes through an alternating current bus bar on a filter inductor access machine; the controller calculates to obtain harmonic components by detecting the voltage and current of the onboard power grid and generates compensation current with the same size and the opposite direction of the harmonic, so that the aim of harmonic suppression is fulfilled, and comprehensive centralized compensation of harmonic, reactive and unbalanced of the onboard power grid is realized.
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Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111585498A (en) * | 2020-06-03 | 2020-08-25 | 能科科技股份有限公司 | Variable-frequency speed regulation control system with load observer and frequency converter |
| CN113992080A (en) * | 2021-11-29 | 2022-01-28 | 中国商用飞机有限责任公司 | Starting power generation control method, system and medium capable of actively suppressing harmonic waves |
| CN117200648A (en) * | 2023-11-07 | 2023-12-08 | 浙江大学 | Control device for power supply harmonic wave of alternating current motor driven by multiple inverters |
Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4043119A (en) * | 1976-02-20 | 1977-08-23 | Sundstrand Corporation | Acceleration and speed control circuit for jet engine accessory equipment |
| CN102780443A (en) * | 2012-08-14 | 2012-11-14 | 西北工业大学 | Aerial three-level electric excitation motor starting control method and aerial three-level electric excitation motor starting control device |
| CN102904284A (en) * | 2012-11-11 | 2013-01-30 | 李木 | Energy-saving triphase wind power generation system and control method thereof |
| CN105207334A (en) * | 2014-06-23 | 2015-12-30 | 通用电气能源能量变换技术有限公司 | Power supply system for a load and corresponding supply method |
| CN105429179A (en) * | 2015-12-22 | 2016-03-23 | 山东华天电气有限公司 | Special filtering energy feedback apparatus and control method for pumping unit |
| CN108880363A (en) * | 2018-05-31 | 2018-11-23 | 南京航空航天大学 | Three-level formula brushless synchronous machine asynchronous starting control method and system |
| CN108964532A (en) * | 2018-05-31 | 2018-12-07 | 南京航空航天大学 | Three-level formula brushless synchronous machine sublevel segmentation start control system and method |
-
2019
- 2019-12-07 CN CN201911246734.7A patent/CN110912464A/en active Pending
Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4043119A (en) * | 1976-02-20 | 1977-08-23 | Sundstrand Corporation | Acceleration and speed control circuit for jet engine accessory equipment |
| CN102780443A (en) * | 2012-08-14 | 2012-11-14 | 西北工业大学 | Aerial three-level electric excitation motor starting control method and aerial three-level electric excitation motor starting control device |
| CN102904284A (en) * | 2012-11-11 | 2013-01-30 | 李木 | Energy-saving triphase wind power generation system and control method thereof |
| CN105207334A (en) * | 2014-06-23 | 2015-12-30 | 通用电气能源能量变换技术有限公司 | Power supply system for a load and corresponding supply method |
| CN105429179A (en) * | 2015-12-22 | 2016-03-23 | 山东华天电气有限公司 | Special filtering energy feedback apparatus and control method for pumping unit |
| CN108880363A (en) * | 2018-05-31 | 2018-11-23 | 南京航空航天大学 | Three-level formula brushless synchronous machine asynchronous starting control method and system |
| CN108964532A (en) * | 2018-05-31 | 2018-12-07 | 南京航空航天大学 | Three-level formula brushless synchronous machine sublevel segmentation start control system and method |
Non-Patent Citations (2)
| Title |
|---|
| 李荷洁: "三级式同步电机起动控制策略研究", 《中国优秀硕士学位论文全文数据库 工程科技Ⅱ辑》 * |
| 白皓然: "高速发电机分布式发电***功率变换技术研究", 《中国博士学位论文全文数据库 工程科技Ⅱ辑》 * |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111585498A (en) * | 2020-06-03 | 2020-08-25 | 能科科技股份有限公司 | Variable-frequency speed regulation control system with load observer and frequency converter |
| CN113992080A (en) * | 2021-11-29 | 2022-01-28 | 中国商用飞机有限责任公司 | Starting power generation control method, system and medium capable of actively suppressing harmonic waves |
| CN117200648A (en) * | 2023-11-07 | 2023-12-08 | 浙江大学 | Control device for power supply harmonic wave of alternating current motor driven by multiple inverters |
| CN117200648B (en) * | 2023-11-07 | 2024-01-26 | 浙江大学 | Control device for power supply harmonic wave of alternating current motor driven by multiple inverters |
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