CN102882455A - Excitation control method and device used in starting process of aeronautical tertiary brushless AC synchronous motor - Google Patents

Abstract

The invention relates to an excitation control method and device used in the starting process of an aeronautical tertiary brushless AC synchronous motor. When the motor stops, a controller can output the maximum AC excitation quantity for an exciter to excite; when the motor rotates at a certain speed, the AC excitation quantity starts to decrease linearly, meanwhile, a PI (Proportion Integration) regulator regulates and intervenes DC excitation quantity, and the regulation upper limit is comprehensively determined by the magnitude of AC excitation component and the bus voltage of the controller. When the AC component decreases to zero, the exciter enters the DC excitation mode. When the excitation control method is used for starting the tertiary brushless AC synchronous motor, flux linkage fluctuation of a main generator rotor, caused when the exciter directly switches the excitation mode, is avoided, and the running stability of a unit which conducts excitation switching in the starting process is effectively improved.

Description

Excitation control method and device in the aviation three-stage brushless ac synchronous motor starting process

Technical field

The present invention relates to excitation control method and device in a kind of aviation three-stage brushless ac synchronous motor starting process, be a kind of control method of utilizing single-phase space vector modulation to solve the excitation problem of aviation three-stage brushless ac synchronous motor in starting process, belong to alternating current machine drive technology field.

Background technology

Starting/generating Dual-functional integrated is an important development direction of following aviation AC power supply system.At present, in aviation high-power ac power system, extensively adopt three-stage brushless ac synchronous motor (theory diagram is seen Fig. 1) as generator, when adopting this motor to realize the start-up function of aero-engine, main generator will move in electronic mode, because this motor is the non-brushing structure, therefore when motor is static, if the DC excitation mode when exciter still adopts generating state can't realize the rotor-exciting of main generator causing motor to start.In " aircraft starts/generate electricity the research of a dual function system motoring condition single phase alternating current (A.C.) excitation " literary composition (author Chen Baolin etc.) of " electrotechnics magazine " calendar year 2001 the 1st phase 3～8 pages of publications, proposition passes into single-phase alternating current in the exciter stator winding, the excitation problem of main generator when the solution unit remains static, the advantage of the method is to need not to change electric machine structure.Experiment shows, when selecting suitable excitation frequency and control method, the exciting current of exciter output can guarantee unit smoothly starting in certain stall square situation, the suitable excitation frequency of herein mentioning refers under the prerequisite that exciting voltage equates, main generator can obtain maximum exciting current when adopting the single phase alternating current (A.C.) excitation of this frequency.

But, exciter is when adopting the single phase alternating current (A.C.) excitation mode, still face following problem: 1) under suitable excitation frequency, because exciter induction reactance is larger, the stator excitation electric current of exciter is much smaller than its rated value, can't effectively bring into play the excitation fan-out capability of exciter, the rotor-exciting that causes main generator a little less than, affected the load capacity of main generator when motoring condition; 2) compare the DC excitation mode, when adopting the single phase alternating current (A.C.) excitation mode pulsation of main generator rotor magnetic linkage larger, the running stability when affecting the main generator motoring condition; 3) after unit reaches certain rotating speed, exciter adopts the excitation fan-out capability of DC excitation mode will be better than adopting the excitation fan-out capability of single phase alternating current (A.C.) excitation mode, run with load performance that can the Effective Raise main generator when adopt the DC excitation mode this moment.For these reasons, after unit reaches certain rotating speed, exciter need to be switched to the DC excitation mode by the AC excitation mode, but because the PWM modulator approach of two kinds of excitation modes differs greatly, if adopt the mode of directly switching, moment main generator rotor magnetic linkage fluctuation is larger switching, and the torque pulsation of generation easily causes the startup of unit failure.

Summary of the invention

The technical problem that solves

For fear of the deficiencies in the prior art part, the present invention proposes a kind of aviation three-stage brushless ac synchronous motor starting process excitation control method and device, the load function of Effective Raise three-stage brushless ac synchronous motor in starting process and the stationarity of unit operation.

Technical scheme

A kind of aviation three-stage brushless ac synchronous motor starting process excitation control method is characterized in that step is as follows:

Step 1: according to the current tachometer value ω of the motor that records _rAnd the AC excitation amount of setting obtains the modulation degree M of current output AC excitation component with the curve of rotation speed change _A, with the modulation upper limit M that then draws DC excitation component modulation degree _DMAX=1-M _A

Step 2: with the rated current i of exciter ^*And the difference e of the exciting current value i of current exciter _i=i ^*-i carries out PI to be regulated, and draws the modulation degree of DC excitation controlled quentity controlled variable

Wherein, K _PsBe the proportionality coefficient of exciting current PI controller, K _Ps＞0; K _IsBe the integral coefficient of exciting current PI controller, K _Is＞0; The modulation degree M of the DC excitation amount of exciter under the current rotating speed of output after the amplitude limiting processing _D

Step 3: draw the voltage phase angle θ of current AC excitation component=∫ ω dt according to the angle integrator of exciter AC excitation component, wherein, and ω=2 π f, f is the frequency of AC excitation component;

Step 4: calculate the action time of effective vector and zero vector, concrete steps are as follows:

Step a: calculating the inverter output reference voltage is V _Ref=M _DV _DC+ M _AV _DCCos θ, wherein, V _DCBe exciter controller busbar voltage;

Step b: according to the weber balance principle, establishing the inverter switching device cycle is T _s, effectively be T the action time of vector ₁, have: V _RefT _s=V _DCT ₁Then in switch periods, effectively be respectively the action time of vector and zero vector: $\left\{\begin{array}{c}{\mathrm{<figure-callout\; id="1"\; label="T"\; filenames="HDA00002147502800022.png"\; state="\{\{state\}\}">T</figure-callout>}}_1=M_D{T}_s+M_A{T}_s\cos \mathrm{\&omega;<figure-callout\; id="0"\; label="t\; T"\; filenames="HDA00002147502800023.png,HDA00002147502800031.png"\; state="\{\{state\}\}">t</figure-callout>}& \\ T_{}{}_0=T_s-{\mathrm{<figure-callout\; id="1"\; label="T"\; filenames="HDA00002147502800022.png"\; state="\{\{state\}\}">T</figure-callout>}}_1\end{array}\right.;$

Step 5: calculate the controlled quentity controlled variable of H bridge inverter, and drive exciter with this controlled quentity controlled variable control H bridge inverter:

When adopting a zero vector and V _RefThe controlled quentity controlled variable of＞0, H bridge inverter $\left\{\begin{array}{c}\mathrm{CMP}\_a={\mathrm{<figure-callout\; id="0"\; label="T"\; filenames="HDA00002147502800023.png,HDA00002147502800031.png"\; state="\{\{state\}\}">T</figure-callout>}}_0/2\\ \mathrm{CMP}\_b=T_s/2\end{array}\right.;$

When adopting a zero vector and V _RefThe controlled quentity controlled variable of＜0, H bridge inverter $\left\{\begin{array}{c}\mathrm{CMP}\_a=T_s/2\\ \mathrm{CMP}\_b={\mathrm{<figure-callout\; id="0"\; label="T"\; filenames="HDA00002147502800023.png,HDA00002147502800031.png"\; state="\{\{state\}\}">T</figure-callout>}}_0/2\end{array}\right.;$

When adopting two zero vectors and V _RefThe controlled quentity controlled variable of＞0, H bridge inverter $\left\{\begin{array}{c}\mathrm{CMP}\_a={\mathrm{<figure-callout\; id="0"\; label="T"\; filenames="HDA00002147502800023.png,HDA00002147502800031.png"\; state="\{\{state\}\}">T</figure-callout>}}_0/4\\ \mathrm{CMP}\_b={\mathrm{<figure-callout\; id="0"\; label="T"\; filenames="HDA00002147502800023.png,HDA00002147502800031.png"\; state="\{\{state\}\}">T</figure-callout>}}_0/4+{\mathrm{<figure-callout\; id="1"\; label="T"\; filenames="HDA00002147502800022.png"\; state="\{\{state\}\}">T</figure-callout>}}_1/2\end{array}\right.;$

When adopting two zero vectors and V _RefThe controlled quentity controlled variable of＜0, H bridge inverter $\left\{\begin{array}{c}\mathrm{CMP}\_a={\mathrm{<figure-callout\; id="0"\; label="T"\; filenames="HDA00002147502800023.png,HDA00002147502800031.png"\; state="\{\{state\}\}">T</figure-callout>}}_0/4+{\mathrm{<figure-callout\; id="1"\; label="T"\; filenames="HDA00002147502800022.png"\; state="\{\{state\}\}">T</figure-callout>}}_1/2\\ \mathrm{CMP}\_b={\mathrm{<figure-callout\; id="0"\; label="T"\; filenames="HDA00002147502800023.png,HDA00002147502800031.png"\; state="\{\{state\}\}">T</figure-callout>}}_0/4\end{array}\right..$

The modulation degree M of described current time DC excitation component _DObtained by following steps:

e _i＝i ^*-i；

$M_D^{*}=K_{\mathrm{ps}}\&CenterDot;e_i+K_{\mathrm{is}}\&Integral;e_i\mathrm{dt}$

$M_D=\left\{\begin{array}{cc}{M}_D^{*}& M_D^{*}<1-M_A\\ 1-M_A& M_D^{*}\&GreaterEqual;1-M_A\end{array}\right..$

Described AC excitation component modulation degree M _ASatisfy: 1 〉=M _A〉=0.

Described DC excitation component modulation degree M _DSatisfy: 1-M _A〉=M _D〉=0.

Described AC excitation angulation speed omega satisfies: ω=200 π.

Described exciter self character and systematic function according to the three-stage brushless ac synchronous motor requires to set K _Ps, K _Is, and satisfy K _Ps＞0, K _Is＞0.

A kind of device of realizing described aviation three-stage brushless ac synchronous motor starting process excitation control method is characterized in that comprising rectification circuit, filter circuit, three-phase full-bridge inverter, single-phase H bridge inverter, position transducer, central controller, driver for isolating and current collection circuit; Rectification circuit carries out the three-phase alternating current of input to export connected filter circuit to after the rectification, and filter circuit connects respectively three-phase full-bridge inverter and single-phase H bridge inverter; Single-phase H bridge inverter connects the stator winding of exciter, drives exciter and realizes main generator excitation; Three-phase full-bridge inverter connects main generator, the starting operation of control main generator; Position transducer is arranged on and detects the motor rotor position part, and its output connects central controller; Current collection circuit is connected to the output of single-phase H bridge inverter and three-phase full-bridge inverter, and its output connects central controller; The output of central controller connects driver for isolating, and the output of driver for isolating connects respectively three-phase full-bridge inverter and single-phase H bridge inverter.

Described position transducer adopts resolver.

Beneficial effect

A kind of aviation three-stage brushless ac synchronous motor starting process excitation control method and device that the present invention proposes, when motor is static, controller with the maximum AC excitation amount that can export to exciter excitation, when motor reaches certain rotating speed, the AC excitation amount begins linearity and reduces, the DC excitation amount adopts pi regulator to regulate intervention simultaneously, its adjusting upper limit is comprehensively determined by size and the controller busbar voltage of AC excitation component, when alternating current component was decreased to 0, exciter entered the DC excitation mode.When the method for the present invention is applied to the start-up function of three-stage brushless ac synchronous motor, the main generator rotor magnetic linkage fluctuation of having avoided exciter when direct switched energization mode, to cause, but the running stability when the Effective Raise unit carries out the excitation switching in starting process.

The present invention has the following advantages: when 1) switching between AC excitation mode and DC excitation mode, AC excitation component and DC excitation component all adopt the mode that is fade-in gradually to go out to realize, during switching without impact; 2) modulation algorithm has merged the characteristics of ac modulation and HVDC Modulation, in whole excitation process without the change on the modulation algorithm; 3) adopt pi regulator to regulate DC excitation output, utilize simultaneously the maximum of AC excitation export-restriction DC excitation output, can in handoff procedure, effectively utilize busbar voltage, when effectively avoiding high rotating speed simultaneously since rotation speed change on the impact of exciter.

Description of drawings

Fig. 1: three-stage brushless ac synchronous motor theory diagram

Fig. 2: the inventive method theory diagram

Fig. 3: the system hardware schematic diagram of the embodiment of the invention

Fig. 4: H bridge inverter schematic diagram

Fig. 5: the output voltage vector figure of H bridge inverter

Fig. 6: the polar plot of H bridge inverter single phase alternating current (A.C.) modulation

Fig. 7: the polar plot of H bridge inverter HVDC Modulation

Fig. 8: the H bridge inverter is with the ac modulation polar plot of direct current biasing

Fig. 9: the H bridge inverter is with the HVDC Modulation polar plot of alternating component

Figure 10: V _Ref＞0 o'clock, the PWM schematic diagram when adopting two kinds of zero vector modulation

Figure 11: V _Ref＞0 o'clock, the PWM schematic diagram when adopting single zero vector modulation

Figure 12: pure AC excitation mode excitation current waveform

Figure 13: with the AC excitation mode excitation current waveform of direct current biasing

Figure 14: with the AC excitation mode excitation current waveform of alternating component

Figure 15: DC excitation mode excitation current waveform

Figure 16: the loaded starting acceleration graph of motor when adopting the inventive method

Embodiment

Now in conjunction with the embodiments, the invention will be further described for accompanying drawing:

The excitation control method (Fig. 2) of the aviation three-stage brushless ac synchronous motor starting process of present embodiment:

The theory diagram of the inventive method as shown in Figure 2, the modulation degree size of AC excitation component is by motor speed ω _rDetermine that the modulation degree of DC excitation component is by exciter rated exciting current i ^*Obtain through the pi regulator adjusting with the exciting current i of reality, it regulates upper limit M _DmaxModulation degree M by the AC excitation component _ADetermine, after the modulation algorithm that the AC/DC excitation output variable that obtains the most at last proposes by the present invention synthesizes, draw the variate-value of control H bridge inverter, realize the excitation control of exciter.Wherein, the excitation frequency of AC excitation component satisfies: ω=2 π f.

The system hardware structure of the embodiment of the invention as shown in Figure 3, comprise: rectification circuit, filter circuit, three-phase full-bridge inverter, single-phase H bridge inverter (Fig. 4), isolated drive circuit, electric current and voltage detecting circuit, central controller and man-machine interface circuit and position transducer adopt resolver to detect motor rotor position and rotating speed in the native system.Wherein, single-phase H bridge inverter connects the exciter stator winding, drives exciter and realizes main generator excitation, and three-phase full-bridge inverter connects main generator, the excitation control performance of the starting operation effect observation the inventive method by the control main generator.

Be checking the inventive method, adopt the 2PT115-T/2PT115-P loading bench simulation aero-engine load of MAGTROL company, utilize a three-stage brushless ac synchronous motor to build verification platform.

The present embodiment method is by controlling respectively alternating current component and DC component size in the exciter excitation signal, the new modulator approach of utilized fusion that the present invention proposes single phase alternating current (A.C.) modulation and HVDC Modulation, calculate the switching signal of H bridge inverter, drive the action of H bridge inverter, realize the exciter control of three-stage brushless ac synchronous motor in starting process, contain successively following steps:

1. record rotational speed omega when front motor by rotor-position sensor and signal processing circuit _r

2. table look-up according to current motor speed and draw AC excitation component modulation degree M _ASize, establishing output AC excitation component amplitude is V _A, the controller busbar voltage is V _DC, M _ASatisfy M _A=V _A/ V _DC

3. drawn the voltage phase angle θ of current AC excitation component by the angle integrator of exciter AC excitation component, that is:

θ＝∫ωdt

Wherein, ω=2 π f, f is the frequency of AC excitation component;

4. calculate the adjusting upper limit M of DC excitation component modulation degree according to the modulation degree size of the AC excitation component of current controller output _DMAX

5. calculate the modulation degree of DC excitation component by following steps:

(5.1). the adjusting parameter of setting the DC excitation component pi regulator of exciter controller is respectively K _Ps=0.1, K _Is=0.05;

(5.2). obtained the modulation degree of exciter controller output DC excitation component by following steps:

(5.2.1).e _i＝i ^*-i

(5.2.2). $M_D^{*}=K_{\mathrm{ps}}\&CenterDot;e_i+K_{\mathrm{is}}{\&Integral;e}_i\mathrm{dt}$

(5.2.3). through the modulation degree upper limit M of DC excitation component _DMAXDo amplitude limiting processing, obtain the DC excitation component modulation degree M of exciter controller output _D, processing mode is as follows:

$M_D=\left\{\begin{array}{cc}{M}_D^{*}& M_D^{*}<1{-M}_A\\ 1-M_A& M_D^{*}\&GreaterEqual;1-M_A\end{array}\right.$

M wherein _D=V _D/ V _DC, V _DVoltage for current output DC excitation component.

(5.3). calculate output reference voltage under the current state by following formula:

V _ref＝V _D+V _Acosωt＝M _DV _DC+M _AV _DCcosωt

Work as V _D=0, when namely exciter was the AC excitation mode, the polar plot of controller output as shown in Figure 6;

Work as V _A=0, when namely exciter was the DC excitation mode, the polar plot of controller output as shown in Figure 7;

Work as V _D＜V _A, when namely exciter is AC excitation mode with direct current biasing, the polar plot of controller output as shown in Figure 8, this moment, exciter began to be switched to the DC excitation mode by the AC excitation mode;

Work as V _D＞V _A, when namely exciter is DC excitation mode with alternating current component, the polar plot of controller output as shown in Figure 9, this moment, exciter was near completion by the switching of AC excitation mode to the DC excitation mode;

(5.4). establishing the PWM switch periods is T _s, effectively be T the action time of vector ₁, according to the weber balance principle, have:

V _refT _s＝V _DCT ₁

Then effectively be respectively the action time of vector and zero vector:

$\left\{\begin{array}{c}{\mathrm{<figure-callout\; id="1"\; label="T"\; filenames="HDA00002147502800022.png"\; state="\{\{state\}\}">T</figure-callout>}}_1=M_D{T}_s+M_A{T}_s\cos \mathrm{\&omega;<figure-callout\; id="0"\; label="t\; T"\; filenames="HDA00002147502800023.png,HDA00002147502800031.png"\; state="\{\{state\}\}">t</figure-callout>}& \\ T_{}{}_0=T_s-{\mathrm{<figure-callout\; id="1"\; label="T"\; filenames="HDA00002147502800022.png"\; state="\{\{state\}\}">T</figure-callout>}}_1\end{array}\right.$

Wherein, T ₁Satisfy following relational expression:

T ₁≤T _s

(5.5). determine H bridge inverter two-phase switch controlling signal S according to the time of basic voltage vectors and zero vector and each self-applying _A, S _B, the upper switching tube conducting of the same brachium pontis of regulation " 1 " expression, lower switching tube is closed, the lower switching tube conducting of the same brachium pontis of " 0 " expression, upper switching tube is closed:

Effective voltage vector and corresponding two phase switching signals of zero vector that inverter produces are respectively v _i(S _A, S _B): v ₁(1,0), v ₂(0,1) and two Zero voltage vector v ₀(0,0), v ₃(1,1) sees Fig. 5; At a switch periods T _sInterior basic voltage vectors and zero vector sequence of operation are seen Figure 10, Figure 11.Wherein, switching sequence shown in Figure 10 is v ₀(0,0), v ₃(1,1) two zero vectors are all made the situation of time spent, and the switching sequence of this moment is:

v ₀(0,0) effect T ₀/ 4 → v ₁(1,0) effect T ₁/ 2 → v ₃(1,1) effect T ₀/ 2 → v ₁(1,0) effect T ₁/ 2 → v ₀(0,0) effect T ₀/ 4;

Figure 11 is for only adopting v ₀The situation of (0,0) vector, the switching sequence of this moment is:

v ₀(0,0) effect T ₀/ 2 → v ₁(1,0) effect T ₁→ v ₀(0,0) effect T ₀/ 2;

(5.6). two phase switching signal S _A, S _BBehind accordingly isolation and signal processing, amplifying circuit, control single-phase H bridge inverter action, drive exciter, the excitation function of realization three-stage brushless ac synchronous motor.

Figure 12-Figure 15 is when adopting modulation algorithm proposed by the invention, exciter is at the excitation current waveform in each excitation stage, wherein, Figure 12 is pure AC excitation mode, Figure 13 is the AC excitation mode with direct current biasing, Figure 14 is the DC excitation mode that contains alternating component, and Figure 15 is the DC excitation mode.

Figure 16 is the loaded starting acceleration graph of unit when adopting the inventive method.

Claims (8)

1. aviation three-stage brushless ac synchronous motor starting process excitation control method is characterized in that step is as follows:

Step 1: according to the current tachometer value ω of the motor that records _rAnd the AC excitation amount of setting obtains the modulation degree M of current output AC excitation component with the curve of rotation speed change _A, with the modulation upper limit M that then draws DC excitation component modulation degree _DMAX=1-M _A

Step 2: with the rated current i of exciter ^*And the difference e of the exciting current value i of current exciter _i=i ^*-i carries out PI to be regulated, and draws the modulation degree of DC excitation controlled quentity controlled variable

Wherein, K _PsBe the proportionality coefficient of exciting current PI controller, K _Ps＞0; K _IsBe the integral coefficient of exciting current PI controller, K _Is＞0;

The modulation degree M of the DC excitation amount of exciter under the current rotating speed of output after the amplitude limiting processing _D

Step 3: draw the voltage phase angle θ of current AC excitation component=∫ ω dt according to the angle integrator of exciter AC excitation component, wherein, and ω=2 π f, f is the frequency of AC excitation component;

Step 4: calculate the action time of effective vector and zero vector, concrete steps are as follows:

Step a: calculating the inverter output reference voltage is V _Ref=M _DV _DC+ M _AV _DCCos θ, wherein, V _DCBe exciter controller busbar voltage;

Step b: according to the weber balance principle, establishing the inverter switching device cycle is T _s, effectively be T the action time of vector ₁, have: V _RefT _s=V _DCT ₁Then in switch periods, effectively be respectively the action time of vector and zero vector: $\left\{\begin{array}{c}{T}_1=M_D{T}_s+M_A{T}_s\cos \mathrm{\&omega;t}\\ T_0=T_s-T_1\end{array}\right.;$

Step 5: calculate the controlled quentity controlled variable of H bridge inverter, and drive exciter with this controlled quentity controlled variable control H bridge inverter:

When adopting a zero vector and V _RefThe controlled quentity controlled variable of＞0, H bridge inverter $\left\{\begin{array}{c}\mathrm{CMP}\_a=T_0/2\\ \mathrm{CMP}\_b=T_s/2\end{array}\right.;$

When adopting a zero vector and V _RefThe controlled quentity controlled variable of＜0, H bridge inverter $\left\{\begin{array}{c}\mathrm{CMP}\_a=T_s/2\\ \mathrm{CMP}\_b=T_0/2\end{array}\right.;$

When adopting two zero vectors and V _RefThe controlled quentity controlled variable of＞0, H bridge inverter $\left\{\begin{array}{c}\mathrm{CMP}\_a=T_0/4\\ \mathrm{CMP}\_b=T_0/4+T_1/2\end{array}\right.;$

When adopting two zero vectors and V _RefThe controlled quentity controlled variable of＜0, H bridge inverter $\left\{\begin{array}{c}\mathrm{CMP}\_a=T_0/4+T_1/2\\ \mathrm{CMP}\_b=T_0/4\end{array}\right..$

2. described aviation three-stage brushless ac synchronous motor starting process excitation control method according to claim 1 is characterized in that: the modulation degree M of described current time DC excitation component _DObtained by following steps:

e _i＝i ^*-i；

$M_D^{*}=K_{\mathrm{ps}}\&CenterDot;e_i+K_{\mathrm{is}}\&Integral;e_i\mathrm{dt}$

$M_D=\left\{\begin{array}{cc}{M}_D^{*}& M_D^{*}<1-M_A\\ 1-M_A& M_D^{*}\&GreaterEqual;1-M_A\end{array}\right..$

3. described aviation three-stage brushless ac synchronous motor starting process excitation control method according to claim 1 and 2 is characterized in that: described AC excitation component modulation degree M _ASatisfy: 1 〉=M _A〉=0.

4. described aviation three-stage brushless ac synchronous motor starting process excitation control method according to claim 1 is characterized in that: described DC excitation component modulation degree M _DSatisfy: 1-M _A〉=M _D〉=0.

5. described aviation three-stage brushless ac synchronous motor starting process excitation control method according to claim 1, it is characterized in that: described AC excitation angulation speed omega satisfies: ω=200 π.

6. described aviation three-stage brushless ac synchronous motor starting process excitation control method according to claim 1, it is characterized in that: described exciter self character and systematic function according to the three-stage brushless ac synchronous motor requires to set K _Ps, K _Is, and satisfy K _Ps＞0, K _Is＞0.

7. a device of realizing each described aviation three-stage brushless ac synchronous motor starting process excitation control method of claim 1 ~ 6 is characterized in that comprising rectification circuit, filter circuit, three-phase full-bridge inverter, single-phase H bridge inverter, position transducer, central controller, driver for isolating and current collection circuit; Rectification circuit carries out the three-phase alternating current of input to export connected filter circuit to after the rectification, and filter circuit connects respectively three-phase full-bridge inverter and single-phase H bridge inverter; Single-phase H bridge inverter connects the stator winding of exciter, drives exciter and realizes main generator excitation; Three-phase full-bridge inverter connects main generator, the starting operation of control main generator; Position transducer is arranged on and detects the motor rotor position part, and its output connects central controller; Current collection circuit is connected to the output of single-phase H bridge inverter and three-phase full-bridge inverter, and its output connects central controller; The output of central controller connects driver for isolating, and the output of driver for isolating connects respectively three-phase full-bridge inverter and single-phase H bridge inverter.

8. device according to claim 7 is characterized in that: described position transducer employing resolver.

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