CN104935214A - Excitation control method for starting stage of aviation tertiary starting power generation system - Google Patents
Excitation control method for starting stage of aviation tertiary starting power generation system Download PDFInfo
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- CN104935214A CN104935214A CN201510270435.2A CN201510270435A CN104935214A CN 104935214 A CN104935214 A CN 104935214A CN 201510270435 A CN201510270435 A CN 201510270435A CN 104935214 A CN104935214 A CN 104935214A
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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
- H02P9/00—Arrangements for controlling electric generators for the purpose of obtaining a desired output
- H02P9/08—Control of generator circuit during starting or stopping of driving means, e.g. for initiating excitation
-
- 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
- H02P25/00—Arrangements or methods for the control of AC motors characterised by the kind of AC motor or by structural details
- H02P25/16—Arrangements or methods for the control of AC motors characterised by the kind of AC motor or by structural details characterised by the circuit arrangement or by the kind of wiring
- H02P25/22—Multiple windings; Windings for more than three phases
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- Engineering & Computer Science (AREA)
- Power Engineering (AREA)
- Control Of Motors That Do Not Use Commutators (AREA)
- Control Of Eletrric Generators (AREA)
- Motor And Converter Starters (AREA)
Abstract
The invention relates to an exciter whole-process two-phase alternating-current excitation control method for the starting stage of an aviation tertiary brushless starting power generation system based on a two-phase exciter. In the motor starting process, an exciter adopts two-phase alternating-current excitation in the whole process. The amplitude of a modulation voltage vector is determined through exciter excitation current closed-loop control, and the phase angle of the modulation voltage vector is determined through motor speed reference. When the method of the invention is applied to the starting stage of a tertiary brushless synchronous starting power generation system, the size of the excitation magnetic field of the exciter can be kept constant, and the speed of a rotor armature winding relative to the excitation magnetic field can be kept constant. Finally, the excitation current of a main generator can be kept constant in the whole motor starting process, and the complexity of main generator variable-frequency starting control is reduced.
Description
Technical field
The invention belongs to aviation alternating current machine technical field, be specifically related to a kind of aviation three grades of formula brushless synchronous starting/generating system start-up period exciter excitation control methods based on two-phase excitation machine, be that a kind of start-up period whole process adopts two-phase AC excitation, and modulate by exciting current closed-loop control and rotating speed reference the excitation control method realizing main generator excitation electric current and keep constant in starting process.
Background technology
Current China aircraft AC electrical power generating systems mostly adopts three grades of formula brushless synchronous machines as generator, and engine is started by independently special starter.Such engine-power-supply system comprises two cover motors, makes the increase of system bulk weight, reliability reduction.If it is generating integrated to realize electric motor starting, just can simplify engine-power-supply system, reduce system bulk weight, improve system reliability.A kind of starting/generating integrated realizing method of simple possible is on the basis of existing power supply system, directly saves special starter, and three grades of formula no-brush synchronous generators are operated in motoring condition to drive Aero-Engine Start.
Based on two-phase excitation machine three grades of formula brushless synchronous starting/generating systems as shown in Figure 1, exciter excitation winding is two phase windings of difference 90 °.Motor is at start-up period, and two-phase excitation machine is powered by two-phase inverter; After motor enters generating state, control power supply by onboard generators control unit (GCU) after being connected by exciter two-phase excitation winding, adopt traditional DC excitation mode.Because exciter two-phase excitation winding produces rotating magnetic field under two-phase AC excitation mode, even if therefore motor is in static and low speed start-up period, exciter excitation efficiency is also very high, can provide enough exciting currents for main generator; After motor enters generating state, two-phase excitation machine is because excitation winding series connection inherently becomes single-phase exciter, identical with traditional three grades of formula no-brush synchronous generator structures, can adopt the control method of existing technology maturation.So there is certain advantage based on three grades of formula brushless synchronous starting/generating systems of two-phase excitation machine.
Three grades of formula brushless synchronous starting/generating systems are in loaded starting process, and main generator excitation electric current can cause main generator excitation magnetic field non-constant with rotation speed change, and this starts control to the optimum of main generator undoubtedly and adds complexity.If main generator excitation current constant can be kept in motor starting process, and then keep main generator excitation magnetic field constant, then can reduce main generator optimum to a great extent and start the complexity controlled.
When electric machine rotation, main generator excitation winding rotates with rotor.When not adding the equipment such as electric brush slip ring, main generator excitation electric current cannot obtain, so it is constant to ensure its basic maintenance in motor starting process to carry out closed-loop control for main generator excitation electric current.Main generator excitation voltage is provided after rotating rectifier rectification by exciter rotor armature voltage, so in motor starting process, if can ensure that exciter rotor output voltage is constant, and then make main generator excitation voltage constant, main generator excitation electric current substantially constant just can be ensured.
Exciter rotor output voltage is relevant relative to the relative rotation speed of excitation field with armature winding to exciter excitation magnetic field size.In motor starting process, if can keep in real time exciter excitation magnetic field size and armature winding constant relative to the relative rotation speed of excitation field, then armature of exciter output voltage just can keep constant substantially.Accelerate in starting process at motor, if exciter adopts DC excitation, can ensure that exciter excitation magnetic field is constant by closed-loop current control, but along with the rising of motor speed, armature winding will certainly change relative to the relative rotation speed of excitation field.If exciter whole process adopts two-phase AC excitation, excitation field constant magnitude can be ensured on the one hand by exciting current closed-loop control, excitation frequency can be adjusted in real time on the other hand according to motor speed, change excitation field rotary rpm, ensure that armature winding is constant relative to the relative rotation speed of excitation field.
Summary of the invention
The technical problem solved
In order to avoid the deficiencies in the prior art part, the present invention proposes a kind of omnidistance AC excitation control method of aviation three grades of formula brushless synchronous starting/generating system start-up period exciters based on two-phase excitation machine, the technical problem solved is mainly: in motor starting process, carry out omnidistance two-phase AC excitation control to two-phase excitation machine, make main generator excitation electric current can keep constant in the whole starting process of motor.
Technical scheme
A kind of aviation three grades of formula starting-generating system start stage excitation control methods, is characterized in that step is as follows:
Step 1: when motor is static, employing exciting voltage is U
0, excitation frequency is f
0two-phase AC excitation mode excitation is carried out to two-phase excitation machine, and to measure now exciting current of exciter amplitude be i
ref, as the reference value of closed-loop current control; Described U
0by two-phase inverter under system dc busbar voltage the maximum two-phase alternating current pressure value that goes out of energy inversion; Described
for motor static time two-phase excitation machine excitation frequency, wherein p
nfor two-phase excitation machine number of pole-pairs; Described motor starting process rotating speed median
n
maxmaximum speed value in motor starting process, unit is rev/min;
Step 2: electric motor starting stage, by two-phase excitation machine exciting current closed-loop control determination exciter excitation voltage vector magnitude, specific as follows:
Step 2.1: the instantaneous value being obtained exciter two-phase excitation electric current by current sample module, is designated as i respectively
αand i
β; Use formula
calculate the amplitude of current excitation current vector, be designated as i
s;
Step 2.2: calculate exciting current reference value i
refwith current exciting current value i
sdifference, be designated as current error e
i, i.e. e
i=i
ref-i
s; To current error e
icarry out PI adjustment, pass through
calculate the current modulation voltage vector magnitude U of two-phase excitation machine; Wherein, K
p, K
ibe respectively the ratio of exciting current closed loop PI controller, integral coefficient, and K
p> 0, K
i> 0;
Step 3: by current for motor rotating speed n
rwith intermediate speed n
scompare, adopt following distinct methods to calculate current modulation voltage vector phase angle according to comparative result; n
rfor speed probe obtains current motor rotating speed, unit is rev/min;
Current rotating speed n
rbe less than intermediate speed n
s(n
r<n
s) time, the rotating magnetic field that two-phase excitation electric current produces is contrary with motor direction of rotation; Use formula
calculate the current excitation frequency f of two-phase excitation machine
e; By formula θ
k=θ
k-1+ Δ θ obtains current voltage vector phase angle θ
k; Wherein, θ
k-1for the voltage vector phase angle in a upper computing cycle moment, Δ θ=2 π f
et
sfor the increment at voltage vector phase angle, t
sfor computing cycle;
Current rotating speed n
rbe more than or equal to speed-changing n
s(n
r>=n
s) time, the rotating magnetic field that two-phase excitation electric current produces is identical with motor direction of rotation; Use formula
calculate the current excitation frequency f of two-phase excitation machine
e; By formula θ
k=θ
k-1-Δ θ obtains current voltage vector phase angle θ
k; Wherein, θ
k-1for the voltage vector phase angle in a upper computing cycle moment, Δ θ=2 π f
et
sfor the increment at voltage vector phase angle, t
sfor computing cycle;
Step 4: integrating step 2 gained current modulation voltage vector magnitude and step 3 gained current modulation voltage vector phase angle, obtain inverter power demand pipe switch controlling signal by voltage modulated method, and drive two-phase inverter to control two-phase excitation machine with this signal.
Described two-phase inverter is two single bridge two-phase inverter, three-phase full-bridge inverter or bridge two-phase inverter of enjoying a double blessing.
Described voltage modulated method is space vector width pulse modulation method SVPWM or sine wave pulse width modulation method SPWM.
Described speed probe is resolver, photoelectric encoder or Hall element.
Beneficial effect
A kind of aviation three grades of formula started with no brush electricity generation system start-up period exciters omnidistance two-phase AC excitation control method based on two-phase excitation machine that the present invention proposes.In motor starting process, exciter whole process adopts two-phase AC excitation, by exciting current of exciter closed-loop control determination modulation voltage vector magnitude, by motor speed with reference to determining modulation voltage vector phase angle.When the inventive method is applied to three grades of formula brushless synchronous starting-generating system start stages, can ensure that exciter excitation magnetic field constant magnitude, armature rotor winding are constant relative to the relative rotation speed of excitation field, finally realize main generator excitation electric current and can keep constant in the whole starting process of motor, reduce the complexity of main generator varying frequency starting control with this.
Accompanying drawing explanation
Fig. 1: based on three grades of formula brushless synchronous starting/generating system structural representations of two-phase excitation machine
Fig. 2: the inventive method theory diagram
Fig. 3: bridge two-phase inverter topological diagram of enjoying a double blessing
Fig. 4: the system hardware structure schematic diagram of the embodiment of the present invention
Fig. 5: the trend that main generator back-emf effective value changes with motor speed
Fig. 6: the trend that the business of main generator back-emf effective value and motor speed changes with motor speed
Fig. 7: the change curve of two-phase excitation machine exciting current near intermediate speed
Embodiment
Now in conjunction with the embodiments, the invention will be further described for accompanying drawing:
As shown in Figure 2, exciter biphase current obtains current flow vector magnitude through over-sampling, calculating, filtering process to the theory diagram of the inventive method, by PI controls obtain current modulation voltage vector magnitude after asking difference with current reference value; By the size of more current rotating speed and intermediate speed, different phase angle computing formula is selected to obtain modulation voltage vector phase angle.Modulation voltage vector drives two-phase inverter to power to two-phase excitation machine through PWM method.In the present embodiment, two-phase inverter adopts bridge two-phase inverter (as shown in Figure 3) of enjoying a double blessing, and voltage modulated method adopts SVPWM, and speed probe adopts resolver.
The system hardware structure of the embodiment of the present invention as shown in Figure 4, comprising: rectification circuit, filter circuit, enjoy a double blessing bridge two-phase inverter, isolated drive circuit, current collection circuit, velocity transducer, voltage-measuring equipment, central controller and man-machine interface circuit.Wherein two-phase inverter is connected with the two-phase excitation machine excitation winding in three grades of formula brushless synchronous starting-generating systems.For verifying feasibility and the validity of the inventive method, utilizing other prime mover to drag these three grades of formula started with no brush generators and accelerating to certain rotating speed from static, simulated machine starting process; Utilize voltage-measuring equipment to measure the back-emf size of main generator under different rotating speeds, and then the variation tendency of main generator excitation electric current with motor speed can be obtained.In addition, Real-Time Monitoring exciter two-phase excitation electric current, for verificating current closed-loop control validity and observe the change curve of two-phase excitation electric current near intermediate speed.
The concrete steps that embodiment comprises are as follows:
1. the maximum speed in the present embodiment in motor starting process is n
max=1200rpm.Use formula
calculate starting process rotating speed median n
s=600rpm;
2. two-phase excitation machine number of pole-pairs p in the present embodiment
n=6, use formula
calculate motor static time two-phase excitation machine excitation frequency f
0=60Hz.
3. adopt in the present embodiment and to enjoy a double blessing bridge two-phase inverter, it is U that the maximum two-phase alternating current that institute's energy inversion goes out under system dc busbar voltage is pressed with valid value
0=40V.
4., when motor is static, use 40V/60Hz two-phase AC excitation mode to carry out excitation to two-phase excitation machine, measuring now exciting current of exciter amplitude is i
ref=1.85A.
5. utilize prime mover to drag three grades of formula brushless synchronous starter-generators and accelerate to 1200rpm, simulated machine starting process.In the process omnidistance two-phase AC excitation control is carried out to two-phase excitation machine, and observe exciter two-phase excitation electric current and main generator back-emf.Specific as follows:
(5.1) obtained the instantaneous value of exciter two-phase excitation electric current by current sample module, be designated as i respectively
αand i
β.Use formula
calculating the amplitude of current excitation current vector, is i through DC filtering postscript
s.
(5.2) exciting current reference value (1.85A) and current exciting current value i is calculated
sdifference, be designated as current error e
i, i.e. e
i=i
ref-i
s.
(5.3) ratio, integral coefficient that current closed-loop PI controls are set: K
p=0.2, K
i=0.1.To current error e
icarry out PI adjustment, calculate the current modulation voltage vector magnitude U of two-phase excitation machine, i.e. U=K
pe
i+ K
i∫ e
idt.
(5.4) obtain current motor rotating speed by speed probe, be designated as n
r(unit be rev/min).
(5.5) by current for motor rotating speed n
rcompare with intermediate speed 600rpm, adopt following distinct methods to calculate current modulation voltage vector phase angle according to comparative result:
(2.5.1) n is worked as
rduring <600, the rotating magnetic field that two-phase excitation electric current produces is contrary with motor direction of rotation.Use formula
calculate the current excitation frequency f of two-phase excitation machine
e.By formula θ
k=θ
k-1+ Δ θ obtains current voltage vector phase angle θ
k.Wherein, θ
k-1for the voltage vector phase angle in a upper computing cycle moment, Δ θ=2 π f
et
sfor the increment at voltage vector phase angle, t
sfor computing cycle.
(2.5.2) n is worked as
rwhen>=600, the rotating magnetic field that two-phase excitation electric current produces is identical with motor direction of rotation.Use formula
calculate the current excitation frequency f of two-phase excitation machine
e.By formula θ
k=θ
k-1-Δ θ obtains current voltage vector phase angle θ
k.
(5.6) the current modulation voltage vector magnitude obtained and phase angle information is combined, SVPWM method is used to obtain inverter power demand pipe switch controlling signal, and drive two-phase excitation machine with this signal controlling two-phase inverter, realize the excitation function of three grades of formula brushless synchronous starter-generators.
Fig. 5 be in the present embodiment main generator back-emf effective value in motor starting process with motor speed change trend.Fig. 6 be business's (reflect main generator excitation situation, be directly proportional to main generator excitation electric current) of main generator back-emf effective value and motor speed in the present embodiment in motor starting process with the trend that motor speed changes.As can be seen from the figure, along with the rising of motor speed, main generator excitation electric current remains unchanged substantially.
Fig. 7 is the change curve of two-phase excitation electric current near electric motor starting stage intermediate speed.As can be seen from the figure, two-phase excitation electric current is very steady from the process of transition after the forward direction of intermediate speed.
Claims (4)
1. aviation three grades of formula starting-generating system start stage excitation control methods, is characterized in that step is as follows:
Step 1: when motor is static, employing exciting voltage is U
0, excitation frequency is f
0two-phase AC excitation mode excitation is carried out to two-phase excitation machine, and to measure now exciting current of exciter amplitude be i
ref, as the reference value of closed-loop current control; Described U
0by two-phase inverter under system dc busbar voltage the maximum two-phase alternating current pressure value that goes out of energy inversion; Described
for motor static time two-phase excitation machine excitation frequency, wherein p
nfor two-phase excitation machine number of pole-pairs; Described motor starting process rotating speed median
n
maxmaximum speed value in motor starting process, unit is rev/min;
Step 2: electric motor starting stage, by two-phase excitation machine exciting current closed-loop control determination exciter excitation voltage vector magnitude, specific as follows:
Step 2.1: the instantaneous value being obtained exciter two-phase excitation electric current by current sample module, is designated as i respectively
αand i
β; Use formula
calculate the amplitude of current excitation current vector, be designated as i
s;
Step 2.2: calculate exciting current reference value i
refwith current exciting current value i
sdifference, be designated as current error e
i, i.e. e
i=i
ref-i
s; To current error e
icarry out PI adjustment, pass through U=K
pe
i+ K
i∫ e
idt calculates the current modulation voltage vector magnitude U of two-phase excitation machine; Wherein, K
p, K
ibe respectively the ratio of exciting current closed loop PI controller, integral coefficient, and K
p> 0, K
i> 0;
Step 3: by current for motor rotating speed n
rwith intermediate speed n
scompare, adopt following distinct methods to calculate current modulation voltage vector phase angle according to comparative result; n
rfor speed probe obtains current motor rotating speed, unit is rev/min;
Current rotating speed n
rbe less than intermediate speed n
stime, the rotating magnetic field that two-phase excitation electric current produces is contrary with motor direction of rotation; Use formula
calculate the current excitation frequency f of two-phase excitation machine
e; By formula θ
k=θ
k-1+ Δ θ obtains current voltage vector phase angle θ
k; Wherein, θ
k-1for the voltage vector phase angle in a upper computing cycle moment, Δ θ=2 π f
et
sfor the increment at voltage vector phase angle, t
sfor computing cycle;
Current rotating speed n
rbe more than or equal to speed-changing n
stime, the rotating magnetic field that two-phase excitation electric current produces is identical with motor direction of rotation; Use formula
calculate the current excitation frequency f of two-phase excitation machine
e; By formula θ
k=θ
k-1-Δ θ obtains current voltage vector phase angle θ
k; Wherein, θ
k-1for the voltage vector phase angle in a upper computing cycle moment, Δ θ=2 π f
et
sfor the increment at voltage vector phase angle, t
sfor computing cycle;
Step 4: integrating step 2 gained current modulation voltage vector magnitude and step 3 gained current modulation voltage vector phase angle, obtain inverter power demand pipe switch controlling signal by voltage modulated method, and drive two-phase inverter to control two-phase excitation machine with this signal.
2. aviation three grades of formula starting-generating system start stage excitation control methods according to claim 1, is characterized in that: described two-phase inverter is two single bridge two-phase inverter, three-phase full-bridge inverter or bridge two-phase inverters of enjoying a double blessing.
3. aviation three grades of formula starting-generating system start stage excitation control methods according to claim 1, is characterized in that: described voltage modulated method is space vector width pulse modulation method SVPWM or sine wave pulse width modulation method SPWM.
4. aviation three grades of formula starting-generating system start stage excitation control methods according to claim 1, is characterized in that: described speed probe is resolver, photoelectric encoder or Hall element.
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| CN105553375A (en) * | 2015-12-28 | 2016-05-04 | 西北工业大学 | Control method for starting aviation AC starter/generator at non-zero rotating speed |
| CN107425763A (en) * | 2017-07-07 | 2017-12-01 | 西北工业大学 | A kind of aviation multi-stag electric excitation synchronous motor torque ripple minimization method |
| CN108599260A (en) * | 2018-06-22 | 2018-09-28 | 合肥为民电源有限公司 | A kind of generated output power control method and device inhibiting harmonic current |
| CN110912478A (en) * | 2019-12-04 | 2020-03-24 | 陕西航空电气有限责任公司 | Constant-voltage constant-frequency power generation control method based on alternating-current bidirectional excitation |
| CN112653365A (en) * | 2020-12-04 | 2021-04-13 | 南京航空航天大学 | AC/DC excitation smooth switching method in starting process of three-stage brushless synchronous motor |
| CN112671282A (en) * | 2020-12-04 | 2021-04-16 | 南京航空航天大学 | AC/DC excitation natural switching method for starting process of three-stage synchronous motor |
| CN113472256A (en) * | 2021-07-05 | 2021-10-01 | 西北工业大学 | Excitation controller of aviation three-stage starting power generation system and rotor position estimation method |
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| CN107425763A (en) * | 2017-07-07 | 2017-12-01 | 西北工业大学 | A kind of aviation multi-stag electric excitation synchronous motor torque ripple minimization method |
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| CN108599260A (en) * | 2018-06-22 | 2018-09-28 | 合肥为民电源有限公司 | A kind of generated output power control method and device inhibiting harmonic current |
| CN110912478A (en) * | 2019-12-04 | 2020-03-24 | 陕西航空电气有限责任公司 | Constant-voltage constant-frequency power generation control method based on alternating-current bidirectional excitation |
| CN112653365A (en) * | 2020-12-04 | 2021-04-13 | 南京航空航天大学 | AC/DC excitation smooth switching method in starting process of three-stage brushless synchronous motor |
| CN112671282A (en) * | 2020-12-04 | 2021-04-16 | 南京航空航天大学 | AC/DC excitation natural switching method for starting process of three-stage synchronous motor |
| CN113472256A (en) * | 2021-07-05 | 2021-10-01 | 西北工业大学 | Excitation controller of aviation three-stage starting power generation system and rotor position estimation method |
| CN113472256B (en) * | 2021-07-05 | 2023-02-10 | 西北工业大学 | Rotor position estimation method of excitation controller of aviation three-stage starting power generation system |
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