CN110445410A - A kind of more closed loops of aircraft are for electric regulating system and power supply adjusting method - Google Patents
A kind of more closed loops of aircraft are for electric regulating system and power supply adjusting method Download PDFInfo
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- CN110445410A CN110445410A CN201910745850.7A CN201910745850A CN110445410A CN 110445410 A CN110445410 A CN 110445410A CN 201910745850 A CN201910745850 A CN 201910745850A CN 110445410 A CN110445410 A CN 110445410A
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Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D47/00—Equipment not otherwise provided for
-
- 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
-
- 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
- H02J3/36—Arrangements for transfer of electric power between ac networks via a high-tension dc link
-
- 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
- H02J3/38—Arrangements for parallely feeding a single network by two or more generators, converters or transformers
-
- H—ELECTRICITY
- H02—GENERATION; CONVERSION OR DISTRIBUTION OF ELECTRIC POWER
- H02M—APPARATUS FOR CONVERSION BETWEEN AC AND AC, BETWEEN AC AND DC, OR BETWEEN DC AND DC, AND FOR USE WITH MAINS OR SIMILAR POWER SUPPLY SYSTEMS; CONVERSION OF DC OR AC INPUT POWER INTO SURGE OUTPUT POWER; CONTROL OR REGULATION THEREOF
- H02M1/00—Details of apparatus for conversion
- H02M1/12—Arrangements for reducing harmonics from ac input or output
-
- H—ELECTRICITY
- H02—GENERATION; CONVERSION OR DISTRIBUTION OF ELECTRIC POWER
- H02M—APPARATUS FOR CONVERSION BETWEEN AC AND AC, BETWEEN AC AND DC, OR BETWEEN DC AND DC, AND FOR USE WITH MAINS OR SIMILAR POWER SUPPLY SYSTEMS; CONVERSION OF DC OR AC INPUT POWER INTO SURGE OUTPUT POWER; CONTROL OR REGULATION THEREOF
- H02M5/00—Conversion of ac power input into ac power output, e.g. for change of voltage, for change of frequency, for change of number of phases
- H02M5/40—Conversion of ac power input into ac power output, e.g. for change of voltage, for change of frequency, for change of number of phases with intermediate conversion into dc
- H02M5/42—Conversion of ac power input into ac power output, e.g. for change of voltage, for change of frequency, for change of number of phases with intermediate conversion into dc by static converters
- H02M5/44—Conversion of ac power input into ac power output, e.g. for change of voltage, for change of frequency, for change of number of phases with intermediate conversion into dc by static converters using discharge tubes or semiconductor devices to convert the intermediate dc into ac
- H02M5/453—Conversion of ac power input into ac power output, e.g. for change of voltage, for change of frequency, for change of number of phases with intermediate conversion into dc by static converters using discharge tubes or semiconductor devices to convert the intermediate dc into ac using devices of a triode or transistor type requiring continuous application of a control signal
- H02M5/458—Conversion of ac power input into ac power output, e.g. for change of voltage, for change of frequency, for change of number of phases with intermediate conversion into dc by static converters using discharge tubes or semiconductor devices to convert the intermediate dc into ac using devices of a triode or transistor type requiring continuous application of a control signal using semiconductor devices only
- H02M5/4585—Conversion of ac power input into ac power output, e.g. for change of voltage, for change of frequency, for change of number of phases with intermediate conversion into dc by static converters using discharge tubes or semiconductor devices to convert the intermediate dc into ac using devices of a triode or transistor type requiring continuous application of a control signal using semiconductor devices only having a rectifier with controlled elements
-
- H—ELECTRICITY
- H02—GENERATION; CONVERSION OR DISTRIBUTION OF ELECTRIC POWER
- H02M—APPARATUS FOR CONVERSION BETWEEN AC AND AC, BETWEEN AC AND DC, OR BETWEEN DC AND DC, AND FOR USE WITH MAINS OR SIMILAR POWER SUPPLY SYSTEMS; CONVERSION OF DC OR AC INPUT POWER INTO SURGE OUTPUT POWER; CONTROL OR REGULATION THEREOF
- H02M7/00—Conversion of ac power input into dc power output; Conversion of dc power input into ac power output
- H02M7/42—Conversion of dc power input into ac power output without possibility of reversal
- H02M7/44—Conversion of dc power input into ac power output without possibility of reversal by static converters
- H02M7/48—Conversion of dc power input into ac power output without possibility of reversal by static converters using discharge tubes with control electrode or semiconductor devices with control electrode
- H02M7/493—Conversion of dc power input into ac power output without possibility of reversal by static converters using discharge tubes with control electrode or semiconductor devices with control electrode the static converters being arranged for operation in parallel
-
- 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
- H02P21/00—Arrangements or methods for the control of electric machines by vector control, e.g. by control of field orientation
- H02P21/0003—Control strategies in general, e.g. linear type, e.g. P, PI, PID, using robust control
-
- 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
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D2221/00—Electric power distribution systems onboard aircraft
-
- 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
- H02P2101/00—Special adaptation of control arrangements for generators
- H02P2101/30—Special adaptation of control arrangements for generators for aircraft
-
- 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
- H02P2103/00—Controlling arrangements characterised by the type of generator
- H02P2103/20—Controlling arrangements characterised by the type of generator of the synchronous type
-
- 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
Landscapes
- Engineering & Computer Science (AREA)
- Power Engineering (AREA)
- Aviation & Aerospace Engineering (AREA)
- Inverter Devices (AREA)
Abstract
The present invention relates to aircraft electrical power supply system technical field, a kind of more closed loops of aircraft are disclosed for electric regulating system, comprising: the inversion unit system of multiple parallel connections is connect with high voltage direct current power supply system and airplane load control system respectively；The invention also discloses a kind of more closed loops power supply adjusting methods of aircraft, are adjusted input linear load system and/or the voltage of nonlinear load system to 115V with the double-closed-loop control device being attached thereto by the inversion unit system of multiple parallel connections；When accessing linear load system, realize that load voltage is adjusted by the outer voltage controller in double-closed-loop control device；The current regulation of the inversion unit system of its connection is realized by the current inner loop controller in double-closed-loop control device；Divide equally algorithm by second order power equalization, the effective of power divides equally after guaranteeing linear load system access；It when access nonlinear load system, is compensated by harmonic voltage ring, realizes the harmonics restraint to each secondary frequencies.
Description
Technical field
The present invention relates to aircraft electrical power supply system technical fields, and in particular to a kind of more closed loops of aircraft are for electric regulating system and confession
Electric adjusting method.
Background technique
In recent years, more and more aircraft utilization electric power replace hydraulic, pneumatic and machine power both at home and abroad, also allow a large amount of
Power adapter and electrical driver are widely applied on all kinds of aircrafts.Studies at home and abroad show that more electricity, electric aircraft
It is still the main trend of aircraft future development, all there is an urgent need to electric power to realize dragging for more loads and equipment on aircraft, and
Guarantee redundancy, the safety and reliability of power supply.More electricity, electric aircrafts development there is an urgent need to power supply systems under the new situation
Innovation and development.
But existing aircraft electrical power supply system is still not perfect, it is necessary to study the power supply system of a kind of high reliability, high redundancy
System model, quality of voltage and power-sharing characteristic after guaranteeing linear load and nonlinear load access system, is reduced as far as possible
Aircraft weight, it is whole to promote aviation power supply performance.
Summary of the invention
The present invention is directed to the prior art, provides a kind of more closed loops of aircraft for electric regulating system, using multiple in parallel inverse
Become cellular system and replace traditional single inversion unit, increase the capacity of inverter, while cancelling constant speed drive device, reduces and fly
Machine total weight increases the redundancy of system.
The present invention also provides a kind of more closed loops power supply adjusting methods of aircraft, technical solutions are as follows: non-linear negative accessing
It when loading system, is compensated using harmonic voltage ring, reduces voltage harmonic component value, provide high reliability voltage for power supply unit, protected
Demonstrate,prove power-sharing.
The present invention is achieved through the following technical solutions: the more closed loops of aircraft are for electric regulating system, including multiple parallel connections
Inversion unit system is connect with high voltage direct current power supply system and airplane load control system respectively；
The high voltage direct current power supply system includes generator, control loop system, PWM modulation module and rectifier, the hair
Motor output end connects PI controller, and control loop system connects PWM modulation module, and PWM modulation module connects rectifier, by whole
Stream device obtains stable high voltage direct current；
Inversion unit system, including three-phase full-bridge inverter, double-closed-loop control device, LCL filter and SPWM modulation module,
The three-phase full-bridge inverter, SPWM modulation module, double-closed-loop control device are sequentially connected, and realize SPWM modulation；Each inversion list
Metasystem is connected to ac bus by bus；The inversion unit system is powered by high voltage direct current power supply system；The LCL
Filter is arranged on the route that inversion unit system is connect with ac bus, and the LCL filter and double-closed-loop control device connect
It connects.
Further, the control loop system includes the first coordinate transformation module group and PI control ring, first coordinate
Conversion module group includes the first Clark conversion module, the first Park conversion module, the first Park inverse transform block, the first Clark
Inverse transform block；The output signal of the generator passes sequentially through the first Clark conversion module, the first Park conversion module,
Input current control ring after one Park inverse transform block, the first Clark inverse transform block；The PI controller connects rectifier.
Further, the double-closed-loop control device includes outer voltage controller and current inner loop controller；Outer voltage
Controller is connected with the second coordinate transformation module connecting with LCL filter；Current inner loop controller is connected with and LCL filter
The third coordinate transformation module of connection；Outer voltage controller is also respectively connected with reference voltage generator and multi-resonant controller；
The multi-resonant controller includes the resonance modules of multiple parallel connections.
The present invention also provides a kind of more closed loops power supply adjusting methods of aircraft, technical solutions are as follows:
The high voltage direct current power supply system being made of generator and rectifier is established, the exchange for the frequency conversion that wherein generator generates
Electricity obtains 270V high voltage direct current by rectifier；
Establish by the inversion unit system of multiple parallel connections form for electric regulating system, pass through the two close cycles of one-to-one connection
Controller adjusts input linear load system and/or the voltage of nonlinear load system to 115V；
When accessing linear load system, load voltage tune is realized by the outer voltage controller in double-closed-loop control device
Section；The current regulation of the inversion unit system of its connection is realized by the current inner loop controller in double-closed-loop control device；Pass through
Second order power-sharing algorithm, the effective of power divides equally after guaranteeing linear load system access；
It when access nonlinear load system, is compensated by harmonic voltage ring, realizes the harmonics restraint to each secondary frequencies.
Further, for the alternating current that generator generates by the adjustment output of PI controller, the PI controller includes electric current
Ring controller and voltage ring controller.
Further, Clarke transformation, Park transformation are carried out by three phase coordinate systems to generator, then passes through anti-Park
Transformation, anti-Park transformation Clarke transformation, the active power of the magnetic flux and q axis that control d axis make generator work in power generation mode；
The coordinate transform formula of Clarke transformation and Park transformation are as follows:
Wherein, [xabc] and [xdq] respectively indicate three phase static abc coordinate system and the variable under two-phase rotation dq coordinate system, θ
For generator's power and angle；
The coordinate transform formula of anti-Park transformation, anti-Park transformation Clarke transformation are as follows:
Vector controlled is used to high voltage direct current power supply system, obtains the voltage equation under dq coordinate system are as follows:
Wherein, s indicates complex frequency domain, RgeAnd LgeFor generator unit stator resistance and inductance；ωeIt (rad/s) is motor rotation speed
Degree；φmFor the magnetic linkage of permanent magnet；idqIt is the stator current of d axis and q axis；
The output DC current of the current loop controller adjustment engine of q axis；
The current loop control link G of vector control of generatordc_iIt may be expressed as:
DC voltage vdcIt is controlled by voltage ring controller, generates the reference value of rectifier input current ring controller
iqref；The ratio and integral coefficient of voltage ring controller are chosen for 0.03 and 0.6 respectively.
Further, realize that load voltage is adjusted by the outer voltage controller in double-closed-loop control device, it is specific to wrap
It includes:
Each inversion unit real-time detection to active and reactive power be passed through resultant voltage reference value after power controller
v*abc；Voltage reference value v* abc, three-phase output voltage vC,abcWith the side electric current i of three-phase full-bridge inverterL,abcIt is converted by Park
The voltage reference value v being respectively converted under dq reference axis* dq, output voltage vC,dqWith inverter side electric current iL,dq；By v* dqWith output
Voltage vC,dqAfter comparing, reference value needed for obtaining current inner loop controller by outer voltage controller, and by being somebody's turn to do
Reference value and inverter side electric current iL,dqIt is poor to make, using the modulated signal of difficult to understand distributed generation resource of current inner loop controller moral, then
It is modulated by SPWM；
Wherein, in outer voltage controller, the corresponding state equation of outer voltage controller with decoupling of design is:
Wherein, φdqFor Voltage loop auxiliary variable, v* CdAnd v* CqFor Voltage loop reference value dq axis component；
Then: algebraic equation shown in formula (3) can be described as:
Wherein φdqFor the auxiliary variable of outer voltage controller, v* CdAnd v* CqFor outer voltage controller reference value dq axis
Component.The corresponding algebraic equation of formula (3) can be described as:
The input signal of outer voltage control is divided into two parts, including reference input matrix BV1With feed back input matrix
BV2, the linearisation condition of small signal space form of outer voltage controller may be expressed as:
Wherein, Δ is small signal disturbance；
In formula (8), matrix BV1And BV2Are as follows:
Formula (6) and (7) can rewrite are as follows:
Wherein, Matrix CV, DV1, DV2It respectively indicates are as follows:
Further, the current regulation of the inversion unit system of its connection is realized by current inner loop controller, it is specific
It include: the reference value that inverter side electric current is generated by outer voltage controllerThe reality of filtered circuit reference value and measurement
Inverter side electric current (iLdq) difference by current inner loop controller obtain for SPWM modulate voltage value；
Wherein, the state equation of current inner loop controller are as follows:
Wherein γdqFor electric current loop auxiliary variable；
The corresponding algebraic equation of formula (12) are as follows:
Wherein, kpcAnd kicThe respectively ratio and integral coefficient of electric current, udacAnd uqacFor the dq axis point of SPWM modulation voltage
Amount；
Formula (10) can be converted into following form:
Further, by second order power-sharing algorithm, the effective of power divides equally after guaranteeing linear load system access,
It specifically includes:
By the instantaneous active and reactive component p and q that will be calculated by the output voltage measured with output electric current, then lead to
Low-pass filter is crossed, the approximation of fundamental active and reactive power P and Q can be obtained.At this point, instantaneous active component p and idle point
Q is measured to calculate by dq shaft voltage electric current:
P=vCdiod+vCqioq (17)
Q=vCdioq+vCqiod (18)
Then the approximation of active-power P and reactive power Q may be expressed as:
Wherein ωcFor low pass filter cutoff frequency；
Output voltage can be obtained by formula (20):
Wherein EiAnd E*Respectively output voltage amplitude and voltage magnitude reference value, ωhFor the height of second order power-sharing algorithm
Logical cutoff frequency, nEFor active power regulation coefficient.
Similarly mode, angular frequency can derive the equation as shown in formula (21):
Wherein ωiAnd ω*Respectively output voltage frequency and electric voltage frequency reference value, mωFor reactive power regulation coefficient.
The reference voltage value that outer voltage controller is further generated by formula (20) and (21), forms complete closed loop system
System, it may be assumed that
Further, when access nonlinear load system, by it is in parallel it is multiple be tuned to needed for compensation harmonic frequency it is humorous
Vibration module obtains multi-resonant controller, and then realizes to the harmonics restraint of each secondary frequencies, specifically includes:
The harmonic voltage of multi-resonant controller compensates Gh(s) are as follows:
Wherein, h is the overtone order of required compensation, and ω 0 is fundamental wave frequency, and kih indicates the resonance gain of each harmonic；
By double-closed-loop control device input signal when accessing linear load system --- active and reactive power is adjusted to base
Wave positive sequence is active, and it is as follows to extract harmonic power using the voltage and current component detected with fundamental positive sequence reactive power:
Wherein, τ is low-pass filter time constant,WithIt is the fundamental positive sequence and negative phase-sequence point for exporting electric current
Amount；Wherein P+For fundamental positive sequence active power, Q+For fundamental positive sequence reactive power, τ is low-pass filter time constant, vα, vβFor
Component of the load voltage on α β axis；
Then, based on the power control of fundamental positive sequence are as follows:
Compared with prior art, the present invention have the following advantages that and the utility model has the advantages that
(1) the more closed loops of a kind of aircraft provided by the present invention are for electric regulating system, by generator, rectifier and it is multiple simultaneously
The Novel DC and ac power supply system structure of the inverter unit system composition of connection, eliminate constant speed drive device, without
Using separate unit large capacity inverter apparatus, aircraft gross weight amount is reduced, promotes aircraft overall performance.
(2) the more closed loops of a kind of aircraft provided by the present invention no longer need to the Excitation Adjustment by generator for electric regulating system
Load voltage can be adjusted to 115V by more Closed loop Controls, while solve the problems, such as that bearing power is divided equally by section.
(3) a kind of more closed loops of aircraft provided by the present invention are powered adjusting methods, provide the linear load system of access and
The adjusting method of nonlinear load system；It after nonlinear load system access, is compensated using harmonic voltage ring, it is humorous to reduce voltage
Wavelength-division magnitude provides high reliability voltage for power supply unit, guarantees power-sharing, the whole redundancy for improving aircraft electrical power supply system
Property, stability and reliability.
Detailed description of the invention
Fig. 1 is the more closed loops of aircraft for electric regulating system design electrical schematic diagram；
Fig. 2 is the more closed loops of aircraft for electric regulating system design complete circuit；
Fig. 3 is static abc coordinate system and static α β coordinate system and dq coordinate system relation schematic diagram；
Fig. 4 is that DC power generation system exports direct current waveform diagram after accessing linear load system；
Fig. 5 exports three-phase voltage for inversion unit system each in electric regulating system for the more closed loops of aircraft after access linear load
Amplitude waveform diagram；
Fig. 6 exports three-phase voltage for inversion unit system each in electric regulating system for the more closed loops of aircraft after access linear load
Frequency waveform diagram；
Fig. 7 exports three-phase electricity for inversion unit system each in electric regulating system for the more closed loops of aircraft after access linear load
Pressure, current waveform figure；
Fig. 8 exports three-phase electricity for inversion unit system each in electric regulating system for the more closed loops of aircraft after access linear load
Pressure, current waveform figure；
Fig. 9 exports three-phase electricity for inversion unit system each in electric regulating system for the more closed loops of aircraft after access linear load
Pressure, current waveform figure；
Figure 10 be access linear load after the more closed loops of aircraft for inversion unit system each in electric regulating system 4 periods
Output voltage, current waveform figure；
Figure 11 exports wattful power for inversion unit system each in electric regulating system for the more closed loops of aircraft after access linear load
Rate waveform diagram；
Figure 12 exports idle function for inversion unit system each in electric regulating system for the more closed loops of aircraft after access linear load
Rate waveform diagram；
Figure 13 is DC power generation system output direct current waveform diagram after access nonlinear load；
Figure 14 exports three-phase for inversion unit system each in electric regulating system for the more closed loops of aircraft after access nonlinear load
Voltage, current waveform figure；
Figure 15 be access nonlinear load after the more closed loops of aircraft for inversion unit system output voltage each in electric regulating system,
Current waveform figure；
Figure 16 is that the more closed loops of aircraft are active for inversion unit system each in electric regulating system output after accessing nonlinear load
Power waveform；
Figure 17 is that the more closed loops of aircraft are idle for inversion unit system each in electric regulating system output after accessing nonlinear load
Power waveform；
Wherein: 1-water inlet cavity, 11-rinse side opening, and 12-water inlet pipes, 13-thread-holes, 2-are discharged cavities,
21-drainage side openings, 22-exit branch, 3-wire guides, 4-traction silk threads, 41-hard segments, 42-soft quality sections, 5-silks
Line outlet, 51-connectors, 6-indwellings folder.
Specific embodiment
The present invention is described in further detail below with reference to embodiment, embodiments of the present invention are not limited thereto.
In the present invention, the engine is permanent magnet synchronous motor (hereafter abbreviated with PMSG), ωmFor mechanical angle speed
Degree, angular rate ωeRevolving speed in 15000~25000r/min, generator magnetic flux and inductance respectively byAnd LgeIt indicates, main hair
Rated motor electrical power is 64kVA, and number of pole-pairs 4, rated output line voltage is 110V；Exciter is 2.4kVA, and number of pole-pairs is
6, rated output line voltage is 270V；Triangular wave frequency needed for rectifier PWM modulation is 5kHz.
Rectifier switch frequency is 10kHz, filter capacitor CdcFor 0.4mF.
As shown in Figure 1 and Figure 2, the more closed loops of aircraft are for electric regulating system, the inversion unit system including multiple parallel connections, respectively
It is connect with high voltage direct current power supply system and airplane load control system；
The high voltage direct current power supply system includes generator, control loop system, PWM modulation module and rectifier, the hair
Motor output end connects PI controller, and control loop system connects PWM modulation module, and PWM modulation module connects rectifier, by whole
Stream device obtains stable high voltage direct current；
Inversion unit system, including three-phase full-bridge inverter, double-closed-loop control device, LCL filter and SPWM modulation module,
The three-phase full-bridge inverter, SPWM modulation module, double-closed-loop control device are sequentially connected, and realize SPWM modulation；Each inversion list
Metasystem is connected to ac bus by bus；The inversion unit system is powered by high voltage direct current power supply system；The LCL
Filter is arranged on the route that inversion unit system is connect with ac bus, and the LCL filter and double-closed-loop control device connect
It connects.
The control loop system includes the first coordinate transformation module group and PI control ring, the first coordinate transformation module group
Including the first Clark conversion module, the first Park conversion module, the first Park inverse transform block, the first Clark contravariant mold changing
Block；It is anti-that the output signal of the generator passes sequentially through the first Clark conversion module, the first Park conversion module, the first Park
Input current control ring after conversion module, the first Clark inverse transform block；The PI controller connects rectifier.
The double-closed-loop control device includes outer voltage controller and current inner loop controller；The connection of outer voltage controller
There is the second coordinate transformation module connecting with LCL filter；Current inner loop controller is connected with the third connecting with LCL filter
Coordinate transformation module；Outer voltage controller is also respectively connected with reference voltage generator and multi-resonant controller；The multi-resonant
Controller includes the resonance modules of multiple parallel connections.
The more closed loops power supply adjusting methods of its aircraft, specifically include:
The high voltage direct current power supply system being made of generator and rectifier is established, the exchange for the frequency conversion that wherein generator generates
Electricity obtains 270V high voltage direct current by rectifier；
Establish by the inversion unit system of multiple parallel connections form for electric regulating system, pass through the two close cycles of one-to-one connection
Controller adjusts input linear load system and/or the voltage of nonlinear load system to 115V；
When accessing linear load system, load voltage tune is realized by the outer voltage controller in double-closed-loop control device
Section；The current regulation of the inversion unit system of its connection is realized by the current inner loop controller in double-closed-loop control device；Pass through
Second order power equalization divides equally algorithm, and the effective of power divides equally after guaranteeing linear load system access；
It when access nonlinear load system, is compensated by harmonic voltage ring, realizes the harmonics restraint to each secondary frequencies.
Generator generate alternating current by PI controller adjustment output, the PI controller include current loop controller and
Voltage ring controller.
Itself the following steps are included:
S1 changes in coordinates as shown in Figure 3) is used, is two on dq axis by the three-phase abc coordinate system change of variable of generator
Phase DC quantity.
Its specifically: the dq axis component of aleatory variable x is expressed as xd, xq, corresponding two dimension column vector [xd, xq]TIt writes a Chinese character in simplified form
For xdq.Variable under dq coordinate system in order to obtain is converted first with the Clarke of constant power by variable in static abc coordinate system
xabcIt transforms in static α β coordinate system, recycles Park transformation by the change of variable in static α β coordinate system to rotation dq coordinate
Variable x is obtained under systemdq, complete coordinate transform formula are as follows:
Wherein, [xabc] and [xdq] respectively indicate three phase static abc coordinate system and the variable under two-phase rotation dq coordinate system, θ
For generator's power and angle.
Correspondingly, being become again under abc coordinate system from the variable under dq coordinate system, only need to be using Park and Clarke inverse transformation
Can, specific transformation for mula are as follows:
With coordinate transform, PMSG is set to work in power generation mode by the active power of the magnetic flux and q axis that control d axis.Q axis
PI controller adjustment output DC current ensure that maximum in base fast (permanent torque region) hereinafter, d shaft current component is zero
Torque current ratio.In high-speed cruising region, the counter electromotive force of PMSG is directly proportional to speed.
Vector controlled is used to PMSG- rectifier, the voltage equation under available dq coordinate system is
Wherein s indicates complex frequency domain, RgeAnd LgeFor generator unit stator resistance and inductance；ωeIt (rad/s) is motor rotation speed
Degree；φmFor the magnetic linkage of permanent magnet；idqIt is the stator current of d axis and q axis.Vector control of generator current inner loop control link
Gdc_iIt may be expressed as:
Interior electric current loop is reduced to centre frequency ω at this timecFirst-order system.And DC voltage vdcAfter being controlled by PI,
Generate the reference value i that rectifier enters to hold alternating current q axis control ringqref, the ratio and integral coefficient point of Voltage loop PI controller
0.03 and 0.6 are not chosen for it.
S2) after obtaining 270V stable high voltage direct current, pass through outer voltage controller and realize linear load system
Voltage is accurately adjusted:
In Fig. 2, vdcIt is DC bus-bar voltage, L, Cf、LoThe respectively inductance of LCL type filter, capacitor and output filtering
Inductance.iLabc、vCabcAnd ioabcRespectively inverter side electric current, capacitance voltage and output electric current, and its corresponding dq axis component point
It Wei not iLd, iLq；vCd, vCq；iod, ioq.Frequencies omegaiThe phase angle of each distributed generation resource can be obtained to time integral, and further will
Phase angle and voltage magnitude E after phase angle and displacement pi/2iCan resultant voltage outer ring reference voltage v* abc。
Fig. 2 includes the three-phase full-bridge inverter and its double-closed-loop control device of multiple parallel connections, and each inversion unit passes through bus
It is connected to ac bus.Wherein, each inverter unit and its double-closed-loop control device contain local controller and corresponding LCL filter
Wave device.The IGBT switching frequency of inverter H bridge is 10kHz, and DC side voltage of converter is what generator was generated by rectifier
High voltage direct current, each inverter side inductance L and LoIt is 1.8mH, filter capacity CfFor 25 μ F.
Each inversion unit real-time detection to active and reactive power be passed through second order power controller after resultant voltage refer to
Value v* abc.Voltage reference value v* abc, three-phase output voltage vC,abcWith three-phase full-bridge inverter side electric current iL,abcData pass through
It is respectively voltage reference value v under dq reference axis that Park transformation, which is converted to,* dq, output voltage vC,dqWith inverter side electric current iL,dq.It will
v* dqWith output voltage vC,dqAfter comparing, current inner loop reference value can be obtained by outer voltage controller, further with it is inverse
Become device side electric current iL,dqIt is poor to make, and the modulated signal of each distributed generation resource can be obtained by current inner loop controller, finally by
SPWM enables the inversion unit system stable operation of multiple parallel connections.
In outer voltage controller, the coupling of occurrences on dq axis, the outer voltage control with decoupling of design are considered
The corresponding state equation of device is:
Wherein φdqFor the auxiliary variable of outer voltage controller, v* CdAnd v* CqFor outer voltage controller reference value dq axis
Component.The corresponding algebraic equation of formula (3) can be described as:
Wherein, kpvAnd kivThe respectively ratio and integral coefficient of outer voltage controller, i* LdAnd i* LqFor electric current loop reference
Value dq axis component, ω*For nominal operating frequency.
The linearisation condition of small signal space form of formula (8) expression voltage controller.At this point, in outer voltage controller
Input is divided into two parts: reference input matrix BV1With feed back input matrix BV2。
Wherein, Δ is small signal disturbance.
In formula (8), matrix BV1And BV2Are as follows:
Formula (6) and (7) can rewrite are as follows:
Wherein, Matrix CV, DV1, DV2It respectively indicates are as follows:
S3) after obtaining 270V stable high voltage direct current, pass through current inner loop controller and realize inverter list in parallel
The current regulation of metasystem improves dynamic performance:
In current inner loop controller, the reference value of inverter side electric current is generated by outer voltage controllerFiltered electrical
Flow the actual inverter side electric current (i of reference value and measurementLdq) difference by PI controller obtain for SPWM modulate voltage
Value.Therefore, the corresponding state equation of current controller are as follows:
Wherein γdqFor electric current loop auxiliary variable, corresponding algebraic equation are as follows:
Wherein, kpcAnd kicThe respectively ratio and integral coefficient of electric current, udacAnd uqacFor the dq axis point of SPWM modulation voltage
Amount.The form of formula (10) writeable accepted way of doing sth (15):
Wherein, Matrix CC, DC1, DC2It respectively indicates are as follows:
S4) after obtaining 270V stable high voltage direct current, cooperate Double closed-loop of voltage and current, it is equal by second order power
Divide algorithm, the effective of power divides equally after guaranteeing linear load system access.
By the instantaneous active and reactive component p and q that will be calculated by the output voltage measured with output electric current, then lead to
After crossing low-pass filter, can approximation obtain fundamental active and reactive power P and Q.At this point, instantaneous active and reactive component p and q are logical
Cross the calculating of dq shaft voltage electric current:
P=vCdiod+vCqioq (17)
Q=vCdioq+vCqiod (18)
The active and reactive power then exported may be expressed as:
Wherein ωcFor low pass filter cutoff frequency.
Above-mentioned output voltage can be obtained by formula (20):
Wherein EiAnd E*Respectively output voltage amplitude and voltage magnitude reference value, ωhFor the height of second order power-sharing algorithm
Logical cutoff frequency, nEFor active power regulation coefficient.
Similarly mode, angular frequency can derive the equation as shown in formula (21):
Wherein ωiAnd ω*Respectively output voltage frequency and electric voltage frequency reference value, mωFor reactive power regulation coefficient.
The reference voltage value that outer voltage controller is further generated by formula (20) and (21), forms complete closed loop system
System, it may be assumed that
S5) after nonlinear load system access, the harmonic current of introducing will cause load terminal voltage distortion, using harmonic wave
Voltage loop compensation, and optimize the second order double-closed-loop control device of outer voltage controller and current inner loop controller composition:
By it is in parallel it is multiple be tuned to needed for the resonance modules of compensation harmonic frequency obtain multi-resonant controller, Jin Ershi
Now to the harmonics restraint of each secondary frequencies:
The harmonic voltage of multi-resonant controller compensates Gh(s) are as follows:
Wherein, h is the overtone order of required compensation, ω0For fundamental wave frequency, kihIndicate the resonance gain of each harmonic.
At this point, by the double-closed-loop control device input signal under the conditions of linear load --- active and reactive power is adjusted to
Fundamental positive sequence is active and fundamental positive sequence reactive power, it may be assumed that input variable, which is changed to voltage, can get each harmonic value of voltage.Benefit
With the voltage and current component detected, the harmonic power for extracting main number is as follows:
Wherein, τ is low-pass filter time constant,WithIt is the fundamental positive sequence and negative phase-sequence for exporting electric current
Component；Wherein P+For fundamental positive sequence active power, Q+For fundamental positive sequence reactive power, τ is low-pass filter time constant, vα, vβ
For component of the load voltage on α β axis.At this time based on the power control loop of fundamental positive sequence are as follows:
Fig. 4~Figure 12 is to consider the more closed loops of linear load system access aircraft under electric regulating system in above-described embodiment
Simulation waveform, wherein E*For voltage magnitude reference value 115V, High Pass Filter Cutoff Frequency ωhFor 4 π, LPF Cutoff
Frequency is 10 π, idle regulation coefficient nEIt is 0.001, active power adjustment Coefficient mωIt is 0.001, electric voltage frequency reference value ω*For
400Hz。
Wherein, Fig. 4 is 270V high voltage direct current output waveform, adjustment time about 2s.After system starts until stablizing, directly
Stream side voltage maintains essentially in 270V, by directly using after distribution system for the equipment of aircraft requirement high pressure.It can be with from Fig. 5
Find out, the regulating system that above-mentioned technical proposal provides can provide stable 115V alternating voltage for linear load system, negative in 5s
It carries in the case of aggravating suddenly, voltage all has good dynamic property, meets loading demand.Fig. 6 is each in above-mentioned technical proposal
Inversion unit system exports three-phase voltage frequency waveform diagram, can stablize under double-closed-loop control device in 400Hz.Fig. 7~Fig. 9 is
Each inverter unit system exports three-phase voltage, current waveform figure in above-mentioned technical proposal, it can be seen that a inversion unit system
When middle current break, output voltage can still be stably maintained at 115V.Figure 10 is single inversion unit system in above-mentioned technical proposal
Output voltage, the current waveform figure in 4 periods of system.In outputting current steadily in 0.8A, voltage stabilization is in 115V.It is electric at this time
Current voltage same-phase shows that the circulation of each inversion unit system is inhibited.Figure 11 and Figure 12 is having for each linear load system
Function and reactive power emulation testing figure.Active as we can see from the figure and reactive power has obtained accurately dividing equally, and respectively may be about
550W and 130Var.
Figure 13~Figure 17 is the more closed loops of aircraft considered in nonlinear load system access above-mentioned technical proposal in embodiment
For the simulation waveform under electric regulating system.Figure 13 is 270V high voltage direct current output waveform, adjustment time about 1.5s.Due to connecing
The load entered is nonlinear load, therefore Figure 13 waveform is more obvious compared to Fig. 4 concussion, but the DC voltage exported remains to maintain
In 270V, loads and use for high voltage direct current.Figure 14 is single inversion in above-mentioned technical proposal after accessing nonlinear load system
Device exports three-phase voltage, current waveform figure.As can be seen that even if introducing current harmonics, but voltage after access nonlinear load
It is remaining to maintain 115V.Figure 14 be single inverter output voltage in above-mentioned technical proposal after access nonlinear load system,
Current waveform figure, although nonlinear load access system brings a large amount of harmonic current (peak value 1A), in multi-resonant control
Under the action of device and double-closed-loop control device processed, remaining to maintenance voltage almost is sine, provides stable 115V alternating current for load
Pressure.Figure 15 and Figure 16 be each nonlinear load fundamental positive sequence is active and reactive power emulation testing figure.As we can see from the figure
Fundamental positive sequence is active and reactive power is available accurate divides equally.
Aircraft more closed loops proposed by the present invention for the load of aircraft linear and nonlinear are for electric regulating system and its power supply
Adjusting method is not necessarily to constant speed driven gas heat pump transposition, adjusts AC load voltage without generator voltage controller, alleviates aircraft weight
Amount and engine controller burden, to improve aircraft overall performance；It can be achieved to linear load and nonlinear load power
Accurate to divide equally, maintenance voltage amplitude is in 115V, and frequency stabilization is in 400Hz；Even if part fault of converter, in the case of load sudden change
It still ensures that supply voltage quality and the effective of power are divided equally, ensure that the redundancy and reliability of system.
The above is only presently preferred embodiments of the present invention, not does limitation in any form to the present invention, it is all according to
According to technical spirit any simple modification to the above embodiments of the invention, equivalent variations, protection of the invention is each fallen within
Within the scope of.
Claims (10)
1. a kind of more closed loops of aircraft are for electric regulating system characterized by comprising
The inversion unit system of multiple parallel connections, connect with high voltage direct current power supply system and airplane load control system respectively；
The high voltage direct current power supply system includes generator, control loop system, PWM modulation module and rectifier, the generator
Output end connects PI controller, and control loop system connects PWM modulation module, and PWM modulation module connects rectifier, passes through rectifier
Obtain stable high voltage direct current；
Inversion unit system, including three-phase full-bridge inverter, double-closed-loop control device, LCL filter and SPWM modulation module, it is described
Three-phase full-bridge inverter, SPWM modulation module, double-closed-loop control device are sequentially connected, and realize SPWM modulation；Each inversion unit system
System is connected to ac bus by bus；The inversion unit system is powered by high voltage direct current power supply system；The LCL filtering
Device is arranged on the route that inversion unit system is connect with ac bus, and the LCL filter is connect with double-closed-loop control device.
The airplane load control system is linear load system or nonlinear load system.
2. the more closed loops of aircraft according to claim 1 are for electric regulating system, it is characterised in that: the control loop system includes
First coordinate transformation module group and PI control ring, the first coordinate transformation module group include the first Clark conversion module, first
Park conversion module, the first Park inverse transform block, the first Clark inverse transform block；The output signal of the generator is successively
Pass through the first Clark conversion module, the first Park conversion module, the first Park inverse transform block, the first Clark inverse transform block
Input current control ring afterwards；The PI controller connects rectifier.
3. the more closed loops of aircraft according to claim 1 are for electric regulating system, it is characterised in that: the double-closed-loop control device packet
Include outer voltage controller and current inner loop controller；Outer voltage controller is connected with second connect with LCL filter and sits
Mark conversion module；Current inner loop controller is connected with the third coordinate transformation module connecting with LCL filter；Outer voltage control
Device is also respectively connected with reference voltage generator and multi-resonant controller；The multi-resonant controller includes the resonant mode of multiple parallel connections
Block.
The adjusting method 4. a kind of more closed loops of aircraft are powered, which comprises the following steps:
The high voltage direct current power supply system being made of generator and rectifier is established, the alternating current for the frequency conversion that wherein generator generates is logical
Over commutation device obtains 270V high voltage direct current；
Establish by the inversion unit system of multiple parallel connections form for electric regulating system, pass through the double-closed-loop control of one-to-one connection
Device adjusts input linear load system and/or the voltage of nonlinear load system to 115V；
When accessing linear load system, realize that load voltage is adjusted by the outer voltage controller in double-closed-loop control device；It is logical
The current inner loop controller crossed in double-closed-loop control device realizes the current regulation of the inversion unit system of its connection；Pass through second order function
Algorithm is divided equally in rate equilibrium, and the effective of power divides equally after guaranteeing linear load system access；
It when access nonlinear load system, is compensated by harmonic voltage ring, realizes the harmonics restraint to each secondary frequencies.
The adjusting method 5. the more closed loops of aircraft according to claim 4 are powered, it is characterised in that: the alternating current that generator generates
It is adjusted and is exported by PI controller, the PI controller includes current loop controller and voltage ring controller.
The adjusting method 6. the more closed loops of aircraft according to claim 5 are powered, which is characterized in that it is specifically included:
Clarke transformation, Park transformation are carried out by three phase coordinate systems to generator, then is become by anti-Park transformation, anti-Park
Clarke transformation is changed, the active power of the magnetic flux and q axis that control d axis makes generator work in power generation mode；
The coordinate transform formula of Clarke transformation and Park transformation are as follows:
Wherein, [xabc] and [xdq] three phase static abc coordinate system and the variable under two-phase rotation dq coordinate system are respectively indicated, θ is hair
Motor generator rotor angle；
The coordinate transform formula of anti-Park transformation, anti-Park transformation Clarke transformation are as follows:
Vector controlled is used to high voltage direct current power supply system, obtains the voltage equation under dq coordinate system are as follows:
Wherein, s indicates complex frequency domain, RgeAnd LgeFor generator unit stator resistance and inductance；ωeIt (rad/s) is motor rotation speed；
φmFor the magnetic linkage of permanent magnet；idqIt is the stator current of d axis and q axis；
The output DC current of the current loop controller adjustment engine of q axis；
The current loop control link G of vector control of generatordc_iIt may be expressed as:
DC voltage vdcIt is controlled by voltage ring controller, generates the reference value i of rectifier input current ring controllerqref；
The ratio and integral coefficient of voltage ring controller are chosen for 0.03 and 0.6 respectively.
The adjusting method 7. the more closed loops of aircraft according to claim 4 are powered, which is characterized in that by double-closed-loop control device
Outer voltage controller realize load voltage adjust, specifically include:
Each inversion unit real-time detection to active and reactive power be passed through resultant voltage reference value v after power controller* abc；Electricity
Press reference value v* abc, three-phase output voltage vC,abcWith the side electric current i of three-phase full-bridge inverterL,abcIt is converted respectively by Park transformation
For the voltage reference value v under dq reference axis* dq, output voltage vC,dqWith inverter side electric current iL,dq；By v* dqWith output voltage vC,dq
After comparing, reference value needed for obtaining current inner loop controller by outer voltage controller, and by the reference value with
Inverter side electric current iL,dqIt is poor to make, and using the modulated signal of difficult to understand distributed generation resource of current inner loop controller moral, then passes through SPWM
Modulation；
Wherein, in outer voltage controller, the corresponding state equation of outer voltage controller with decoupling of design is:
Wherein, φdqFor Voltage loop auxiliary variable, v* CdAnd v* CqFor Voltage loop reference value dq axis component；
Then: algebraic equation shown in formula (3) can be described as:
Wherein φdqFor the auxiliary variable of outer voltage controller, v* CdAnd v* CqFor outer voltage controller reference value dq axis component.
The corresponding algebraic equation of formula (3) can be described as:
The input signal of outer voltage control is divided into two parts, including reference input matrix BV1With feed back input matrix BV2, electricity
The linearisation condition of small signal space form of pressure outer ring controller may be expressed as:
Wherein, Δ is small signal disturbance；
In formula (8), matrix BV1And BV2Are as follows:
Formula (6) and (7) can rewrite are as follows:
Wherein, Matrix CV, DV1, DV2It respectively indicates are as follows:
The adjusting method 8. the more closed loops of aircraft according to claim 4 are powered, which is characterized in that pass through current inner loop controller
The current regulation for realizing the inversion unit system of its connection, specifically includes: generating inverter side electricity by outer voltage controller
The reference value of streamThe actual inverter side electric current (i of filtered circuit reference value and measurementLdq) difference pass through current inner loop
Controller obtains the voltage value modulated for SPWM；
Wherein, the state equation of current inner loop controller are as follows:
Wherein γdqFor current inner loop controller auxiliary variable；
The corresponding algebraic equation of formula (12) are as follows:
Wherein, kpcAnd kicThe respectively ratio and integral coefficient of electric current, udacAnd uqacFor the dq axis component of SPWM modulation voltage；
Formula (10) can be converted into following form:
Wherein, Matrix CC, DC1, DC2It respectively indicates are as follows:
The adjusting method 9. the more closed loops of aircraft according to claim 4 are powered, which is characterized in that calculated by second order power-sharing
Method, the effective of power divides equally after guaranteeing linear load system access, specifically includes:
By the instantaneous active and reactive component p and q that will be calculated by the output voltage measured with output electric current, then by low
The approximation of fundamental active and reactive power P and Q can be obtained in bandpass filter.At this point, instantaneous active component p and reactive component q is logical
Cross the calculating of dq shaft voltage electric current:
P=vCdiod+vCqioq (17)
Q=vCdioq+vCqiod (18)
Then the approximation of active-power P and reactive power Q may be expressed as:
Wherein ωcFor low pass filter cutoff frequency；
Output voltage can be obtained by formula (20):
Wherein EiAnd E*Respectively output voltage amplitude and voltage magnitude reference value, ωhIt is cut for the high pass of second order power-sharing algorithm
Only frequency, nEFor active power regulation coefficient.
Similarly mode, angular frequency can derive the equation as shown in formula (21):
Wherein ωiAnd ω*Respectively output voltage frequency and electric voltage frequency reference value, mωFor reactive power regulation coefficient.
The reference voltage value that outer voltage controller is further generated by formula (20) and (21), forms complete closed-loop system, it may be assumed that
The adjusting method 10. the more closed loops of aircraft according to claim 4 are powered, which is characterized in that when access nonlinear load
System, by it is in parallel it is multiple be tuned to needed for the resonance modules of compensation harmonic frequency obtain multi-resonant controller, and then realize
To the harmonics restraint of each secondary frequencies, specifically include:
The harmonic voltage of multi-resonant controller compensates Gh(s) are as follows:
Wherein, h is the overtone order of required compensation, and ω 0 is fundamental wave frequency, and kih indicates the resonance gain of each harmonic；
By double-closed-loop control device input signal when accessing linear load system --- active and reactive power is being adjusted to fundamental wave just
Sequence is active, and it is as follows to extract harmonic power using the voltage and current component detected with fundamental positive sequence reactive power:
Wherein, τ is low-pass filter time constant,WithIt is the fundamental positive sequence and negative sequence component for exporting electric current；
Wherein P+For fundamental positive sequence active power, Q+For fundamental positive sequence reactive power, τ is low-pass filter time constant, vα, vβIt is negative
Carry component of the voltage on α β axis；
Then, based on the power control of fundamental positive sequence are as follows:
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Application publication date: 20191112 |