CN108736481A - A kind of aviation more electric engin AC/DC mixed power system and its design method - Google Patents
A kind of aviation more electric engin AC/DC mixed power system and its design method Download PDFInfo
- Publication number
- CN108736481A CN108736481A CN201810413035.6A CN201810413035A CN108736481A CN 108736481 A CN108736481 A CN 108736481A CN 201810413035 A CN201810413035 A CN 201810413035A CN 108736481 A CN108736481 A CN 108736481A
- Authority
- CN
- China
- Prior art keywords
- converters
- bus
- voltage
- electric
- power
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Pending
Links
Classifications
-
- 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
- H02J3/02—Circuit arrangements for ac mains or ac distribution networks using a single network for simultaneous distribution of power at different frequencies; using a single network for simultaneous distribution of ac power and of dc power
-
- 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
- H02J3/28—Arrangements for balancing of the load in a network by storage of energy
- H02J3/32—Arrangements for balancing of the load in a network by storage of energy using batteries with converting means
-
- 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
- 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
- H02J3/46—Controlling of the sharing of output between the generators, converters, or transformers
-
- 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
- Y02E40/20—Active power filtering [APF]
Abstract
The present invention provides a kind of aviation more electric engin AC/DC mixed power system and its design methods, the aviation more electric engin AC/DC mixed power system includes two built-in frequency-changing AC starting/generators in parallel, the output end of each built-in frequency-changing AC starting/generator is connected with AC/DC converters, the output end of AC/DC converters is connected with DC bus, DC bus is connected with DC/AC converters, two-way DC/DC converters, DC/AC converters are connected with ac bus and as outputs, and two-way DC/DC converters are connected with accumulator；Load is respectively connected on DC bus, ac bus；The AC/DC converters are self coupling transformation active power filtering rectifier, and the DC/AC converters are the inverter using virtual synchronous generator techniques.The present invention solves the problems, such as that existing aero-engine conventional electric power system power generation capacity cannot meet aviation more electric engin requirement.
Description
Technical field
The invention belongs to aviation more electric engin technical field, more particularly to a kind of electric power of Aviation more electric engin
Design method.
Background technology
Generator in traditional aero-engine is to realize supply of electric power by extracting shaft power, is typically mounted at casing
On, power generation capacity is smaller.The concept of more electric engin proposes to replace traditional hydraulic energy, air pressure and mechanical energy using electric energy
Equal secondary energy sources, this aspect can reduce the volume weight of aero-engine, reduce the complexity of attachment, also help simultaneously
The maintenance and maintenance of equipment improve aero-engine reliability of operation.More electric engin uses built-in starting/power generation
Machine, this makes the structure of engine become compact, reduces front face area, is conducive to further increase fuel oil utilization ratio, therefore
It is the developing direction of the following aero-engine.
Since traditional aero-engine power generation capacity is smaller, power supply system successively live through 28V direct currents,
The hybrid power system that 115V400Hz is exchanged or the two is combined, but with the proposition of aviation more electric engin concept, pass
The power supply system of system cannot meet the power demand of aircraft, it is therefore necessary to study novel electric system.Mesh
The preceding more electric engin power system power supply system being applied have 270V high voltage direct current (being mainly used on F-35) and
Frequency-changing AC (is mainly used on A380 and B787), compared to traditional power supply system, 270V high voltage direct current power supply system tool
There are high generating efficiency, power generation and distribution system light weight, easily realize uninterrupted power supply and high reliability；And in order to subtract
The quality of light power distribution network, up to 360~800Hz, this is effectively alleviated the frequency of frequency-changing AC power supply system output alternating current
The weight of electromagnetic equipment.Since the power supply system of current mainstream is still based on variable speed constant frequency and constant-speed and constant-frequency, according to novel
Power supply system, certainly will be faced with and extensive replace electrical equipment or increase many converters for existing equipment
Situation.Therefore, desirable scheme is locally powered using high voltage direct current in some necessary occasions, and most electrical equipment is still
So by constant frequency Alternating Current Power Supply.
Invention content
It cannot meet aviation more electric engin use for the above-mentioned aero-engine conventional electric power system power generation capacity of solution to want
The problem of asking, the object of the present invention is to provide a kind of aviation more electric engin AC/DC mixed power system design methods.
To achieve the above object, the present invention uses following technical scheme：
A kind of aviation more electric engin AC/DC mixed power system, including two built-in frequency-changing ACs in parallel rise
The output end of dynamic/generator, each built-in frequency-changing AC starting/generator is connected with AC/DC converters, AC/DC converters
Output end be connected with DC bus, DC bus is connected with DC/AC converters, two-way DC/DC converters, DC/AC converters
It is connected with ac bus and as output, two-way DC/DC converters is connected with accumulator；Connect on DC bus, ac bus
It is connected to load；
The AC/DC converters are self coupling transformation active power filtering rectifier by three-phase alternating-current supply, polygon self coupling transformation
Device, three-phase uncontrollable rectifier bridge, DC side parallel type active electric power filter, Equilibrium Reactor and output loading composition；Three intersections
Galvanic electricity source connects polygon auto-transformer, and polygon auto-transformer connects three-phase uncontrollable rectifier bridge, three-phase uncontrollable rectifier bridge
Output termination DC side parallel type active electric power filter, the balanced reactance of output end connection of parallel connection type active electric filter
Device, Equilibrium Reactor connect output loading；
The DC/AC converters are the inverter using virtual synchronous generator techniques.
The rated voltage of the DC bus is 270V, and the rated voltage of ac bus is 115V, frequency 400Hz.
The polygon auto-transformer is twelve-pulse auto-transformer.
A kind of aviation more electric engin AC/DC mixed power system design method, includes the following steps：
Active Power Filter-APF is combined by step 1 with polygon connection self coupling vertoro, designs self coupling transformation
Active power filtering rectifier, and by self coupling transformation active power filtering rectifier be connected to built-in frequency-changing AC starting/generator with it is straight
Between stream busbar；Self coupling transformation active power filtering rectifier is by three-phase alternating-current supply, polygon auto-transformer, three-phase uncontrollable rectifier
Bridge, DC side parallel type active electric power filter, Equilibrium Reactor and output loading composition, polygon auto-transformer use ten
Two pulse auto-transformers export termination DC side parallel type active electric power filter in three-phase uncontrollable rectifier bridge and realize single three
It is defeated to be followed by Equilibrium Reactor stable DC side in DC side parallel type active electric power filter for the active power filtering of phase uncontrollable rectifier bridge
Go out voltage；
Step 2 is become using using the inverter of virtual synchronous generator techniques as DC/AC converters, and by DC/AC
Parallel operation is connected between DC bus and ac bus, and the voltage magnitude of ac bus and frequency is made to keep stablizing；
Step 3 compensates the power of DC bus using accumulator and two-way DC/DC converters, makes DC bus
Voltage maintain near rated voltage；
Step 4, using the self coupling transformation active power filtering rectifier of step 1 as AC/DC converters, the DC/AC of step 2
Converter, the accumulator of step 3 and two-way DC/DC converters, as a part for designed electric system, with power generation part,
DC bus, ac bus, load connection, complete global design.
In the step 2, virtual synchronous generated power frequency modulation and idle voltage adjustment characteristic are described as follows：
θ=∫ ω dt
Its is idle, and voltage adjustment characteristic can be described as follows：
In formula, J is the rotary inertia of rotor,For the first derivative of J, TmIt is machine torque, TeElectromagnetic torque, DpIt is resistance
Buddhist nun's coefficient, θ are rotor angle,For the first derivative of θ, ω is rotor velocity, QsetIt is the given of reactive power, DqIt is sagging
Coefficient, U0For output voltage virtual value, UnFor rated voltage virtual value, EmFor modulating wave virtual value, QeFor electromagnetic power；
Above formula exports the amplitude and angular speed of modulating wave, and the triggering of inverter switching device pipe has just been obtained by carrying wave modulation
Signal.
In the step 3, Buck circuits and Boost circuit are integrated in a circuit by two-way DC/DC converters, should
There are two switching tubes for circuit, and the break-make by controlling switching tube can be realized as the two-way flow of energy, work as high voltage dc bus
When voltage is less than 265V, two-way DC/DC converters is enabled to be operated in Boost patterns, at this point, the energy of accumulator is female to high voltage direct current
Line flows, on the contrary, when high voltage dc bus voltage is higher than 275V, two-way DC/DC converters are operated in Buck patterns, electric power storage
Pond absorbs the extra energy of high voltage dc bus, to make its voltage stabilization near rated value.
In the step 4, the rated voltage of DC bus is 270V, and the rated voltage of ac bus is 115V, and frequency is
400Hz；Power generation part is two built-in frequency-changing AC starting/generators in parallel.
Advantageous effect：The present invention has the following advantages：
1. the present invention is according to the job requirement of aviation more electric engin electric system, to maintain alternating current-direct current busbar to stabilize to out
Send out point, it is proposed that a kind of electric system of alternating current-direct current mixing, and stable state research is expanded to new electric system.
2. the present invention devises the overall knot of AC/DC mixed power system first against the use electrical characteristics of more electric engin
Structure.This configuration avoids constant speed drive devices, at the same in order to using 270V high voltage direct current distribution systems it is light-weight, reliability is high,
The advantages that easily realizing uninterrupted power supply, Partial DC load such as flight control system are DC bus powered by 270V.In order to avoid
Power supply system change and caused by the problem of replacing electrical equipment on a large scale, it is in parallel using multiple virtual synchronous generator VSG
270V DC inverters are that 115V400Hz alternating currents are used for most of electrical equipments by scheme.
3. considering that used AC/DC converters are still with vertoro TRU and self coupling in current aero-engine
Based on vertoro ATRU, present invention proposition redesigns traditional TRU and ATRU using active filter circuit, this
On the one hand it disclosure satisfy that the powerful transmission requirement of engine, realize input current low harmonic content, volume weight can also be reduced
Amount.
4. the DC/AC converters in traditional aero-engine are Aviation Static Inverter, main function is by direct current
The electric energy of source or aircraft battery is converted to the use of alternating current electricity supply and use equipment.With carrying for aviation more electric engin concept
Go out, traditional Aviation Static Inverter cannot meet the requirement of big power supply capacity, while airborne equipment is to power quality
It is required that also higher and higher, it is therefore necessary to trial applies the technology of more DC/AC converters parallel runnings in aviation field, this
Aspect can reduce the capacity of separate unit DC/AC converters, can also realize redundancy feature, ensure reliable power supply.
The present invention is to ensure aviation more electric engin stability of power system and ensure that bearing power reasonable distribution is
Point is sent out, proposes the design for carrying out aviation DC/AC converters using VSG.Compared to the control program of traditional DC/AC converters,
It can ensure the stability of system, simultaneously by the active frequency modulation of control algolithm simulation synchronous generator, the characteristic of idle pressure regulation
It can also realize the reasonable distribution being supported between each converter.
5. aero-engine is the case where there are load sudden changes for different state of flights, this can lead to the wave of busbar voltage
Dynamic, the present invention is directed to the stability problem of high voltage dc bus voltage, proposes using accumulator and two-way DC/DC converters to height
The voltage of pressure DC bus compensates, it is made to maintain near rated voltage.
6. Simulation results show：The AC/DC mixed power system proposed meets US military to airborne power supply
It is required that.
Description of the drawings
Fig. 1 is the aviation more electric engin AC and DC power system overall construction drawing of one embodiment of the invention；
Fig. 2 is the self coupling transformation active power filtering rectifier of one embodiment of the invention；
Fig. 3 is the DC side parallel type APF equivalent circuit diagrams of one embodiment of the invention；
Fig. 4 is the digital voltage regulator of one embodiment of the invention；
Fig. 5 a- Fig. 5 b are the high voltage dc bus response curve of one embodiment of the invention；
Fig. 6 a- Fig. 6 d are the ac bus response curve of one embodiment of the invention；
In figure, the built-in frequency-changing AC starting/generators of 1-, 2-AC/DC converters, 3- DC bus, 4-DC/AC transformation
Device, the two-way DC/DC converters of 5-, 6- accumulators, 7- ac bus, 8- loads.
Specific implementation mode
Further explanation is done to the present invention with reference to embodiment.
In the accompanying drawings and embodiments of the present invention, the meaning of each abbreviation is：
APF：Active Power Filter-APF；
ATRU：Polygon connection self coupling vertoro；
ATPFRU：Self coupling transformation active power filtering rectifier；
VSG：Virtual synchronous generator
DC：Direct current；
AC：Exchange；
GEN：Alternating current generator；
Loads：Load.
Embodiment
As shown in Figure 1, a kind of aviation more electric engin AC/DC mixed power system, including two built-in changes in parallel
Frequency exchange starting/generator 1, the output end of each built-in frequency-changing AC starting/generator 1 are connected with AC/DC converters 2,
The output end of AC/DC converters 2 is connected with DC bus 3, and DC bus 3 is connected with DC/AC converters 4, two-way DC/DC transformation
Device 5, DC/AC converters 4 are connected with ac bus 7 and as outputs, and two-way DC/DC converters 5 are connected with accumulator 6；Direct current
It is respectively connected with load 8 on busbar 3, ac bus 7；
Such as Fig. 2, AC/DC converters are that self coupling transformation active power filtering rectifier is become by three-phase alternating-current supply, polygon self coupling
Depressor, three-phase uncontrollable rectifier bridge, DC side parallel type active electric power filter, Equilibrium Reactor and output loading composition；Three-phase
AC power connects polygon auto-transformer, and polygon auto-transformer connects three-phase uncontrollable rectifier bridge, three-phase uncontrollable rectifier
Bridge output termination DC side parallel type active electric power filter, the balanced reactance of output end connection of parallel connection type active electric filter
Device, Equilibrium Reactor connect output loading；
DC/AC converters are the inverter using virtual synchronous generator techniques.
The rated voltage of DC bus is 270V, and the rated voltage of ac bus is 115V, frequency 400Hz.
Polygon auto-transformer is twelve-pulse auto-transformer.
The design method of the aviation more electric engin AC/DC mixed power system is：
1, AC/DC mixed power system designs
It is constant that traditional constant-speed and constant-frequency power supply system needs constant speed drive device to be transformed to continually changing engine speed
Rotating speed input generator, and the device volume weight is larger, complicated, maintenance difficult, this efficiency to improving engine
For be unfavorable；According to variable speed constant frequency power supply system, a part of frequency-changing AC electricity is become permanent by the current transformer to be increased that is bound to
Frequency exports, and the increased current transformer of institute is mainly made of powerful power electronic devices, reliability poor with overload capacity
Low disadvantage, therefore using the type of the power supply system and few.Based on above-mentioned analysis, the present invention proposes a kind of alternating current-direct current mixing
Electric system.
1.1, AC/DC mixed power system master-plan
Fig. 1 show the put forward NETWORK STRUCTURE PRESERVING POWER SYSTEM of the present invention, and the rated voltage of high voltage dc bus is 270V, ac bus
Rated voltage be 115V, frequency 400Hz.Wherein power generation part is two built-in frequency-changing AC starting/power generations in parallel
Machine, AC/DC converters are the self coupling transformation active power filtering rectifier ATPFRU designed by the present invention, and it acts as generator is defeated
The frequency-changing AC electric rectification gone out is 270V direct current outputs, and DC/AC converters are the inverter using virtual synchronous generator techniques,
It acts as be that 115V400Hz exchanges electricity output by 270V DC inverters.In addition to this, in order to ensure DC bus-bar voltage
Stablize, using two-way DC/DC converters between accumulator and DC bus transimission power, in real time to DC bus-bar voltage into
Row compensation, in addition all has load on two busbares.
As seen from Figure 1, which avoids constant speed drive device, while in order to utilize 270V high voltage direct current power distribution systems
It unites the advantages that light-weight, reliability is high, easy realization uninterrupted power supply, Partial DC load is if flight control system is by 270V direct currents
Bussed supply.The problem of electrical equipment being replaced on a large scale caused by order to avoid the change of power supply system, using multiple VSG parallel connections
Scheme by 270V DC inverters be 115V400Hz alternating currents used for most of electrical equipments.
1.2, AC/DC converter designs
At present in aero-engine used AC/DC converters still with vertoro TRU and self coupling Transformer Rectifier
Based on device ATRU.For example, it is 270V direct currents and 28V that ATRU and TRU, which is just respectively adopted, by 230V frequency-changing AC electric rectifications in B787
Direct current.In the evolution of TRU and ATRU, basic thinking is to reach harmonic wave control by increasing the quantity of rectifier bridge
Purpose, umber of pulse more TRU and ATRU, the ripple of output voltage and the harmonic content of input current are smaller, but the thinking
The shortcomings that be that the volume weight that high impulse number also results in equipment becomes larger, while being also one to the reliability operation of engine
Challenge.In view of aero-engine is the equipment for requiring height reliability, how under the premise of ensureing safety to existing
There is scheme to be improved to be more feasible, therefore the present invention proposes to carry out traditional TRU and ATRU using active filter circuit
It redesigns, this aspect disclosure satisfy that the powerful transmission requirement of engine, realize input current low harmonic content, can be with
Reduce volume weight.
Fig. 2 show the self coupling transformation active power filtering rectifier designed by the present invention, by three-phase alternating-current supply, polygon
Auto-transformer, three-phase uncontrollable rectifier bridge, parallel connection type active electric filter, Equilibrium Reactor and output loading composition.The dress
It sets using twelve-pulse auto-transformer as main structure, auto-transformer selection is polygonized structure, straight in rectifier bridge output
Stream side parallel connection three phase active electric power filter realizes the active power filtering of single rectifier bridge, and electricity is followed by three phase active electric power filter
Anti- device stable DC side output voltage.
Because ± 1 subharmonic of input current 12k is the main source of total harmonic distortion, DC side output voltage is 12 arteries and veins
Punching, if therefore apply it is appropriate control so that the waveform of DC side electric current is consistent with DC voltage, in exchange side
Also there can be identical phase relation, i.e. the current-voltage waveform of exchange side can be also consistent.At this point, having been seen from exchange side
It goes, rectifier bridge, DC side parallel type APF and load are equivalent to an equivalent resistance jointly, to realize the improvement to harmonic wave.
Fig. 3 show the equivalent circuit diagram of carried topological structure.
From the figure 3, it may be seen that when Sp1 and Sn1 is closed, filter inductance is directly attached with power supply, and power supply is to filtering at this time
Induction charging, i.e. inductive current increase, and have：
Wherein Upm、UmnRespectively half bridge voltage up and down, ULp、iLpCorresponding LpVoltage and current, ULn、iLnCorresponding Ln's
Voltage and current, when Sp2 and Sn2 is closed, filter inductance both end voltage can be expressed as at this time：
UCpCorresponding CpVoltage, UCnCorresponding CnVoltage, from the above equation, we can see that, inductance both end voltage reduces, i.e. inductive current
Reduce.As the above analysis, the voltage at filter inductance both ends can just be born, that is, inductive current can increase or subtract
Few, electric current is controllable.By application control appropriate, DC side current phase is made to be consistent with DC voltage phase,
Harmonic wave control is achieved the purpose that.
1.3, DC/AC converter designs
DC/AC converters in traditional aero-engine are Aviation Static Inverter, and main function is by DC power supply
Or the electric energy of aircraft battery is converted to the use of alternating current electricity supply and use equipment.With the proposition of aviation more electric engin concept,
Traditional Aviation Static Inverter cannot meet the requirement of big power supply capacity, while requirement of the airborne equipment to power quality
Also higher and higher, it is therefore necessary to which that trial applies the technology of more DC/AC converters parallel runnings in aviation field, this aspect
The capacity of separate unit DC/AC converters can be reduced, can also realize redundancy feature, ensures reliable power supply.
The present invention is to ensure aviation more electric engin stability of power system and ensure that bearing power reasonable distribution is
Point is sent out, proposes the design for carrying out aviation DC/AC converters using VSG.Compared to the control program of traditional DC/AC converters,
It can ensure the stability of system, simultaneously by the active frequency modulation of control algolithm simulation synchronous generator, the characteristic of idle pressure regulation
It can also realize the reasonable distribution being supported between each converter.
VSG can simulate the inertia of synchronous generator, and active frequency modulation characteristic can use the torque of generator mechanical part
Formula indicates：
θ=∫ ω dt (6)
Its is idle, and voltage adjustment characteristic can be described as follows：
In formula, J is the rotary inertia of rotor, TmIt is machine torque, TeElectromagnetic torque, DpIt is damped coefficient, θ is rotor angle
Degree, ω is rotor velocity, QsetIt is the given of reactive power, DqFor sagging coefficient, U0For output voltage virtual value, UnIt is specified
Voltage effective value, EmFor modulating wave virtual value.Formula (5) and (7) export the amplitude and angular speed of modulating wave respectively, pass through carrier wave
Modulation has just obtained the trigger signal of inverter switching device pipe.
2, steady-state characteristic research
The case where aero-engine can face load sudden change under different state of flights, this can lead to the wave of busbar voltage
It is dynamic, it is therefore necessary to necessary measure be taken to ensure the stability of busbar voltage.The present invention is with aviation more electric engin alternating current-direct current
The stable operation of electric system is starting point expansion research.
2.1, generator voltage regulating system
Pressure regulator is one of the measure for maintaining power system voltage stabilization, and the pressure regulator of early stage is oscillatory type or carbon plate
Formula has been replaced by magnetic amplifier and transistor type pressure regulator since five sixties of 20th century, is widely used at present.Closely
Over 20 years, with the appearance of microprocessor, digital voltage regulator is paid attention to, insensitive to the variation of frequency, simultaneously
The problem of also avoiding analog circuit element Parameters variation, therefore it is applied to frequency conversion alternating-current generator with prodigious excellent
Gesture.Fig. 4 show typical digital voltage regulator control block diagram：
The effect of pressure regulator is other than it can stablize the output voltage of separate unit generator, in the situation of multiple generator parallel connection
It can also realize evenly distributing for power by adjusting exciting current down.
2.2, the steady-state characteristic research of high voltage dc bus voltage
For aero-engine the case where there are load sudden changes for different state of flights, this can lead to the fluctuation of busbar voltage,
The present invention is directed to the stability problem of high voltage dc bus voltage, proposes using accumulator and two-way DC/DC converters to high pressure
The voltage of DC bus compensates, it is made to maintain near rated voltage.
Buck circuits and Boost circuit are integrated in a circuit by two-way DC/DC converters, and there are two switches for the circuit
Pipe, the break-make by controlling switching tube can realize the two-way flow of energy, in the present invention, when high voltage dc bus voltage
When less than 265V, two-way DC/DC converters is enabled to be operated in Boost patterns, at this point, the energy of accumulator is to high voltage dc bus stream
Dynamic, on the contrary, when high voltage dc bus voltage is higher than 275V, two-way DC/DC converters are operated in Buck patterns, and accumulator is inhaled
The extra energy of high voltage dc bus is received, to make its voltage stabilization near rated value.Traditional integer rank PI controllers are still
It is so most popular controller, compared to integer rank PI controllers, fractional order PI controllers have better dynamic property,
But parameter determination is also increasingly complex, therefore the present embodiment is designed using fractional order PI controllers.
2.3 ac bus steady-state characteristic researchs
The air environments such as flight control system need constant frequency AC source to power, therefore for the stabilization of ac bus
Property for, in addition to voltage magnitude to be ensured stablize near rated value other than, also should ensure that frequency stabilization.
VSG of the present invention is the research hotspot in current grid-connected field, compared to traditional inversion utensil
Have the advantages that following：1) it can simulate the characteristic of the active frequency modulation of synchronous generator, when facing load sudden change the case where, system
Inertia can make frequency maintain rated frequency, and system inertia needs DC side that there are energy storage devices, and be released in the very short time
Put or absorb energy.Therefore there are two effects for accumulator proposed by the invention and two-way DC/DC converters tool, first, maintaining
High voltage dc bus voltage stabilization, second is that providing system inertia for VSG.2) VSG can also simulate the idle pressure regulation of synchronous generator
Characteristic, maintenance voltage stablize.
3, analysis of simulation result
In order to adapt to the demand for development of airborne power-supply system, US military has promulgated MIL-STD-704F to ensure to fly
The safe and reliable operation of electromechanical source system has all made specific requirement to the characteristic of each alternating current-direct current busbar.It is to airborne power supply
The requirement of steady-state characteristic is as shown in Table 1 and Table 2：
1 constant frequency AC source standard of table
Its requirement to DC bus, as shown in table 2：
2 270V DC power supply standards of table
Simulating, verifying is divided into two parts：1) the carried AC/DC converters ATPFRU harmonics restraints verification of the present invention；2) it hands over straight
Galvanic electricity Force system stability study is verified.
3.1, ATPFRU harmonics restraints verification analysis
From the foregoing it will be appreciated that ± 1 subharmonic of input current 12k is the main source of total harmonic distortion, therefore the present invention only needle
The harmonic wave of above-mentioned order is analyzed, filter inductance is 4mH, filter capacitor 6mF in simulation model.Table 3 show 12 arteries and veins
Rush ATRU and the put forward each order harmonic contents of ATPFRU of the present invention：
Table 3 filters front and back harmonic content
By table 3 as it can be seen that each harmonic content drops to 2% hereinafter, total harmonic distortion drops to 4% hereinafter, meeting beautiful
The military of state airplane power source standard.
3.2 AC and DC power system steady-state characteristic researchs
The present invention show height by the different working condition of impact anticlimax load simulation aero-engine, Fig. 5 a and Fig. 5 b
Press the amplitude transformation curve graph of voltage oscillogram and input current of the DC bus in load sudden change：
The preceding 1s of system operation is startup stage, is not considered herein.In t=1.5s, the load of impact 33%, at this time directly
Galvanic electricity pressure under the adjusting of pressure regulator, reaches stable again there are one falling after rise by the time of 1s or so；It, will in t=2.5s
Load excision, voltage is increased to 275V at this time, this is because the two-way DC/DC converter voltages set by the present invention adjust boundary
Caused by 275V, under the state, DC bus conveys energy to accumulator, while pressure regulator reduces exciting current, passes through 0.5s
The time of left and right reaches stable again.It can be seen that the entire adjustment process of voltage is satisfied by US military high voltage dc bus
Standard.Fig. 6 a- Fig. 6 d show the voltage and power waveform figure of VSG in parallel：
By Fig. 6 a- Fig. 6 d as it can be seen that distinguishing impact and anticlimax load in t=1.5s and t=2.5s, two VSG are in parallel at this time
Work, the load of the two shared simulate VSG1 failures in t=4s, and VSG1 is disconnected at this time, and bearing power is all by VSG2
It undertakes.
The shock load in t=1.5s, at this time ac bus voltage magnitude and frequency have temporary falling, due to VSG energy
Enough characteristics of the active pressure regulation of simulation synchronous generator, idle pressure regulation, thus voltage magnitude and it is rapid be stabilized to command value, together
Sample in t=2.5s, voltage magnitude and frequency have of short duration raising.It is disconnected in t=4s, VSG1, at this time whole bearing powers
It is undertaken by VSG2, is equivalent to shock load, therefore voltage magnitude and frequency are temporarily fallen after rise, in entire adjustment process, exchange
The voltage magnitude of busbar is stablized near 115V, and electric voltage frequency is stablized near 400Hz, meets MIL STD and is directed to
In the standard of constant frequency AC pressure.
The above is only a preferred embodiment of the present invention, it should be pointed out that：For the ordinary skill people of the art
For member, various improvements and modifications may be made without departing from the principle of the present invention, these improvements and modifications are also answered
It is considered as protection scope of the present invention.
Claims (7)
1. a kind of aviation more electric engin AC/DC mixed power system, it is characterised in that：Including two built-in changes in parallel
Frequency exchange starting/generator, the output end of each built-in frequency-changing AC starting/generator are connected with AC/DC converters, AC/
The output end of DC converters is connected with DC bus, and DC bus is connected with DC/AC converters, two-way DC/DC converters, DC/
AC converters are connected with ac bus and as outputs, and two-way DC/DC converters are connected with accumulator；DC bus, exchange are female
Load is respectively connected on line；
The AC/DC converters are self coupling transformation active power filtering rectifier, and self coupling transformation active power filtering rectifier is by three-phase alternating current
Power supply, polygon auto-transformer, three-phase uncontrollable rectifier bridge, DC side parallel type active electric power filter, Equilibrium Reactor and
Output loading forms；Three-phase alternating-current supply connects polygon auto-transformer, and polygon auto-transformer connection three-phase is not controlled whole
Bridge, three-phase uncontrollable rectifier bridge output termination DC side parallel type active electric power filter are flowed, parallel connection type active electric filter
Output end connects Equilibrium Reactor, and Equilibrium Reactor connects output loading；
The DC/AC converters are the inverter using virtual synchronous generator techniques.
2. aviation more electric engin AC/DC mixed power system according to claim 1, it is characterised in that：The direct current
The rated voltage of busbar is 270V, and the rated voltage of ac bus is 115V, frequency 400Hz.
3. aviation more electric engin AC/DC mixed power system according to claim 1, it is characterised in that：It is described polygon
Shape auto-transformer is twelve-pulse auto-transformer.
4. a kind of aviation more electric engin AC/DC mixed power system design method, it is characterised in that：Include the following steps：
Active Power Filter-APF is combined by step 1 with polygon connection self coupling vertoro, and design self coupling transformation is active
Filter-rectifier, and self coupling transformation active power filtering rectifier is connected to built-in frequency-changing AC starting/generator and direct current mother
Between line；Self coupling transformation active power filtering rectifier by three-phase alternating-current supply, polygon auto-transformer, three-phase uncontrollable rectifier bridge,
DC side parallel type active electric power filter, Equilibrium Reactor and output loading composition, polygon auto-transformer use 12
Pulse auto-transformer exports termination DC side parallel type active electric power filter in three-phase uncontrollable rectifier bridge and realizes single three-phase
The active power filtering of uncontrollable rectifier bridge is followed by Equilibrium Reactor stable DC side in DC side parallel type active electric power filter and exports
Voltage；
Step 2, using the inverter using virtual synchronous generator techniques as DC/AC converters, and by DC/AC converters
It is connected between DC bus and ac bus, the voltage magnitude of ac bus and frequency is made to keep stablizing；
Step 3 compensates the power of DC bus using accumulator and two-way DC/DC converters, makes the electricity of DC bus
Pressure maintains near rated voltage；
Step 4, using the self coupling transformation active power filtering rectifier of step 1 as AC/DC converters, the DC/AC of step 2 is converted
Device, the accumulator of step 3 and two-way DC/DC converters, as a part for designed electric system, with power generation part, direct current
Busbar, ac bus, load connection, complete global design.
5. aviation more electric engin AC/DC mixed power system design method according to claim 4, it is characterised in that：
In the step 2, virtual synchronous generated power frequency modulation and idle voltage adjustment characteristic are described as follows：
θ=∫ ω dt
Its is idle, and voltage adjustment characteristic can be described as follows：
In formula, J is the rotary inertia of rotor,For the first derivative of J, TmIt is machine torque, TeElectromagnetic torque, DpIt is damping system
Number, θ is rotor angle,For the first derivative of θ, ω is rotor velocity, QsetIt is the given of reactive power, DqFor sagging system
Number, U0For output voltage virtual value, UnFor rated voltage virtual value, EmFor modulating wave virtual value, QeFor electromagnetic power；
Above formula exports the amplitude and angular speed of modulating wave, and the triggering that inverter switching device pipe has just been obtained by carrying wave modulation is believed
Number.
6. aviation more electric engin AC/DC mixed power system design method according to claim 4, it is characterised in that：
In the step 3, Buck circuits and Boost circuit are integrated in a circuit by two-way DC/DC converters, which has two
A switching tube, the break-make by controlling switching tube can be realized as the two-way flow of energy, when high voltage dc bus voltage is less than
When 265V, two-way DC/DC converters is enabled to be operated in Boost patterns, at this point, the energy of accumulator is flowed to high voltage dc bus,
On the contrary, when high voltage dc bus voltage is higher than 275V, two-way DC/DC converters are operated in Buck patterns, and accumulator absorbs
The extra energy of high voltage dc bus, to make its voltage stabilization near rated value.
7. aviation more electric engin AC/DC mixed power system design method according to claim 4, it is characterised in that：
In the step 4, the rated voltage of DC bus is 270V, and the rated voltage of ac bus is 115V, frequency 400Hz；Hair
Electric part is two built-in frequency-changing AC starting/generators in parallel.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810413035.6A CN108736481A (en) | 2018-05-03 | 2018-05-03 | A kind of aviation more electric engin AC/DC mixed power system and its design method |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810413035.6A CN108736481A (en) | 2018-05-03 | 2018-05-03 | A kind of aviation more electric engin AC/DC mixed power system and its design method |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN108736481A true CN108736481A (en) | 2018-11-02 |
Family
ID=63936938
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201810413035.6A Pending CN108736481A (en) | 2018-05-03 | 2018-05-03 | A kind of aviation more electric engin AC/DC mixed power system and its design method |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN108736481A (en) |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109301824A (en) * | 2018-11-15 | 2019-02-01 | 紫光测控有限公司 | Zero based on the support of double path system power supply disturbs flexible distribution system |
| CN111122203A (en) * | 2020-01-02 | 2020-05-08 | 上海电力大学 | Virtual configuration device of inertia and drag experiment platform |
| EP3703220A1 (en) * | 2019-03-01 | 2020-09-02 | The Boeing Company | Active voltage control for hybrid electric aircraft |
| CN112736891A (en) * | 2020-12-29 | 2021-04-30 | 中国航发控制系统研究所 | Power supply device of multi-electric control system of aircraft engine |
Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN1988339A (en) * | 2006-12-31 | 2007-06-27 | 重庆大学 | Three phase rectifier bridge active power filter circuit using impedance coupling |
| CN102142692A (en) * | 2011-02-25 | 2011-08-03 | 南京航空航天大学 | Full-power converter suitable for variable speed wind power generation |
| CN104065099A (en) * | 2014-05-29 | 2014-09-24 | 国家电网公司 | AC/DC hybrid modularized microgrid network structure based on hybrid energy storage and networking method of structure |
| EP2869420A1 (en) * | 2013-10-31 | 2015-05-06 | Siemens Aktiengesellschaft | Power system for a floating vessel |
| CN105098807A (en) * | 2015-07-20 | 2015-11-25 | 安阳师范学院 | Complementary optimization control method among multiple hybrid energy storage devices in energy storage system |
| CN105305478A (en) * | 2015-01-11 | 2016-02-03 | 北京清能世福科技有限公司 | New-energy power generation system friendly to power grid and flexible to extend |
| CN105977984A (en) * | 2016-06-28 | 2016-09-28 | 江苏省镇江船厂（集团）有限公司 | Variable-frequency main power source ship power station |
-
2018
- 2018-05-03 CN CN201810413035.6A patent/CN108736481A/en active Pending
Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN1988339A (en) * | 2006-12-31 | 2007-06-27 | 重庆大学 | Three phase rectifier bridge active power filter circuit using impedance coupling |
| CN102142692A (en) * | 2011-02-25 | 2011-08-03 | 南京航空航天大学 | Full-power converter suitable for variable speed wind power generation |
| EP2869420A1 (en) * | 2013-10-31 | 2015-05-06 | Siemens Aktiengesellschaft | Power system for a floating vessel |
| CN104065099A (en) * | 2014-05-29 | 2014-09-24 | 国家电网公司 | AC/DC hybrid modularized microgrid network structure based on hybrid energy storage and networking method of structure |
| CN105305478A (en) * | 2015-01-11 | 2016-02-03 | 北京清能世福科技有限公司 | New-energy power generation system friendly to power grid and flexible to extend |
| CN105098807A (en) * | 2015-07-20 | 2015-11-25 | 安阳师范学院 | Complementary optimization control method among multiple hybrid energy storage devices in energy storage system |
| CN105977984A (en) * | 2016-06-28 | 2016-09-28 | 江苏省镇江船厂（集团）有限公司 | Variable-frequency main power source ship power station |
Non-Patent Citations (3)
| Title |
|---|
| LEILEI JIANG 等: "Asymmetrical Operation Analysis of Multi-Pulse ATRU", 《2012 IEEE 7TH INTERNATIONAL POWER ELECTRONICS AND MOTION CONTROL CONFERENCE-ECCE ASIA》 * |
| 吴恒 等: "虚拟同步发电机功率环的建模与参数设计", 《中国电机工程学报》 * |
| 祝钧: "交直流混合微电网接口变换器虚拟同步发电机控制方法", 《电力系统保护与控制》 * |
Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109301824A (en) * | 2018-11-15 | 2019-02-01 | 紫光测控有限公司 | Zero based on the support of double path system power supply disturbs flexible distribution system |
| CN109301824B (en) * | 2018-11-15 | 2022-07-12 | 清能华控科技有限公司 | Zero-disturbance flexible power distribution system based on double-circuit system power supply support |
| EP3703220A1 (en) * | 2019-03-01 | 2020-09-02 | The Boeing Company | Active voltage control for hybrid electric aircraft |
| CN111641250A (en) * | 2019-03-01 | 2020-09-08 | 波音公司 | Active voltage control for hybrid electric aircraft |
| CN111122203A (en) * | 2020-01-02 | 2020-05-08 | 上海电力大学 | Virtual configuration device of inertia and drag experiment platform |
| CN111122203B (en) * | 2020-01-02 | 2021-12-24 | 上海电力大学 | Virtual configuration device of inertia and drag experiment platform |
| CN112736891A (en) * | 2020-12-29 | 2021-04-30 | 中国航发控制系统研究所 | Power supply device of multi-electric control system of aircraft engine |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN108736481A (en) | A kind of aviation more electric engin AC/DC mixed power system and its design method | |
| Nikkhajoei et al. | A matrix converter based micro-turbine distributed generation system | |
| Chen et al. | Evaluation on the autoconfigured multipulse AC/DC rectifiers and their application in more electric aircrafts | |
| CN111382525B (en) | Low-frequency power transmission closed-loop test system and method | |
| Zhang et al. | Application of low harmonic 18-pulse rectifier power supply for radar power system | |
| CN103051212A (en) | Composite ac-to-dc power converter using midpoint method | |
| CN103124142A (en) | Integrated ac/dc power converter with autotransformer and boosting capabilities | |
| CN209516959U (en) | A kind of vehicle-mounted multiple-pulse rectifier power source of CYZL-50KW | |
| CN206585341U (en) | A kind of energy router controlled based on virtual motor | |
| Setlak et al. | Comparative analysis and simulation of selected components of modern on-board autonomous power systems (ASE) of modern aircraft in line with the concept of MEA/AEA | |
| CN110138244B (en) | 48-pulse voltage transformation rectifier adopting direct-current side passive harmonic suppression technology | |
| CN101009431A (en) | Rotating electromagnetic energy transformation device | |
| Wu et al. | Application and challenges of power electronics for variable frequency electric power system of more electric aircraft | |
| CN112531718B (en) | Tidal current calculation method suitable for multi-electric aircraft power system | |
| Mastromauro et al. | An advanced active rectifier based on the single-star bridge cells modular multilevel cascade converter for more-electric-aircrafts applications | |
| Khodabakhsh et al. | Primary Frequency Control in Islanded Microgrids Using Solid-State Transformers as Virtual Synchronous Machines | |
| Weilin et al. | Design of star-connected autotransformer based 24-pulse rectifier and its application in the more electric aircraft | |
| Jassim | SEPIC AC-DC converter for aircraft application | |
| Dias et al. | Dc current redistributor for electric aircraft system | |
| Li | Modeling and simulation of micro gas turbine generation system for grid connected operation | |
| Kondreddy et al. | Integrated buck and boost converter for a universal battery charger of an Electric Vehicle | |
| Setlak et al. | Study of the transformer rectifier unit compatible with the concept of a more electric aircraft | |
| Shravan et al. | Emulation of AC and DC subgrids using power converters for islanded hybrid microgrid applications | |
| Merai et al. | Coordinated control of multiple multi-function grid connected converters for power quality improvement in micro-grid applications | |
| Jeung et al. | AC power supply system using vehicle engine-generator set with battery |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| RJ01 | Rejection of invention patent application after publication |
Application publication date: 20181102 |
|
| RJ01 | Rejection of invention patent application after publication |