CN107908829A - Onboard electric systems method for analyzing stability based on unified large-signal model - Google Patents
Onboard electric systems method for analyzing stability based on unified large-signal model Download PDFInfo
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Abstract
The present invention relates to a kind of onboard electric systems method for analyzing stability based on unified large-signal model, including：Step 1, establishes the unified large-signal model of aircraft electrical power system；Step 2, solve based on the aircraft electrical power system stability criteria under unified large-signal model：The big signal stabilization criterion drawn under unified large-signal model is solved with reference to Liapunov type energy function using mixed potential function theory, this stability criteria is equally also the stability criteria of aircraft electrical power system small-signal.
Description
Technical field
The present invention relates to aviation electric system stability analysis field, a kind of big signal mode of unification is specifically proposed
Type, the method that small-signal stability for disturbance and big signal disturbance stability to aircraft electrical power system are analyzed.
Background technology
Modern aircraft is substituted using electric energy more and more for the performance for saving the energy, reducing cost and improving mobile system
The supply form of hydraulic pressure, the air pressure energy as the energy in conventional airplane.As following airplane design progressively incorporates more electricity
Concept, will become more dependent on electric system to ensure the safe operation of aircraft.
Aircraft electrical power system is mainly responsible for the generation, conversion, distribution of electric energy, and is transmitted in a manner of appropriate safety negative
Carry.More electricity aircrafts must rely on substantial amounts of Technics of Power Electronic Conversion device, as self coupling vertoro (ATRU), Buck/Boost become
Parallel operation etc., electric power driving is provided for secondary power component, and the operation control to aircraft brings great convenience.But due to electric power electricity
The dynamic of sub- converting means, it is non-linear and each other before cascade, the connection mode such as parallel connection so that aircraft electrical power system exists
Obtain it is high performance at the same time, stability problem also becomes more prominent.In addition, in more electricity aircraft electrical power systems, most of load
For equipment since the fast response characteristic of controller shows as constant power load, its negative resistance character gives aircraft electrical power system stability
Bring serious harm.Therefore, carry out stability analysis to more electric aircraft electrical power systems to have great importance, mainly including aircraft
Modeling and simulation, small-signal and the analysis of big signal stabilization of electric system etc..
Aircraft electrical power system is a strongly non-linear system, and modeling method is relative complex, is concentrated mainly on state sky at present
Between average (SSA) method, dq converter techniques, average value (AVM) method etc..SSA methods are widely used in various direct currents and AC system electric
The modeling of force transducer, but when it is applied to three-phase system, the high order mathematical model of complexity can be produced, be unfavorable for the steady of system
Qualitative analysis；Dq converter techniques can establish the time-varying transformer model of converters, be widely used in building for AC system
Mould is analyzed；AVM is used for many 6 pulses and the modeling of 12 pulse diode rectifiers, while is also widely used for band commutation rectification
The modeling of device generator, these rectifiers can be as constant direct voltage sources, its model is relatively easy, and still has higher
Precision, is applicable not only to high-speed simulation analysis, is also applied for the stability analysis of system.
Aircraft electrical power system stability analysis includes small-signal analysis and large-signal analysis：Small-signal stability analysis refers to
Influenced caused by disturbance it is sufficiently small, it can be achieved that to the linearisation of system model and not impact analysis precision, as load increases and decreases at random,
Stability problem caused by the slowly varying grade of parameter；Main research load changing, the short trouble of big signal stabilization analysis, get rid of it is negative
The influence of the large disturbances to system stability such as lotus and broken string.At present, analyzed for aircraft electrical power system small-signal stability, it is domestic
Substantial amounts of research work has been carried out in outer scholar, but small-signal stability analysis has some limitations, and is only limitted to being
Steadiness near system steady operation point is studied, and is not suitable for the situation of the big signal disturbance such as short trouble.In addition,
At the same time consider aircraft electrical power system be in large-and small-signal disturb under stability there has been no simply and easily analysis tool.
The content of the invention
The method that the present invention uses for reference average value modeling, proposes a kind of unified large-signal model foundation side of aircraft electrical power system
Method, and provide a kind of onboard electric systems method for analyzing stability based on this model.Technical scheme is as follows：
A kind of onboard electric systems method for analyzing stability based on unified large-signal model, comprises the following steps：
Step 1：Establish the unified large-signal model of aircraft electrical power system
For more electric aircraft electrical power systems, carry out including the simplification handled as follows, the unification for establishing aircraft electrical power system is big
Signal model：Generator is equivalent to ideal voltage source；Self coupling vertoro uses mean value model；Power electronics driving
Airborne electrical equipment is considered as constant power load, with constant current source-representation；Fluctuation and the exchange for ignoring high voltage AC bus voltage are resistive
Load and the influence of variable-speed motor load.
Step 2：Solve based on the aircraft electrical power system stability criteria under unified large-signal model
Liapunov linearization technique is respectively adopted and mixed potential function theory solves the small of more electric aircraft electrical power systems
Signal and big signal stabilization criterion, then draw the unified stability criteria of aircraft electrical power system by comparative analysis.It is based on
The unified large-signal model of the aircraft electrical power system of foundation, show that the small-signal of system is steady using Liapunov linearization technique
Qualitative criteria is：
Wherein, PcplFor the equivalent constant power load of the airborne electrical equipment of power electronics driving；Rf、LfIt is respectively unified big
The sum of all resistance in signal model equivalent circuit and the sum of all inductance；CdcFor the capacitance parameter of equivalent circuit DC side；
Vs,0For the output voltage values of equivalent circuit homeostasis limit.
In addition, unified large-signal model is drawn using theoretical solved with reference to Liapunov type energy function of mixed potential function
Under big signal stabilization criterion be：
Wherein, VsFor equivalent circuit capacitance CdcThe magnitude of voltage of both ends output.
The stability criteria of formula (2) is equally also the stability criteria of aircraft electrical power system small-signal.
The present invention makes every effort to simple, the accurate and comprehensively stability of analysis of aircraft electric system, using average value modeling
Method, studies angle from big signal, establishes the big signal simplified model of unification of aircraft electrical power system.And should by this model
It is right respectively using Liapunov linearization technique and mixed potential function theory for the stability analysis of aircraft electrical power system
The small-signal of aircraft electrical power system and big signal stabilization are analyzed, and obtain the unified stability criteria of system.By detailed
Large-and small-signal disturbance emulation experiment and using permasyn morot as load example progress the big letter of short trouble
The accuracy of number disturbance experiments verification model.The result shows that unified large-signal model proposed by the present invention not only can be effectively
The small-signal stability problem of analysis of aircraft electric system, at the same can also analysis of aircraft electric system be under big signal disturbance
Stability, there is certain accuracy, universality and structure uniformity.The present invention by the unified large-signal model carried at the same time
Applied to complicated aircraft electrical power system large-and small-signal stability analysis, design process is simplified, is aircraft electrical power system
Optimization design provide reference.
Brief description of the drawings
Fig. 1：Aircraft electrical power system exemplary block diagram
Fig. 2：12 pulse wave self coupling vertoro schematic diagrams
Fig. 3：The simplification mean value model of 12 pulse wave auto-transformers
Fig. 4：Unified large-signal model equivalent circuit
Fig. 5：Simulation Example schematic diagram based on permasyn morot load
Embodiment
In view of the deficiency of traditional analysis of aircraft stability of power system method, the method based on average value modeling proposes
A kind of aircraft electrical power system for having preferable Global Stability Analysis ability and being more advantageous to solution stability criteria is unified big
Signal model, analyzes the large-and small-signal stability of aircraft electrical power system.Utilize the large and small letter of this model solution system
Number stablize a little criterions, be combined into one by analysis, obtain unified stability criteria.Compared with conventional method, this method
Complicated cumbersome impedance computation process is avoided, and still is able to realize to system fast and accurately determination of stability, the letter of model
Just property, universality and structure uniformity are had laid a good foundation for the stability analysis of aircraft electrical power system and optimization design.
In conjunction with embodiment, attached drawing, the invention will be further described：
Step 1：Establish the unified large-signal model of aircraft electrical power system
For the typical structure of more electricity aircraft electrical power systems as shown in Figure 1, mainly including synchronous frequency conversion generator, it exports connection
To 235V high-voltage alternatings (HVAC) busbar, and be fed to wing anti-ice system (Wing ice protection system,
WIPS the resistive load in)；270V high voltage direct current (HVDC) bus, it passes through auto-transformer rectifier unit (Auto
Transformer Rectifier, ATRU) obtained from HVAC buses；The output of ATRU is supplied to airborne by R-L-C wave filters
Power electronics drives variable-speed motor in electrical equipment, such as environmental control system (ECS) and airplane operation system；In addition,
Constant pressure resistive load there may also be HVDC buses at.
In the various compositions of aircraft electrical power system, since the circuit structure of 12 pulse wave self coupling vertoroes is relatively multiple
It is miscellaneous, first using average value model method it is carried out to simplify modeling, secondly progress generator and related load it is equivalent, obtain
To the unified large-signal model of system.
1) 12 pulse wave self coupling vertoro average values model
The schematic diagram of 12 pulse wave self coupling transformer rectifier circuits is illustrated in figure 2, AC power is by three balanced voltage source VA、
VB、 VCComposition, circuit voltage to neutral vnIt is represented by
Wherein, VmFor voltage magnitude.
Phase shifting equipment produces two groups of three-phase voltages for differing 30 ° each other, and two 6 Pulses Rectifiers are in parallel to pass through DC filtering
Link is energized to load, LrRepresent the primary side leakage inductance and power cord inductance of phase shifting equipment, LsRepresent the secondary leakage inductance of phase shifting equipment,
LiprRepresent DC side inductance.The output voltage V of two rectifiers1,V2It can be expressed as
Wherein, i1=[I1 I2 I3]T, i2=[I4 I5 I6]TFor rectifier input current vector；A1,B1,C1For coefficient square
Battle array, its value depend on type, circuit inductance and its commutation overlap angle of transformer etc..12 pulse wave self coupling vertoroes output electricity
Press VrV can be passed through1,V2Average value try to achieve：
In formula, iLFor DC side load current, matrix A, B, C are still coefficient matrix, and the value of D depends on rectifier output and connects
Connect the setting of situation and its interphase reactor.VrAverage output voltageBy (3) formula in 30 ° of section θ1＜ θ ＜ θ2On product
Point divided by the time determine：
In formula,For the local average change rate of DC link current；The ω of Δ t=π/6.
For the common 12 pulse wave self coupling vertoro of more electric aircraft electrical power systems, its average output voltage can be obtained
For
It can show that the simplification mean value model of 12 pulse wave auto-transformers is as shown in Figure 3 by formula (5).
2) unified large-signal model modeling
To establish unified large-signal model, there is generator good voltage control action can be equivalent to desired voltage
Source；Self coupling vertoro uses mean value model as shown in Figure 3；The speed-regulating AC motor of power electronics driving etc. is airborne
Electrical equipment is since the fast response characteristic of controller can be considered constant power load, with constant current source-representation；High voltage AC bus electricity
Pressure is relatively stablized, and exchanges the influence of resistive load and variable-speed motor load and can also ignore.Therefore, in mean value modeling approach
On the basis of by the rationally appropriate simplification of aircraft electrical power system typical structure, establishing the aircraft electricity based on unified large-signal model
Force system stability analysis equivalent circuit is as shown in Figure 4.
In Fig. 4,It is AC power in the equivalent voltage source of DC side, VmFor voltage magnitude； Leq
=2Lr+LsIt is self coupling vertoro original secondary leakage inductance, line inductance etc. in the equivalent inductance of DC side, LrFor primary side leakage inductance and
The inductance of power cord, LsFor secondary leakage inductance；To consider that the factors such as rectifier commutation overlap angle influence
DC side equivalent resistance, n=6.464；Ldc,Rdc,CdcFor wave filter on DC side parameter, load equivalent is constant power load
Pcpl。
Step 2：Solve based on the aircraft electrical power system stability criteria under unified large-signal model
Aircraft electrical power system is a complicated nonlinear time_varying system, and stability analysis includes small-signal analysis and big letter
Number analysis.Suitable method need to be taken to solve respectively for the stability criteria of its large-and small-signal, specific steps describe such as
Under：
1) small-signal stability criterion
The small-signal stability criterion of aircraft electrical power system is solved using Liapunov linearization technique, passes through its feature
Root judges the stability of system.According to equivalent circuit as shown in Figure 4, if the state variable of system is：
X=<If,Vs> (6)
Input variable
U=<Veq,Pcpl> (7)
Output variable
Y=Vs (8)
The state equation for drawing system is
Small-signal stability criterion by Liapunov linearization technique solving system is：
Wherein,For steady state equilibrium point.
2) big signal stabilization criterion
Using the big signal stabilization criterion of mixed potential function theory solving system, mixed potential function P can be according to system
Element and topological relation in circuit obtain, its general type is
P (i, v)=- A (i)+B (v)+D (i, v) (11)
Wherein, i, v are respectively inductive current and capacitance voltage in circuit, and A (i) is the electric current potential function of circuit, B (v)
For the voltage potential function of circuit, D (i, v)=iTγ v are the energy of the non-energy-storage travelling wave tube of energy and part of capacitance in circuit,
γ is the constant coefficient matrix related with circuit topology.
According to the unified large-signal model of Fig. 4, the big signal stabilization criterion that can try to achieve aircraft electrical power system is
3) the unified stability criteria of large-and small-signal
, should be by output voltage V in order to ensure formula (12) constant establishment during the big signal disturbance of aircraft electrical power systems
The critical minimum V being likely to be breached in perturbation processsminTake into account, therefore the stability criteria of formula (12) system under big signal
It can be rewritten as
Formula (13) contains all restrictive conditions of formula (10), therefore formula (13) is the large and small letter of aircraft electrical power system
Number unified stability criteria.When (13) are set up, aircraft electrical power system is no matter in the case of small-signal disturbance or big signal disturbance
It can keep stablizing, two stability criterias are combined into one, simplify analytic process during aircraft electrical power system design.
Step 3：The validation verification of unified large-signal model
Using MATLAB emulation tools, the model built first according to Fig. 4, passes through detailed time-domain-simulation experiment and step
The calculated results of large-and small-signal stability criteria compare and analyze the credibility of verification model, associated control parameters in 2
As shown in table 1.
1 aircraft electrical power system simulation parameter of table
In order to further verify that the present invention puies forward the accuracy of unified large-signal model method, using the permanent magnetism shown in Fig. 5
Synchronous motor (PMSM) carries out the big signal disturbance experiment of short trouble, permanent magnetism as the example of unified large-signal model load
The relevant parameter of synchronous motor and its controller is as shown in table 2.
The relevant parameter of 2 permanent magnet synchronous motor of table and its controller
Claims (1)
1. a kind of onboard electric systems method for analyzing stability based on unified large-signal model, comprises the following steps：
Step 1：Establish the unified large-signal model of aircraft electrical power system
For more electric aircraft electrical power systems, carry out including the simplification handled as follows, establish the big signal of unification of aircraft electrical power system
Model：Generator is equivalent to ideal voltage source；Self coupling vertoro uses mean value model；Power electronics drives airborne
Electrical equipment is considered as constant power load, with constant current source-representation；Ignore fluctuation and the exchange resistive load of high voltage AC bus voltage
With the influence of variable-speed motor load.
Step 2：Solve based on the aircraft electrical power system stability criteria under unified large-signal model
Liapunov linearization technique and the theoretical small-signal for solving more electric aircraft electrical power systems of mixed potential function is respectively adopted
With big signal stabilization criterion, the unified stability criteria of aircraft electrical power system is then drawn by comparative analysis；Based on foundation
The unified large-signal model of aircraft electrical power system, the small-signal stability of system is drawn using Liapunov linearization technique
Criterion is：
Wherein, PcplFor the equivalent constant power load of the airborne electrical equipment of power electronics driving；Rf、LfRespectively unify big signal
The sum of all resistance in model equivalent circuit and the sum of all inductance；CdcFor the capacitance parameter of equivalent circuit DC side；Vs,0For
The output voltage values of equivalent circuit homeostasis limit；
In addition, drawn using theoretical solved with reference to Liapunov type energy function of mixed potential function under unified large-signal model
Big signal stabilization criterion is：
Wherein, VsFor equivalent circuit capacitance CdcThe magnitude of voltage of both ends output；
The stability criteria of formula (2) is equally also the stability criteria of aircraft electrical power system small-signal.
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| CN109861229A (en) * | 2019-01-31 | 2019-06-07 | 清华大学 | Ac/dc Power Systems method for analyzing stability and system based on mixed potential function |
| CN110676841A (en) * | 2019-09-12 | 2020-01-10 | 天津大学 | Transient stability analysis method for power electronic power system based on direct method |
| CN111193259A (en) * | 2020-01-10 | 2020-05-22 | 燕山大学 | Power system stability detection method and system of power electronic transformer |
| CN111259571A (en) * | 2020-03-07 | 2020-06-09 | 西南交通大学 | Stability analysis method for motor train unit grid-side single-phase pulse rectifier |
| CN112531685A (en) * | 2020-11-20 | 2021-03-19 | 东风汽车集团有限公司 | Method and device for controlling stability margin of automobile power system |
| CN113824154A (en) * | 2021-11-18 | 2021-12-21 | 中国科学院电工研究所 | Centralized operation control method for alternating current-direct current hybrid system containing renewable energy sources/hydrogen energy |
| CN114050590A (en) * | 2021-11-23 | 2022-02-15 | 北方工业大学 | Converter control parameter design method of hybrid energy storage system |
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| CN109492897A (en) * | 2018-11-05 | 2019-03-19 | 南瑞集团有限公司 | Transient stability and the dynamic united analysis method, apparatus of oscillation and system based on energy |
| CN109861229A (en) * | 2019-01-31 | 2019-06-07 | 清华大学 | Ac/dc Power Systems method for analyzing stability and system based on mixed potential function |
| CN110676841A (en) * | 2019-09-12 | 2020-01-10 | 天津大学 | Transient stability analysis method for power electronic power system based on direct method |
| CN110676841B (en) * | 2019-09-12 | 2022-06-14 | 天津大学 | Transient stability analysis method for power electronic power system based on direct method |
| CN111193259A (en) * | 2020-01-10 | 2020-05-22 | 燕山大学 | Power system stability detection method and system of power electronic transformer |
| CN111193259B (en) * | 2020-01-10 | 2023-09-22 | 燕山大学 | Power system stability detection method and system for power electronic transformer |
| CN111259571B (en) * | 2020-03-07 | 2022-04-29 | 西南交通大学 | Stability analysis method for motor train unit grid-side single-phase pulse rectifier |
| CN111259571A (en) * | 2020-03-07 | 2020-06-09 | 西南交通大学 | Stability analysis method for motor train unit grid-side single-phase pulse rectifier |
| CN112531685A (en) * | 2020-11-20 | 2021-03-19 | 东风汽车集团有限公司 | Method and device for controlling stability margin of automobile power system |
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| CN113824154B (en) * | 2021-11-18 | 2022-03-11 | 中国科学院电工研究所 | Centralized operation control method for alternating current-direct current hybrid system containing renewable energy sources/hydrogen energy |
| CN114050590A (en) * | 2021-11-23 | 2022-02-15 | 北方工业大学 | Converter control parameter design method of hybrid energy storage system |
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