CN104820751B - Aircraft electrical power system small disturbed stability analysis method based on generalized state space average - Google Patents
Aircraft electrical power system small disturbed stability analysis method based on generalized state space average Download PDFInfo
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Abstract
The present invention relates to a kind of aircraft electrical power system small disturbed stability analysis method based on generalized state space average, including step the power flow equation for according to aircraft electrical power system structure, establishing aircraft electrical power system, determines the steady operation point of aircraft electrical power system；The equivalent circuit of the generalized state space average modeling for aircraft electrical power system is established, obtains the nonlinear differential equation of aircraft electrical power system；The state variable of nonlinear differential equation is determined, the Generalized State Space Averaging model of Fourier coefficient description is obtained through Fourier decomposition；It is computed handling according to model, judges the small disturbed stability of aircraft electrical power system.Effect of the present invention is that this method realizes that the small disturbed stability under aircraft electrical power system Different Dynamic is analyzed, the sensitivity analysis of small disturbance stability can be realized, design and improvement to power system in big aircraft manufacturing are provided with value proposition, while reliable aircraft electrical power system operation information can be provided for crew.
Description
Technical field
The present invention relates to a kind of aircraft electrical power system small disturbed stability analysis method, more particularly to one kind to be based on broad sense shape
The average aircraft electrical power system small disturbed stability analysis method of state space, passes through the state using Fourier coefficient as state variable
Matrix analysis, accurate aircraft electrical power system small disturbance stability can be achieved and judge.
Background technology
For the performance for saving the energy, reducing cost and improving mobile system, present generation aircraft is taken using electric energy more and more
For the hydraulic pressure in conventional airplane, the air pressure energy, i.e., the load of the machinery of engine direct drive, hydraulic pressure and pneumatic actuation is changed
For electrically driven load.Thus " how electric aircraft (More Electric Aircraft) " concept proposed, it has also become aircraft work
The main trend of industry development.Development and increasingly mature, importance of the aircraft electrical power system in aircraft along with how electric aircraft
Increasingly highlight.Aircraft electrical power system includes electrical equipment three parts on aircraft power system, flight sequencing, machine：Aircraft electricity
Source system is to be used for producing the equipment combination of electric energy on machine, including main power source, accessory power supply, emergency power supply and secondary power supply etc.；
Flight sequencing is the group for being used for transmitting, distribute, change and control the equipment of electric energy and cable is carried out by certain way on machine
Close, also referred to as aircraft power network, mainly include electric power transmission lead and cable, prevent wire and equipment from being protected by short circuit or damages of overloading
Protection unit, power distribution equipment, secondary power supply, the control of electrical equipment and conversion equipment and power check instrument etc.；Electricity consumption is set on machine
It is standby to refer to by the workable equipment of electricity.
With coming into operation for the how electric aircraft such as B787, A380, the safe and stable operation problem of aircraft electrical power system also obtains
Increasing attention is arrived, its stability once wrecks, and will cause huge economic loss and catastrophic effect.By
The airplane fault caused by aircraft electrical power system problem happens occasionally, as the core of how electric aircraft, the peace of aircraft electrical power system
Full stable operation is then further important.Because aircraft electrical power system multi-machine parallel connection, multiple transformer crosslinking, electrical load property are various,
It is a higher-dimension Complex Nonlinear System to cause aircraft electrical power system, and its stability is not only by conventional electric power element dynamic characteristic shadow
Ring, and it is closely related with the dynamic characteristic of power electronic equipment.Simultaneously as the running environment thousand poor ten thousand of aircraft electrical power system
Not, aircraft electrical power system operation state is caused very big difference to be present, it is therefore necessary to establish the mathematical modulo for reflecting its dynamic characteristic
Type simultaneously carries out stability analysis based on this, realizes that aircraft electrical power system is fast and accurately steady under normal and fault condition
Qualitatively judge, and determine aircraft electrical power system each component links electrically and control parameter is to the influence degree of System Small Disturbance,
Finally the design to power system in big aircraft manufacturing and improvement provide suggestion.
The content of the invention
In view of the above-mentioned problems, it is an object of the invention to provide a kind of aricraft electrical power system based on generalized state space average
System small disturbed stability analysis method, it is possible to achieve the small disturbance stability sex determination under aircraft electrical power system Different Dynamic characteristic needs
Ask.
To achieve the above object, the technical solution adopted by the present invention is to provide a kind of winged based on generalized state space average
Electro-mechanical force System Small Disturbance method for analyzing stability, the generalized state space average are exactly using Fourier coefficient as state variable
A kind of space average, this method comprises the following steps：
1) according to aircraft electrical power system structure, it is straight that power supply in aircraft electrical power system, distribution system, the friendship of electricity system are established
Mixed current equation is flowed, determines the steady operation point of aircraft electrical power system；
In formula：VsFor three-phase alternating voltage virtual value, VbusFor AC voltage steady-state value, i.e. vertoro AC
Phase difference, the Z ∠ γ of input voltage value, λ between above-mentioned two voltageZFor the folding of transmission line of alternation current impedance, including transformer
It is respectively constant power load active power, reactive power to calculate reactance, P, Q, PlossTo be damaged due to power caused by DC side circuit
Consumption
2) to step 1) aircraft electrical power system carry out circuit equivalent, it is equivalent after circuit built for generalized state space average
Mould, and obtain the nonlinear differential equation of aircraft electrical power system according to the equivalent circuit：
Wherein, x=[x1,x2,…,xn]TFor system state variables, Ψ is system state variables matrix, is n × n rank squares
Battle array, u=[u1,u2,…,um]TFor system algebraic variable, Γ is system algebraic variable matrix, is n × m rank matrixes；
3) nonlinear differential equation of the aircraft electrical power system obtained according to step 2), determines aircraft electrical power system power supply system
System, distribution system, electricity system nonlinear differential equation state variable, aperiodic state variable r in state variable, cycle shape
State variable s, and Fourier decomposition is carried out to state variable, according to obtained Fourier coefficient<xi>k(τ), introduce new state
Matrix of variables Q, Q=[q1,q2,…,qr+2ks]T, Q matrix each elements are as follows：
0<During i≤r,<xi>0(τ)=qi
r<During i≤n,<xi>k(τ)=q2s(k-1)+(2i-r-1)+jq2s(k-1)+(2i-r)
4) Fourier decomposition is carried out to the nonlinear differential equation of the aircraft electrical power system in step 2), and step 3) is obtained
The state variable matrix Q arrived is substituted into, and finally gives the aircraft electrical power system generalized state space average side of Fourier coefficient description
Journey：
In formula：Q represents the system state variables matrix of Fourier coefficient description, and A represents Fourier coefficient state variable system
Matrix number, Y are the output of this link nonlinear differential equation, and the dynamic characteristic of a link under the influence of its size, B is Y coefficient
Matrix, UxFor system operation control parameter；
5) the aircraft electrical power system generalized state space average equation obtained according to step 4), in the aircraft that step 1) obtains
Linearized at the steady operation point of power system, obtain the sytem matrix A of the state equation of linearized system：
6) calculation procedure 5) the obtained characteristic value of sytem matrix, calculation formula is as follows：
Det [λ I-A]=0
In formula：A is the sytem matrix of state equation, and I is unit matrix, and λ is characteristic value to be asked.
According to the small disturbed stability of the positive negative judgement aircraft electrical power system of characteristic value real part, change the operation control of system
Parameter, and according to characteristic value in complex plane with the variation tendency of system operation control parameter, if characteristic value is in the complex plane imaginary axis
Left-sided system then to be stable, in imaginary axis right-sided system then to be unstable, to judge aircraft electrical power system operational parameter control
Change influences on small disturbed stability.
The effect that the present invention reaches is the method for analyzing stability, compared to the time-domain-simulation that can not embody extent of stability
Method, and the State-space Averaging Principle of aircraft electrical power system dynamic characteristic is not considered, realize under aircraft electrical power system Different Dynamic
Small disturbed stability analysis, while the sensitivity analysis of small disturbance stability can be realized, finally to electric power in big aircraft manufacturing
The design and improvement of system are provided with value proposition, while reliable aircraft electrical power system operation information can be provided for crew
Brief description of the drawings
Fig. 1 is aircraft electrical power system sma1l signal stability flow chart of the present invention；
Fig. 2 is certain how electric aircraft electrical power system structure diagram；
Fig. 3 is aircraft electrical power system alternating current-direct current Load flow calculation line chart；
Fig. 4 is certain how electric airplane power system generalized state space average modelled equivalent circuit diagram.
Embodiment
It is small to the aircraft electrical power system based on generalized state space average of the invention with reference to the accompanying drawings and examples to disturb
Dynamic stability analysis method further illustrates.
Fig. 1 is aircraft electrical power system sma1l signal stability flow chart.
The aircraft electrical power system small disturbed stability analysis method based on generalized state space average of the present invention is described wide
Adopted State space averaging is exactly a kind of space average using Fourier coefficient as state variable, and this method comprises the following steps：
1) according to aircraft electrical power system structure, it is straight that power supply in aircraft electrical power system, distribution system, the friendship of electricity system are established
Mixed current equation is flowed, determines the steady operation point of aircraft electrical power system；
In formula：VsFor three-phase alternating voltage virtual value, VbusFor AC voltage steady-state value, i.e. vertoro AC
Phase difference, the Z ∠ γ of input voltage value, λ between above-mentioned two voltageZFor the folding of transmission line of alternation current impedance, including transformer
It is respectively constant power load active power, reactive power to calculate reactance, P, Q, PlossTo be damaged due to power caused by DC side circuit
Consumption.
2) to step 1) aircraft electrical power system carry out circuit equivalent, it is equivalent after circuit built for generalized state space average
Mould, and obtain the nonlinear differential equation of aircraft electrical power system according to the equivalent circuit：
Wherein, x=[x1,x2,…,xn]TFor system state variables, Ψ is system state variables matrix, is n × n rank squares
Battle array, u=[u1,u2,…,um]TFor system algebraic variable, Γ is system algebraic variable matrix, is n × m rank matrixes.
3) nonlinear differential equation of the aircraft electrical power system obtained according to step 2), determines aircraft electrical power system power supply system
System, distribution system, electricity system nonlinear differential equation state variable, aperiodic state variable r in state variable, cycle shape
State variable s, and Fourier decomposition is carried out to state variable, according to obtained Fourier coefficient<xi>k(τ), introduce new state
Matrix of variables Q, Q=[q1,q2,…,qr+2ks]T, Q matrix each elements are as follows：
0<During i≤r,<xi>0(τ)=qi
r<During i≤n,<xi>k(τ)=q2s(k-1)+(2i-r-1)+jq2s(k-1)+(2i-r)。
4) Fourier decomposition is carried out to the nonlinear differential equation of the aircraft electrical power system in step 2), and step 3) is obtained
The state variable matrix Q arrived is substituted into, and finally gives the aircraft electrical power system generalized state space average side of Fourier coefficient description
Journey：
In formula：Q represents the system state variables matrix of Fourier coefficient description, and A represents Fourier coefficient state variable system
Matrix number, Y are the output of this link nonlinear differential equation, and the dynamic characteristic of a link under the influence of its size, B is Y coefficient
Matrix, UxFor system operation control parameter.
5) the aircraft electrical power system generalized state space average equation obtained according to step 4), in the aircraft that step 1) obtains
Linearized at the steady operation point of power system, obtain the sytem matrix A of the state equation of linearized system：
6) calculation procedure 5) the obtained characteristic value of sytem matrix, calculation formula is as follows：
Det [λ I-A]=0
In formula：A is the sytem matrix of state equation, and I is unit matrix, and λ is characteristic value to be asked.
According to the small disturbed stability of the positive negative judgement aircraft electrical power system of characteristic value real part, change the operation control of system
Parameter, and according to characteristic value in complex plane with the variation tendency of system operation control parameter, if characteristic value is in the complex plane imaginary axis
Left-sided system then to be stable, in imaginary axis right-sided system then to be unstable, to judge aircraft electrical power system operational parameter control
Change influences on small disturbed stability.
The aircraft electrical power system alternating current-direct current mixed current equation established in the step 1), to exchange aviation based on 400Hz
The equation that generator, transmission line of alternation current, wave filter, vertoro, DC power transmission line, inversion link are established, based on institute
The voltage steady-state value that equation calculates vertoro AC is stated, is closed further according to the ac-dc conversion of the vertoro
System, obtains steady state voltage value V of the vertoro DC side under different capacity P, Qout。
Equivalent circuit and the aircraft electricity for aircraft electrical power system generalized state spatial modeling established in the step 2)
Force system nonlinear differential equation, it is to be based on three phase static abc coordinate systems, includes 400Hz exchanges aerogenerator, ac transmission
Circuit, wave filter, vertoro, the alternating current-direct current hybrid equivalent circuit of DC power transmission line link.
The Generalized State Space Averaging model of the aircraft electrical power system obtained in the step 4), to include aricraft electrical power system
The Generalized State Space Averaging model for dynamic characteristic of uniting, and the working condition that the dynamic characteristic of aircraft electrical power system is run with aircraft
And the moment adjusts.
The sytem matrix of the state equation of linearized system in the step 5), it is the dynamic spy according to aircraft electrical power system
Property, obtained using different rank Fourier coefficient as state variable.
The operating mode that the dynamic characteristic of aircraft electrical power system is started with aircraft, slided, taking off, climbing, cruising, declining, landing
And the moment adjusts, including component-level dynamic, behavioral scaling dynamic, functional level dynamic, structural level four kinds of levels of dynamic, the component-level
Dynamically refer to power electronic devices in aircraft electrical power system, the internal dynamics of electromagnetic actuator；The behavioral scaling dynamically refers to group
Dynamic is switched into aircraft electrical power system vertoro, chopper, inverter are caused in work process；The functional level moves
State refer to complete aircraft start, landing, anti-icing, defrosting function, aircraft electrical power system progress electric motor starting, stopping, changing load,
Switching dynamic behaviour；The structural level dynamically refer to aircraft for the taking off of the different mission phase of reply, climb, cruise, institute of landing
Caused NETWORK STRUCTURE PRESERVING POWER SYSTEM switches dynamic characteristic.
In the step 6), the system operation control parameter of effect characteristicses value variation tendency in complex plane includes circuit
Inductance, electric capacity, active power, reactive power, frequency.
Embodiment
The present embodiment is based on certain how electric aircraft electrical power system, establishes its Generalized State Space Averaging model and carries out microvariations
Stability analysis.Fig. 2 is the how electric aircraft electrical power system structure diagram comprising specific link, wherein it is assumed that GCU governing speeds are sufficient
It is enough fast, therefore alternating current generator can be replaced with exchange 400Hz voltage stabilizing AC powers, electrical actuation and control system is replaced with constant power load,
Remaining building block includes：Transmission line of electricity, vertoro, DC filter capacitor.Req,Leq,CeqRespectively circuit and transformer
Equivalent resistance, reactance, electric capacity.
1) according to how electric aircraft electrical power system structure diagram, AC is arrived into the conversion of direct current lateral circuit, obtained shown in Fig. 3
Aircraft electrical power system alternating current-direct current mixed current calculates line chart, and calculation formula is as follows：
Wherein, VsFor three-phase alternating voltage virtual value, 230V is taken；
VbusFor AC voltage steady-state value, i.e. vertoro AC input voltage value, for amount to be asked；
Phase differences of the λ between above-mentioned two voltage, for amount to be asked；
Z∠γZFor transmission line of alternation current impedance (referring reactance for including transformer), it is calculated as follows：
P, Q is respectively constant power load active power, reactive power, is the amount for changing with load and changing, and it changes meeting
Influence the change of steady state voltage value.
Thus, it is possible to the voltage steady-state value of AC is calculated, can further according to the ac-dc conversion relation of vertoro
To obtain steady state voltage value V of the DC side under different capacity P, Qout。
2) according to how electric aircraft electrical power system structure diagram, vertoro is subjected to circuit equivalent, obtains generalized state
Space average modelled equivalent circuit diagram, as shown in figure 4, the nonlinear differential equation that can obtain the equivalent circuit is as follows, wherein public
Parameters in formula mark in figure：
3) according to the nonlinear differential equation in step 2), the state variable x=[V of aircraft electrical power system are determinedout,Idc,
ILa,ILb,ILc,VCa,VCb,VCc]T, wherein aperiodic state variable r=2, be Vout,Idc, periodic state variable s=6, it is
ILa,ILb,ILc,VCa,VCb,VCc, Fourier decomposition is carried out to state variable, takes k=1, and ignore DC ripple, then what is introduced is new
State variable matrix Q in element it is as follows：
<Vout>0=q1
<Idc>0=q2
<ILa>1=q3+jq4
<ILb>1=q5+jq6
<ILc>1=q7+jq8
<VCa>1=q9+jq10
<VCb>1=q11+jq12
<VCc>1=q13+jq14
4) the aircraft electrical power system nonlinear differential equation obtained to step 2) carries out Fourier decomposition, and substitutes into step 3)
Obtained new state variable matrix Q, finally give the aircraft electrical power system generalized state space average of Fourier coefficient description
Equation：
5) Generalized State Space Averaging model obtained for step 4), under a certain certain power P, Q that step 1 obtains
Steady operation point at linearized, obtain for Fourier coefficient description linearized system state equation system square
Battle array A.
In formula, PCPLFor the active power of constant power load.
6) formula det [λ I-A]=0 calculating matrix A characteristic value is utilized, the positive negative judgement aircraft electricity according to characteristic value real part
The small disturbed stability of Force system, and pass through P in transformation matrix respectivelyCPL, LF,CF,rF,Req,Leq,CeqEtc. parameter, feature is obtained
Value follows the variation tendency of above-mentioned different parameters in complex plane, and then determines each Parameters variation of aircraft electrical power system to microvariations
The influence of stability.
Thus, the present invention realizes the aircraft electrical power system small disturbed stability analysis based on generalized state space average,
The small disturbed stability analysis demand of aircraft electrical power system under the conditions of Different Dynamic can be met.
Finally it should be noted that：Only illustrate technical scheme with reference to above-described embodiment rather than it is limited
System.Those of ordinary skills in the art should understand that to：Those skilled in the art can be carried out to embodiments of the present invention
Modification or equivalent substitution, but these modifications or change are being applied within pending claims.
Claims (7)
1. a kind of aircraft electrical power system small disturbed stability analysis method based on generalized state space average, the generalized state
Space average is exactly a kind of space average using Fourier coefficient as state variable, and this method comprises the following steps：
1) according to aircraft electrical power system structure, power supply in aircraft electrical power system, distribution system, the alternating current-direct current of electricity system is established and is mixed
Equation in the swim, determine the steady operation point of aircraft electrical power system；
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In formula：VsFor three-phase alternating voltage virtual value, VbusFor AC voltage steady-state value, i.e. vertoro AC input electricity
Phase difference, the Z ∠ γ of pressure value, λ between above-mentioned two voltageZFor transmission line of alternation current impedance, including transformer referring reactance,
P, Q is respectively constant power load active power, reactive power, PlossFor due to power attenuation caused by DC side circuit
2) to step 1) aircraft electrical power system carry out circuit equivalent, it is equivalent after circuit be used for generalized state space average modeling,
And obtain the nonlinear differential equation of aircraft electrical power system according to the equivalent circuit：
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<mi>x</mi>
<mo>&CenterDot;</mo>
</mover>
<mo>=</mo>
<mi>&Psi;x</mi>
<mo>+</mo>
<mi>&Gamma;u</mi>
</mrow>
Wherein, x=[x1,x2,…,xn]TFor system state variables, Ψ is system state variables matrix, is n × n rank matrixes, u=
[u1,u2,…,um]TFor system algebraic variable, Γ is system algebraic variable matrix, is n × m rank matrixes；
3) nonlinear differential equation of the aircraft electrical power system obtained according to step 2), determine aircraft electrical power system power-supply system,
Distribution system, electricity system nonlinear differential equation state variable, aperiodic state variable r in state variable, periodic state
Variable s, and Fourier decomposition is carried out to state variable, according to obtained Fourier coefficient<xi>k(τ), introduce new state and become
Moment matrix Q, Q=[q1,q2,…,qr+2ks]T, Q matrix each elements are as follows：
0<During i≤r,<xi>0(τ)=qi
r<During i≤n,<xi>k(τ)=q2s(k-1)+(2i-r-1)+jq2s(k-1)+(2i-r)
4) Fourier decomposition is carried out to the nonlinear differential equation of the aircraft electrical power system in step 2), and step 3) is obtained
State variable matrix Q is substituted into, and finally gives the aircraft electrical power system generalized state space average equation of Fourier coefficient description：
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In formula：Q represents the system state variables matrix of Fourier coefficient description, and A represents Fourier coefficient state variable coefficient square
Battle array, Y are the output of this link nonlinear differential equation, and the dynamic characteristic of a link under the influence of its size, B is Y coefficient matrix,
UxFor system operation control parameter；
5) the aircraft electrical power system generalized state space average equation obtained according to step 4), in the aricraft electrical power that step 1) obtains
Linearized at the steady operation point of system, obtain the sytem matrix A of the state equation of linearized system：
6) calculation procedure 5) the obtained characteristic value of sytem matrix, calculation formula is as follows：
Det [λ I-A]=0
In formula：A is the sytem matrix of state equation, and I is unit matrix, and λ is characteristic value to be asked；
According to the small disturbed stability of the positive negative judgement aircraft electrical power system of characteristic value real part, the operation control for changing system is joined
Number, and according to characteristic value in complex plane with the variation tendency of system operation control parameter, if characteristic value is in the complex plane imaginary axis
Left-sided system is then to be stable, in imaginary axis right-sided system then to be unstable, to judge that aircraft electrical power system operational parameter control becomes
Change influences on small disturbed stability.
2. the aircraft electrical power system small disturbed stability analysis side according to claim 1 based on generalized state space average
Method, it is characterized in that：The aircraft electrical power system alternating current-direct current mixed current equation established in the step 1), to be exchanged based on 400Hz
The equation that aerogenerator, transmission line of alternation current, wave filter, vertoro, DC power transmission line, inversion link are established, base
The voltage steady-state value of vertoro AC is calculated in the equation, further according to the ac-dc conversion of the vertoro
Relation, obtain steady state voltage value V of the vertoro DC side under different capacity P, Qout。
3. the aircraft electrical power system small disturbed stability analysis side according to claim 1 based on generalized state space average
Method, it is characterized in that：The equivalent circuit for being used for aircraft electrical power system generalized state spatial modeling established in the step 2) and winged
The electro-mechanical force mission nonlinear differential equation, it is to be based on three phase static abc coordinate systems, includes 400Hz exchanges aerogenerator, exchange
Transmission line of electricity, wave filter, vertoro, the alternating current-direct current hybrid equivalent circuit of DC power transmission line link.
4. the aircraft electrical power system small disturbed stability analysis side according to claim 1 based on generalized state space average
Method, it is characterized in that：The Generalized State Space Averaging model of the aircraft electrical power system obtained in the step 4), to include aircraft electricity
The Generalized State Space Averaging model of Force system dynamic characteristic, and the work that the dynamic characteristic of aircraft electrical power system is run with aircraft
Situation and moment adjust.
5. the aircraft electrical power system small disturbed stability analysis side according to claim 1 based on generalized state space average
Method, it is characterized in that：The sytem matrix of the state equation of linearized system in the step 5), it is according to the dynamic of aircraft electrical power system
Step response, obtained using different rank Fourier coefficient as state variable.
6. the aircraft electrical power system small disturbed stability analysis side according to claim 4 based on generalized state space average
Method, it is characterized in that：What the dynamic characteristic of aircraft electrical power system was started with aircraft, and slided, and taking off, and climbing, and cruising, and declining, landing
Operating mode and moment adjust, including component-level dynamic, behavioral scaling dynamic, functional level dynamic, structural level four kinds of levels of dynamic, the member
Part level dynamically refers to power electronic devices in aircraft electrical power system, the internal dynamics of electromagnetic actuator；The behavioral scaling dynamic
Refer to composition aircraft electrical power system vertoro, chopper, the inverter caused switch dynamic in work process；The function
Level, which dynamically refers to, completes aircraft startup, landing, anti-icing, defrosting function, electric motor starting, stopping, the load of aircraft electrical power system progress
Change, switching dynamic behaviour；The structural level dynamically refers to aircraft to tackle taking off, climb, cruising, dropping for different mission phases
NETWORK STRUCTURE PRESERVING POWER SYSTEM switching dynamic characteristic caused by falling.
7. the aircraft electrical power system small disturbed stability analysis side according to claim 1 based on generalized state space average
Method, it is characterized in that：In the step 6), effect characteristicses value system operation control parameter of variation tendency in complex plane includes
Line inductance, electric capacity, active power, reactive power, frequency.
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| CN106451419B (en) * | 2016-09-18 | 2020-01-31 | 天津大学 | airplane power system average value model and large disturbance stability domain construction method |
| CN106655166B (en) * | 2016-11-28 | 2019-05-17 | 中国民航大学 | Aircraft electrical power system method for analyzing stability based on Impedance Criterion |
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| CN110032802B (en) * | 2019-04-15 | 2023-05-26 | 中国民航大学 | Sensitivity analysis and calculation method for aircraft power supply system based on dq transformation |
| CN110020510B (en) * | 2019-06-06 | 2019-09-10 | 西南交通大学 | A kind of method for analyzing stability of the EMU net side Pulse rectifier based on Floquet theory |
| CN111103796B (en) * | 2019-12-06 | 2021-11-23 | 华南理工大学 | Alternating current-direct current system stability domain analysis method based on square sum decomposition optimization algorithm |
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