CN105281328A - Static model and steady power flow analysis method of more electric aircraft electric system - Google Patents
Static model and steady power flow analysis method of more electric aircraft electric system Download PDFInfo
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Abstract
The invention provides a static model and steady power flow analysis method of a more electric aircraft electric system. The electric system comprises a power flow model wiring diagram composed of a generator model, a converter model, an electric transmission line model, a load model, a filter and reactive compensation model, and en energy storage device model. The method is based on an AC/DC power flow computing method of a land electric system and in consideration of a feature that a DC bus carries the DC load at the same time, a DC equation in an improved network equation is adopted so as to fit the power flow computing analysis of the more electric aircraft electric system, and the power flow distributions of the aircraft electric system under different working conditions are computed through MATLAB programming. Through the adoption of the method provided by the invention, the steady state of the more electric aircraft electric system can be researched on the whole, the method pays more attention to the system integrity, and is capable of clearly analyzing the power flow distributions under different flight working conditions.
Description
Technical field
The present invention relates to the steady-state analysis field of how electric aircraft electrical power system, be specifically related to the calculation and analysis methods that how electric aircraft static modelling and trend distribute.
Background technology
Aircraft electrical power system is the general name of electric power system and power consumption equipment, it is one of important component part of aircraft, can it normally work and all play vital effect to aircraft safety and normal operation, particularly along with aircraft is to many electricity, complete electric future development, its safety and reliability obtains more and more concern.
Find by prior art documents, the direction of the how electric aircraft electrical power system of existing research is mainly: several aspects such as the integrated management of motor and power-supply system, distribution technique, dynamo-electric start technology, power-by-wire, all-electric braking system and multimachine electric system, and wherein the research of motor and power-supply system aspect also more focuses on failure diagnosis, distribution technique and load stability.
Searching document finds, from aircraft electric network reliability and failure diagnosis aspect, there is limit to the south, Zhou Yuying, a kind of topological method of quantitative analysis electrical power system of more electric aircraft and a kind of algorithm being applicable to how electric aircraft electrical power system reliability assessment is proposed in the document " electrical power system of more electric aircraft reliability network Topological analysis " that Ma Qishuan delivers at BJ University of Aeronautics & Astronautics's journal, but just carry out analyzing from network topology and proposed reliability index, and also only give topological framework slightly at the beginning of, can not research and analyse from actual operating mode aspect, in " development that electrical power system of more electric aircraft and power quality require " document that Feng Yulian, Diao Xuemin deliver on " Silicon Valley " magazine, based on the new power system structure of how electric aircraft, new load request and the application of power electronic equipment in aviation, aircraft power supply quality is studied, but be also the particular/special requirement based on conventional power system and aircraft electrical power system, give the requirement of a series of power quality aspect, not further investigation, the Yao Jing of Northwestern Polytechnical University discusses expert system theory and the application of artificial neural network theories in electrical power system of more electric aircraft failure diagnosis in its Master's thesis " the failure diagnosis research of electrical power system of more electric aircraft ", introduce and analyze structure and the feature of how electric aircraft electrical power system, but be all carry out Analysis on Fault Diagnosis from each independent module, also do not carry out stable state research from the aspect of overall aircraft electric power system.
The document of comprehensive these classifications above, can find, mainly have the following disadvantages in existing how electric aircraft electrical power system research method:
The overall operation situation of aircraft electrical power system can not be reflected.Many electric aircraft electrical power system building blocks are numerous, System's composition is complicated, each building block and System's composition cannot ensure reliability service completely, therefore the ruuning situation of aircraft electrical power system local is mainly separately discussed in existing major part research, and be main mainly with the Study on Fault, and not yet find the report carrying out steady-state analysis with how electric aircraft electrical power system entirety at present.
Not in conjunction with the physical cabling of aircraft, the electric power networks ruuning situation of aircraft can not be reflected really.The research method of existing how electric aircraft electrical power system is independent from power-supply system, or distribution system is studied, and does not consider complete aricraft electrical power network physical cabling.
Do not consider the ruuning situation under the different operating mode of aircraft.The total electricity of aircraft electrical power system is limited in one's ability, the requirement of operation at full load while of all power equipments on aircraft can not be met, therefore the duty requirements according to each stage of flight is needed, in conjunction with the electrical load requirement of power equipment on machine, controlled the total load of aricraft electrical power equipment by switching manipulation.For this reason, the how electric aircraft electrical power system safety analysis under variable working condition state is needed to carry out.
Summary of the invention
The present invention is directed to the problem of above-mentioned prior art, provide a kind of static models and steady-state load flow analytical method of how electric aircraft electrical power system, consider from how electric aircraft electrical power system overall structure, equivalent circuit modeling is carried out to the main element in how electric aircraft system, tide model winding diagram is drawn again according to the physical cabling of specific model, utilize the alternative iteration method after improving, by the flow situations under the different operating mode of the how electric aircraft of MATLAB program calculation specific model.
For achieving the above object, the technical solution adopted in the present invention is as follows:
Static models for how electric aircraft electrical power system, comprise the tide model winding diagram of generator model, current transformer model, model of power transmission system, load model, filter and reactive power compensation model and energy storage device model-composing, wherein:
Described generator model is the equivalence to how electric aircraft power system;
Described current transformer model is the equivalence to rectifier and inverter in how electric aircraft electrical power system;
Described model of power transmission system is the equivalence to power circuit in how electric aircraft electrical power system;
Described load model is the equivalence to running load in how electric aircraft electrical power system;
Described filter and reactive power compensation model are the equivalences to the filter in rectifier AC, inverter ac side and DC line in how electric aircraft electrical power system and reactive-load compensator;
Described energy storage device model is the equivalence to how electric aircraft stand-by power supply.
Described model of power transmission system adopts substitutional resistance model.
Described filter and reactive power compensation model adopt the branch road over the ground of resistance, inductance, electric capacity composition to come equivalent.
Described energy storage device model equivalence is DC power supply.
Described static models form aircraft electrical power system power flow algorithm in conjunction with aircraft physical cabling, based on the alternating current-direct current tidal current computing method of land electric power system, consider the feature of DC bus with DC load simultaneously, adopt the direct current equation improved in network equation, to be applicable to the Load flow calculation analysis of how electric aircraft electrical power system, to be got off the plane electric power system tide distribution situation by the different operating mode of MATLAB program calculation.
When calculating trend distribution under different operating mode, take regulator generator terminal voltage, regulate converter transformer no-load voltage ratio and regulate the mode of the three kinds of methods combining in converter control angle to determine control strategy, and choose running time the longest running working condition as initial 0 grade.
Described generator model, when not considering the system failure and then not considering that stand-by power supply affects, when how electric aircraft power supply design redundancy be generally larger, using generator as balance node, determines voltage magnitude and initial phase.
According to the control mode of aircraft power system characteristic determination current transformer, inverter is selected determine pilot angle and determine output power mode, and rectifier is selected to determine pilot angle and rated transformation ratio control mode.
In Load flow calculation, using rectifier and inverter as PQ node, in how electric aircraft electrical power system, on the right side of inverter, directly connect load, for passive system, now, need to install a bulky capacitor additional in the DC side of inverter, adopt voltage source inverter, the reactive power utilizing bulky capacitor to produce is idle to what provide needed for inverter and load, in Load flow calculation, bulky capacitor is thought a part for inverter, ideally output reactive power.
In described load model, all loads equal equivalence in tidal current analysis is PQ node, and its size is determined according to the loading configuration of Different periods.
Compared with prior art, the present invention has following beneficial effect:
By the static modelling of equivalence, according to the concrete wiring condition of how electric aircraft, the power flow algorithm of how electric aircraft electrical power system can be listed; The analytical method of land electric power system be incorporated in the steady-state analysis of how electric aircraft electrical power system, utilize the method for Load flow calculation, the situation that can get more information about the change of aircraft operating condition is got off the plane the stable of each important node of electric power system or situation of change; Utilize MATLAB programming realization Load flow calculation process, convenient and swift, the trend distribution situation of how electric aircraft electrical power system under each operating mode of observation that can be very clear and definite; The basic operation that Load flow calculation runs as research power system mesomeric state is the basis of Model for Stability Calculation of Power System and accident analysis, can complete all kinds of work such as aircraft network planning, Scheme of Reactive Power Compensation, accident analysis by trend distribution research.
Accompanying drawing explanation
By reading the detailed description done non-limiting example with reference to the following drawings, other features, objects and advantages of the present invention will become more obvious:
Fig. 1 is the analytical method hierarchy chart that the present invention studies how electric aircraft electrical power system;
Fig. 2 is each component static model of the embodiment of the present invention and power flow algorithm winding diagram;
Fig. 3 is embodiment of the present invention Load flow calculation flow chart.
Embodiment
Below in conjunction with specific embodiment, the present invention is described in detail.Following examples will contribute to those skilled in the art and understand the present invention further, but not limit the present invention in any form.It should be pointed out that to those skilled in the art, without departing from the inventive concept of the premise, some distortion and improvement can also be made.These all belong to protection scope of the present invention.
The present invention includes how electric aircraft electrical power system static modelling and steady-state load flow analyzes two parts.Static modelling is namely by the tide model winding diagram of generator model, current transformer model, model of power transmission system, load model, filter and reactive power compensation model and energy storage device model-composing.Steady-state load flow analysis is the trend distribution research under the different operating condition of how electric aircraft, alternative iteration method after improving according to how electric aircraft electrical power system feature employing.
Generator model is the equivalence to how electric aircraft power system, is not considering under system fault conditions, the impact of stand-by power supply can not be considered, therefore, when how electric aircraft power supply design redundancy be generally larger, using generator as balance node, determine voltage magnitude and initial phase.
Current transformer model is the equivalence to rectifier and inverter in how electric aircraft electrical power system.Rectifier absorbs active power and reactive power from AC system, and inverter discharges active power, absorbing reactive power to AC system, therefore in Load flow calculation, using rectifier and inverter as PQ node.In how electric aircraft electrical power system, directly connecing load on the right side of inverter, is passive system, now, need to install a bulky capacitor additional in the DC side of inverter, adopt voltage source inverter, the reactive power utilizing bulky capacitor to produce is idle to what provide needed for inverter and load.In Load flow calculation, bulky capacitor is thought a part for inverter, ideally output reactive power.
Model of power transmission system is the equivalence to power circuit in how electric aircraft electrical power system.Many electric aircraft power distribution networks adopt Distributed power technology, and circuit model is comparatively simple, and adopting three-phase four-wire system electric-powered manner, take body as the neutral line.All kinds of loads on aircraft are connected by cable, compared with general transmission line, Aircraft Cables length is short, can ignore the capacitive reactance in π type equivalent model, direct use series impedance is come equivalent, adopts experiment to record the model parameter of civil aircraft cable actual motion state.
Load model is the equivalence to operating load in how electric aircraft electrical power system, and AC load power factor is unified is assumed to be 0.85.All loads equal equivalence in tidal current analysis is PQ node, and its size is determined according to the loading configuration of Different periods.
Filter and reactive power compensation model are the equivalences to the filter in rectifier AC, inverter ac side and DC line in how electric aircraft electrical power system and reactive-load compensator.Come equivalent with the branch road over the ground of resistance, inductance, electric capacity composition.
Energy storage device model is the equivalence to how electric aircraft stand-by power supply.Energy storage device on aircraft as emergency power supply for subsequent use, to critical fligh load electric, and starts main generator by the mode of delivery of electrical energy in flight course, the general form adopting aircraft battery.But the charging process of storage battery can complete on ground usually, do not need to its charging in aircraft flight, and only just drop into when aircraft main power source cannot work, can equivalence be DC power supply in alternating current-direct current Load flow calculation.Consider it generally as subsequent use, and ground power supply is the outside energy storage device of aircraft, be aircraft when airport is standby as piloting engine or supplying the need for electricity of other electric equipments of aircraft, therefore can not join in trend computing.
Tide model winding diagram is according to given example, connects described main element model, forms winding diagram needed for how electric aircraft electrical power system Load flow calculation.
Alternative iteration method after improving, on the alternative iteration method basis of alternating current-direct current tidal current computing method, in conjunction with the special character of how electric aircraft electrical power system, by analyzing the tidal current computing method improving and adopt, to be applicable to the Load flow calculation of how electric aircraft electrical power system, by MATLAB programming realization.The feature of many electric aircraft electrical power systems is: how electric aircraft electrical power system is alternating current-direct current combined hybrid system, and compared with the AC-HVDC net electric power system of land, with load on its DC bus, transmission range is short, and essence is power distribution network; Filter in many electric aircraft electrical power systems, the relatively whole network system of the parameter value of reactive power compensation device be can not ignore, and need them all to take into account when Load flow calculation; The load power fluctuation ratio of many electric aircraft electrical power systems under different operating mode is comparatively large, can cause larger change, need all to carry out Load flow calculation analysis to each operating mode to trend distribution.Therefore, the tidal current analysis method of many electric aircraft systems can not be analyzed according to the method for land electric power system alternating current-direct current Load flow calculation completely, and must improve, difference is: how electric the DC network equation of aircraft electrical power system be different from the DC network equation of land DC transmission system, rectifier DC side electric current and inverter direct-flow side electric current are also unequal, but a difference DC load electric current, need to be considered in DC network equation and go.
One embodiment of the invention is used for the static modelling of Boeing 787 (B787) aircraft electrical power system and each operating mode Load flow calculation is analyzed.
As shown in Figure 1, the present embodiment comprises: generator model, current transformer model, circuit model, load model, filter and Reactive Power Device model.
Generator model: generator is as balance node, and voltage magnitude is 235V, and initial phase is 0;
Current transformer model: according to the control mode of aircraft power system characteristic determination current transformer, inverter is selected determine pilot angle and determine output power mode, and rectifier is selected to determine pilot angle and rated transformation ratio control mode, and rectifier and inverter are as PQ node.
Model of power transmission system: adopt substitutional resistance model, resistance size is 0.081 Ω;
Load model: the load condition under each operating mode is not identical, the load value when trend calculated under each operating mode distributes under corresponding each operating mode of employing;
Filter and reactive power compensation model: adopt the branch road over the ground of resistance, inductance, electric capacity composition to come equivalent, its single-phase resistance is 0.05 Ω, and single-phase inductance is 15.915 μ H, and single-phase capacitance is 82.373 μ F;
Energy storage device model: do not consider under stable situation.
In Fig. 2,1,2,3,4 is 4 nodes of power flow algorithm, 4 nodes corresponding 230V interchange respectively, 270V direct current, 115V interchange, 28V DC bus.Circuit between node 1,2 and node 2,3 is direct current component, by equivalent for AC system for being added in the voltage source at direct current system two ends, with AC side of converter voltage
solving separately direct current system equation as input, is a node by direct current system equivalence, obtains coming to solve separately AC system equation as input from the extraction of AC system or the power of injection with it again, obtains AC side of converter voltage
iteration like this, until meet the condition of convergence.
Load flow calculation process adopts MATLAB programming realization, and idiographic flow lists flow chart as shown in Figure 3.The advantage of program is that computational speed is fast, is easy to realize, parameter integrity degree is high, only need inputting the workload demand power of each load bus and the converter primary side voltage of supposition, just can calculating the power flow solutions of whole how electric aircraft electrical power supply system, without the need to inputting other any parameters again.
The present embodiment considers the trend distribution situation under the different operating mode of aircraft.Under running working condition, 28V DC load is 22.62KW, 270V DC load is 171.68KW, 115V AC load be 56.93KVA, 230V AC load is 24.36KVA, running working condition is aircraft duration the longest operating mode, is 0 grade with the load tap changer under aircraft navigation operating mode.Take regulator generator terminal voltage, regulate converter transformer no-load voltage ratio, and regulate the mode of the three kinds of methods combining in converter control angle to regulate because operating mode changes formation load change thus the whole network variation in voltage caused.In the present embodiment, the main no-load voltage ratio of adjustment 230V bus to the rectifier transformer of 270V bus and the pilot angle of this rectifier, under running working condition, its no-load voltage ratio is 0.78, and pilot angle is 17 °.Utilize Voltage Cortrol strategy to be stabilized near rated value to make busbar voltage, the adjustable strategies under each flight operating mode can be drawn.By computational analysis, in conjunction with the trend distribution situation of all operating modes, can find out, the voltage compare of each busbar voltage under different operating mode (six operating modes of taking off, climb, navigate by water, decline, slide and land) is steady, is all near rated voltage.Under running working condition, 230V bus is slightly high relative to other operating modes with 28V busbar voltage, and the reactive power compensation of 230V bus bar side and 115V bus bar side is very steady, and the reactive power compensation of inverter bulky capacitor needs to compensate very many reactive powers under running working condition.
The present embodiment result can be found out, the node voltage calculated value of how electric aircraft electrical power system is all near rated voltage, and steady operation trend can balance, and illustrates that the model constructed by the present invention effectively can be applied to the steady-state analysis of how electric aircraft electrical power system.
Meanwhile, the flow calculation program mean iterative number of time of the present embodiment is 9 times, and average calculation times is 0.11 second, and calculated performance is good.
Above specific embodiments of the invention are described.It is to be appreciated that the present invention is not limited to above-mentioned particular implementation, those skilled in the art can make various distortion or amendment within the scope of the claims, and this does not affect flesh and blood of the present invention.
Claims (10)
1. more than, static models for electric aircraft electrical power system, is characterized in that, comprise the tide model winding diagram of generator model, current transformer model, model of power transmission system, load model, filter and reactive power compensation model and energy storage device model-composing, wherein:
Described generator model is the equivalence to how electric aircraft power system;
Described current transformer model is the equivalence to rectifier and inverter in how electric aircraft electrical power system;
Described model of power transmission system is the equivalence to power circuit in how electric aircraft electrical power system;
Described load model is the equivalence to running load in how electric aircraft electrical power system;
Described filter and reactive power compensation model are the equivalences to the filter in rectifier AC, inverter ac side and DC line in how electric aircraft electrical power system and reactive-load compensator;
Described energy storage device model is the equivalence to how electric aircraft stand-by power supply.
2. the static models of according to claim 1 how electric aircraft electrical power system, is characterized in that, described model of power transmission system adopts substitutional resistance model.
3. the static models of according to claim 1 how electric aircraft electrical power system, is characterized in that, described filter and reactive power compensation model adopt the branch road over the ground of resistance, inductance, electric capacity composition to come equivalent.
4. the static models of according to claim 1 how electric aircraft electrical power system, is characterized in that, described energy storage device model equivalence is DC power supply.
5. the steady-state load flow analytical method of according to claim 1 how electric aircraft electrical power system, it is characterized in that, described static models form aircraft electrical power system power flow algorithm in conjunction with aircraft physical cabling, based on the alternating current-direct current tidal current computing method of land electric power system, consider the feature of DC bus with DC load simultaneously, adopt the direct current equation improved in network equation, to be applicable to the Load flow calculation analysis of how electric aircraft electrical power system, to be got off the plane electric power system tide distribution situation by the different operating mode of MATLAB program calculation.
6. the steady-state load flow analytical method of according to claim 5 how electric aircraft electrical power system, it is characterized in that, when calculating trend distribution under different operating mode, take regulator generator terminal voltage, regulate converter transformer no-load voltage ratio and regulate the mode of converter control angle three kinds of methods combining to determine control strategy, and choose running time the longest running working condition as initial 0 grade.
7. the steady-state load flow analytical method of according to claim 5 how electric aircraft electrical power system, it is characterized in that, described generator model, when not considering the system failure and then not considering that stand-by power supply affects, using generator as balance node, determines voltage magnitude and initial phase.
8. the steady-state load flow analytical method of according to claim 5 how electric aircraft electrical power system, it is characterized in that, according to the control mode of aircraft power system characteristic determination current transformer, inverter is selected determine pilot angle and determine output power mode, and rectifier is selected to determine pilot angle and rated transformation ratio control mode.
9. the steady-state load flow analytical method of according to claim 5 how electric aircraft electrical power system, it is characterized in that, in Load flow calculation, using rectifier and inverter as PQ node, in how electric aircraft electrical power system, directly load is connect on the right side of inverter, for passive system, now, need to install a bulky capacitor additional in the DC side of inverter, adopt voltage source inverter, the reactive power utilizing bulky capacitor to produce is idle to what provide needed for inverter and load, in Load flow calculation, bulky capacitor is thought a part for inverter, ideally output reactive power.
10. the steady-state load flow analytical method of according to claim 5 how electric aircraft electrical power system, is characterized in that, in described load model, all loads equal equivalence in tidal current analysis is PQ node, and its size is determined according to the loading configuration of Different periods.
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| CN106980704A (en) * | 2017-02-13 | 2017-07-25 | 上海交通大学 | Multiple target applied to how electric aircraft power failure load turns for tactful Flexible Optimizing Method |
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| CN112531718A (en) * | 2020-12-21 | 2021-03-19 | 陕西航空电气有限责任公司 | Load flow calculation method suitable for multi-electric-plane power system |
| CN112531718B (en) * | 2020-12-21 | 2024-03-15 | 陕西航空电气有限责任公司 | Tidal current calculation method suitable for multi-electric aircraft power system |
| CN113901590A (en) * | 2021-11-17 | 2022-01-07 | 中国飞机强度研究所 | Large aircraft climate environment laboratory temperature rise and fall transient load analysis method |
| CN113901590B (en) * | 2021-11-17 | 2022-03-01 | 中国飞机强度研究所 | Large aircraft climate environment laboratory temperature rise and fall transient load analysis method |
| CN114462201A (en) * | 2021-12-29 | 2022-05-10 | 中国航天空气动力技术研究院 | Energy flow analysis device and method for power system of solar unmanned aerial vehicle |
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