CN103490779A - Simulator for permanent magnet alternating-current generator - Google Patents
Simulator for permanent magnet alternating-current generator Download PDFInfo
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Abstract
The invention relates to a simulator for a permanent magnet alternating-current generator. The simulator is used for testing hardware of an aero-engine in a loop, and comprises a permanent magnet alternating-current generator model machine module, a permanent magnet alternating-current generator controller module, and a permanent magnet alternating-current generator actuator module. The permanent magnet alternating-current generator model machine module is provided with a permanent magnet alternating-current generator model and a fault model, wherein the permanent magnet alternating-current generator model and the fault model are real-time mathematical models, and the module outputs a first output signal after processing a first input signal. The first output signal and a second input signal serve as the input signals of the permanent magnet alternating-current generator controller module, and the permanent magnet alternating-current generator controller module outputs a first control signal after processing the input signals. The permanent magnet alternating-current generator actuator module outputs a corresponding second output signal according to the first control signal and outputs a feedback signal used for closed-loop control of the permanent magnet alternating-current generator controller module. The second output signal is the output signal, simulated by the simulator for the permanent magnet alternating-current generator, of the permanent magnet alternating-current generator.
Description
Technical field
The present invention relates to a kind of magneto alternator simulator, relate in particular to the magneto alternator simulator of a kind of hardware of controlling for aero-engine full powers limit digital and electronic in the loop simulation test.
Background technology
Modern aeroengine full powers limits digital and electronic is controlled (Full Authority Digital Engine Control:FADEC) and has been realized electric tune, by electronic controller complete engine body the control function and with the task of aircraft collaborative work.For in the seaworthiness demand that meets aero-engine for the power reguirements of electronic controller, the power supply of electronic controller will have redundancy, its redundancy mainly comes from two aspects: the one, the 28V direct current of voltage regulation that aircraft provides; Another one is mounted on engine and by high pressure and turns the alternating current that shaft-driven small-power alternating current generator provides.The latter's alternating current needs change into the 28V direct current of voltage regulation by AC/DC (ac/dc) converter technique in electronic controller inside.The stability of AC/DC power supply is for guaranteeing that the full authority digital electronic control system fail safe is significant, and complete AC/DC module testing is the important step of aeroengine electronic controller software and hardware integration testing comprehensively.
The function of AC/DC module and the test of aspect of performance have two kinds of modes usually: a kind of is to be the AC/DC module for power supply by magneto alternator, by adjusting the power supply situation of AC/DC module under the various operating states of generator output shaft rotating speed simulation aero-engine; Another is to simulate magneto alternator output by programmable current source.Above-mentioned two kinds of methods respectively have pluses and minuses in actual test process.Use magneto alternator to power for AC/DC, can test the power supply state of AC/DC module under any possibility of magneto alternator working speed.But the method need be equipped with a set of complete as shown in Figure 1 drag platform, comprise motor, motor driver, gear box and corresponding Cooling and Lubricator equipment.Drag the platform electric rotor and there is the disalignment error, and motor maximum functional rotating speed is more than 16000rpm, form high frequency noise sources, experimental situation is caused to larger vibrations and noise jamming, limited the fitting limit of testing equipment; In addition, the lubricating fluid that drags platform adopts lubricating oil, has inflammable risk, and fail safe is lower; And motor has moment of inertia, while following the tracks of input speed, can produce tracking error, and then cause the error of magneto alternator output voltage and frequency, affect experimental precision; Moreover, between generator phase fault, winding, short circuit experiment can produce larger short circuit current, can burn the magneto alternator winding under limiting case, cause higher experimental cost and generator turn-to-turn short circuit can't realize dynamic analog, and then can't realize the full test of electronic controller, affect the seaworthiness authorization.Generally speaking, this test mode relies on the cooperating of generator, but generator also exists the R&D cycle longer as the engine accessory kit, and technical conditions wait problem repeatedly.Delay once occur paying, can directly affect the test assignment of power module, and then affect the lead time of controller.
And use programmable current source lower as magneto alternator simulator cost; And, due to programmable current source machinery-free moving component, therefore there is not the noise jamming problem.But the method has following shortcoming in application: lack short circuit and tripper, can't carry out the AC/DC module verification under the magneto alternator malfunction; In addition, due to the device restriction of existing programmable current source, limiting frequency is lower, can't cover all frequency ranges of magneto alternator work.
Therefore, on the basis of existing technology, the function of AC/DC module and the test of aspect of performance still have the space of further raising, for example how by technological innovation, to reach safety and to carry out at low cost the test of AC/DC module.
Summary of the invention
In view of this, understanding according to the above-mentioned technical problem to background technology and existence, it is lower that the present invention aims to provide a kind of cost, and the aero-engine hardware that can comprehensively meet the function of AC/DC module and performance test is at loop magneto alternator (Permanent Magnet Alternator:PMA) simulator.
The present invention proposes a kind of magneto alternator simulator, its for aero-engine hardware at loop-around test, described magneto alternator simulator comprises magneto alternator prototype module, it comprises magneto alternator model and fault model, described magneto alternator model and described fault model are Real time mathematical model, and described magneto alternator prototype module is exported the first output signal after the first input signal is processed, the magneto alternator controller module, it is usingd described the first output signal and the second input signal as its input signal and exports after treatment the first control signal, and magneto alternator executor module, it exports corresponding the second output signal according to described the first control signal, and output simultaneously is for the feedback signal of described magneto alternator controller module closed-loop control, wherein, N2 tach signal and fault mode signal that described the first input signal is exported for the engine mockup be connected with described magneto alternator simulator, described the second input signal is described feedback signal, the output signal that described the second output signal is the described magneto alternator simulator magneto alternator of simulating.
In one embodiment, described magneto alternator prototype module realizes by analog simulation software.With this, this prototype module can be passed through development environment Simulink (simulation software of Mathworks company) and produce virtually in computer, and can be applied to by this Software Create operation the real-time code of test.
In one embodiment, described magneto alternator prototype module can be accepted parameter setting and adjustment.With this, can in test process, according to testing requirement, manually regulate relevant parameter, reach the purpose of purposively being tested.
In one embodiment, described magneto alternator executor module comprises supply unit, and it for exporting direct current by the 220V alternating current after step-down, filtering and rectification; Three-phase inverter, it is the alternating current consistent with magneto alternator frequency to be simulated for the DC inverter by described supply unit output, the output voltage of described three-phase inverter is lower than the output voltage of magneto alternator to be simulated; Three-phase voltage increasing transformer and impedance-matching device, it is promoted to consistent with the output voltage of magneto alternator to be simulated and by its filtering for the output voltage by described three-phase inverter, produce the output impedance consistent with the output impedance of magneto alternator to be simulated simultaneously; The electric current and voltage detecting sensor, it is for output voltage and the electric current of measuring described three-phase voltage increasing transformer and feed back to described magneto alternator controller module using it as described feedback signal; And fault injection relay, it realizes opening circuit of magneto alternator to be simulated and short trouble by solid-state relay.
In one embodiment, described magneto alternator controller module comprises the transducer Acquisition Circuit, and it is for receiving the output signal of described electric current and voltage detecting sensor; Inverter driving circuit, it is for driving described three-phase inverter; And telecommunication circuit, it is for transmitting described the first control signal.With this, the required feedback signal of control module can be collected and be transferred to control module.
In one embodiment, described three-phase inverter is used MOSFET (Metallic Oxide Semiconductor Field Effect Transistor: metal oxide semiconductor field effect tube) as switch element and based on the space vector pulse width modulation principle, realize the output of inversion waveform.
In one embodiment, described three-phase voltage increasing transformer and impedance-matching device comprise power inductance and power resistor and it are series in current circuit.
In one embodiment, described power inductance is Wound-rotor type magnetic screen power inductance, and described power resistor is the metal film noninductive resistor.With this, can realize easily the replacing of those power devices.
In one embodiment, described fault is injected the on off state that relay is series at current circuit and is controlled described fault injection relay by described magneto alternator controller module.
Aero-engine hardware all adopts electronic component to realize the magneto alternator simulation at loop magneto alternator simulator, the machinery-free noise, and environmental friendliness, in the experimental situation higher to environmental requirement; Simultaneously, system configuration is simple, the machinery-free wearing and tearing, and the life-span is longer and reliability is higher; System, without the Cooling and Lubricator parts, has improved maintainability.
The electrical system time constant is less than the mechanical system time constant, simulator calculates output current and voltage by the magneto alternator model, through inversion, boost, impedance matching, by sensor measurement, obtain actual output voltage, electric current, compare both differences and it is sent into to proportional integral (Proportional Integration:PI) controller, forming closed-loop system.Therefore this system response time and dynamic accuracy are much larger than dragging platform.
By the magneto alternator fault model, can realize dragging equipments on stage and damage higher short circuit and the open circuit fault injection experiments of risk, reduced experimental cost.
The magneto alternator simulator adopts program control fully, is easy to realize test automation, has improved the test macro testability; In addition, simulator conveniently is integrated on more massive emulation platform, for example with the aircraft power supply simulator, has worked in coordination with the seaworthiness experiment.
Generally speaking, aero-engine hardware of the present invention can cover all normal and improper operating states of aero-engine magneto alternator at loop magneto alternator simulator, the every input state of simulation AC/DC module, realize electric current that the aero-engine magneto alternator may input speed be exported under conditions at all and the simulation of voltage, there is cable and winding failure injectability simultaneously, and with advantages such as low cost, low noise, high response speeds.
Above characteristic of the present invention and other characteristics are partly set forth embodiment hereinafter clearly.
The accompanying drawing explanation
Read the following detailed description to non-limiting example by the reference accompanying drawing, other features, objects and advantages of the present invention will become more obvious:
Fig. 1 shows the schematic diagram of AC/DC module test device in prior art;
Fig. 2 shows the schematic diagram of an embodiment of the AC/DC module test device with magneto alternator simulator of the present invention; And
Fig. 3 shows the detail of construction of the embodiment shown in Fig. 2.
In the drawings, run through different diagrams, same or similar Reference numeral means same or analogous module (device).
Embodiment
Fig. 1 shows the schematic diagram of AC/DC module test device in prior art.Wherein, drag platform 120 and comprise motor 122, motor driver 121, gear box 123 and corresponding Cooling and Lubricator equipment 124 and 125, and magneto alternator winding 126 and 127.Can produce larger short circuit current during short circuit experiment between its simulation generator phase fault, winding, can burn the magneto alternator winding under limiting case, cause higher experimental cost and generator turn-to-turn short circuit can't realize dynamic analog, and then can't realize the full test of electronic controller; In addition, during motor work, the high-speed rotary change of team forms high frequency noise sources, and experimental situation is caused to larger vibrations and noise jamming, has limited the fitting limit of testing equipment.In order effectively to address the above problem, the present invention proposes technical scheme as shown in Figure 2, drag platform 120 in the magneto alternator simulator alternate figures 1 proposed with the present invention, and other two parts, i.e. all not variations of engine mockup 110 and AC/DC module 130.
Fig. 2 shows the schematic diagram of an embodiment of the AC/DC module test device with magneto alternator simulator of the present invention.The aero-engine magneto alternator simulator 220 that the present invention proposes, it receives N2 tach signal and the fault mode signal of engine mockup 110 outputs, according to generator real-time model result of calculation, inject relay by power component and fault, the simulation magneto alternator normally reaches malfunction output, thereby realizes the full test to the AC/DC module.
Particularly, above-mentioned aero-engine magneto alternator simulator 220 consists of the following components:
1) prototype 221, its operation magneto alternator Real time mathematical model, the load signal that the engine mockup 110 of take is exported N2 rotating speeds, fault mode and transducer 226 (a), 226 (b) and 226 (c) feedback EEC module 230 is input, obtain as calculated magneto alternator to be simulated and normally reach electric current, voltage and the frequency values under abnormality, as control command, input to magneto alternator emulator controller 223; This prototype is supported the Simulink model, but and the generation of the RTW of implementation model (Real-time Workshop:Mathworks company software) code, compiling, link, download and operation.
2) step-down, filtering and rectifying device 222 (a), 222 (b), it generates low-voltage DC by the electric main of input after step-down rectifier and filtering, is the three-phase inverter power supply.
3) the magneto alternator emulator controller 223, and it is realized, and the output of magneto alternator simulator is controlled, the feedback signal collection.Output control part comprises two-way three-phase converter and fault injection Control; The feedback signal collection comprises impedance matching network (S25 (a), S25 (b)) output current and voltage measurement and collection.
4) three-phase inverter 224 (a), 224 (b), three-phase inverter is converted to alternating current by the direct current of step-down, filtering and rectifying device 222 (a), 222 (b) output.Above-mentioned alternating current output frequency is consistent with magneto alternator frequency to be simulated, and output voltage is less than magneto alternator voltage to be simulated.
5) three-phase voltage increasing transformer/impedance matching network 225 (a), 225 (b), the three-phase voltage increasing transformer improves inverter output voltage, realizes the inverter output filtering; Impedance matching network is that removable resistance and inductance are in series, for mating output impedance, consistent with true magneto alternator.
6) electric current and voltage sensor 226 (a), 226 (b), 226 (c), phase current, phase voltage that it measures three-phase transformer output, provide AC/DC module load condition feedback.
7) fault is injected relay 227 (a), 227 (b), by solid-state relay, realizes that magneto alternator opens circuit, short trouble.
Aero-engine hardware is at loop magneto alternator simulator 220, by the modeling magneto alternator under all thrust ratings of engine, under the excess revolutions state, electric current, voltage and frequency output under faults itself (short circuit between phase fault, turn-to-turn short circuit, winding) state; Realize power stage by magneto alternator analog controller 223, three-phase inverter 224 (a), 224 (b), step-up transformer 225 (a), 225 (b); The series network formed by inductance and resistance is realized the output impedance coupling, makes simulator output impedance consistent with the impedance of magneto alternator winding; Measure output voltage and electric current by transducer 226 (a), 226 (b), 226 (c), feed back in magneto alternator emulator controller 223 and compare with the model calculation, and eliminate static difference by the PI algorithm, make value of feedback and model calculate output valve consistent, form closed-loop system, realize aero-engine magneto alternator analog functuion.
Fig. 3 shows the detail of construction of the embodiment shown in Fig. 2.More specifically, the modules shown in Fig. 2 can be realized by following virtual module or electronic devices and components.
Wherein, magneto alternator prototype 321, its major function has: the magneto alternator Real time mathematical model calculates, the magneto alternator fault mode is stored, engine mockup machine command signal receives, feedback signal receives, control command information sends.System hardware composition aspect: preferred TI TMS320F28335DSP (Digital Signal Processor: digital signal processor) as master chip, resolve the magneto alternator Mathematical Modeling; Preferably ethernet physical layer and protocol layer chip, receive engine mockup machine command signal; Preferably spi bus receives as the current/voltage feedback signal and control command transmission physical layer; The nonvolatile storage that preferably in sheet, Flash stores as fault mode.And step-down, filtering and rectifying device 323 (a), 323 (b), its function is to provide constant low-voltage dc power supply for the inversion three-phase inverter, as important control assembly, magneto alternator emulator controller 322, the user-programmable gate array) and MCU (S322 (c)) (Microcontroller Unit: micro controller unit) form it is responsible for, and bus driver, performer drive, the feedback signal collection, and this controller is by mosfet driver 322 (a), 322 (b), FPGA (322 (d)) (Field Programmable Gate Array:.The preferred STM32F205 chip of MCU, built-in analog to digital conversion circuit, gather feedback current and feedback voltage signal; The external power driving circuit of MCU, control fault and inject relay 327 (a) and 327 (b) switch, realizes that short circuit and open circuit fault inject; MCU is responsible for bus communication, receives magneto alternator prototype control command, and the feedback load state information.FPGA receives frequency and the information of voltage from MCU, and (Space Vector Pulse Width Modulation: space vector pulse width modulation) waveform, the control mosfet driver is realized the control of three-phase inverter to be converted into SVPMW.
In addition, three-phase inverter 324 (a), 324 (b) can adopt six MOSFET chips as the power drive chip, by controlling each chip switching sequence, realize invert function.Step-up transformer 325 (a), 325 (b) boost to magneto alternator actual output voltage to be simulated by lower inverter output voltage; The step-up transformer coil is equivalent to inductance, but the higher harmonic components in the filtering inverter output voltage; Transformer has isolation features, can simulate magneto alternator winding isolation characteristic.Every equal series resistance and inductance exported mutually of impedance matching network 326 (a), 326 (b), the resistance that often is in series is consistent with magneto alternator to be simulated with transformer phase resistance value sum, and series inductance is consistent with the every phase inductance of magneto alternator to be simulated with the every phase inductance sum of transformer.Above-mentioned resistance and inductance form impedance matching network, consistent with true magneto alternator output impedance.And current detecting 328 (a), 328 (b), 328 (c) circuit are by the collection of isolating difference amplifying circuit and amplify the poor detection that realizes output current of resistance both end voltage.Simultaneously, voltage detecting 329 (a), 329 (b), 329 (c) circuit by divider resistance measure every phase output voltage, through isolation with realize the detection of output voltage after amplifying.Finally, fault is injected relay 327 (a), 327 (b) by solid-state relay, realizes that magneto alternator opens circuit, short-circuit fault simulation.
Those skilled in the art will be understood that above-described embodiment is all exemplary and nonrestrictive.The different technologies feature occurred in different embodiment can be combined, to obtain beneficial effect.Those skilled in the art, on the basis of research accompanying drawing, specification and claims, will be understood that and realize the embodiment of other variations of disclosed embodiment.In claims, term " comprises " does not get rid of other devices or step; " one " does not get rid of a plurality of; Term " first ", " second " are for indicating title but not for meaning any specific order.Any Reference numeral in claim all should not be understood to the restriction to protection range.Some technical characterictic appears in different dependent claims and does not mean that and these technical characterictics can not be combined to obtain beneficial effect.This patent covers literal all devices and the product of going up or falling into the scope of claims in doctrine of equivalents.
Claims (9)
1. a magneto alternator simulator, it is for aero-engine hardware at loop-around test, and described magneto alternator simulator comprises:
Magneto alternator prototype module, it comprises magneto alternator model and fault model, described magneto alternator model and described fault model are Real time mathematical model, and described magneto alternator prototype module is exported the first output signal after the first input signal is processed;
The magneto alternator controller module, it is usingd described the first output signal and the second input signal as its input signal and exports after treatment the first control signal; And
The magneto alternator executor module, it exports corresponding the second output signal according to described the first control signal, and output simultaneously is for the feedback signal of described magneto alternator controller module closed-loop control;
Wherein, N2 tach signal and fault mode signal that described the first input signal is exported for the engine mockup be connected with described magneto alternator simulator, described the second input signal is described feedback signal, the output signal that described the second output signal is the described magneto alternator simulator magneto alternator of simulating.
2. magneto alternator simulator according to claim 1, is characterized in that, described magneto alternator prototype module realizes by analog simulation software.
3. magneto alternator simulator according to claim 1, is characterized in that, described magneto alternator prototype module can be accepted parameter setting and adjustment.
According to claim 1 to the described magneto alternator simulator of any one in-3, it is characterized in that, described magneto alternator executor module comprises:
Supply unit, it for exporting direct current by the 220V alternating current after step-down, filtering and rectification;
Three-phase inverter, it is the alternating current consistent with magneto alternator frequency to be simulated for the DC inverter by described supply unit output, the output voltage of described three-phase inverter is lower than the output voltage of magneto alternator to be simulated;
Three-phase voltage increasing transformer and impedance-matching device, it is promoted to consistent with the output voltage of magneto alternator to be simulated and by its filtering for the output voltage by described three-phase inverter, produce the output impedance consistent with the output impedance of magneto alternator to be simulated simultaneously;
The electric current and voltage detecting sensor, it is for output voltage and the electric current of measuring described three-phase voltage increasing transformer and feed back to described magneto alternator controller module using it as described feedback signal; And
Fault is injected relay, and it realizes opening circuit of magneto alternator to be simulated and short trouble by solid-state relay.
5. magneto alternator simulator according to claim 4, is characterized in that, described magneto alternator controller module comprises:
The transducer Acquisition Circuit, it is for receiving the output signal of described electric current and voltage detecting sensor;
Inverter driving circuit, it is for driving described three-phase inverter; And
Telecommunication circuit, it is for transmitting described the first control signal.
6. magneto alternator simulator according to claim 4, is characterized in that, described three-phase inverter is used MOSFET to realize the output of inversion waveform as switch element and based on the space vector pulse width modulation principle.
7. magneto alternator simulator according to claim 4, is characterized in that, described three-phase voltage increasing transformer and impedance-matching device comprise power inductance and power resistor and it is series in current circuit.
8. magneto alternator simulator according to claim 4, is characterized in that, described power inductance is Wound-rotor type magnetic screen power inductance, and described power resistor is the metal film noninductive resistor.
9. magneto alternator simulator according to claim 4, is characterized in that, described fault is injected relay and is series at current circuit and controls by described magneto alternator controller module the on off state that described fault is injected relay.
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| CN201210193031.4A CN103490779B (en) | 2012-06-12 | 2012-06-12 | Simulator for permanent magnet alternating-current generator |
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Cited By (6)
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| CN104932486A (en) * | 2015-06-05 | 2015-09-23 | 中国人民解放军61330部队 | AC permanent magnet servo motor electronic simulator |
| CN105717461A (en) * | 2014-12-05 | 2016-06-29 | 中国航空工业集团公司航空动力控制系统研究所 | Rack power supply fault simulation testing device |
| CN105717908A (en) * | 2014-12-05 | 2016-06-29 | 中国航空工业集团公司航空动力控制系统研究所 | Test signal fault simulation device for engine control system stand |
| CN106124810A (en) * | 2016-08-17 | 2016-11-16 | 中国航空工业集团公司西安飞行自动控制研究所 | A kind of emulator simulating PMG alternating current power supply |
| CN107870269A (en) * | 2016-09-26 | 2018-04-03 | 维谛技术有限公司 | A kind of generating set analogue means |
| CN108446493A (en) * | 2018-03-20 | 2018-08-24 | 北京润科通用技术有限公司 | A kind of power of motor grade emulation mode and device |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| CN108446493A (en) * | 2018-03-20 | 2018-08-24 | 北京润科通用技术有限公司 | A kind of power of motor grade emulation mode and device |
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|---|---|
| CN103490779B (en) | 2016-12-14 |
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