CN103699114A - Controller and control method for debugging tests of aviation fuel regulating device - Google Patents
Controller and control method for debugging tests of aviation fuel regulating device Download PDFInfo
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Abstract
The invention provides a controller and a control method for debugging tests of an aviation fuel regulating device. The controller 5 consists of a power supply unit 1, a signal conditioning unit 2, a main control unit 3, an output driving unit 4 and a host computer 6, wherein the power supply unit 1 realizes the power supply to the main control unit 3, the output driving unit 4 and the signal conditioning unit 2, the power supply input of the controller 7 is 220 V AC (alternating current), a power supply conversion unit is realized by a designed printed circuit board, and three kinds of power supplies are respectively related, and include simulation 24V DC (direct current) adopted by the main control unit 3, digital 24V DC adopted by the output driving unit 4 and +/-15V DC adopted by the signal conditioning unit 2. The controller and the method provided by the invention have the advantages that a power supply integration and false grounding technology is adopted for realizing power supply to inside elements of the fuel regulating device and the controller, in the use process, users only need to provide 220V AC, the test ground requirements do not exist, and the use is convenient.
Description
Technical field
Patent of the present invention belongs to Aeroengine control technology field, particularly aeromotor fuel oil regulating device debugging test control technology.
Background technology
Along with improving constantly of aero-engine performance, engine control system has also been proposed to more and more higher requirement.In decades, there is deep variation in aeroengine control system, and main manifestations is to be controlled to digital and electronic and controlled development by mechanical hydraulic-pressure type.In 20 th century later, aeroengine control system has revolutionary variation most and by hydraulic mechanical type, controls the development of controlling to digital electronic beyond doubt.As far back as the 40-50 age in 20th century, engine just once used electronic controller to control, and electronic controller is at that time analog, used the large-scale elements such as electron tube, and reliability is very poor.Subsequently, due to semi-conductive appearance, electronic controller quality, volume are greatly reduced, Digital Logic control program can increase the dirigibility of control in addition, can make digital control system have decision-making and logic judgement.Be accompanied by the development of digital computer technique, digital electronic controller progressively obtains practical application in aeromotor.
Fuel flow, as the major control amount of aeroengine control, has determined state and the performance of aeromotor, and fuel flow regulating device is to realize the crucial topworks that fuel flow is controlled.Follow the widespread use of digital electronic controller in aeromotor, the debugging test of various fuel oil regulating device is operated in aeromotor development and seems extremely crucial.
According to public technology document, patent documentation, external very few about the relevant report of aeromotor fuel oil regulating device debug controller.And the domestic several producers that are engaged in aeromotor fuel oil regulating device design, processing not for fuel oil regulating device debug controller be particularly applicable to many types of product versatility debug controller carry out corresponding design, development.Corresponding controller, when carrying out production debugging test, must be built for the fuel oil regulating device of different model by certain aeromotor fuel oil regulating device testing department, can test; And, build controller due to the analog control mode adopting based on discrete component, cause controlling volume larger, use very flexible; In process of the test, comprise more manual operation operation, cause that test accuracy is poor, test findings obtaining means falls behind, the test period is long.
Summary of the invention
The technical problem to be solved in the present invention:
What face that testing laboratory must be for different model is that fuel oil regulating device is built the present situation that corresponding controller can be tested, and, original control is owing to having adopted in design the reasons such as a large amount of discrete components, integrated level be relatively low, each type controller volume is larger, in addition, substantially in process of the test, adopt manually operated mode, test efficiency, test findings obtain and processing aspect all there is obvious deficiency.
Technical scheme of the present invention:
For above-mentioned technical matters, by designing universal controller, raising controller integrated level and the automaticity of many types of fuel oil regulating device, can strengthen controller function, improve test efficiency.Adopt the technology of Programmable control technology and integrated circuit, the controller that design volume is little, function is strong; Adopt modular technology, can improve the dirigibility of controller function expansion; Adopt good man-machine interface and software engineering, can reduce controller and use difficulty.
Controller for Aviation Fuel regulating device debugging test, is characterized in that: described controller 5 comprises power supply unit 1, signal condition unit 2, main control unit 3, output driver element 4 and host computer 6, wherein:
Power supply unit 1 input 220VAC, through power supply unit 1 converter ic output simulation 24VDCV, digital 24VDCV, ± 15VDCV, respectively as the working power of signal condition unit 2, main control unit 3, output driver element 4;
Signal condition unit 2 is responsible for producing fuel regulator 7 metering valve angular displacement sensor 10 pumping signals, is gathered valve angular displacement sensor 10 output signals and nurse one's health as the d. c. voltage signal relevant to physics angular displacement, is transferred to main control unit 3;
Main control unit 3 comprises CPU module, digital signal output modules, collection of simulant signal module, pulse-width signal output module and other supplementary modules; Wherein, fuel oil regulating device 7 metering valve angular displacement sensor 10 signals of processing through signal condition unit 2 that CPU module synthesis collection analogue collection module receives and fuel oil regulating device 7 each point fuel pressure signals, host computer 6 command signals, through control algorithm and logic judgement, produce control signal; The control signal that CPU module arithmetic produces outputs to output driver element 4 and implements to control;
Output driver element 4 receives the control signal of main control unit 3, after power amplification, outputs to fuel oil regulating device and controls; Output driver element 4 adopts solid-state relay M22 as power amplification element, output terminal design inductive load electric discharge continuous current circuit M23;
For the control method of Aviation Fuel regulating device debugging test, specifically control step as follows:
Control method is from step S01, and in this step, main control unit 3, by the simulating signal from signal condition unit 2 and fuel oil regulating device 7 collecting, carries out the conversion of engineering value;
Step S02 resolves host computer 6 command signals that receive, and instruction comprises control mode instruction, fuel oil regulating device maximum fuel flow WFMAX, equilibrium point dutycycle BP parameter information, the given instruction WFG of fuel flow;
Step S03 is according to the control mode instruction judgement control mode of step S02 and enter the algorithm of open loop control or closed-loop control;
Step S04, S05 are respectively open-loop control method, closed loop control method, wherein,
Step S04 is controlled in open loop: according to the fuel oil regulating device maximum fuel flow WFMAX of the given instruction WFG of the fuel flow of step S02, step S02, provide the pwm control signal PWMQ=WFG/WFMAX*100 of fuel oil regulating device 7 high-speed electromagnetic valves 9;
Closed-loop control step S05: the fuel flow signal WF exporting according to the given instruction WFG of the fuel flow of step S02, fuel flow metering device 3 is as feedback signal, calculate deviation signal DWF=WFG-WF, input as PI control algolithm 8, and according to the fuel oil regulating device equilibrium point dutyfactor value BP of step S02, after PI computing, export the pwm control signal PWMQ of fuel oil regulating device 7 high-speed electromagnetic valves 9, the control signal PWMQ producing is input to fuel oil regulating device 7 high-speed electromagnetic valves 9, and the PI control algolithm 8 of employing is as follows:
DWF=WFG-WF;
SWF=SWF+DWF;
PWMQ=BP+kp*DWFA+ki*SWFA;
Step S06 is output processing and control signal output; The control letter of output comprises that fuel oil regulating device 7 switches valve and opens/close control signal, accelerates the pwm control signal that valve opened/closed control signal, fuel oil regulating device 7 high-speed electromagnetic valves 9, wherein:
Switching valve opens/closes and control letter logic and be: if the given instruction WFG of fuel flow be greater than 3 and host computer 6 send engine oil instruction, open and switch valve;
Acceleration valve opens/close to control believes that logic is: if host computer 6 sends, valve instruction is accelerated in unlatching and host computer 6 sends engine oil instruction, and switching valve is accelerated in unlatching;
The pwm control signal of fuel oil regulating device 7 high-speed electromagnetic valves 9 comes from step S04, S05.
Beneficial effect of the present invention:
(1) adopt modular technology to concentrate and measure and control, improve dirigibility and the versatility of controller
Adopt modular design method, the extendability of controller and versatility strengthen, and for different model testpieces, the difference of controller function demand are all solved in software.With respect to existing employing discrete component method for designing fuel oil regulating device debugging control system, this is invented related controller reliability, test efficiency, extendability, adaptive capacity and is improved;
(2) adopt digital control technology, improve system control accuracy
Adopt digital control technology, by Fast Ethernet, user control interface is connected with controller, reduced system monitoring precision and the interference problem in the conversion of simulating signal, transmitting procedure, brought, improved system accuracy;
(3) power supply integration
Product is used novel employing power supply integration and virtual earth technology to controller and the power supply of fuel oil regulating device inner member, only needs user that 220V alternating current is provided during use, and not test ground requirement is easy to use.
Accompanying drawing explanation
Fig. 1 is fuel oil regulating device debug controller structural representation;
Fig. 2 is power supply unit structural representation;
Fig. 3 is structure of driving unit schematic diagram;
Fig. 4 is control method process flow diagram;
Fig. 5 is fuel flow loop control theory figure.
Embodiment
Below with reference to accompanying drawing, specific embodiment of the invention method is elaborated.
As shown in Figure 1, controller 5 is comprised of power supply unit 1, signal condition unit 2, main control unit 3, output driver element 4 and host computer 6.Power supply unit 1 is realized the power supply of main control unit 3, output driver element 4, signal condition unit 2, and controller 5 power supplys are input as 220VAC.Power supply unit 1 is realized by the printed circuit board designing, and relates to main control unit 3 use simulation 24VDC, the digital 24VDC of output driver element 4 use, signal condition unit 2 use ± 15VDC tri-class power supplys.
As shown in Figure 2 (a) shows, simulation 24VDC, digital 24VDC all adopt step-down transformer M01, rectifier bridge stack M02,7824 three terminal regulator M03 and filtering circuit M04 to form, in order to prevent the interference of digital power to analog power, in design, two class power supplys are taked to physical isolation.As shown in Fig. 2 (b), ± 15VDC consists of dual output step-down transformer M11, rectifier bridge stack M12, M15,7815 three terminal regulator M13, M16 and filtering circuit M14, M17, in design, the 15V of the 0V of filtering circuit M14 output terminal and filtering circuit M17 output terminal is linked up, as the 0V output terminal O2 of ± 15VDC ,+15V output terminal is that O1 ,-15V output terminal are O3.
Metering valve angular displacement sensor 10 pumping signals are responsible for producing in signal condition unit 2, collection metering valve angular displacement sensor 10 is exported and nursed one's health as the d. c. voltage signal relevant to physics angular displacement, for main control unit 3 acquisition process.Signal condition of the present invention unit 2 adopts the U.S. AD698 of AD company chip to produce the ac-excited signal of 400Hz, the 10V of 10 requirements of metering valve angular displacement sensor, according to AD698 databook, for generation of the key components type selecting of pumping signal, be respectively: C
1=0.1[μ F], R
1=1.5[k Ω], C
2=C
3=C
4=2.5 μ F, after this pumping signal, same frequency AC signal under sensor output terminal output corresponding angle, this signal is output dc voltage signal after AD698 rectification, in order to get galvanic current, press signal, modulate circuit output terminal has designed wave filter, d. c. voltage signal filtering to AD698 output is processed, filter input signal is the d. c. voltage signal of AD698 conditioning output, through 10k Ω resistance, electric capacity 0.1uF forms resistance capacity filter, after wave filter, adopt LM158 budget Amplifier Design voltage follower, after the processing of output, voltage signal enters main control unit 3.
As shown in Figure 4, output driver element 4 adopts solid-state relay M22 as power amplification element, from the command signal of main control unit 3, enters power amplifier M22 after bleeder circuit M21.Command signal after amplification continues and flows back to road M23 through output, and output is controlled electric signal to fuel oil regulating device 7 respective execution mechanisms.Wherein, bleeder circuit M21 adopts two 5k Ω resistance series connection dividing potential drops; Inductive load continues and flows return circuit module M23 employing afterflow diode and 100k Ω resistance formation.
Main control unit 3 comprises CPU module, digital signal output modules, collection of simulant signal module, pulse-width signal output module and other supplementary modules.Wherein, fuel oil regulating device 7 metering valve angular displacement sensor 10 signals of processing through signal condition unit 2 that CPU module synthesis collection analogue collection module receives and fuel oil regulating device each point fuel pressure signal, host computer 6 command signals, produce control signal through control program computing.The control signal that CPU module arithmetic produces, is implemented to control to output driver element 4 through pulse-width signal output module, digital signal output modules.
As shown in Figure 5, by a process flow diagram, this controller control method flow process is described below,
Described flow process is from step S01, and in this step, main control unit 3, by the simulating signal from signal condition unit 2 and fuel oil regulating device 7 collecting, carries out the conversion of engineering value;
Step S02 resolves host computer 6 command signals that receive, and these instructions comprise control mode instruction, fuel oil regulating device 7 maximum fuel flow WFMAX, equilibrium point dutycycle BP parameter information, the given instruction WFG of fuel flow;
Step S03 is according to the control mode instruction judgement control mode of step S02 and enter corresponding open loop or closed loop control algorithm;
Step S04, S05 are respectively open-loop control method, closed loop control method, wherein,
(step S04) controlled in open loop: according to the fuel oil regulating device 7 maximum fuel flow WFMAX of the given instruction WFG of the fuel flow of step S02, step S02, provide the pwm control signal PWMQ=WFG/WFMAX*100 of fuel oil regulating device 7 high-speed electromagnetic valves 9;
Closed-loop control (step S05): the fuel flow signal WF exporting according to the given instruction WFG of the fuel flow of step S02, fuel flow metering valve 10 is as feedback signal, calculate deviation signal DWF=WFG-WF, input as PI control algolithm 8, and according to the fuel oil regulating device 7 equilibrium point dutyfactor value BP of step S02, after PI computing, export the pwm control signal PWMQ of fuel oil regulating device 7 high-speed electromagnetic valves 9, the control signal PWMQ producing is input to fuel oil regulating device 7 high-speed electromagnetic valves 9, and the PI control algolithm of employing is as follows:
DWF=WFG-WF;
SWF=SWF+DWF;
PWMQ=BP+0.5*DWFA+0.03*SWFA;
Step S06 is output processing and control signal output.The control signal of output mainly comprises that fuel oil regulating device 7 switches valve and opens/close control signal, accelerates the pwm control signal that valve opened/closed control signal, fuel oil regulating device 7 high-speed electromagnetic valves 9, wherein:
Switching valve opens/closes and control letter logic and be: if the given instruction WFG of fuel flow be greater than 3 and host computer 6 send engine oil instruction, open and switch valve;
Acceleration valve opens/close to control believes that logic is: if host computer sends, valve instruction is accelerated in unlatching and host computer 6 sends engine oil instruction, and valve is switched in acceleration;
The pwm control signal of fuel oil regulating device 7 high-speed electromagnetic valves 9 comes from step S04, S05.
Claims (2)
1. for the controller of Aviation Fuel regulating device debugging test, it is characterized in that: described controller (5) comprises power supply unit (1), signal condition unit (2), main control unit (3), output driver element (4) and host computer (6), wherein:
Power supply unit (1) input 220VAC, through power supply unit (1) converter ic output simulation 24VDCV, digital 24VDCV, ± 15VDCV, respectively as the working power of signal condition unit (2), main control unit (3), output driver element (4);
Signal condition unit (2) is responsible for producing fuel regulator (7) metering valve angular displacement sensor (10) pumping signal, is gathered valve angular displacement sensor (10) output signal and nurse one's health as the d. c. voltage signal relevant to physics angular displacement, is transferred to main control unit (3);
Main control unit (3) comprises CPU module, digital signal output modules, collection of simulant signal module, pulse-width signal output module and other supplementary modules; Wherein, fuel oil regulating device (7) metering valve angular displacement sensor (10) signal of processing through signal condition unit (2) that CPU module synthesis collection analogue collection module receives and fuel oil regulating device (7) each point fuel pressure signal, host computer (6) command signal, through control algorithm and logic judgement, produce control signal; The control signal that CPU module arithmetic produces outputs to output driver element (4) and implements to control;
Output driver element (4) receives the control signal of main control unit (3), after power amplification, outputs to fuel oil regulating device and controls; Output driver element (4) adopts solid-state relay (M22) as power amplification element, output terminal design inductive load electric discharge continuous current circuit (M23);
Host computer (6) carries out communication by Ethernet and main control unit (3), descending to main control unit (3) sending controling instruction, state parameter and the control information of the relevant fuel oil regulating device (7) that uplink receiving main control unit (3) sends; Host computer (6) is responsible for data recording simultaneously.
2. for the control method of Aviation Fuel regulating device debugging test, it is characterized in that, specifically control step as follows:
Control method is from step S01, and in this step, main control unit (3), by the simulating signal from signal condition unit (2) and fuel oil regulating device (7) collecting, carries out the conversion of engineering value;
Step S02 resolves the host computer receiving (6) command signal, and instruction comprises control mode instruction, fuel oil regulating device maximum fuel flow WFMAX, equilibrium point dutycycle BP parameter information, the given instruction WFG of fuel flow;
Step S03 is according to the control mode instruction judgement control mode of step S02 and enter the algorithm of open loop control or closed-loop control;
Step S04, S05 are respectively open-loop control method, closed loop control method, wherein,
Step S04 is controlled in open loop: according to the fuel oil regulating device maximum fuel flow WFMAX of the given instruction WFG of the fuel flow of step S02, step S02, provide the pwm control signal PWMQ=WFG/WFMAX*100 of fuel oil regulating device (7) high-speed electromagnetic valve (9);
Closed-loop control step S05: according to the given instruction WFG of the fuel flow of step S02, the fuel flow signal WF of fuel flow metering device (3) output is as feedback signal, calculate deviation signal DWF=WFG-WF, input as PI control algolithm (8), and according to the fuel oil regulating device equilibrium point dutyfactor value BP of step S02, after PI computing, export the pwm control signal PWMQ of fuel oil regulating device (7) high-speed electromagnetic valve (9), the control signal PWMQ producing is input to fuel oil regulating device (7) high-speed electromagnetic valve (9), the PI control algolithm (8) adopting is as follows:
DWF=WFG-WF;
SWF=SWF+DWF;
PWMQ=BP+kp*DWFA+ki*SWFA;
Step S06 is output processing and control signal output; The control letter of output comprises that fuel oil regulating device (7) switches valve and opens/close control signal, accelerates the pwm control signal that valve opened/closed control signal, fuel oil regulating device (7) high-speed electromagnetic valve (9), wherein:
Switching valve opens/closes and control letter logic and be: if the given instruction WFG of fuel flow be greater than 3 and host computer (6) send engine oil instruction, open and switch valve;
Acceleration valve opens/close to control believes that logic is: if host computer (6) sends, valve instruction is accelerated in unlatching and host computer (6) sends engine oil instruction, and switching valve is accelerated in unlatching;
The pwm control signal of fuel oil regulating device (7) high-speed electromagnetic valve (9) comes from step S04, S05.
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Cited By (11)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN104314696A (en) * | 2014-08-26 | 2015-01-28 | 北京动力机械研究所 | Fuel metering valve control system and fuel regulator |
| CN104481705A (en) * | 2014-11-05 | 2015-04-01 | 沈阳黎明航空发动机(集团)有限责任公司 | Apparatus for controlling angle of aeroengine fuel-oil regulator by using steel rope |
| CN105784376A (en) * | 2016-03-01 | 2016-07-20 | 西安航空动力股份有限公司 | Fault eliminating method for performance decay of aero-engine fuel regulator |
| CN106444722A (en) * | 2016-11-18 | 2017-02-22 | 贵州航天电器股份有限公司 | Simulation system for electrical performance of fuel regulator |
| CN106762978A (en) * | 2016-11-29 | 2017-05-31 | 四川凌峰航空液压机械有限公司 | Anti-interference test retractable actuating cylinder class testing stand signal test system |
| CN109269398A (en) * | 2018-10-16 | 2019-01-25 | 北京动力机械研究所 | A kind of digitlization angular displacement sensor signal conditioning circuit design method |
| CN109958537A (en) * | 2019-04-04 | 2019-07-02 | 中国科学院工程热物理研究所 | The metering valve with displacement self-checking function based on capacitance sensor |
| CN110778572A (en) * | 2019-10-30 | 2020-02-11 | 中国航发控制***研究所 | Reliability and service life testing device for hydraulic valve matching parts |
| CN111208797A (en) * | 2019-12-20 | 2020-05-29 | 四川大学 | Integrated tester for electronic regulator of aircraft aeroengine |
| CN113311277A (en) * | 2021-06-25 | 2021-08-27 | 贵阳永青仪电科技有限公司 | Engineering machinery display and control integrated hardware and software function test system |
| CN113759809A (en) * | 2021-09-29 | 2021-12-07 | 中国航发动力股份有限公司 | Calibration instrument for calibrating adjusting mechanism and calibrating method of adjusting mechanism |
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| CN105784376A (en) * | 2016-03-01 | 2016-07-20 | 西安航空动力股份有限公司 | Fault eliminating method for performance decay of aero-engine fuel regulator |
| CN106444722A (en) * | 2016-11-18 | 2017-02-22 | 贵州航天电器股份有限公司 | Simulation system for electrical performance of fuel regulator |
| CN106762978A (en) * | 2016-11-29 | 2017-05-31 | 四川凌峰航空液压机械有限公司 | Anti-interference test retractable actuating cylinder class testing stand signal test system |
| CN109269398A (en) * | 2018-10-16 | 2019-01-25 | 北京动力机械研究所 | A kind of digitlization angular displacement sensor signal conditioning circuit design method |
| CN109958537A (en) * | 2019-04-04 | 2019-07-02 | 中国科学院工程热物理研究所 | The metering valve with displacement self-checking function based on capacitance sensor |
| CN109958537B (en) * | 2019-04-04 | 2024-05-07 | 中国科学院工程热物理研究所 | Metering valve with displacement self-detection function based on capacitance sensor |
| CN110778572A (en) * | 2019-10-30 | 2020-02-11 | 中国航发控制***研究所 | Reliability and service life testing device for hydraulic valve matching parts |
| CN111208797A (en) * | 2019-12-20 | 2020-05-29 | 四川大学 | Integrated tester for electronic regulator of aircraft aeroengine |
| CN113311277A (en) * | 2021-06-25 | 2021-08-27 | 贵阳永青仪电科技有限公司 | Engineering machinery display and control integrated hardware and software function test system |
| CN113759809A (en) * | 2021-09-29 | 2021-12-07 | 中国航发动力股份有限公司 | Calibration instrument for calibrating adjusting mechanism and calibrating method of adjusting mechanism |
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Application publication date: 20140402 |