CN105223893A - Aeromotor ground stand trystate supervisory system - Google Patents
Aeromotor ground stand trystate supervisory system Download PDFInfo
- Publication number
- CN105223893A CN105223893A CN201510735786.6A CN201510735786A CN105223893A CN 105223893 A CN105223893 A CN 105223893A CN 201510735786 A CN201510735786 A CN 201510735786A CN 105223893 A CN105223893 A CN 105223893A
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- module
- data
- serial ports
- aeromotor
- electronic controller
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Classifications
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- G—PHYSICS
- G05—CONTROLLING; REGULATING
- G05B—CONTROL OR REGULATING SYSTEMS IN GENERAL; FUNCTIONAL ELEMENTS OF SUCH SYSTEMS; MONITORING OR TESTING ARRANGEMENTS FOR SUCH SYSTEMS OR ELEMENTS
- G05B19/00—Programme-control systems
- G05B19/02—Programme-control systems electric
- G05B19/04—Programme control other than numerical control, i.e. in sequence controllers or logic controllers
- G05B19/048—Monitoring; Safety
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M15/00—Testing of engines
- G01M15/04—Testing internal-combustion engines
- G01M15/05—Testing internal-combustion engines by combined monitoring of two or more different engine parameters
-
- G—PHYSICS
- G08—SIGNALLING
- G08C—TRANSMISSION SYSTEMS FOR MEASURED VALUES, CONTROL OR SIMILAR SIGNALS
- G08C19/00—Electric signal transmission systems
Abstract
The present invention relates to a kind of aeromotor ground stand based on labview test supervisory system, for carrying out condition monitoring when aeromotor bench test, comprise the also display in real time of setup control parameter, sending controling instruction, accepting state parameter, preserve experimental data and also analyze.Comprising data acquisition unit and the computing machine with labview Software Development Platform.Do not lose number when this system utilizes serial port communication method to ensure high speed acquisition and transmission data, reliable control is implemented to engine, and can preserve experimental data and analyze.The present invention may be used for condition monitoring and performance evaluation etc. in aeromotor predevelopment phase ground run process, is the aeromotor ground run supervisory system that current function is more complete.
Description
Technical field
The present invention designs a kind of Monitor Computer Control System, is specifically related to a kind of aeromotor ground stand trystate supervisory system based on labview, for carrying out status monitoring and control when aeromotor bench test.
Background technology
A kind of basic skills of test to be people by test understanding objective world the obtain qualitative or quantitative information of experimental subjects.In contemporary science and technology evolution, test job is the guarantee of Technology for Modern Equipment system performance and quality.Along with aero-engine performance improves constantly, the parameter obtained in Engine pedestal trial run gets more and more, to the precision of observing and controlling and the rate request of observing and controlling also more and more higher, the method for traditional hand-kept firing test data can not meet modern aeroengine requirement of experiment.
Summary of the invention
The present invention is directed to above-mentioned problems of the prior art, a kind of aeromotor ground stand trystate supervisory system based on labview is provided, solves hand-kept in prior art and cannot meet the problem of aeromotor requirement of experiment.
The technical scheme that the present invention adopts is:
Aeromotor ground stand trystate supervisory system, comprising: on-site data gathering end, electronic controller, data transmission module and host computer; Described on-site data gathering end comprises at least one speed probe, at least one temperature sensor, at least one pressure transducer, wherein said speed probe detects engine rotor rotating speed, temperature sensor detects engine inlets intake air temperature and jet pipe outlet temperature, and pressure transducer detects pneumatic plant inlet and outlet pressure; Described electronic controller comprises communication interface, transducer, power module and digital signal processor DSP, and communication interface provides instruction and service data for supervisory control comuter; Transducer provides rotating speed, voltage, current signal to communication interface; Each module that power module is electronic controller provides power supply; Digital signal processor DSP comprises speed setting and closed loop control function, according to power setting rotating speed of target, and with relay protective scheme; The digital signal that electronic controller sends by data transmission module sends host computer to, and described host computer is provided with serial ports configuration module, serial ports sending module, serial ports read module, data storage module, data readback module, frequency-domain analysis module; Wherein serial ports configuration module is used for arranging serial ports number and baud rate; Wherein the steering order of engine start, parking, setting speed is issued electronic controller by serial ports sending module, and the setting of control system correlation parameter, and according to user's input selection automatic mode or manual mode; Serial ports read module receives the state parameter that electronic controller returns, and shows in real time; Experimental data is preserved with set form by data storage module; Data readback module ejects playback of data in interface to graphically; Frequency-domain analysis module adopts the frequency of three point method test signal.
All adopt in described serial ports sending module and serial ports read module data head with and the communication protocol that verify, judge that whether data correct by data head verification, incorrect then reception or transmission again; If data head is correct, then by and verification judged whether packet loss phenomenon, if having, then again receive or transmission.
Described data transmission module is that RS-422 turns USB data transmission module, when being connected with electronic controller, adopts ADM2582E chip to carry out signal conversion.
Described temperature sensor adopts K type thermopair, and K type thermopair is pyroelectric temperature sensitive element, and the electromotive force exported during normal work is 0-50mv.
Described communication interface adopts RS-422 interface standard.
Compared with prior art, advantage of the present invention is:
A, serial communication protocol provided by the invention, ensure communication stability, can prevent data packetloss phenomenon.
B, the present invention adopt RS-422 to turn USB data transmission line, can directly be connected with notebook computer.
C, may be used for obtaining aeromotor bench test drive parameter more, precision and the speed of observing and controlling are high.
D, directly can carry out manual mode on host computer or automatic mode carries out status monitoring and control.
E, three point method is utilized to carry out signal frequency measurement online.
Accompanying drawing explanation
Fig. 1 is overall design structural drawing of the present invention.
Fig. 2 is electronic controller theory diagram.
Fig. 3 is serial communication protocol process flow diagram.
Fig. 4 is ipc monitor process flow diagram.
Embodiment
Below in conjunction with accompanying drawing, the specific embodiment of the present invention is elaborated, thus more explicit defining is made to protection scope of the present invention.
Fig. 1 gives the overall construction drawing of aeromotor ground stand trystate supervisory system of the present invention, this system comprise connect in turn on-site data gathering end, electronic controller, there is the computing machine of labview development platform as host computer.
On-site data gathering end comprises at least one speed probe, at least one temperature sensor, at least one pressure transducer, wherein said speed probe detects engine rotor rotating speed, temperature sensor detects engine inlets intake air temperature and jet pipe outlet temperature, and pressure transducer detects pneumatic plant inlet and outlet pressure.
Fig. 2 gives the theory diagram of electronic controller, and this electronic controller, with communication interface, provides instruction and service data for supervisory control comuter, and communication interface adopts RS-422 interface standard; With transducer, provide rotating speed, voltage, current signal to signaling interface, transducer communication interface adopts RS-422 standard; With power module, each module for electronic controller provides the power supply of 28V and 5V; With digital signal processor DSP, comprise speed setting and closed loop control function.Speed setting, i.e. power planning, according to power setting rotating speed of target, and with relay protective scheme.
Fig. 3 is serial communication protocol process flow diagram, the communication protocol that serial ports sends and all adopts data head to add and verify in read module, judges that whether data are correct, incorrect, re-execute by data head verification; When data head is correct, then by and verification judged whether packet loss phenomenon, if having, then Resurvey or transmission.
Fig. 4 is ipc monitor process flow diagram, and host computer comprises serial ports configuration module, serial ports sending module, serial ports read module, data storage module, data readback module, frequency-domain analysis module; Wherein serial ports configuration module is used for arranging serial ports number and baud rate; Wherein the steering orders such as engine start, parking, setting speed are issued electronic controller by serial ports sending module, and the setting of control system correlation parameter, and can according to user's input selection automatic mode or manual mode; Serial ports read module receives the state parameter that electronic controller returns, and shows in real time; Experimental data is preserved with set form by data storage module; Data readback module ejects playback of data in interface to graphically; Frequency-domain analysis module adopts the frequency of three point method test signal.
Described data transmission module is that RS-422 turns USB data transmission module, when being connected with electronic controller, adopts ADM2582E chip to carry out signal conversion.
Described temperature sensor adopts K type thermopair, and K type thermopair is pyroelectric temperature sensitive element, and the electromotive force exported during normal work is 0-50mv.
Claims (5)
1. aeromotor ground stand trystate supervisory system, is characterized in that comprising: on-site data gathering end, electronic controller, data transmission module and host computer; Described on-site data gathering end comprises at least one speed probe, at least one temperature sensor, at least one pressure transducer, wherein said speed probe detects engine rotor rotating speed, temperature sensor detects engine inlets intake air temperature and jet pipe outlet temperature, and pressure transducer detects pneumatic plant inlet and outlet pressure; Described electronic controller comprises communication interface, transducer, power module and digital signal processor DSP, and communication interface provides instruction and service data for supervisory control comuter; Transducer provides rotating speed, voltage, current signal to communication interface; Each module that power module is electronic controller provides power supply; Digital signal processor DSP comprises speed setting and closed loop control function, according to power setting rotating speed of target, and with relay protective scheme; The digital signal that electronic controller sends by data transmission module sends host computer to, and described host computer is provided with serial ports configuration module, serial ports sending module, serial ports read module, data storage module, data readback module, frequency-domain analysis module; Wherein serial ports configuration module is used for arranging serial ports number and baud rate; Wherein the steering order of engine start, parking, setting speed is issued electronic controller by serial ports sending module, and the setting of control system correlation parameter, and according to user's input selection automatic mode or manual mode; Serial ports read module receives the state parameter that electronic controller returns, and shows in real time; Experimental data is preserved with set form by data storage module; Data readback module ejects playback of data in interface to graphically; Frequency-domain analysis module adopts the frequency of three point method test signal.
2. aeromotor ground stand trystate supervisory system as claimed in claim 1, it is characterized in that all adopting in described serial ports sending module and serial ports read module data head with and the communication protocol that verifies, judge that whether data are correct by data head verification, incorrect then reception or transmission again; If data head is correct, then by and verification judged whether packet loss phenomenon, if having, then again receive or transmission.
3. aeromotor ground stand trystate supervisory system as claimed in claim 1, is characterized in that described data transmission module is that RS-422 turns USB data transmission module, when being connected with electronic controller, adopts ADM2582E chip to carry out signal conversion.
4. aeromotor ground stand trystate supervisory system as claimed in claim 1, it is characterized in that described temperature sensor adopts K type thermopair, K type thermopair is pyroelectric temperature sensitive element, and the electromotive force exported during normal work is 0-50mv.
5. aeromotor ground stand trystate supervisory system as claimed in claim 1, is characterized in that described communication interface adopts RS-422 interface standard.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
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| CN201510735786.6A CN105223893A (en) | 2015-11-02 | 2015-11-02 | Aeromotor ground stand trystate supervisory system |
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| Application Number | Priority Date | Filing Date | Title |
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| CN201510735786.6A CN105223893A (en) | 2015-11-02 | 2015-11-02 | Aeromotor ground stand trystate supervisory system |
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| CN201510735786.6A Pending CN105223893A (en) | 2015-11-02 | 2015-11-02 | Aeromotor ground stand trystate supervisory system |
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Cited By (13)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105739488A (en) * | 2016-04-07 | 2016-07-06 | 中国南方航空工业(集团)有限公司 | Outfield test maintenance method and device of aviation engine |
| CN106198034A (en) * | 2016-06-27 | 2016-12-07 | 大连海事大学 | A kind of rotary punching Compressor test system |
| CN107219077A (en) * | 2017-05-27 | 2017-09-29 | 中国航发湖南动力机械研究所 | Method, apparatus and system for engine testsand control |
| CN107421745A (en) * | 2017-05-31 | 2017-12-01 | 中国人民解放军空军工程大学 | A kind of engine automation ground detection system and method based on engine data logger |
| CN109283868A (en) * | 2018-08-24 | 2019-01-29 | 江西洪都航空工业集团有限责任公司 | A method of it reissues and starts bicycle and motorcycle and cutoff command |
| CN109338290A (en) * | 2018-11-02 | 2019-02-15 | 中国航空工业集团公司上海航空测控技术研究所 | A kind of film temperature sensor for aero engine turbine blades |
| CN110044634A (en) * | 2019-04-01 | 2019-07-23 | 绵阳小巨人动力设备有限公司 | A kind of micro turbojet engine state and performance monitor apparatus |
| CN110535852A (en) * | 2019-08-28 | 2019-12-03 | 象限空间（天津）科技有限公司 | A kind of General Aviation piston engine TT&C system |
| CN111272434A (en) * | 2018-12-04 | 2020-06-12 | 中发天信(北京)航空发动机科技股份有限公司 | Distributed aeroengine test measurement and control system |
| CN111273782A (en) * | 2020-03-24 | 2020-06-12 | 江苏无国界航空技术有限公司 | Virtual and real interaction system and method for aircraft engine |
| CN111693292A (en) * | 2020-06-16 | 2020-09-22 | 成都航利航空科技有限责任公司 | Detection system and method for engine gas turbine starter |
| CN111999064A (en) * | 2020-06-30 | 2020-11-27 | 中国航发南方工业有限公司 | Engine health monitoring unit |
| CN114545805A (en) * | 2020-11-24 | 2022-05-27 | 中国航发商用航空发动机有限责任公司 | Method, device and system for online adjustment of control parameters of aircraft engine |
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Cited By (19)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105739488B (en) * | 2016-04-07 | 2018-11-27 | 中国南方航空工业(集团)有限公司 | The field testing maintaining method and device of aero-engine |
| CN105739488A (en) * | 2016-04-07 | 2016-07-06 | 中国南方航空工业(集团)有限公司 | Outfield test maintenance method and device of aviation engine |
| CN106198034A (en) * | 2016-06-27 | 2016-12-07 | 大连海事大学 | A kind of rotary punching Compressor test system |
| CN106198034B (en) * | 2016-06-27 | 2018-05-25 | 大连海事大学 | A kind of rotary punching Compressor test system |
| CN107219077A (en) * | 2017-05-27 | 2017-09-29 | 中国航发湖南动力机械研究所 | Method, apparatus and system for engine testsand control |
| CN107421745B (en) * | 2017-05-31 | 2019-05-14 | 中国人民解放军空军工程大学 | A kind of engine automation ground detection system and method based on engine data logger |
| CN107421745A (en) * | 2017-05-31 | 2017-12-01 | 中国人民解放军空军工程大学 | A kind of engine automation ground detection system and method based on engine data logger |
| CN109283868B (en) * | 2018-08-24 | 2020-11-24 | 江西洪都航空工业集团有限责任公司 | Method for reissuing slow vehicle and stop instruction of engine |
| CN109283868A (en) * | 2018-08-24 | 2019-01-29 | 江西洪都航空工业集团有限责任公司 | A method of it reissues and starts bicycle and motorcycle and cutoff command |
| CN109338290A (en) * | 2018-11-02 | 2019-02-15 | 中国航空工业集团公司上海航空测控技术研究所 | A kind of film temperature sensor for aero engine turbine blades |
| CN111272434A (en) * | 2018-12-04 | 2020-06-12 | 中发天信(北京)航空发动机科技股份有限公司 | Distributed aeroengine test measurement and control system |
| CN110044634A (en) * | 2019-04-01 | 2019-07-23 | 绵阳小巨人动力设备有限公司 | A kind of micro turbojet engine state and performance monitor apparatus |
| CN110535852A (en) * | 2019-08-28 | 2019-12-03 | 象限空间（天津）科技有限公司 | A kind of General Aviation piston engine TT&C system |
| CN111273782A (en) * | 2020-03-24 | 2020-06-12 | 江苏无国界航空技术有限公司 | Virtual and real interaction system and method for aircraft engine |
| CN111273782B (en) * | 2020-03-24 | 2023-06-20 | 江苏无国界航空技术有限公司 | Virtual and real interaction system and method for aero-engine |
| CN111693292A (en) * | 2020-06-16 | 2020-09-22 | 成都航利航空科技有限责任公司 | Detection system and method for engine gas turbine starter |
| CN111999064A (en) * | 2020-06-30 | 2020-11-27 | 中国航发南方工业有限公司 | Engine health monitoring unit |
| CN114545805A (en) * | 2020-11-24 | 2022-05-27 | 中国航发商用航空发动机有限责任公司 | Method, device and system for online adjustment of control parameters of aircraft engine |
| CN114545805B (en) * | 2020-11-24 | 2023-08-04 | 中国航发商用航空发动机有限责任公司 | Method, device and system for on-line adjustment of aero-engine control parameters |
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Application publication date: 20160106 |