CN202433505U - Automatic detection system of airplane start generator - Google Patents
Automatic detection system of airplane start generator Download PDFInfo
- Publication number
- CN202433505U CN202433505U CN2012200307177U CN201220030717U CN202433505U CN 202433505 U CN202433505 U CN 202433505U CN 2012200307177 U CN2012200307177 U CN 2012200307177U CN 201220030717 U CN201220030717 U CN 201220030717U CN 202433505 U CN202433505 U CN 202433505U
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- generator
- checkout system
- automatic checkout
- modules dragged
- temperature sensor
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Abstract
The utility model relates to an automatic detection system of an airplane start generator. The automatic detection system is used for detecting a start generator (5) and comprises a man-machine interface (1), a control module (2), a measuring module (3) and a drag module (4), wherein the man-machine interface (1), the measuring module (3) and the drag module (4) are respectively connected with the control module (2), the measuring module (3) is respectively connected with the drag module (4) and the start generator (5), and the drag module (4) is connected with the start generator (5). Compared with the prior art, the automatic detection system of the airplane start generator has the advantages of high stability, good safety, convenience in operation, wide application scope and the like.
Description
Technical field
The utility model relates to a kind of aircraft starter-generator detection technique, especially relates to a kind of automatic checkout system of aircraft starter-generator.
Background technology
Various aircraft is dispatching from the factory preceding or after flight a period of time, all need all kinds of airborne equipments that assembled on the aircraft detected, and with the working condition of checking relevant device device, guarantees the flight safety of aircraft.
The power supply of aerogenerator each airborne equipment during as aircraft flight, its serviceability are the important factor that guarantees flight safety.The test of generator mainly comprises its output voltage, output current, field voltage, exciting current etc., also will test the pressure regulating performance of its supporting pressure regulator simultaneously.
The method of testing of generator normally drives the generator rotary electrification by dragging motor, and generator output is connected to testing table and carries out parameter testing.Testing table also need connect the generating that utility appliance such as pressure regulator, contactor assist to accomplish generator.Testing table adopts traditional logic control, utilizes the mode of switch pilot relay to control measurement circuit.All kinds of voltameter test generator parameters are installed on the testing table panel.Conventional test methodologies has following defectives:
The first, because test parameter is many, control relation is many, and the quantity of all kinds of test instrumentations of installing on the testing table, Test Switchboard, CS is all many.For example CS just comprises that start-stop, the start-stop of generator fan, the unequally loaded of start-stop, the cooling blower of dragging motor connect or the like.Therefore the whole operation platform is bigger, inconvenience concerning the operator.
The second, because the complicacy of control relation just has requirement for the order in the test process,, can exert an influence, even damage generator testing table and generator self in case test process is disorderly.Therefore the tester generally is that the operation of working specification limit is seen on the limit, not only is easy to generate misoperation, also influences testing efficiency greatly.
The 3rd, present test macro can only be tested a kind of generator of model, if test the generator of other models, corresponding measurement circuit can be different, is a very thing of difficulty and will change the testing table internal wiring.
The utility model content
The purpose of the utility model is exactly the automatic checkout system that the aircraft starter-generator that a kind of stability is high, security is good, easy to operate, applied widely is provided for the defective that overcomes above-mentioned prior art existence.
The purpose of the utility model can realize through following technical scheme:
A kind of automatic checkout system of aircraft starter-generator; This automatic checkout system is used to detect starter-generator; It is characterized in that described automatic checkout system comprises man-machine interface, control module, measurement module and modules dragged, described man-machine interface, measurement module, modules draggedly be connected with control module respectively; Described measurement module is connected with modules dragged, generator respectively, described modules draggedly be connected with generator.
Described man-machine interface is a touch-screen.
Described control module comprises PLC, Data Receiving unit and communication unit, and described PLC is connected with Data Receiving unit, communication unit respectively, and described Data Receiving unit is connected with measurement module, and described communication unit is connected with modules dragged.
Described Data Receiving unit comprises analog quantity input subelement and temperature sensor input subelement.
Described communication unit is 485 communication buses.
Described measurement module comprises electric parameters transducer, temperature sensor and speed pickup; Described electric parameters transducer is connected with generator, analog quantity input subelement respectively; Described temperature sensor is connected with modules dragged, temperature sensor input subelement respectively, and described speed pickup is connected with modules dragged, analog quantity input subelement respectively.
Described modules dragged frequency converter and the dragging motor that connects successively that comprise, described frequency converter is connected with PLC, and described dragging motor is connected with temperature sensor, speed pickup respectively.
This automatic checkout system also comprises cooling blower, and this cooling blower is connected with PLC (22).
Compared with prior art, the utlity model has following advantage:
1, stability is high, controls with PLC, can reduce the quantity of auxiliary reclay; Design, installation, wiring workload are significantly reduced; Failure rate in the middle of also having reduced simultaneously, PLC has adopted a series of hardware and software interference protection measures, has improved the antijamming capability of equipment.
2, security is good, and PLC adopts ladder diagram as programming language, and its circuit symbol and expression way and relay circuit schematic diagram are similar; Programming is easily understood; Program through PLC is carried out sequential control, can realize automatic measuring ability, the generation of maloperation in the time of also can effectively preventing manual test.
3, easy to operate, adopt touch-screen as man-machine interface, switch and instrument a large amount of on the panel have been saved in operation and show all more intuitively simultaneously, can make the testing table miniaturization.
4, applied widely, can test the generator of multiple model, when changing, control relation can realize with crossing change PLC program.
Description of drawings
Fig. 1 is the structural representation of the utility model.
Embodiment
Below in conjunction with accompanying drawing and specific embodiment the utility model is elaborated.
Embodiment
As shown in Figure 1; A kind of automatic checkout system of aircraft starter-generator; This automatic checkout system is used to detect starter-generator 5, and described automatic checkout system comprises man-machine interface 1, control module 2, measurement module 3 and modules dragged 4, and described man-machine interface 1, measurement module 3, modules dragged 4 are connected with control module 2 respectively; Described measurement module 3 is connected with modules dragged 4, generator 5 respectively, and described modules dragged 4 are connected with generator 5.Described man-machine interface 1 is a touch-screen.
Described control module 2 comprises PLC22, Data Receiving unit 21 and communication unit 23; Described PLC22 is connected with Data Receiving unit 21, communication unit 23 respectively; Described Data Receiving unit 21 is connected with measurement module 3, and described communication unit 23 is connected with modules dragged 4.Described Data Receiving unit 21 comprises analog quantity input subelement 211 and temperature sensor input subelement 222.Described communication unit 23 is 485 communication buses.
Described measurement module 3 comprises electric parameters transducer 31, temperature sensor 32 and speed pickup 33; Described electric parameters transducer 31 is connected with generator 5, analog quantity input subelement 211 respectively; Described temperature sensor 32 is connected with modules dragged 4, temperature sensor input subelement 222 respectively, and described speed pickup 33 is imported subelement 211 and is connected with modules dragged 4, analog quantity respectively.Described modules dragged 4 comprise the frequency converter 41 and dragging motor 42 that connects successively, and described frequency converter 41 is connected with PLC22, and described dragging motor 42 is connected with temperature sensor 32, speed pickup 33 respectively.
The test process of the utility model carries out sequential control by PLC according to internal processes.After the startup, at first PLC controls to frequency converter, each cooling blower power supply.PLC makes the dragging motor rotation through 485 Communication Control frequency converter timings then, drives the generator rotary electrification then.The output of generator is read the analog quantity load module of giving PLC after the conversion through electric parameters transducer, shows on touch-screen through calculating the back.After generator speed arrives the appointment rotating speed, keep the constant speed rotation.Control to the generator loading by PLC again, the load capacity of test generator, loading can add different loads in different rotating speed.Load and finish back reduction motor speed, make generator generation outage gradually.
Test process also can be accomplished through manual operation, and operation all realizes through pushing touch-screen.In the test procedure each item defencive function can be set, when manual operation, prevent maloperation.
Claims (8)
1. the automatic checkout system of an aircraft starter-generator; This automatic checkout system is used to detect starter-generator (5); It is characterized in that; Described automatic checkout system comprises man-machine interface (1), control module (2), measurement module (3) and modules dragged (4); Described man-machine interface (1), measurement module (3), modules dragged (4) are connected with control module (2) respectively, and described measurement module (3) is connected with modules dragged (4), generator (5) respectively, and described modules dragged (4) are connected with generator (5).
2. the automatic checkout system of a kind of aircraft starter-generator according to claim 1 is characterized in that, described man-machine interface (1) is a touch-screen.
3. the automatic checkout system of a kind of aircraft starter-generator according to claim 1; It is characterized in that; Described control module (2) comprises PLC (22), Data Receiving unit (21) and communication unit (23); Described PLC (22) is connected with Data Receiving unit (21), communication unit (23) respectively, and described Data Receiving unit (21) is connected with measurement module (3), and described communication unit (23) is connected with modules dragged (4).
4. the automatic checkout system of a kind of aircraft starter-generator according to claim 3 is characterized in that, described Data Receiving unit (21) comprises analog quantity input subelement (211) and temperature sensor input subelement (222).
5. the automatic checkout system of a kind of aircraft starter-generator according to claim 3 is characterized in that, described communication unit (23) is 485 communication buses.
6. the automatic checkout system of a kind of aircraft starter-generator according to claim 4; It is characterized in that; Described measurement module (3) comprises electric parameters transducer (31), temperature sensor (32) and speed pickup (33); Described electric parameters transducer (31) is connected with generator (5), analog quantity input subelement (211) respectively; Described temperature sensor (32) is connected with modules dragged (4), temperature sensor input subelement (222) respectively, and described speed pickup (33) is connected with modules dragged (4), analog quantity input subelement (211) respectively.
7. the automatic checkout system of a kind of aircraft starter-generator according to claim 6; It is characterized in that; Described modules dragged (4) comprise frequency converter (41) and the dragging motor (42) that connects successively; Described frequency converter (41) is connected with PLC (22), and described dragging motor (42) is connected with temperature sensor (32), speed pickup (33) respectively.
8. the automatic checkout system of a kind of aircraft starter-generator according to claim 3 is characterized in that, this automatic checkout system also comprises cooling blower, and this cooling blower is connected with PLC (22).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2012200307177U CN202433505U (en) | 2012-01-31 | 2012-01-31 | Automatic detection system of airplane start generator |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2012200307177U CN202433505U (en) | 2012-01-31 | 2012-01-31 | Automatic detection system of airplane start generator |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN202433505U true CN202433505U (en) | 2012-09-12 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN2012200307177U Expired - Lifetime CN202433505U (en) | 2012-01-31 | 2012-01-31 | Automatic detection system of airplane start generator |
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| CN (1) | CN202433505U (en) |
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103197244A (en) * | 2013-03-26 | 2013-07-10 | 广州飞机维修工程有限公司 | General testing system of airplane direct-current generator |
| CN103558561A (en) * | 2013-10-22 | 2014-02-05 | 中国商用飞机有限责任公司 | Aircraft engine N2 rotation speed simulator |
| CN106526480A (en) * | 2016-11-11 | 2017-03-22 | 凌云科技集团有限责任公司 | Combined transmission generator test system and output frequency analysis test method |
| CN108449000A (en) * | 2018-04-04 | 2018-08-24 | 中国商用飞机有限责任公司北京民用飞机技术研究中心 | A kind of aircraft starting-generating system analog architectures and hardware design schematic circuit |
| CN109342943A (en) * | 2018-11-05 | 2019-02-15 | 长沙源婕科技有限公司 | A kind of generator starting failure detection method |
| CN110161411A (en) * | 2019-06-28 | 2019-08-23 | 贵州航天林泉电机有限公司 | A kind of Motor Measuring System based on PLC |
-
2012
- 2012-01-31 CN CN2012200307177U patent/CN202433505U/en not_active Expired - Lifetime
Cited By (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103197244A (en) * | 2013-03-26 | 2013-07-10 | 广州飞机维修工程有限公司 | General testing system of airplane direct-current generator |
| CN103558561A (en) * | 2013-10-22 | 2014-02-05 | 中国商用飞机有限责任公司 | Aircraft engine N2 rotation speed simulator |
| CN103558561B (en) * | 2013-10-22 | 2016-05-18 | 中国商用飞机有限责任公司 | Aircraft engine N2 rotating speed analogue means |
| CN106526480A (en) * | 2016-11-11 | 2017-03-22 | 凌云科技集团有限责任公司 | Combined transmission generator test system and output frequency analysis test method |
| CN106526480B (en) * | 2016-11-11 | 2019-08-30 | 凌云科技集团有限责任公司 | A kind of combination driven generator test macro and output frequency analyze test method |
| CN108449000A (en) * | 2018-04-04 | 2018-08-24 | 中国商用飞机有限责任公司北京民用飞机技术研究中心 | A kind of aircraft starting-generating system analog architectures and hardware design schematic circuit |
| CN109342943A (en) * | 2018-11-05 | 2019-02-15 | 长沙源婕科技有限公司 | A kind of generator starting failure detection method |
| CN110161411A (en) * | 2019-06-28 | 2019-08-23 | 贵州航天林泉电机有限公司 | A kind of Motor Measuring System based on PLC |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| ASS | Succession or assignment of patent right |
Owner name: SHANGHAI HAIYING MACHINERY FACTORY Free format text: FORMER OWNER: SHANGHAI KAIDIKE AVIATION ENGINEERING TECHNOLOGY CO.,LTD. Effective date: 20140625 Owner name: SHANGHAI KAIDIKE AVIATION ENGINEERING TECHNOLOGY C Effective date: 20140625 |
|
| C41 | Transfer of patent application or patent right or utility model | ||
| C53 | Correction of patent of invention or patent application | ||
| CB03 | Change of inventor or designer information |
Inventor after: Yan Zhengming Inventor after: Gao Zheng Inventor after: Chen Zhiquan Inventor after: Cheng Xiaochuang Inventor after: Jin Weijie Inventor before: Yan Zhengming Inventor before: Cheng Xiaochuang Inventor before: Jin Weijie |
|
| COR | Change of bibliographic data |
Free format text: CORRECT: INVENTOR; FROM: YAN ZHENGMING CHENG XIAOCHUANG JIN WEIJIE TO: YAN ZHENGMING GAO ZHENG CHEN ZHIQUAN CHENG XIAOCHUANG JIN WEIJIE Free format text: CORRECT: ADDRESS; FROM: 200443 BAOSHAN, SHANGHAI TO: 200436 ZHABEI, SHANGHAI |
|
| TR01 | Transfer of patent right |
Effective date of registration: 20140625 Address after: 200436 No. 3127 middle market, Shanghai Patentee after: SHANGHAI HAIYING MACHINERY PLANT Patentee after: Shanghai Kaidike Aviation Engineering Technology Co., Ltd. Address before: 200443 Shanghai city Baoshan District Dakang Road No. 100 Patentee before: Shanghai Kaidike Aviation Engineering Technology Co., Ltd. |
|
| CX01 | Expiry of patent term | ||
| CX01 | Expiry of patent term |
Granted publication date: 20120912 |