CN212433290U - Multi-parameter testing device for aviation starting power generation system - Google Patents
Multi-parameter testing device for aviation starting power generation system Download PDFInfo
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- CN212433290U CN212433290U CN201922478880.4U CN201922478880U CN212433290U CN 212433290 U CN212433290 U CN 212433290U CN 201922478880 U CN201922478880 U CN 201922478880U CN 212433290 U CN212433290 U CN 212433290U
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Abstract
The utility model provides an aviation start power generation system multi-parameter testing arrangement which characterized in that: the upper computer controls the PC to perform man-machine interaction and final data processing, display and record, and sends instructions to the lower computer to realize the control of the whole system and the acquisition of related parameter data; the lower computer is communicated with all instruments through a Modbus to complete control and data acquisition, and all the instruments are connected to the lower computer through the Modbus. The defects that the existing device can only measure a single parameter or a few parameters, the manual recording generates errors and the abnormal processing cannot be responded in time are overcome.
Description
Technical Field
The utility model relates to an aviation starting power generation system multi-parameter testing arrangement can test and the device of record to each spare part electrical property parameter among the aviation starting power generation system as required for the spare part tests the device of overhauing among the aviation starting power generation system.
Background
At present, the known devices for testing and overhauling the components of the aviation starting power generation system adopt a discrete multimeter or a gauge head to carry out single-performance parameter testing and manually record. This kind of mode troublesome poeration, artifical reading produces the error easily moreover, appears when unusual to detecting or test procedure by it, and manual operation can not in time make a response, causes secondary damage to system or part easily, and this brings a great deal of inconvenience for the detection and maintenance.
SUMMERY OF THE UTILITY MODEL
In order to overcome can only single parameter or few parameter measurement of current device, artifical record produces the error and can not in time respond not enough of abnormal handling, the utility model provides an aviation starting power generation system multi-parameter testing arrangement, the device can all required test performance parameters of automatic test record to can set up each parameter normal range according to actual conditions, can carry out corresponding action immediately when the system detects the parameter anomaly, realize the quick response operation.
The utility model provides a technical scheme that its technical problem adopted is: the upper computer industrial control PC machine performs man-machine interaction and data final processing display and recording, and sends an instruction to the lower computer to realize the control of the whole system and the acquisition of related parameter data; the lower computer is communicated with each instrument through a Modbus bus to complete control and data acquisition. Wherein each instrument is connected to the lower computer by a Modbus bus.
The utility model has the advantages that: all required test performance parameters can be automatically tested and recorded, normal ranges of all parameters can be set according to actual conditions, corresponding actions can be immediately executed when the system detects that the parameters are abnormal, quick response operation is realized, intelligent detection is easily realized by computer control, and the control is simple and quick.
Drawings
Fig. 1 is a block diagram of the working principle of the present invention.
Detailed Description
The present invention will be described in detail with reference to fig. 1 by way of specific examples. According to the multi-parameter testing device for the aviation starting power generation system, the upper computer PC1 is realized by adopting an industrial control host, is used for finally processing and displaying a human-computer interaction interface and data, is connected and communicated with the lower computer MCU 2, and realizes instruction operation and data uploading. The lower computer is communicated with each instrument 3 through a Modbus bus to complete control and data acquisition. In the implementation of the current example, 5 blocks of the direct current voltmeter and 5 blocks of the direct current ammeter are respectively used for testing the input voltage and current, the power generation output voltage and current, the starting input voltage and current, the voltage and current of the balance winding and the excitation voltage and current of the system; and simultaneously, the device is also connected with instruments and meters required by different tests, such as an alternating current voltage ammeter, an alternating current parameter instrument, a direct current power supply, a direct current load, an alternating current load, a torque and rotating speed tester, an exciter, a dragging device and the like.
When the device is used, the upper computer realizes man-machine interaction and communicates with the lower computer to realize control and data acquisition; and each instrument for collection is connected to the lower computer through a Modbus. The host computer controls the lower computer and communicates with each instrument through a Modbus to realize control and data acquisition.
Description of reference numerals:
1 upper computer PC
2 lower computer MCU
3 instruments and meters.
Claims (1)
1. The utility model provides an aviation start power generation system multi-parameter testing arrangement which characterized in that: the upper computer controls the PC to perform man-machine interaction and final data processing, display and record, and sends instructions to the lower computer to realize the control of the whole system and the acquisition of related parameter data; the lower computer is communicated with all instruments through a Modbus to complete control and data acquisition, and all the instruments are connected to the lower computer through the Modbus.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201922478880.4U CN212433290U (en) | 2019-12-31 | 2019-12-31 | Multi-parameter testing device for aviation starting power generation system |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201922478880.4U CN212433290U (en) | 2019-12-31 | 2019-12-31 | Multi-parameter testing device for aviation starting power generation system |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN212433290U true CN212433290U (en) | 2021-01-29 |
Family
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201922478880.4U Active CN212433290U (en) | 2019-12-31 | 2019-12-31 | Multi-parameter testing device for aviation starting power generation system |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN212433290U (en) |
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2019
- 2019-12-31 CN CN201922478880.4U patent/CN212433290U/en active Active
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