CN104330129A - Aeroengine force application main pipe oil cup liquid level measuring system - Google Patents
Aeroengine force application main pipe oil cup liquid level measuring system Download PDFInfo
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- CN104330129A CN104330129A CN201410568453.4A CN201410568453A CN104330129A CN 104330129 A CN104330129 A CN 104330129A CN 201410568453 A CN201410568453 A CN 201410568453A CN 104330129 A CN104330129 A CN 104330129A
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- liquid level
- measuring system
- level measuring
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- power lead
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Abstract
The invention provides an aeroengine force application main pipe oil cup liquid level measuring system, which consists of a measuring structure (1), an RS485 bus (2), a 485 data collecting card (3) and a control system (4), wherein the measuring structure (1) is concretely a magnetostrictive liquid level sensor, and the control system (4) comprises a socket (XS1), a first power supply wire (XP1), a second power supply wire (XP2), an industrial liquid crystal display (U10), a machine case (U20), a PXI controller (U21), an RS485 communication card (U22) and an RS485 nine-pin socket (DB9). The aeroengine force application main pipe oil cup liquid level measuring system has the advantages that the anti-jamming performance is improved, the realness and the reliability of the measured data are ensured, the operation is convenient and fast, and the automation degree of equipment is improved.
Description
Technical field
The present invention relates to structural design and the applied technical field of liquid level measuring system, specifically provide a kind of aeroengine thrust augmentation house steward lubricating cup liquid level measuring system.
Background technology
When adopting simulating signal to measure, due to the interference of Large Copacity power supply and motor, considerable influence is produced to measuring-signal, causes measurement data inaccurate.In addition, the afterburning house steward's flow distribution exerciser had needs measurement 48 lubricating cup liquid levels, shows, bring a lot of inconvenience to the analysis of data while traditional digital instrument can not meet 48 liquid levels.
People urgently wish to obtain the excellent aeroengine thrust augmentation house steward lubricating cup liquid level measuring system of a kind of technique effect.
Summary of the invention
The object of this invention is to provide the aeroengine thrust augmentation house steward lubricating cup liquid level measuring system that a kind of technique effect is excellent.Realize the measurement of afterburning house steward's flow distribution exerciser 48 lubricating cup liquid levels; Improve the anti-interference of data acquisition, ensure that measurement data is true and reliable, meanwhile, measurement data is analyzed by computer coordinates, and man machine operation interface shows, and is convenient to keeping records.
The invention provides a kind of aeroengine thrust augmentation house steward lubricating cup liquid level measuring system.Described aeroengine thrust augmentation house steward lubricating cup liquid level measuring system is constructed as follows: measure structure 1, RS485 bus 2,485 data collecting card 3 and control system 4; Described measurement structure 1 is specially magnetostrictive liquid level sensor, and described control system 4 comprises: socket XS1, power lead I XP1, power lead II XP2, industrial liquid crystal display U10, cabinet U20, PXI controller U21, RS485 address card U22, RS485 nine kinds of needles socket DB9; Described power lead I XP1 and power lead II XP2: be connected with socket XS1 respectively, described power lead I XP1 is connected with industrial liquid crystal display U10 phase, power lead II XP2: be connected with RS485 address card U22 with PXI controller U21, described PXI controller U21 and RS485 address card U22 is all positioned at cabinet U20, described RS485 nine kinds of needles socket DB9 is connected with RS485 address card U22 by transmission line, described measurement structure 1 is connected with 485 data collecting cards 3 by RS485 bus 2, measures structure 1 and is connected with RS485 nine kinds of needles socket DB9.The quantity of described magnetostrictive liquid level sensor is 48.
Magnetostrictive liquid level sensor 1 output digit signals of described aeroengine thrust augmentation house steward lubricating cup liquid level measuring system, by 485 bus 2 modes, the output terminal of 48 liquid level sensors is in parallel, namely all A ends connect together, all B ends connect together, all ground connects a bit, is connected on RS485 nine kinds of needles socket DB9, is connected on 485 address card U22 of control system 4 by transmission line.
Described aeroengine thrust augmentation house steward lubricating cup liquid level measuring system, the digital signal of magnetostrictive liquid level sensor 1 is sent to control system 4 by RS485 bus 2, when some lubricating cup liquid levels measured by needs, magnetostrictive liquid level sensor 1 is controlled by PXI controller U21, after magnetostrictive liquid level sensor 1 receives control signal, measure corresponding lubricating cup liquid level, metrical information is fed back to control system 4 by magnetostrictive liquid level sensor 1.
Described aeroengine thrust augmentation house steward lubricating cup liquid level measuring system improves anti-interference, ensures the true and reliable of measurement data; Simple operation, improves the automaticity of equipment.
Accompanying drawing explanation
Below in conjunction with drawings and the embodiments, the present invention is further detailed explanation:
Fig. 1 is aeroengine thrust augmentation house steward lubricating cup liquid level measuring system one-piece construction schematic diagram;
Fig. 2 is control system schematic diagram;
Fig. 3 is for measuring cubic schematic diagram.
Embodiment
Embodiment 1
Aeroengine thrust augmentation house steward lubricating cup liquid level measuring system described in the present embodiment.Described aeroengine thrust augmentation house steward lubricating cup liquid level measuring system is constructed as follows: measure structure 1, RS485 bus 2,485 data collecting card 3 and control system 4; Described measurement structure 1 is specially magnetostrictive liquid level sensor, and described control system 4 comprises: socket XS1, power lead I XP1, power lead II XP2, industrial liquid crystal display U10, cabinet U20, PXI controller U21, RS485 address card U22, RS485 nine kinds of needles socket DB9; Described power lead I XP1 and power lead II XP2: be connected with socket XS1 respectively, described power lead I XP1 is connected with industrial liquid crystal display U10 phase, power lead II XP2: be connected with RS485 address card U22 with PXI controller U21, described PXI controller U21 and RS485 address card U22 is all positioned at cabinet U20, described RS485 nine kinds of needles socket DB9 is connected with RS485 address card U22 by transmission line, described measurement structure 1 is connected with 485 data collecting cards 3 by RS485 bus 2, measures structure 1 and is connected with RS485 nine kinds of needles socket DB9.The quantity of described magnetostrictive liquid level sensor is 48.
Magnetostrictive liquid level sensor 1 output digit signals of described aeroengine thrust augmentation house steward lubricating cup liquid level measuring system, by 485 bus 2 modes, the output terminal of 48 liquid level sensors is in parallel, namely all A ends connect together, all B ends connect together, all ground connects a bit, is connected on RS485 nine kinds of needles socket DB9, is connected on 485 address card U22 of control system 4 by transmission line.
Described aeroengine thrust augmentation house steward lubricating cup liquid level measuring system, the digital signal of magnetostrictive liquid level sensor 1 is sent to control system 4 by RS485 bus 2, when some lubricating cup liquid levels measured by needs, magnetostrictive liquid level sensor 1 is controlled by PXI controller U21, after magnetostrictive liquid level sensor 1 receives control signal, measure corresponding lubricating cup liquid level, metrical information is fed back to control system 4 by magnetostrictive liquid level sensor 1.
Described aeroengine thrust augmentation house steward lubricating cup liquid level measuring system improves anti-interference, ensures the true and reliable of measurement data; Simple operation, improves the automaticity of equipment.
Claims (2)
1. an aeroengine thrust augmentation house steward lubricating cup liquid level measuring system, is characterized in that: described aeroengine thrust augmentation house steward lubricating cup liquid level measuring system is constructed as follows: measure structure (1), RS485 bus (2), 485 data collecting cards (3) and control system (4); Described measurement structure (1) is specially magnetostrictive liquid level sensor, and described control system (4) comprising: socket, power lead I, power lead II, industrial liquid crystal display, cabinet, PXI controller, RS485 address card, RS485 nine kinds of needles socket; Described power lead I is connected with socket respectively with power lead II, described power lead I is connected with industrial liquid crystal display, power lead II is connected with RS485 address card with PXI controller, described PXI controller and RS485 address card are all positioned at cabinet, described RS485 nine kinds of needles socket is connected with RS485 address card by transmission line, described measurement structure (1) is connected with 485 data collecting cards (3) by RS485 bus (2), measures structure (1) and is connected with RS485 nine kinds of needles socket.
2. aeroengine thrust augmentation house steward lubricating cup liquid level measuring system as claimed in claim 1, is characterized in that: the quantity of described magnetostrictive liquid level sensor is 48.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410568453.4A CN104330129A (en) | 2014-10-22 | 2014-10-22 | Aeroengine force application main pipe oil cup liquid level measuring system |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410568453.4A CN104330129A (en) | 2014-10-22 | 2014-10-22 | Aeroengine force application main pipe oil cup liquid level measuring system |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN104330129A true CN104330129A (en) | 2015-02-04 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201410568453.4A Pending CN104330129A (en) | 2014-10-22 | 2014-10-22 | Aeroengine force application main pipe oil cup liquid level measuring system |
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Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN202599469U (en) * | 2012-04-11 | 2012-12-12 | 航天科工深圳（集团）有限公司 | Tunnel water level detecting device |
| CN102928040A (en) * | 2012-11-01 | 2013-02-13 | 江苏科技大学 | Ship-lock multi-channel water level measuring system and filter method thereof |
| WO2013051996A1 (en) * | 2011-10-05 | 2013-04-11 | Scania Cv Ab | Level measurement system and method in a level measurement system |
| CN104091557A (en) * | 2014-07-29 | 2014-10-08 | 中国航空无线电电子研究所 | Display screen test device and method based on image recognition technology |
-
2014
- 2014-10-22 CN CN201410568453.4A patent/CN104330129A/en active Pending
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2013051996A1 (en) * | 2011-10-05 | 2013-04-11 | Scania Cv Ab | Level measurement system and method in a level measurement system |
| CN202599469U (en) * | 2012-04-11 | 2012-12-12 | 航天科工深圳（集团）有限公司 | Tunnel water level detecting device |
| CN102928040A (en) * | 2012-11-01 | 2013-02-13 | 江苏科技大学 | Ship-lock multi-channel water level measuring system and filter method thereof |
| CN104091557A (en) * | 2014-07-29 | 2014-10-08 | 中国航空无线电电子研究所 | Display screen test device and method based on image recognition technology |
Non-Patent Citations (2)
| Title |
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| 刘涛 等: "磁致伸缩飞机油位传感器的电路设计", 《电子测量技术》 * |
| 刘龙飞: "基于PXI总线的温度检测***的设计与实现", 《中国优秀硕士学位论文全文数据库 信息科技辑》 * |
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Application publication date: 20150204 |
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