CN201522356U - Aircraft engine alternating current supply pressure sensor calibrating device - Google Patents
Aircraft engine alternating current supply pressure sensor calibrating device Download PDFInfo
- Publication number
- CN201522356U CN201522356U CN2009202176722U CN200920217672U CN201522356U CN 201522356 U CN201522356 U CN 201522356U CN 2009202176722 U CN2009202176722 U CN 2009202176722U CN 200920217672 U CN200920217672 U CN 200920217672U CN 201522356 U CN201522356 U CN 201522356U
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- alternating current
- pressure transducer
- supply pressure
- power supply
- pressure sensor
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Abstract
The utility model belongs to detection techniques, and relates to an aircraft engine alternating current supply pressure sensor calibrating device. The calibrating device comprises a pressure source (2), a standard pressure sensor (3) and a standard pressure display gauge outfit (4), and is characterized by further comprising an alternating current power supply (1) of 36V output voltage and 400Hz frequency and a high-precision digital voltage meter (6), wherein the alternating current power supply (1) is connected with a power input end of a to-be-calibrated alternating current supply pressure sensor (5) via a conducting wire, and a signal output end of the to-be-calibrated alternating current supply pressure sensor (5) is connected with a signal input end of the high-precision digital voltage meter (6) via a conducting wire. The aircraft engine alternating current supply pressure sensor calibrating device can calibrate aircraft engine alternating current supply pressure sensors and meet calibration requirements thereof.
Description
Technical field
The utility model belongs to detection technique, relates to a kind of aeromotor Alternating Current Power Supply pressure transducer calibrating installation.
Background technology
At present, aeromotor direct current supply pressure transducer calibrating installation is by pressure source, standard pressure transducer and normal pressure display gauge head are formed, the pressure that standard pressure generator produces acts on tested direct current pressure transducer and the standard pressure transducer, the standard pressure transducer power supply is powered by the normal pressure display gauge head, the signal output part of standard pressure transducer is connected with the signal input part of normal pressure display gauge head, after the force value that pressure source produces is converted to corresponding electric signal by standard pressure transducer, show by the normal pressure display gauge head, tested direct current pressure transducer and the supporting use of tested pressure gauge outfit, tested direct current pressure transducer is powered by tested pressure gauge outfit, the signal output part of tested direct current pressure transducer is connected with the signal input part of tested pressure display table head, demonstrate the force value of pressure source equally, and compare with value that normal pressure pressure transducer and normal pressure display gauge head show, whether obtain examining and determine conclusion qualified.For aeromotor Alternating Current Power Supply pressure transducer,, use existing pressure transducer calibrating installation to examine and determine because it, does not have special-purpose communication power supply not with supporting pressure gauge outfit yet.
Summary of the invention
The purpose of this utility model is: propose a kind of aeromotor Alternating Current Power Supply pressure transducer calibrating installation, to satisfy the needs of aeromotor Alternating Current Power Supply pressure transducer calibrating.
The technical solution of the utility model is: aeromotor Alternating Current Power Supply pressure transducer calibrating installation, and it comprises pressure source, standard pressure transducer and normal pressure display gauge head; Pressure source is connected by the pressure input port of pipeline with tested Alternating Current Power Supply pressure transducer and standard pressure transducer, and the signal output part of standard pressure transducer is connected by the signal input part of lead with the normal pressure display gauge head; It is characterized in that, it is that 36V, frequency are 400Hz AC power and a high accuracy number voltage table that an output voltage is arranged, AC power is connected by the power input of lead with tested Alternating Current Power Supply pressure transducer, and the signal output part of tested Alternating Current Power Supply pressure transducer is connected by the signal input part of lead with the high accuracy number voltage table.
The utility model has the advantages that: can examine and determine aeromotor Alternating Current Power Supply pressure transducer, satisfy the needs of aeromotor Alternating Current Power Supply pressure transducer calibrating.
Description of drawings
Fig. 1 is a structural principle block diagram of the present utility model.
Embodiment
Below the utility model is described in further details.Referring to Fig. 1, aeromotor Alternating Current Power Supply pressure transducer calibrating installation, it comprises pressure source 2, standard pressure transducer 3 and normal pressure display gauge head 4; Pressure source 2 is connected by the pressure input port of pipeline with tested Alternating Current Power Supply pressure transducer 5 and standard pressure transducer 3, and the signal output part of standard pressure transducer 3 is connected by the signal input part of lead with normal pressure display gauge head 4; It is characterized in that, it is that 36V, frequency are 400Hz AC power 1 and a high accuracy number voltage table 6 that an output voltage is arranged, AC power 1 is connected by the power input of lead with tested Alternating Current Power Supply pressure transducer 5, and the signal output part of tested Alternating Current Power Supply pressure transducer 5 is connected by the signal input part of lead with high accuracy number voltage table 6.
Principle of work of the present utility model is: tested Alternating Current Power Supply pressure transducer and standard pressure transducer and normal pressure display gauge head are connected by Fig. 1, the on-stream pressure source, produce pressure, and act on simultaneously on tested Alternating Current Power Supply pressure transducer and the standard pressure transducer, the size of pressure is shown by the normal pressure display gauge head, when force value reaches the calibrating point value, note the output AC voltage value of the tested Alternating Current Power Supply pressure transducer that force value and high accuracy number voltage table read, and compare with design load that sensor producer provides, whether qualified to differentiate tested Alternating Current Power Supply pressure transducer.
Claims (1)
1. aeromotor Alternating Current Power Supply pressure transducer calibrating installation, it comprises pressure source [2], standard pressure transducer [3] and normal pressure display gauge head [4]; Pressure source [2] is connected with the pressure input port of tested Alternating Current Power Supply pressure transducer [5] with standard pressure transducer [3] by pipeline, and the signal output part of standard pressure transducer [3] is connected by the signal input part of lead with normal pressure display gauge head [4]; It is characterized in that, it is that 36V, frequency are a 400Hz AC power [1] and a high accuracy number voltage table [6] that an output voltage is arranged, AC power [1] is connected by the power input of lead with tested Alternating Current Power Supply pressure transducer [5], and the signal output part of tested Alternating Current Power Supply pressure transducer [5] is connected by the signal input part of lead with high accuracy number voltage table [6].
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2009202176722U CN201522356U (en) | 2009-09-30 | 2009-09-30 | Aircraft engine alternating current supply pressure sensor calibrating device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2009202176722U CN201522356U (en) | 2009-09-30 | 2009-09-30 | Aircraft engine alternating current supply pressure sensor calibrating device |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN201522356U true CN201522356U (en) | 2010-07-07 |
Family
ID=42508534
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN2009202176722U Expired - Fee Related CN201522356U (en) | 2009-09-30 | 2009-09-30 | Aircraft engine alternating current supply pressure sensor calibrating device |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN201522356U (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102721508A (en) * | 2012-05-29 | 2012-10-10 | 西北工业大学 | Device for detecting precision of output data of pressure, voltage and current (PVC) data table |
| CN104075841A (en) * | 2014-06-13 | 2014-10-01 | 四川亚美动力技术有限公司 | Detection circuit for pressure sensor of aeroengine |
| CN106546381A (en) * | 2015-09-18 | 2017-03-29 | 哈尔滨飞机工业集团有限责任公司 | A kind of fuel pressure gauge exerciser |
-
2009
- 2009-09-30 CN CN2009202176722U patent/CN201522356U/en not_active Expired - Fee Related
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102721508A (en) * | 2012-05-29 | 2012-10-10 | 西北工业大学 | Device for detecting precision of output data of pressure, voltage and current (PVC) data table |
| CN102721508B (en) * | 2012-05-29 | 2014-04-02 | 西北工业大学 | Device for detecting precision of output data of pressure, voltage and current (PVC) data table |
| CN104075841A (en) * | 2014-06-13 | 2014-10-01 | 四川亚美动力技术有限公司 | Detection circuit for pressure sensor of aeroengine |
| CN104075841B (en) * | 2014-06-13 | 2016-06-08 | 四川亚美动力技术有限公司 | aircraft engine pressure sensor detection circuit |
| CN106546381A (en) * | 2015-09-18 | 2017-03-29 | 哈尔滨飞机工业集团有限责任公司 | A kind of fuel pressure gauge exerciser |
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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: GUIZHOU LIYANG AERO-ENGINE CO., LTD. Free format text: FORMER OWNER: GUIZHOU LIYANG AERO ENGINE CO., LTD. Effective date: 20110415 |
|
| C41 | Transfer of patent application or patent right or utility model | ||
| COR | Change of bibliographic data |
Free format text: CORRECT: ADDRESS; FROM: 561102 MAILBOX 5, PINGBA COUNTY, GUIZHOU PROVINCE TO: 561102 MAILBOX 207, PINGBA COUNTY, GUIZHOU PROVINCE |
|
| TR01 | Transfer of patent right |
Effective date of registration: 20110415 Address after: 561102 Guizhou province Pingba County box 207 Patentee after: Guizhou Liyang Aerospace Power Co., Ltd. Address before: 561102 Guizhou province Pingba County box No. 5 Patentee before: Guizhou Liyang Aero Engine Co., Ltd. |
|
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20100707 Termination date: 20150930 |
|
| EXPY | Termination of patent right or utility model |