CN203116909U - Field calibrating device for airplane gas pressure signal and mounting structure thereof - Google Patents
Field calibrating device for airplane gas pressure signal and mounting structure thereof Download PDFInfo
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- CN203116909U CN203116909U CN 201220325686 CN201220325686U CN203116909U CN 203116909 U CN203116909 U CN 203116909U CN 201220325686 CN201220325686 CN 201220325686 CN 201220325686 U CN201220325686 U CN 201220325686U CN 203116909 U CN203116909 U CN 203116909U
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- pipe joint
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Abstract
The utility model relates to a mounting structure and a device for a field calibrating device for airplane pressure. The mounting structure for the field calibrating device for the airplane pressure comprises the following components: a multi-head pipeline connector 1, pipeline joints 2, a plurality of pipeline 3, pipeline switches 4, an operation pressure test device 5 and a detachable plug 6. The detachable plug 6 is mounted on more than one pipeline joint 2. The other pipeline joints 2 are connected with the pipeline 3. The pipeline 3 is provided with pipeline switches 4. At least one pipeline 3 is provided with the operation pressure test device 5. The operation pressure test device 5 is provided between one pipeline joint 2 and the pipeline switch 4. According to the field calibrating device for airplane pressure, the detachable plug 6 is removed based on the mounting structure of the mounting structure for the field calibrating device for the airplane pressure, and pipeline 3 is added on a corresponding pipeline joint 2. The pipeline 3 is connected with a pressure source 7 and a pressure detection reference device 8. The mounting structure and the device for the field calibrating device for airplane pressure have the following advantages: simple structure, high safety, high reliability, high convenience in use, low fabricating cost, and capability of effectively settling a problem of field calibration of an airplane pressure test device.
Description
Technical field
The utility model belongs to aircraft gas pressure sensor and indicating pressure gauge field calibration field.
Background technology
Aircraft gas gauge field calibration device near of the present invention be to adopt manual method in the past, pressure transducer is disassembled, deliver to the laboratory and examine and determine or calibrate.Adopt the present utility model, can under the situation of not dismantling pressure transducer, directly carry out field calibration aboard.Adopt present technique, can reduce cost, have higher utility.
At present, the calibrating of aircraft airborne pressure transducer or calibration, the general method of concentrating dismounting that adopts, the present utility model is adopted in unified calibrating or calibration when the aircraft overhaul, can carry out field calibration to airborne pressure transducer at any time.Aircraft has gaseous tension.Generally speaking, for the sensor of indicated pressure, aircraft can not be examined and determine or be calibrated in operational process, main cause: the bad dismounting of pressure transducer, only when the aircraft overhaul or sensor when breaking down, just sensor is implemented dismounting.Aircraft flight is produced very big hidden danger safely.
Summary of the invention
The purpose of this utility model is: a kind of aircraft gaseous tension signal field calibration device and mounting structure simple in structure, easy to use are provided.
The technical solution of the utility model is: a kind of aircraft pressure field calibration Unit Installation structure, comprise manifold path connector 1, pipe joint 2 on the manifold path connector, the pipeline 3 of some connection manifold path connectors 1, pipeline switch 4, work pressure test device 5, detachable plug 6, at manifold path connector 1 more than one pipe joint 2 detachable plug 6 is installed, remaining pipe joint 2 connecting line 3, installation pipeline switch 4 on the pipeline 3, have the work that is equipped with on the pipeline 3 at least with pressure test device 5, work with pressure test device 5 between pipe joint 2 and pipeline switch 4.
The quantity of the pipe joint 2 on the manifold path connector 1 is more than two.Pipeline switch 4 is manual or motor operated switch.
A kind of aircraft pressure field calibration device on above-mentioned aircraft pressure field calibration Unit Installation structure, removes detachable plug 6, installs pipeline 3 additional at the pipe joint 2 of correspondence, connects pressure source 7, pressure detection standard apparatus 8 on this pipeline 3.
The beneficial effects of the utility model are: simple in structure, safe and reliable, easy to use, cheap, efficiently solve the problem of aircraft pressure test device field calibration.The utility model also can be applicable to the field calibration of the gas piping work usefulness pressure test device of other association areas.
Description of drawings
Fig. 1 is the aircraft pressure field calibration Unit Installation structural representation on single tube road;
Fig. 2 is the aircraft pressure field calibration Unit Installation structural representation of dual circuit;
Fig. 3 is the structural representation of the aircraft pressure field calibration device of dual circuit;
Wherein, 1 is 1 for the manifold path connector, and 2 is pipe joint, and 3 is pipeline, and 4 is the pipeline switch, and 5 are the work pressure test device, and 6 is detachable plug, and 7 is pressure source, and 8 is the pressure detection standard apparatus.
Embodiment
Below in conjunction with accompanying drawing the utility model is described in further detail:
Present embodiment describes aircraft pressure field calibration Unit Installation structure in detail.The aircraft pressure field calibration Unit Installation structure that the utility model relates to, comprise manifold path connector 1, pipe joint 2 on the manifold path connector, the pipeline 3 that connects manifold path connector 1, pipeline switch 4, work pressure test device 5, detachable plug 6, at manifold path connector 1 more than one pipe joint 2 detachable plug 6 is installed, remaining pipe joint 2 connecting line 3, installation pipeline switch 4 on the pipeline 3, have the work that is equipped with on the pipeline 3 at least with pressure test device 5, work with pressure test device 5 between pipe joint 2 and pipeline switch 4.
With reference to figure 1, at three pipe joints 2 of four-head pipeline connector 1 detachable plug 6 is installed, detachable plug 6 can be rapid-acting coupling or the screwed blocking cap of self-closing.Connecting line 3 on the pipe joint 2 of detachable plug 6 is not installed at four-head pipeline connector 1, and connecting line switch 4 on the pipeline, pipeline switch 4 can be manual or automatic switches.At pipeline 3 work pressure test device 5 is installed, work uses pressure test device 5 between pipe joint 2 and pipeline switch 4, work can be tensimeter or pressure transducer with pressure test device 5, is to be used for the pressure of installation and measuring pipeline at pipeline as required.
With reference to figure 2, two pipe joints 2 up and down at four-head pipeline connector 1 are installed detachable plug 6, about on two pipe joints 2 respectively installation pipeline 3, pipeline switch 4 and work with pressure test device 5, according to concrete need of work, job pressure test device 5 can only be installed on two pipelines 3.
Present embodiment describes structure and the principle of work of aircraft pressure field calibration device in detail.
With reference to figure 3, the aircraft pressure field calibration device that the utility model relates to is to use under align mode, on the basis of the described aircraft pressure of Fig. 2 field calibration Unit Installation structure, remove the detachable plug 6 of four-head pipeline connector 1 top, pipe joint 2 in correspondence installs pipeline 3 additional, connect pressure source 7, pressure detection standard apparatus 8 on this pipeline 3, wherein pressure detection standard apparatus 8 can be any one of master gauge, standard pressure transducer or normal pressure source apparatus.During calibration, close the pipeline switch 4 on the left and right sides pipeline 3, by pressure source 7 build-up pressure in the pipeline 3 of sealing, pressure limit is 0.005MPa～60MPa, by pressure detection standard apparatus 8 and work are compared with the pressure value that pressure test device 5 shows respectively, the work of namely knowing realizes the calibration of work with pressure test device 5 with the measuring accuracy of pressure test device 5.
The aircraft pressure field calibration device that the utility model relates to is installed on pipeline 3 if desired for a long time, can be on the pipeline 3 between upper pipeline joint 2 and the pressure source 7 installation pipeline switch 4, should close this pipeline switch 4 during pipeline 3 operate as normal, open the pipeline switch on other pipelines.
Manifold path connector 1 of the present utility model can be the web member of standard, as threeway, four-way, also can be the joint that connects more multi-link pipeline.
Claims (10)
1. aircraft pressure field calibration Unit Installation structure, comprise manifold path connector (1), pipe joint on the manifold path connector (2), the pipeline (3) of some connection manifold path connectors (1), pipeline switch (4), work pressure test device (5), detachable plug (6), it is characterized in that: at the more than one pipe joint of manifold path connector (1) (2) detachable plug (6) is installed, remaining pipe joint (2) connecting line (3), pipeline (3) is gone up installation pipeline switch (4), have the work that is equipped with on the pipeline (3) pressure test device (5) at least, work is positioned between pipe joint (2) and the pipeline switch (4) with pressure test device (5).
2. a kind of aircraft pressure field calibration Unit Installation structure as claimed in claim 1: it is characterized in that: the quantity of the pipe joint (2) on the described manifold path connector (1) is more than two.
3. a kind of aircraft pressure field calibration Unit Installation structure as claimed in claim 1: it is characterized in that: described pipeline switch (4) is for manually or motor operated switch.
4. a kind of aircraft pressure field calibration Unit Installation structure as claimed in claim 1: it is characterized in that: described detachable plug (6) is the rapid-acting coupling of self-closing.
5. a kind of aircraft pressure field calibration Unit Installation structure as claimed in claim 1: it is characterized in that: described detachable plug (6) is screwed blocking cap.
6. aircraft pressure field calibration device, it is characterized in that: as claimed in claim 1 on aircraft pressure field calibration Unit Installation structure, remove detachable plug (6), pipe joint (2) in correspondence installs pipeline (3) additional, and this pipeline (3) is gone up and connected pressure source (7), pressure detection standard apparatus (8).
7. a kind of aircraft pressure field calibration device as claimed in claim 6, it is characterized in that: described pressure detection standard apparatus (8) comprises master gauge, standard pressure transducer, normal pressure source apparatus.
8. a kind of aircraft pressure field calibration device as claimed in claim 6 is characterized in that: the last installation pipeline switch (4) of the pipeline (3) between pipe joint (2) and pressure source (7).
9. a kind of aircraft pressure field calibration device as claimed in claim 6, it is characterized in that: pipeline (3) gas circuit pressure limit is 0.005MPa～60MPa.
10. a kind of aircraft pressure field calibration device as claimed in claim 6 is characterized in that: described work is tensimeter or pressure transducer with pressure test device (5).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 201220325686 CN203116909U (en) | 2012-07-06 | 2012-07-06 | Field calibrating device for airplane gas pressure signal and mounting structure thereof |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 201220325686 CN203116909U (en) | 2012-07-06 | 2012-07-06 | Field calibrating device for airplane gas pressure signal and mounting structure thereof |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN203116909U true CN203116909U (en) | 2013-08-07 |
Family
ID=48897245
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN 201220325686 Expired - Lifetime CN203116909U (en) | 2012-07-06 | 2012-07-06 | Field calibrating device for airplane gas pressure signal and mounting structure thereof |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN203116909U (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112393788A (en) * | 2020-11-16 | 2021-02-23 | 沈阳新石科技有限公司 | Calibration device for oil well dynamic liquid level echo tester |
| CN113720527A (en) * | 2021-09-02 | 2021-11-30 | 北京航空航天大学 | Pressure test unit field calibration method of test flight parameter test system |
-
2012
- 2012-07-06 CN CN 201220325686 patent/CN203116909U/en not_active Expired - Lifetime
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112393788A (en) * | 2020-11-16 | 2021-02-23 | 沈阳新石科技有限公司 | Calibration device for oil well dynamic liquid level echo tester |
| CN112393788B (en) * | 2020-11-16 | 2021-11-26 | 沈阳新石科技有限公司 | Calibration device for oil well dynamic liquid level echo tester |
| CN113720527A (en) * | 2021-09-02 | 2021-11-30 | 北京航空航天大学 | Pressure test unit field calibration method of test flight parameter test system |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| CX01 | Expiry of patent term | ||
| CX01 | Expiry of patent term |
Granted publication date: 20130807 |