CN102252708B - Aviation capsule instrument tester - Google Patents
Aviation capsule instrument tester Download PDFInfo
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- CN102252708B CN102252708B CN 201110092194 CN201110092194A CN102252708B CN 102252708 B CN102252708 B CN 102252708B CN 201110092194 CN201110092194 CN 201110092194 CN 201110092194 A CN201110092194 A CN 201110092194A CN 102252708 B CN102252708 B CN 102252708B
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Abstract
The invention discloses an aviation capsule instrument tester, which comprises an air source triplet, a negative pressure generator and a connecting pipeline, and is characterized in that: the air source triplet is connected with an electrically controlled ratio regulating valve through the pipeline; a first outlet of the electrically controlled ratio regulating valve is connected with the negative pressure generator; the negative pressure generator is connected with a negative pressure stabilizing tank through a negative pressure high-speed stop valve and a negative pressure fast throttling valve; the negative pressure stabilizing tank is connected with a negative pressure high-precision sensor; a second outlet of the electrically controlled ratio regulating valve is connected with a low-pressure stabilizing tank through a low-pressure throttling valve and a low-pressure high-speed stop valve; the low-pressure stabilizing tank is connected with a low-pressure high-precision sensor; a third outlet of the electrically controlled ratio regulating valve is connected with a medium-pressure stabilizing tank through a pressure-limiting valve, a throttling valve and a medium-pressure three-position five-way valve; the medium-pressure stabilizing tank is connected with a medium-pressure high-precision sensor; and a fourth outlet of the electrically controlled ratio regulating valve is connected with the high-pressure stabilizing tank through a pressurizing valve, an electrically controlled pressure-reducing valve, a high-pressure three-position five-way pilot valve and the throttling valve; and the high-pressure stabilizing tank is connected with a high-pressure high-precision sensor. The invention has the advantages that: the tester has high reliability and control accuracy, the needed high-precision pressure is easily obtained, and testing automation can be realized.
Description
Technical field
When [0001] the present invention mainly solves bellows class instrument on detecting aviation aircraft, a kind of aviation capsule instrument tester that adopts virtual technology.
Background technology
At present in aviation aircraft section, annex Repairing Enterprises, height indicator, airspeed indicator, climb meter on the sense aircraft, and when other tensimeters take air as medium and sensor all are push-and-pull vacuum generator by hand usually, obtain negative pressure, perhaps obtain low-pressure air with small air pump.These two kinds of methods all can not obtain high vacuum and high pressure, bring limitation to test.Manual operations brings unstable and higher labour intensity in addition, and inconvenience realizes robotization.
Summary of the invention
The purpose of this invention is to provide a kind of aviation capsule instrument tester, utilize a source of the gas, can obtain the pressurized air of the cleaning of the different pressures such as required high-precision pressure negative pressure, low pressure, middle pressure, high pressure, virtual instrument technology in conjunction with outer setting can neatly, carry out the detection of aviation diaphragm capsule instrument and the instrument take air as medium and sensor accurately.The pneumatic element standardization level is high, reliability is strong, and precise control reduces cost.
The technical solution adopted in the present invention is as follows: it comprises gas source triplet, negative pressure generator and connecting line, it is characterized in that: gas source triplet connects automatically controlled ratio adjusting valve by pipeline, automatically controlled ratio adjusting valve four way outlets connect as follows by pipeline respectively: the first via connects negative pressure generator, negative pressure generator connects the negative pressure buffer tank by negative pressure high speed stop valve and negative pressure fast throttle valve, and the negative pressure buffer tank connects the negative pressure high-precision sensor; The second the tunnel by low pressure throttling valve, low-voltage high speed stop valve connection low pressure buffer tank, and the low pressure buffer tank connects the low-voltage high-precision sensor; Third Road is pressed buffer tank by pressure limiting valve, throttling valve, middle pressure three position five-way valve in connecting, and middle pressure buffer tank is pressed high-precision sensor in connecting; The four the tunnel by pressure charging valve, electronic control pressure reducing valve, high pressure 3 position-5 way pilot valve, throttling valve connection high voltage stabilizing tank, and the high voltage stabilizing tank connects the high-pressure and high-precision sensor.
Advantage of the present invention: utilize a source of the gas, can obtain the pressurized air of the cleaning of the different pressures such as required high-precision pressure negative pressure, low pressure, middle pressure, high pressure, virtual instrument technology in conjunction with outer setting can neatly, carry out the detection of aviation diaphragm capsule instrument and the instrument take air as medium and sensor accurately.The pneumatic element standardization level is high, reliability is strong, and precise control can realize the robotization of test.
Description of drawings
Fig. 1 is structural representation of the present invention.
Component serial number among the figure: negative pressure generator 1, high speed negative pressure air release 2, negative pressure fast throttle valve 3, negative pressure high speed stop valve 4, low-voltage high-precision sensor 5, low pressure buffer tank 6, negative pressure buffer tank 7, negative pressure high-precision sensor 8, negative pressure is throttling valve 9 at a slow speed, low-voltage high speed stop valve 10, gas source triplet 11, automatically controlled ratio adjusting valve 12, pressure charging valve 13, middle pressure high-precision sensor 14, electronic control pressure reducing valve 15, high pressure 3 position-5 way pilot valve 16, middle pressure buffer tank 17, high voltage stabilizing tank 18, middle pressure three position five-way valve 19, high-pressure and high-precision sensor 20, low speed throttling valve 21, entrance 22.Embodiment
The present invention utilizes a source of the gas, can obtain the pressurized air of the cleaning of the different pressures such as negative pressure, low pressure, middle pressure, high pressure, virtual instrument technology in conjunction with outer setting can neatly, carry out the detection of aviation diaphragm capsule instrument and the instrument take air as medium and sensor accurately.
Concrete structure is as follows: a gas source triplet 11 is set, and gas source triplet 11 1 end inlet portings 22, the other end connects automatically controlled ratio adjusting valve 12 by pipeline, and automatically controlled ratio adjusting valve 12 arranges four way outlets, and four way outlets connect as follows by pipeline respectively:
The first via connects negative pressure generator 1, and negative pressure generator 1 connects negative pressure buffer tank 7 by negative pressure high speed stop valve 4 and negative pressure fast throttle valve 3, and negative pressure buffer tank 7 connects negative pressure high-precision sensor 8.
Pressurized air (0-0.7MPa) enters gas source triplet 11, the airborne steam of elimination, and greasy dirt, particle floating dust etc. can manually carry out pressure and regulate.Clean air enters automatically controlled ratio adjusting valve 12, and this valve can carry out fine adjustment to pressure by external unit is automatically controlled, can be for four road pressure.
Gas enters negative pressure generator 1, the negative pressure of generation-90KPa-0Pa, air in the negative pressure buffer tank 7 is through negative pressure high speed stop valve 4, (break-make pipeline air negative pressure) and negative pressure fast throttle valve 3(regulate flow velocity), be sucked in the negative pressure generator air intake opening, so that whole gas circuit forms negative pressure.Negative pressure high-precision sensor 8 and tested capsule instrument are connected on the three-way interface of negative pressure buffer tank 7.By negative pressure high speed stop valve 4, obtain accurate vacuum tightness, the vacuum tightness that negative pressure high-precision sensor 8 obtains can numeral show or virtual vacuum meter demonstration theoretical level on by the Virtual Instrument of external unit, thus the actual height indicator indicated value of comparison.So just very intuitively and exactly detected the error of measured piece.
The second the tunnel by low pressure throttling valve 21, low-voltage high speed stop valve 10 connection low pressure buffer tanks 6, and low pressure buffer tank 6 connects low-voltage high-precision sensors 5;
Gas enters low pressure line, clean air enters the automatically controlled very low-pressure that transfers to of automatically controlled ratio adjusting valve 12(), low pressure throttling valve 21, low-voltage high speed stop valve 10 and low pressure buffer tank 6, low-voltage high-precision sensor 5 and measured workpiece, can obtain the low pressure of (0-50KPa), with 2 venting of high speed negative pressure air release.Be convenient to measure the flying instruments or the sensor that require low pressure.
Third Road is pressed buffer tank 17 in connecting by the pressure limiting valve on the conventional pipeline, throttling valve (not shown) and the pressure three position five-way valve 19 of being connected, and presses high-precision sensor 14 during middle pressure buffer tank 17 connects;
Gas enters middle pressure pipe road, clean air enters the automatically controlled lower pressure that transfers to of automatically controlled ratio adjusting valve 12(), enter again pressure limiting valve, throttling valve, middle pressure three position five-way valve 19 and middle pressure buffer tank 17, middle pressure high-precision sensor 14 and measured workpiece, can obtain the middle pressure of (0-150KPa).Be convenient to measure flying instruments or the sensor of pressing in the requirement.
The four the tunnel by pressure charging valve 13, electronic control pressure reducing valve 15, high pressure 3 position-5 way pilot valve 16, throttling valve (parts on the conventional pipeline, not shown) connection high voltage stabilizing tank 18, and high voltage stabilizing tank 18 connects high-pressure and high-precision sensors 14.
Gas enters pressure duct, clean air enters automatically controlled ratio and regulates the automatically controlled high energy of 12(and transfer to 0.8MPa), entering pressure charging valve 13(can double again, can reach 1.5MPa), electronic control pressure reducing valve 15, high pressure 3 position-5 way pilot valve 16, throttling valve, high voltage stabilizing tank 18, high-pressure and high-precision sensor 20 and measured workpiece, the high pressure of (0-1.5MPa) be can obtain, the flying instruments or the sensor that require high pressure are convenient to measure.
The negative pressure generator 1 that relates in the technical solution of the present invention, high speed negative pressure air release 2, negative pressure fast throttle valve 3, negative pressure high speed stop valve 4, low-voltage high-precision sensor 5, low pressure buffer tank 6, negative pressure buffer tank 7, negative pressure high-precision sensor 8, negative pressure is throttling valve 9 at a slow speed, low-voltage high speed stop valve 10, gas source triplet 11, automatically controlled ratio adjusting valve 12, pressure charging valve 13, middle pressure high-precision sensor 14, electronic control pressure reducing valve 15, high pressure 3 position-5 way pilot valve 16, middle pressure buffer tank 17, high voltage stabilizing tank 18, middle pressure three position five-way valve 19,, high-pressure and high-precision sensor 20 and low speed throttling valve 21 all adopt prior art products.
Claims (1)
1. aviation capsule instrument tester, it comprises gas source triplet, negative pressure generator and connecting line, it is characterized in that: gas source triplet connects automatically controlled ratio adjusting valve by pipeline, automatically controlled ratio adjusting valve four way outlets connect as follows by pipeline respectively: the first via connects negative pressure generator, negative pressure generator connects the negative pressure buffer tank by negative pressure high speed stop valve and negative pressure fast throttle valve, and the negative pressure buffer tank connects the negative pressure high-precision sensor; The second the tunnel by low pressure throttling valve, low-voltage high speed stop valve connection low pressure buffer tank, and the low pressure buffer tank connects the low-voltage high-precision sensor; Third Road is pressed buffer tank by pressure limiting valve, throttling valve, middle pressure three position five-way valve in connecting, and middle pressure buffer tank is pressed high-precision sensor in connecting; The four the tunnel by pressure charging valve, electronic control pressure reducing valve, high pressure 3 position-5 way pilot valve, throttling valve connection high voltage stabilizing tank, and the high voltage stabilizing tank connects the high-pressure and high-precision sensor.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 201110092194 CN102252708B (en) | 2011-04-13 | 2011-04-13 | Aviation capsule instrument tester |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 201110092194 CN102252708B (en) | 2011-04-13 | 2011-04-13 | Aviation capsule instrument tester |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN102252708A CN102252708A (en) | 2011-11-23 |
| CN102252708B true CN102252708B (en) | 2013-01-16 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN 201110092194 Active CN102252708B (en) | 2011-04-13 | 2011-04-13 | Aviation capsule instrument tester |
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| Country | Link |
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| CN (1) | CN102252708B (en) |
Family Cites Families (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2000121482A (en) * | 1998-10-15 | 2000-04-28 | Fukuda:Kk | Leakage tester |
| CN200941077Y (en) * | 2006-08-30 | 2007-08-29 | 北京康斯特仪表科技有限公司 | Gas pressure meter parity checker |
| CN201096592Y (en) * | 2007-08-16 | 2008-08-06 | 上海航天设备制造总厂 | Device for detecting sensor leakage |
| CN201532293U (en) * | 2009-10-22 | 2010-07-21 | 中国石油化工股份有限公司 | Tightness detector |
| RU94696U1 (en) * | 2010-01-22 | 2010-05-27 | Павел Юрьевич Борисов | TEST COMPLEX FOR ANEROID-MEMBRANE INSTRUMENTS |
| CN202024785U (en) * | 2011-04-13 | 2011-11-02 | 沈阳圣飞航空科技有限公司 | Tester for aviation diaphragm capsule instrument |
-
2011
- 2011-04-13 CN CN 201110092194 patent/CN102252708B/en active Active
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| CN102252708A (en) | 2011-11-23 |
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