CN108100294A - A kind of Portable aircraft hydraulic system fault somascope - Google Patents
A kind of Portable aircraft hydraulic system fault somascope Download PDFInfo
- Publication number
- CN108100294A CN108100294A CN201611052422.9A CN201611052422A CN108100294A CN 108100294 A CN108100294 A CN 108100294A CN 201611052422 A CN201611052422 A CN 201611052422A CN 108100294 A CN108100294 A CN 108100294A
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- somascope
- portable
- wall
- pipe clamp
- hydraulic system
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- 238000007689 inspection Methods 0.000 claims description 2
- PEDCQBHIVMGVHV-UHFFFAOYSA-N Glycerine Chemical compound OCC(O)CO PEDCQBHIVMGVHV-UHFFFAOYSA-N 0.000 claims 1
- 238000004458 analytical method Methods 0.000 abstract description 3
- 239000000463 material Substances 0.000 abstract description 3
- 238000010586 diagram Methods 0.000 description 5
- 230000003534 oscillatory effect Effects 0.000 description 4
- 238000005516 engineering process Methods 0.000 description 2
- 239000012530 fluid Substances 0.000 description 2
- 238000009434 installation Methods 0.000 description 2
- 238000011835 investigation Methods 0.000 description 2
- 238000000034 method Methods 0.000 description 2
- 238000013024 troubleshooting Methods 0.000 description 2
- 230000000712 assembly Effects 0.000 description 1
- 238000000429 assembly Methods 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000010276 construction Methods 0.000 description 1
- 238000013461 design Methods 0.000 description 1
- 238000001514 detection method Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
- 238000005259 measurement Methods 0.000 description 1
- 230000007246 mechanism Effects 0.000 description 1
- 230000010349 pulsation Effects 0.000 description 1
- 239000013589 supplement Substances 0.000 description 1
- 238000012360 testing method Methods 0.000 description 1
- 239000002699 waste material Substances 0.000 description 1
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Abstract
A kind of Portable aircraft hydraulic system fault somascope, including portable fluctuation pressure somascope and patch pressure sensor apparatus, portable fluctuation pressure somascope includes the first pincerlike pipe clamp wall, the second pincerlike pipe clamp wall, the first patch pressure sensor, the first semilune briquetting, wing nut and wing bolt, first pincerlike pipe clamp wall and the second pincerlike pipe clamp wall are tested mounted on aircraft on hydraulic pipe by wing nut and wing bolt, and the conducting wire of the first patch pressure sensor is connected through the first wire guide with portable fluctuation pressure somascope.The Portable aircraft hydraulic system fault somascope is simple in structure, easy to carry, can carry out fault locating analysis everywhere, and it is not required to dismounting plane hydraulic system functional unit attachment, with quick positioning plane hydraulic system guilty culprit, a large amount of manpower and materials are saved, are improved work efficiency.
Description
Technical field
The present invention relates to plane hydraulic systems to manufacture applied technical field, and in particular to a kind of Portable aircraft hydraulic system
Defectograph.
Background technology
In plane hydraulic system manufactures test adjustment, since plane hydraulic system is made of wherein many functional assemblies
Including various servo actuators, hydraulic pipe and hydraulic pump etc., each component part interface is numerous, in actual hydraulic work system
During performance checking, often due to a variety of causes causes some operating mechanisms that can not work normally, immediate cause is exactly hydraulic system
Unit failure, component connection error caused by artificial origin.In previous work, generally be directed to the work of partial function device
Analyzed as feature, then in plane hydraulic system by fluid pressure line on disconnection machine, replace certain partial function device or
Person in fluid pressure line using pressure gauge is concatenated, to analyze and monitor the working condition of a certain section hydraulic subsystem, Jin Erjin
Row fault location.However in the small space of aircraft, the string part investigation of certain partial function part and installation pressure table look-up are carried out,
It is very time-consuming and laborious, and hydraulic system pollution is easily caused in continuous disassembly process, cause entire airplane hydraulic pressure system
System needs to clean again, some consumables need to supplement again, the secondary harm that troubleshooting inspection is caused to generate, and confirms in investigation repeatedly
During, this secondary risk is repeated and amplifies, and very big manpower and materials is caused to waste on machine.How
The situation of hydraulic system functional unit attachment is not removed and then quickly positions guilty culprit, is urgent problem.
The content of the invention
In order to solve the above technical problems, the present invention mainly realize it is a kind of do not dismount hydraulic system functional unit attachment or
Quick analyzing and positioning plane hydraulic system failure in the case of external hydraulic gage is conducive to carry out plane hydraulic system failure
The Portable aircraft hydraulic system fault somascope of analyzing and positioning.
A kind of Portable aircraft hydraulic system fault somascope is passed including portable fluctuation pressure somascope and patch pressure
Sensor arrangement, portable fluctuation pressure somascope include the first pincerlike pipe clamp wall, the second pincerlike pipe clamp wall, the first patch pressure and pass
Sensor, the first semilune briquetting, wing nut and wing bolt, the first semilune briquetting are arranged on the first pincerlike pipe clamp wall inner wall
Groove on, the first wire guide is offered in the middle part of the first semilune briquetting, it is pincerlike that the first patch pressure sensor is arranged on first
On pipe clamp wall inner wall, the first pincerlike pipe clamp wall and the second pincerlike pipe clamp wall are mounted on aircraft quilt by wing nut and wing bolt
It surveys on hydraulic pipe, the conducting wire of the first patch pressure sensor connects through the first wire guide and portable fluctuation pressure somascope
It connects.
Further, which further includes the second patch pressure sensor, the second half
Month shape briquetting and the second wire guide, the second semilune briquetting are arranged on the groove of the second pincerlike pipe clamp wall inner wall, the second patch
Pressure sensor is arranged on the second pincerlike pipe clamp wall inner wall, and the second wire guide is arranged on the second pincerlike pipe clamp wall middle part, the
The conducting wire of two patch pressure sensors is connected through the second wire guide with portable fluctuation pressure somascope.
More than Summary on technology and applicable cases are occupy, which achieves beneficial
Technique effect is as follows：It is simple in structure, it is easy to carry, fault locating analysis can be carried out everywhere, and is not required to dismounting airplane hydraulic pressure system
System functional unit attachment has quick positioning plane hydraulic system guilty culprit, saves a large amount of manpower and materials, improve work
Efficiency.
Description of the drawings
Schematic diagram when Fig. 1 is the use of the present invention.
Fig. 2 is the schematic diagram of the patch pressure sensor apparatus of the present invention.
Fig. 3 is the B of the present invention to schematic diagram.
Fig. 4 is the A of the present invention to schematic diagram.
Fig. 5 is the pincerlike pipe clamp wall construction diagram of the present invention.
In figure：1st, portable fluctuation pressure somascope；2nd, aircraft is tested hydraulic pipe；3rd, patch pressure sensor fills
It puts；4th, the first pincerlike pipe clamp wall；5th, the second pincerlike pipe clamp wall；6th, the first patch pressure sensor；7th, the second patch pressure sensing
Device；8th, the first semilune briquetting；9th, the second semilune briquetting；10th, the second wire guide；11st, wing nut；12nd, wing bolt；
13rd, the first wire guide.
Specific embodiment
The principle and features of the present invention will be described below with reference to the accompanying drawings, and example is served only for explaining invention, not
For limiting the scope of the present invention.
A kind of Portable aircraft hydraulic system fault somascope, including portable fluctuation pressure somascope 1 and patch pressure
Sensor device 3, portable fluctuation pressure somascope 1 include first pincerlike the 4, second pincerlike pipe clamp wall 5 of pipe clamp wall, the first patch
Pressure sensor 6, the first semilune briquetting 8, wing nut 11 and wing bolt 12, the first semilune briquetting 8 are arranged on first
On the groove of pincerlike 4 inner wall of pipe clamp wall, 8 middle part of the first semilune briquetting offers the first wire guide 13, and the first patch pressure passes
Sensor 6 is arranged on the first pincerlike 4 inner wall of pipe clamp wall, and the first pincerlike 4 and second pincerlike pipe clamp wall 5 of pipe clamp wall passes through wing nut
11 and wing bolt 12 be tested mounted on aircraft on hydraulic pipe 2, the conducting wire of the first patch pressure sensor 6 passes through the first conducting wire
Hole 13 is connected with portable fluctuation pressure somascope 1.
To make more accurately to check airplane hydraulic pressure manifold pressure pulsation situation, guilty culprit is more accurately positioned.This is just
It takes formula plane hydraulic system defectograph and further includes the second patch pressure sensor 7, the second semilune briquetting 9 and the second conducting wire
Hole 10, the second semilune briquetting 9 are arranged on the groove of the second pincerlike 5 inner wall of pipe clamp wall, and the second patch pressure sensor 7 is set
On the second pincerlike 5 inner wall of pipe clamp wall, the second wire guide 10 is arranged on the second pincerlike 5 middle part of pipe clamp wall, the second patch pressure
The conducting wire of sensor 7 is connected through the second wire guide 10 with portable fluctuation pressure somascope 1.
The present invention operation principle be：Due to have on aircraft various hydraulic pipes i.e. aircraft be tested hydraulic pipe 2 there are
The inherent characteristic of pressure fluctuation, by tested airplane hydraulic pressure conduit 2 installation Portable aircraft hydraulic system fault examine
Instrument is looked into, is fitted in by the first patch pressure sensor 6 and the second patch pressure sensor 7 of patch pressure sensor apparatus 3
On tested airplane hydraulic pressure conduit 2, the pressure fluctuation of tested airplane hydraulic pressure conduit 2 is gathered to hand-held pressure somascope, is passed through
Check this intrinsic pressure fluctuation fluctuation, to analyze the pressure condition of current pipeline, and then each hydraulic system is each on judgement machine
Whether the pressure value in working line meets the requirements, if there are under-voltage, the fault conditions such as no pressure.
After hydraulic work system is started, it is possible to which the working condition in the current pipeline of dynamic detection is set by hand-held
The pressure state of the standby interior software conversion current pipeline of real-time display.When current pipeline meets design requirement, it is necessary to search another
There may be on the pipeline of failure at one, can by replacing various sizes of binary channels external clamping oscillatory pressure pick-up, after
It is continuous to measure.Certainly we can prepare such as in real work：Outside the different binary channels for corresponding to caliber Φ 6, Φ 8, Φ 10
Clip oscillatory pressure pick-up passes through a hydraulic system pressure supply, it is possible to disposable measurement all hydraulic accident analysis point
Pressure condition.What we needed to do is exactly to install oscillatory pressure pick-up early period and connect plug i.e. when measuring the point pressure
It can.It is very convenient, real-time, efficient, economical.Binary channels external clamping oscillatory pressure pick-up can also repeatedly make after being measured
With.In the case where condition of external field complicated ground supportability is not in place, which is equipped with the tool box of a hand-held, once
Property just can be by outfield trouble shooting in place.
Claims (2)
1. a kind of Portable aircraft hydraulic system fault somascope, it is characterised in that：The Portable aircraft hydraulic system fault
Somascope includes portable fluctuation pressure somascope (1) and patch pressure sensor apparatus (3), the portable fluctuation pressure inspection
Looking into instrument (1) includes the first pincerlike pipe clamp wall (4), the second pincerlike pipe clamp wall (5), the first patch pressure sensor (6), the first first quarter moon
Shape briquetting (8), wing nut (11) and wing bolt (12), the first semilune briquetting (8) are arranged on the first pincerlike pipe clamp
On the groove of wall (4) inner wall, the first wire guide (13), first patch are offered in the middle part of the first semilune briquetting (8)
Pressure sensor (6) is arranged on first pincerlike pipe clamp wall (4) inner wall, the described first pincerlike pipe clamp wall (4) and the second pincerlike pipe
Double wall (5) is tested mounted on aircraft on hydraulic pipe (2) by wing nut (11) and wing bolt (12), first patch
The conducting wire of pressure sensor (6) is connected through the first wire guide (13) with portable fluctuation pressure somascope (1).
2. Portable aircraft hydraulic system fault somascope according to claim 1, it is characterised in that：It is described portable winged
Machine hydraulic system defectograph further includes the second patch pressure sensor (7), the second semilune briquetting (9) and the second wire guide
(10), the second semilune briquetting (9) is arranged on the groove of second pincerlike pipe clamp wall (5) inner wall, the second patch pressure
Force snesor (7) is arranged on second pincerlike pipe clamp wall (5) inner wall, and second wire guide (10) is arranged on the second pincerlike pipe clamp
On wall (5) middle part, the conducting wire of the second patch pressure sensor (7) passes through the second wire guide (10) and portable fluctuation pressure
Somascope (1) connects.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201611052422.9A CN108100294A (en) | 2016-11-24 | 2016-11-24 | A kind of Portable aircraft hydraulic system fault somascope |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201611052422.9A CN108100294A (en) | 2016-11-24 | 2016-11-24 | A kind of Portable aircraft hydraulic system fault somascope |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN108100294A true CN108100294A (en) | 2018-06-01 |
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ID=62205131
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201611052422.9A Pending CN108100294A (en) | 2016-11-24 | 2016-11-24 | A kind of Portable aircraft hydraulic system fault somascope |
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| Country | Link |
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| CN (1) | CN108100294A (en) |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20030083794A1 (en) * | 2001-10-27 | 2003-05-01 | Juergen Halm | System and method for diagnosing aircraft components for maintenance purposes |
| CN201837497U (en) * | 2010-10-25 | 2011-05-18 | 江苏三恒科技集团有限公司 | Pressure sensor for mines |
| CN102494193A (en) * | 2011-12-12 | 2012-06-13 | 北京航空航天大学 | Hoop for airplane hydraulic pipeline and design method thereof |
| CN202852325U (en) * | 2012-09-11 | 2013-04-03 | 宝钢不锈钢有限公司 | Magnetic pipeline leakage blocking clamp |
| CN104155040A (en) * | 2014-04-17 | 2014-11-19 | 中国航空工业集团公司沈阳飞机设计研究所 | Method for determining dynamic stress test on aircraft hydraulic pipeline |
| CN206318039U (en) * | 2016-11-24 | 2017-07-11 | 中航贵州飞机有限责任公司 | A kind of Portable aircraft hydraulic system fault somascope |
-
2016
- 2016-11-24 CN CN201611052422.9A patent/CN108100294A/en active Pending
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20030083794A1 (en) * | 2001-10-27 | 2003-05-01 | Juergen Halm | System and method for diagnosing aircraft components for maintenance purposes |
| CN201837497U (en) * | 2010-10-25 | 2011-05-18 | 江苏三恒科技集团有限公司 | Pressure sensor for mines |
| CN102494193A (en) * | 2011-12-12 | 2012-06-13 | 北京航空航天大学 | Hoop for airplane hydraulic pipeline and design method thereof |
| CN202852325U (en) * | 2012-09-11 | 2013-04-03 | 宝钢不锈钢有限公司 | Magnetic pipeline leakage blocking clamp |
| CN104155040A (en) * | 2014-04-17 | 2014-11-19 | 中国航空工业集团公司沈阳飞机设计研究所 | Method for determining dynamic stress test on aircraft hydraulic pipeline |
| CN206318039U (en) * | 2016-11-24 | 2017-07-11 | 中航贵州飞机有限责任公司 | A kind of Portable aircraft hydraulic system fault somascope |
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Application publication date: 20180601 |