CN106596387A - Corrosion rate on-line monitoring sensing probe of airplane metal matrix structure - Google Patents
Corrosion rate on-line monitoring sensing probe of airplane metal matrix structure Download PDFInfo
- Publication number
- CN106596387A CN106596387A CN201611112098.5A CN201611112098A CN106596387A CN 106596387 A CN106596387 A CN 106596387A CN 201611112098 A CN201611112098 A CN 201611112098A CN 106596387 A CN106596387 A CN 106596387A
- Authority
- CN
- China
- Prior art keywords
- probe
- monitoring
- corrosion
- protective layer
- aircraft
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Pending
Links
Classifications
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01N—INVESTIGATING OR ANALYSING MATERIALS BY DETERMINING THEIR CHEMICAL OR PHYSICAL PROPERTIES
- G01N17/00—Investigating resistance of materials to the weather, to corrosion, or to light
- G01N17/02—Electrochemical measuring systems for weathering, corrosion or corrosion-protection measurement
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01N—INVESTIGATING OR ANALYSING MATERIALS BY DETERMINING THEIR CHEMICAL OR PHYSICAL PROPERTIES
- G01N17/00—Investigating resistance of materials to the weather, to corrosion, or to light
- G01N17/006—Investigating resistance of materials to the weather, to corrosion, or to light of metals
Landscapes
- Life Sciences & Earth Sciences (AREA)
- Biodiversity & Conservation Biology (AREA)
- Ecology (AREA)
- Environmental & Geological Engineering (AREA)
- Environmental Sciences (AREA)
- Physics & Mathematics (AREA)
- Health & Medical Sciences (AREA)
- Chemical & Material Sciences (AREA)
- Analytical Chemistry (AREA)
- Biochemistry (AREA)
- General Health & Medical Sciences (AREA)
- General Physics & Mathematics (AREA)
- Immunology (AREA)
- Pathology (AREA)
- Testing Resistance To Weather, Investigating Materials By Mechanical Methods (AREA)
Abstract
The invention provides a corrosion rate on-line monitoring sensing probe of an airplane metal matrix structure. The corrosion rate on-line monitoring sensing probe comprises a tubular protection layer, a monitoring probe, a hole sealing agent and a connection lead; the tubular protective layer employs a PVC material; a monitoring probe material is same with a metal material on the surface of an airplane monitoring part; an array shape is formed by several monitoring probes, the monitoring probes are not contacted, a probe diameter is 1 mm, the spacing between the probes is 2 mm; the connection is connected with the monitoring probe and external equipment; the tubular protective layer is filled with the hole sealing agent, and isolation of the monitoring probe and fixation of the monitoring probe and lead connection effects are generated. Based on a coupled multielectrode matrix sensing technology principle, the metal matrix corrosion rate is monitored under air weak electrolyte environment, the sensing probe provides the important technical support for corrosion environment characteristic research, structure corrosion-resistant design, usage maintenance, corrosion damage assessment and prediction, provides reference for maintenance, and determines the optimum maintenance time and maintenance scheme.
Description
Technical field
The present invention relates to aircraft metallic matrix structural health monitoring technical field, specially a kind of aircraft metallic matrix structure
Corrosion rate monitors sensor probe on-line.
Background technology
Aircraft is experienced by high/low temperature, damp and hot, salt fog, illumination, chemical contamination, sleet, greasy weather when coastal area uses
And sea water sputtering etc. exceedingly odious marine environment effect, easily cause its housing construction, system, electronic equipment and adnexa
Corrosion, has a strong impact on the structural intergrity and feature of aircraft, in order to slow down and control corrosion rate, needs to carry out corrosion prison to aircraft
Survey and keep in repair.
The Corrosion Maintenance of conventional airplane mainly formulates optimal frequently with the method for periodic maintenance according to using experience
Detection time and corrosion protection are keeped in repair, and its major drawbacks is the too early and hysteresis that maintenance engineering occurs, premature maintenance meeting
The huge waste of manpower and materials and time cost is caused, while reducing the usage cycles of equipment and facility, and delayed can be caused
The further deterioration of corrosion condition, maintenance not in time then can more reduce service life, safety and the reliability of aircraft.Accordingly
Corrosion condition maintenarnce strategy is introduced, the tactful successful implementation depends on advanced technology, the corrosion of dependable performance exists in real time
Line monitors sensor probe, provides reference for condition maintenarnce, it is determined that optimal maintenance time and maintenance program, it is to avoid keep in repair too early and
The drawbacks of keeping in repair delayed.
In recent years, corrosion monitoring technology seems more and more important with the increase of aircraft maintenance expense, and American-European countries is to flying
The sensor-based system of machine metallic matrix structure erosion monitoring technology has carried out substantial amounts of research, has succeeded in developing for air light current solution
Metallic matrix corrosion rate monitors sensor probe on-line and realizes the engineer applied on aircraft under matter environment, but its technology is to state
Interior secrecy.Open in terms of the domestic rate of metal corrosion sensor based on principles such as electrochemistry noise method, harmonic modulation analytic process
A large amount of principles and confirmatory study are opened up, but has been contributed in liquid strong electrolyte environment, such as oil, sea water environment, nothing
Method realizes the corrosion monitoring under aircraft air weak electrolyte environment.
The content of the invention
To solve the problems, such as prior art, it is online that the present invention proposes a kind of aircraft metallic matrix structure erosion speed
Monitoring sensor probe, can realize that aircraft life. cycle phase inner structure metallic matrix corrosion damage is monitored on-line, can be used to be tieed up regarding feelings
The important technical repaiied and safeguard.The present invention is based on coupling multi-electrode matrix sensing technology principle, by air light current solution
Metallic matrix corrosion rate is monitored under matter environment, is corrosive environment characteristic research, structure design against corrosion, use and maintenance, corrosion
Lesion assessment and prediction provide important technology and support, and for condition maintenarnce reference is provided, and determine therefrom that optimal maintenance time and dimension
Scheme is repaiied, is to ensure Airplane Structure Durability, damage tolerance quality and use safety, service life, continuing airworthiness ability, maintenance
With the important means of maintenance cost.
The technical scheme is that：
A kind of aircraft metallic matrix structure erosion speed monitors sensor probe on-line, it is characterised in that：Including tubulose
Protective layer, monitoring probe, hole sealing agent and connecting wire；
The tubular protective layer adopts PVC material；The tubular protective layer geomery monitors position preformed hole with aircraft
Shape is consistent；
The monitoring probe material is identical with aircraft monitoring portion faces metal material；Some monitoring probes constitute array shape
Shape, does not contact, probe diameter 1mm between each monitoring probe, spacing 2mm between each probe；
The connecting wire connection monitoring probe and external equipment, play connection electric action；
The hole sealing agent is filled in tubular protective layer, plays each monitoring probe of isolation and stationary monitoring probe and connecting wire
Effect.
A kind of further preferred version, aircraft metallic matrix structure erosion speed monitors sensor probe on-line, its
It is characterised by：The hole sealing agent adopts epoxy resin.
Beneficial effect
Aircraft metallic matrix structure erosion speed on-line monitoring sensor probe proposed by the present invention can simulate aircraft monitoring portion
Anode region and cathode chamber in the actual corrosion process of position surface metal metal, rectangular probe electrode simulates anode region, and corrosion is sent out
Electronics is lost when raw, the electric current between coupling electrode is measured and is carried out corresponding signal processing, it is possible to obtain the corruption of anode electrode
Erosion speed, with this corrosion rate of aircaft configuration metallic matrix is determined.Its major advantage is as follows：(1) measure when need not with treat
Survey metal structure directly contact；(2) " passive " device, it is not necessary to which driving voltage is applied to electrode；(3) it is relatively wet in detecting head surface
Degree is very low or in the case of lacking conducting liquid, and probe still can effectively carry out corrosion measurement, to the media environment being continually changing
Rapid reaction is made, with high sensitivity；(4) probe electrode can be made up of any metal material, only need to be with metal to be measured
Material is consistent.
The additional aspect and advantage of the present invention will be set forth in part in the description, and partly will become from the following description
Obtain substantially, or recognized by the practice of the present invention.
Description of the drawings
The above-mentioned and/or additional aspect and advantage of the present invention will become from the description with reference to accompanying drawings below to embodiment
It is substantially and easy to understand, wherein：
Fig. 1：Aircraft metallic matrix structure erosion speed monitors sensor probe schematic diagram on-line；
Fig. 2：Corrosion rate changes over curve under different humidity；
Fig. 3：Corrosion progressive damage amount changes over curve.
Wherein：1 is tubular protective layer, and 2 is hole sealing agent, and 3 is monitoring probe, and 4 is connecting wire.
Specific embodiment
Embodiments of the invention are described below in detail, the embodiment is exemplary, it is intended to for explaining the present invention, and
It is not considered as limiting the invention.
The present invention proposes that a kind of aircraft metallic matrix structure erosion speed monitors sensor probe on-line, can realize that aircraft is complete
Lifetime inner structure metallic matrix corrosion damage is monitored on-line, can be used for condition maintenarnce with the important technical safeguarded.The spy
Head corrodes speed based on coupling multi-electrode matrix sensing technology principle by monitoring metallic matrix under air weak electrolyte environment
Rate, for corrosive environment characteristic research, structure design against corrosion, use and maintenance, corrosion damage assessment and prediction important technology is provided
Support, for condition maintenarnce reference is provided, determine therefrom that optimal maintenance time and maintenance program, be that guarantee aircaft configuration is durable
Property, damage tolerance quality with using safety, service life, continuing airworthiness ability, safeguard and the important means of maintenance cost.
As shown in figure 1, the aircraft metallic matrix structure erosion speed on-line monitoring sensor probe, including tubular protective layer,
Monitoring probe, hole sealing agent and connecting wire.
The tubular protective layer adopts PVC material；Tubular protective layer is cylindrical, internal diameter 7.5mm, external diameter 10mm, height
32mm。
The monitoring probe material is identical with aircraft monitoring portion faces metal material；16 metal electrode probes constitute 4*
4 array configurations, do not contact, probe diameter 1mm, length 15mm between each probe, spacing 2mm between each probe, each probe
Extent of corrosion average magnitude reflect the extent of corrosion of aircraft monitored area surface metal material.
The connecting wire is copper core cable wire, connection monitoring probe and external equipment, plays connection electric action.
The hole sealing agent adopts epoxy resin, is filled in tubular protective layer, plays each monitoring probe of isolation and stationary monitoring
Probe and connecting wire are acted on.
The metallic matrix corrosion rate monitors the basic role principle of sensor probe：It is due to its surface that metal occurs corrosion
The uneven of tissue causes, the uneven potential difference that local is formed in metal surface of this tissue, i.e., in metal surface shape
Into small electrochemical corrosion anode region and cathode chamber, electronics flows to cathode chamber from anode region, and electric current flows to anode from cathode chamber
Area, the continuous corrosion failure of metal.The present invention is divided into metal surface small enough based on coupling multi-electrode matrix sensing technology
Part, each several part independently of one another, and is coupled together these separate parts one path of composition by external circuit wire,
The anode region and cathode chamber of so metal erosion reflection is just simulated.Probe tip electrode material and monitoring metal matrix material
Unanimously, for simulating anode region, when the aircaft configuration metallic matrix of monitoring corrodes, likewise, probe electrode also can occur
Corrosion, loses electronics, measures the electric current between coupling electrode and carries out corresponding signal processing, it is possible to obtain the corruption of anode electrode
Erosion speed, so that it is determined that the corrosion rate of aircaft configuration metallic matrix.
Embodiment 1：
The present embodiment carries out verification experimental verification according to above-mentioned probe designs：Popped one's head under different humidity environment using above-mentioned design
Carry out sensitivity test checking, selected relative humidity conditions are followed successively by 40%, 60%, 80%, 90%, Fig. 2 exists for corrosion rate
Corrosion rate checking example under line monitoring probe different humidity environment.Figure it is seen that when humidity is 40%, 60%, it is rotten
Erosion speed is relatively low, hardly corrodes；At 80%, corrosion rate has and raises by a small margin；When 90%, corrosion rate has bright
Aobvious rising.Usually, when relative humidity is less than 60%, corrosion hardly occurs, and when relative humidity reaches 80%, corrosion is opened
Life is originated, test result is consistent with practical situation, this probe has high sensitivity.
Embodiment 2：
The present embodiment carries out verification experimental verification according to above-mentioned probe designs：Carried out under external field environment using above-mentioned design probe
Accuracy test verifies that 5 plane plate specimens of design carry out contrast test.Follow-on test 5 days, the change of observation probe corrosion rate
Change, calculate accumulation etching extent, as a result such as Fig. 3, and contrasted with the actual etching extent of sample measurement.Test result accumulates 5 days
Corrosion thickness is about 18 μm, and sample is Jing after removing corrosion product and the difference of initial thickness is about 19um, result of the test and reality
Measurement is close, and this probe has good accuracy.
Although embodiments of the invention have been shown and described above, it is to be understood that above-described embodiment is example
Property, it is impossible to limitation of the present invention is interpreted as, one of ordinary skill in the art is in the principle and objective without departing from the present invention
In the case of above-described embodiment can be changed within the scope of the invention, change, replace and modification.
Claims (2)
1. a kind of aircraft metallic matrix structure erosion speed monitors sensor probe on-line, it is characterised in that：Including tubular protective layer,
Monitoring probe, hole sealing agent and connecting wire；
The tubular protective layer adopts PVC material；The tubular protective layer geomery and the reserved hole shape in aircraft monitoring position
Unanimously；
The monitoring probe material is identical with aircraft monitoring portion faces metal material；Some monitoring probes constitute array configuration,
Do not contact between each monitoring probe, probe diameter 1mm, spacing 2mm between each probe；
The connecting wire connection monitoring probe and external equipment, play connection electric action；
The hole sealing agent is filled in tubular protective layer, plays each monitoring probe of isolation and stationary monitoring probe and connecting wire is made
With.
2. according to claim 1 a kind of aircraft metallic matrix structure erosion speed monitors sensor probe on-line, and its feature exists
In：The hole sealing agent adopts epoxy resin.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201611112098.5A CN106596387A (en) | 2016-12-07 | 2016-12-07 | Corrosion rate on-line monitoring sensing probe of airplane metal matrix structure |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201611112098.5A CN106596387A (en) | 2016-12-07 | 2016-12-07 | Corrosion rate on-line monitoring sensing probe of airplane metal matrix structure |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN106596387A true CN106596387A (en) | 2017-04-26 |
Family
ID=58596782
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201611112098.5A Pending CN106596387A (en) | 2016-12-07 | 2016-12-07 | Corrosion rate on-line monitoring sensing probe of airplane metal matrix structure |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN106596387A (en) |
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110411935A (en) * | 2019-07-25 | 2019-11-05 | 岭澳核电有限公司 | For assessing the detection device and detection method of metal material homogeneous corrosion |
| CN111103031A (en) * | 2020-01-02 | 2020-05-05 | 北京瑞赛长城航空测控技术有限公司 | Intrinsic safety type oil-water interface detection probe |
| CN113484396A (en) * | 2021-06-24 | 2021-10-08 | 中国电建集团华东勘测设计研究院有限公司 | Corrosion monitoring sensor, monitoring device and monitoring method for coupling four-probe potential drop measurement and tow electrode technology |
| CN113777019A (en) * | 2021-09-30 | 2021-12-10 | 广东建科创新技术研究院有限公司 | Concrete reinforcement local corrosion monitoring method and probe |
| CN114235675A (en) * | 2021-12-08 | 2022-03-25 | 潍柴动力股份有限公司 | Corrosion monitoring system and method for engine exhaust system |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN201637652U (en) * | 2010-03-19 | 2010-11-17 | 南京工业大学 | Double-electrode corrosion measuring sensor |
| CN201662525U (en) * | 2010-04-12 | 2010-12-01 | 天津市水利科学研究院 | Cathode protection monitoring probe and cathode protection monitoring probe monitoring system |
| CN104390907A (en) * | 2014-10-24 | 2015-03-04 | 海南电力技术研究院 | Four-electrode soil corrosion detection probe |
| CN105021519A (en) * | 2015-08-13 | 2015-11-04 | 中国石油化工股份有限公司 | On-line atmospheric corrosion measuring device |
-
2016
- 2016-12-07 CN CN201611112098.5A patent/CN106596387A/en active Pending
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN201637652U (en) * | 2010-03-19 | 2010-11-17 | 南京工业大学 | Double-electrode corrosion measuring sensor |
| CN201662525U (en) * | 2010-04-12 | 2010-12-01 | 天津市水利科学研究院 | Cathode protection monitoring probe and cathode protection monitoring probe monitoring system |
| CN104390907A (en) * | 2014-10-24 | 2015-03-04 | 海南电力技术研究院 | Four-electrode soil corrosion detection probe |
| CN105021519A (en) * | 2015-08-13 | 2015-11-04 | 中国石油化工股份有限公司 | On-line atmospheric corrosion measuring device |
Cited By (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110411935A (en) * | 2019-07-25 | 2019-11-05 | 岭澳核电有限公司 | For assessing the detection device and detection method of metal material homogeneous corrosion |
| CN111103031A (en) * | 2020-01-02 | 2020-05-05 | 北京瑞赛长城航空测控技术有限公司 | Intrinsic safety type oil-water interface detection probe |
| CN113484396A (en) * | 2021-06-24 | 2021-10-08 | 中国电建集团华东勘测设计研究院有限公司 | Corrosion monitoring sensor, monitoring device and monitoring method for coupling four-probe potential drop measurement and tow electrode technology |
| CN113484396B (en) * | 2021-06-24 | 2024-04-09 | 中国电建集团华东勘测设计研究院有限公司 | Corrosion monitoring device and method for coupling four-probe potential drop measurement and tow electrode |
| CN113777019A (en) * | 2021-09-30 | 2021-12-10 | 广东建科创新技术研究院有限公司 | Concrete reinforcement local corrosion monitoring method and probe |
| CN113777019B (en) * | 2021-09-30 | 2024-05-17 | 广东建科创新技术研究院有限公司 | Method and probe for monitoring local corrosion of concrete reinforcing steel bar |
| CN114235675A (en) * | 2021-12-08 | 2022-03-25 | 潍柴动力股份有限公司 | Corrosion monitoring system and method for engine exhaust system |
| CN114235675B (en) * | 2021-12-08 | 2023-12-15 | 潍柴动力股份有限公司 | Corrosion monitoring system and method for engine exhaust system |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN106596387A (en) | Corrosion rate on-line monitoring sensing probe of airplane metal matrix structure | |
| US7388386B2 (en) | Method and apparatus for corrosion detection | |
| CN106596650B (en) | It is a kind of based on graphene/cement composite material to the detection device and detection method of Chloride Ion in Concrete content | |
| JP6574356B2 (en) | Capacitance type corrosion sensor and corrosion detection method | |
| CN105823703B (en) | It is a kind of to wash away under operating mode the device and method for evaluating inhibitor film integrality | |
| CN102353628B (en) | Polarization testing probe and testing method for cathodic protection of underground steel pipelines | |
| JP2014505178A (en) | Cathodic protection monitoring probe | |
| JP2011219173A5 (en) | ||
| JP5780792B2 (en) | System and method for online monitoring of corrosion | |
| CN110455705A (en) | A kind of erosion corrosion monitoring sensor and monitoring method | |
| CN110274869A (en) | A kind of in-situ monitoring experimental rig and method for metal material crevice corrosion | |
| CN106596391A (en) | On-line monitoring sensing probe for corrosion protection of aircraft structure coating | |
| JP2011174823A (en) | Crack monitoring device and crack monitoring method | |
| CN110044976A (en) | For detecting the interdigital capacitive sensor of Q235 corrosion of carbon steel | |
| KR100828829B1 (en) | A corrosion test equipment for vehicle's electric parts | |
| CN106441500A (en) | Electric-conductive liquid level sensor applied to severe environments | |
| JP6574355B2 (en) | Corrosion sensor and corrosion detection method | |
| CN1657902A (en) | On-line monitoring method for failure state of metal and protection layer inter face | |
| TW201821786A (en) | Coating corrosion accelerating test method capable of shortening the test cycle by generating a special corrosion accelerating effect different from the corrosion factor reaction | |
| JP5956368B2 (en) | Corrosion potential sensor | |
| CN214585052U (en) | Coating sensor probe device | |
| RU149571U1 (en) | BIMETALLIC ELECTRODE DEVICE FOR EVALUATING CORROSION SPEED | |
| Muchaidze et al. | Steel reinforcement corrosion detection with coaxial cable sensors | |
| CN109269974A (en) | A kind of test method of the online Electrochemical corrosion rate of boiler | |
| Hurley et al. | A condition monitor for atmospheric induced stress corrosion cracking |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| WD01 | Invention patent application deemed withdrawn after publication | ||
| WD01 | Invention patent application deemed withdrawn after publication |
Application publication date: 20170426 |