CN106442285A - Corrosion testing method for anti-corrosion protection capability of exposed part of lower surface of aircraft - Google Patents
Corrosion testing method for anti-corrosion protection capability of exposed part of lower surface of aircraft Download PDFInfo
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- CN106442285A CN106442285A CN201610805436.7A CN201610805436A CN106442285A CN 106442285 A CN106442285 A CN 106442285A CN 201610805436 A CN201610805436 A CN 201610805436A CN 106442285 A CN106442285 A CN 106442285A
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- 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
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Abstract
The invention discloses a corrosion testing method for anti-corrosion protection capability of an exposed part of the lower surface of an aircraft. The corrosion testing method for the anti-corrosion protection capability of the exposed part of the lower surface of the aircraft comprises the following steps that 1, damp and hot exposure testing is conducted on the exposed part of the lower surface of the aircraft; 2, ultraviolet radiation testing is conducted on the exposed part of the lower surface of the aircraft; 3, thermal shock testing is conducted on the exposed part of the lower surface of the aircraft; 4, low-temperature fatigue testing is conducted on the exposed part of the lower surface of the aircraft; 5, salt spray testing is conducted on the exposed part of the lower surface of the aircraft; 6, the steps from first to fifth are executed repeatedly. According to the corrosion testing method for the anti-corrosion protection capability of the exposed part of the lower surface of the aircraft, multiple corrosive environment factors are integrated into the testing method, accelerated testing is conducted by means of the testing method, the anti-corrosion protection capability of a corrosion protection system, subjected to seawater flushing, on the lower surface of the aircraft can be verified more truly in a short time, and corrosion accidents are avoided.
Description
Technical field
The present invention relates to aero-manufacturing technology field, the anticorrosive protection of more particularly to a kind of aircraft lower surface exsertion part
The corrosion tests of ability.
Background technology
Some aircrafts may be exposed in marine corrosion environment for a long time.Now, aircraft lower surface stands seawater scouring, pole
Significant corrosion problems easily occur, therefore it is required that the protection system of aircraft lower surface has higher corrosion protection ability.
The checking of structure erosion protection system anti-corrosion effects typically can adopt field test.Field test is close
Actual Service Environment, its result have the advantages that true, reliable, but needed for field test, the cycle is longer, according to
The difference of verified content, typically needs 8～10 years.
Thus, it is desirable to have a kind of technical scheme come to overcome or at least mitigate prior art at least one drawbacks described above.
Content of the invention
It is an object of the invention to provide a kind of corrosion test side of the anticorrosive protective capacities of aircraft lower surface exsertion part
Method come to overcome or at least mitigate prior art at least one of drawbacks described above.
For achieving the above object, the present invention provides a kind of corrosion examination of the anticorrosive protective capacities of aircraft lower surface exsertion part
Proved recipe method, is subject to the anticorrosive protective capacities of corrosion protection system of seawater scouring for check flight, and described aircraft lower surface exposes
The corrosion tests of the anticorrosive protective capacities in position comprise the steps：Step 1：Carry out wet for aircraft lower surface exsertion part
Beat exposure is tested；Step 2：Carry out ultraviolet radiation test for aircraft lower surface exsertion part；Step 3：Outside for aircraft lower surface
Dew position carries out thermal shock test；Step 4：Carry out fatigue testing at low temperature for aircraft lower surface exsertion part；Step 5：For aircraft
Lower surface exsertion part carries out salt spray test；Step 6：Repeating said steps 1 are to step 5；Wherein, carry out damp heat exposure test
Experimental condition is：Relative humidity RH >=95%, temperature T=43 DEG C, open-assembly time 12d；Carry out the test of ultraviolet radiation test
Condition is：Radiation intensity Q=50W/m2To 70W/m2, temperature T=55 DEG C, 9 hours open-assembly times；Carry out the examination of thermal shock test
The condition of testing is：Temperature T=155 DEG C, intensification 10min to 15min, temperature retention time 1.5 hours；Carry out the test of fatigue testing at low temperature
Condition is：Temperature T=-53 DEG C, f=5Hz, apply 500 constant amplitude load, load σ max=110MPa, σ min=20MPa；Enter
The experimental condition of row salt spray test is：Temperature T=35 DEG C, solution NaCl concentration 5%, salt fog deposition 1ml/h × 80cm2Extremely
2ml/h×80cm2, 7 days open-assembly times, pH value be 4.5 to 5.0 acidic salt spray corrosion 3 days 23 hours 40 minutes after, in pH
It is worth corrosion 20min under the acid salt fog for 2.0.
Preferably, the repetition period of described step 6 is 8 to 12 cycle periods.
The corrosion tests of the anticorrosive protective capacities of aircraft lower surface exsertion part of the application are by multiple corrosive environments
Factor is integrated among test method, by accelerated test is carried out using this test method, can be more real at short notice
Verify the anticorrosive protective capacities of corrosion protection system that aircraft lower surface is subject to seawater scouring, it is to avoid the generation of corrosion accident.From
And reach shortening contrast verification required time, improve contrast verification efficiency it is ensured that aircraft utilization safety purpose.
Brief description
Fig. 1 is the corrosion test of the anticorrosive protective capacities of aircraft lower surface exsertion part according to a first embodiment of the present invention
The schematic flow sheet of method.
Specific embodiment
For making purpose, technical scheme and advantage that the present invention is implemented clearer, below in conjunction with the embodiment of the present invention
Accompanying drawing, the technical scheme in the embodiment of the present invention is further described in more detail.In the accompanying drawings, identical from start to finish or class
As the label element that represents same or similar element or there is same or like function.Described embodiment is the present invention
A part of embodiment, rather than whole embodiments.Embodiment below with reference to Description of Drawings is exemplary it is intended to use
In the explanation present invention, and it is not considered as limiting the invention.Based on the embodiment in the present invention, ordinary skill people
The every other embodiment that member is obtained under the premise of not making creative work, broadly falls into the scope of protection of the invention.Under
Face combines accompanying drawing and embodiments of the invention is described in detail.
In describing the invention it is to be understood that term " " center ", " longitudinal ", " horizontal ", "front", "rear",
The orientation of instruction such as "left", "right", " vertical ", " level ", " top ", " bottom " " interior ", " outward " or position relationship are based on accompanying drawing institute
The orientation showing or position relationship, are for only for ease of the description present invention and simplify description, rather than the dress of instruction or hint indication
Put or element must have specific orientation, with specific azimuth configuration and operation, therefore it is not intended that protecting to the present invention
The restriction of scope.
Fig. 1 is the corrosion test of the anticorrosive protective capacities of aircraft lower surface exsertion part according to a first embodiment of the present invention
The schematic flow sheet of method.
The corrosion tests of the anticorrosive protective capacities of aircraft lower surface exsertion part as shown in Figure 1, winged for checking
Machine is subject to the anticorrosive protective capacities of corrosion protection system of seawater scouring, this anticorrosive protective capacities of aircraft lower surface exsertion part
Corrosion tests comprise the steps：Step 1：Carry out damp heat exposure test for aircraft lower surface exsertion part；Step 2：For
Aircraft lower surface exsertion part carries out ultraviolet radiation test；Step 3：Carry out thermal shock examination for aircraft lower surface exsertion part
Test；Step 4：Carry out fatigue testing at low temperature for aircraft lower surface exsertion part；Step 5：Carry out for aircraft lower surface exsertion part
Salt spray test；Step 6：Repeat step 1 is to step 5；Wherein, the experimental condition carrying out damp heat exposure test is：Relative humidity RH
>=95%, temperature T=43 DEG C, open-assembly time 12d；
The experimental condition carrying out ultraviolet radiation test is：Radiation intensity Q=50W/m2To 70W/m2, temperature T=55 DEG C,
9 hours open-assembly times；
The experimental condition carrying out thermal shock test is：Temperature T=155 DEG C, intensification 10min to 15min, temperature retention time 1.5
Hour；
The experimental condition carrying out fatigue testing at low temperature is：Temperature T=-53 DEG C, f=5Hz, apply 500 constant amplitude load, carry
Lotus σ max=110MPa, σ min=20MPa；
The experimental condition carrying out salt spray test is：Temperature T=35 DEG C, solution NaCl concentration 5%, salt fog deposition 1ml/h
×80cm2To 2ml/h × 80cm2, 7 days open-assembly times, 40 points of acidic salt spray corrosion 3 days 23 hours being 4.5 to 5.0 in pH value
Zhong Hou, corrodes 20min under the acid salt fog that pH value is 2.0.
Advantageously, the repetition period of step 6 is 8 to 12 cycle periods.
Adopt above-mentioned condition simultaneously, be that the environmental key-element being subject primarily in a year with aircraft includes temperature, humidity, precipitation
Amount, solid sediment, wind, mist, salt fog, seawater, in the air chlorine ion concentration, sulphion concentration and atmosphere pollution and Industry Waste
Gas etc. carries out statistical analysis, obtained by the Main Function time of these environmental key-elements, frequency etc. are carried out equivalent conversion, one
The accelerated corrosion test action effect in cycle, is equivalent to the corrosive environment effect effect that this position is subjected to for a year in outfield military service
Really, project embody external structure exsertion part and be often subject to ultraviolet radiation zone domain ultraviolet, damp and hot, salt fog, thermal shock and
The comprehensive function of fatigue at low temperatures etc., has specific aim and acceleration feature.
Corrosion test to the anticorrosive protective capacities of aircraft lower surface exsertion part of the application by way of example below
Method is described in detail.It should be understood that this is illustrated does not constitute any restriction to the application.
, this first taking the first structure testpieces of any aircraft lower surface exsertion part and the second structural test part as a example
Testpieces and the second testpieces all include by 30CrMnSiA bolt connection 7B04 aluminium alloy and 7B04 aluminium alloy structure, the
One testpieces and the second testpieces are respectively adopted different protective coating systems.
Specifically, the protective coating system of the first testpieces is：To aluminum alloy surface sulfur acid anodizing, bichromate is filled
Process；
Spray aviation Primers Primer to after aluminum alloy part surface treatment, coating layer thickness controls at 25 μm～35 μm；
Outer surface spraying enamel paint after assembling, coating layer thickness controls at 40 μm～60 μm.
The protective coating system of the second testpieces：
To aluminum alloy surface sulfur acid anodizing, bichromate filling is processed；
To spray-applied primer after aluminum alloy part surface treatment, coating layer thickness controls at 25 μm～35 μm；
Coatings are glued to securing member and carries out hygrometric state assembling；
Outer surface spraying enamel paint after assembling, coating layer thickness controls at 40 μm～60 μm；
Inner surface spraying enamel paint after assembling, coating layer thickness controls at 40 μm～60 μm.
The corrosion of the application is adopted to try to using the first testpieces of different protective coating systems and the second testpieces
Proved recipe method is tested.
Verification the verifying results：
Accelerated corrosion contrast test carries out 6 altogether and circulates, about 6 months.First testpieces and the second testpieces are respectively the 2nd
Corrosion in cycle (about 2 months), the 4th cycle (about April).Test carries out having occurred to the first testpieces during the 6th cycle (6)
Serious corrosion, and the second testpieces extent of corrosion is relatively low.So far contrast test terminates, through the accelerated test of about 10 months,
The corrosion protection system anti-corrosion effects that the second testpieces can be verified will be substantially better than the first testpieces, has reached shortening examination
The purpose that cycle of testing completes contrast verification simultaneously.
Last it is to be noted that：Above example only in order to technical scheme to be described, is not intended to limit.To the greatest extent
Pipe has been described in detail to the present invention with reference to the foregoing embodiments, it will be understood by those within the art that：It is still
Technical scheme described in foregoing embodiments can be modified, or wherein some technical characteristics are carried out with equivalent replacing
Change；And these modifications or replacement, do not make the essence of appropriate technical solution depart from the essence of various embodiments of the present invention technical scheme
God and scope.
Claims (2)
1. a kind of corrosion tests of the anticorrosive protective capacities of aircraft lower surface exsertion part, are rushed by seawater for check flight
The anticorrosive protective capacities of corrosion protection system of brush is it is characterised in that the anticorrosive protection energy of described aircraft lower surface exsertion part
The corrosion tests of power comprise the steps：
Step 1：Carry out damp heat exposure test for aircraft lower surface exsertion part；
Step 2：Carry out ultraviolet radiation test for aircraft lower surface exsertion part；
Step 3：Carry out thermal shock test for aircraft lower surface exsertion part；
Step 4：Carry out fatigue testing at low temperature for aircraft lower surface exsertion part；
Step 5：Carry out salt spray test for aircraft lower surface exsertion part；
Step 6：Repeating said steps 1 are to step 5；Wherein,
The experimental condition carrying out damp heat exposure test is：Relative humidity RH >=95%, temperature T=43 DEG C, open-assembly time 12d；
The experimental condition carrying out ultraviolet radiation test is：Radiation intensity Q=50W/m2To 70W/m2, temperature T=55 DEG C, expose
9 hours time；
The experimental condition carrying out thermal shock test is：Temperature T=155 DEG C, intensification 10min to 15min, temperature retention time 1.5 hours；
The experimental condition carrying out fatigue testing at low temperature is：Temperature T=-53 DEG C, f=5Hz, apply 500 constant amplitude load, load σ
Max=110MPa, σ min=20MPa；
The experimental condition carrying out salt spray test is：Temperature T=35 DEG C, solution NaCl concentration 5%, salt fog deposition 1ml/h ×
80cm2To 2ml/h × 80cm2, 7 days open-assembly times, the acidic salt spray corrosion 3 days 23 hours 40 minutes being 4.5 to 5.0 in pH value
Afterwards, corrode 20min under the acid salt fog that pH value is 2.0.
2. the corrosion tests of the anticorrosive protective capacities of aircraft lower surface exsertion part as claimed in claim 1, its feature
It is, the repetition period of described step 6 is 8 to 12 cycle periods.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610805436.7A CN106442285A (en) | 2016-09-07 | 2016-09-07 | Corrosion testing method for anti-corrosion protection capability of exposed part of lower surface of aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610805436.7A CN106442285A (en) | 2016-09-07 | 2016-09-07 | Corrosion testing method for anti-corrosion protection capability of exposed part of lower surface of aircraft |
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| Publication Number | Publication Date |
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| CN106442285A true CN106442285A (en) | 2017-02-22 |
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| CN201610805436.7A Pending CN106442285A (en) | 2016-09-07 | 2016-09-07 | Corrosion testing method for anti-corrosion protection capability of exposed part of lower surface of aircraft |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112666003A (en) * | 2020-12-04 | 2021-04-16 | 中国航发北京航空材料研究院 | Accelerated test method for simulating coupling effect of carrier-based platform multi-element environmental factors |
Citations (4)
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| US5243298A (en) * | 1991-11-04 | 1993-09-07 | Teledyne Ryan Aeronautical, Division Of Teledyne Industries, Inc. | Corrosion monitor by creating a galvanic circuit between an anode wire and a test structure |
| CN101712563A (en) * | 2009-12-16 | 2010-05-26 | 西安超码科技有限公司 | Surface anti-oxidation processing method for aircraft carbon brake disc |
| CN103439202A (en) * | 2013-08-19 | 2013-12-11 | 北京航空航天大学 | System for testing fatigue in corrosion environment |
| CN104493431A (en) * | 2014-11-19 | 2015-04-08 | 中国航空工业集团公司沈阳飞机设计研究所 | Method for airplane folding mechanism to resist stress corrosion |
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Patent Citations (4)
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|---|---|---|---|---|
| US5243298A (en) * | 1991-11-04 | 1993-09-07 | Teledyne Ryan Aeronautical, Division Of Teledyne Industries, Inc. | Corrosion monitor by creating a galvanic circuit between an anode wire and a test structure |
| CN101712563A (en) * | 2009-12-16 | 2010-05-26 | 西安超码科技有限公司 | Surface anti-oxidation processing method for aircraft carbon brake disc |
| CN103439202A (en) * | 2013-08-19 | 2013-12-11 | 北京航空航天大学 | System for testing fatigue in corrosion environment |
| CN104493431A (en) * | 2014-11-19 | 2015-04-08 | 中国航空工业集团公司沈阳飞机设计研究所 | Method for airplane folding mechanism to resist stress corrosion |
Non-Patent Citations (1)
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| 刘文珽 等: ""飞机结构腐蚀部位涂层加速试验环境谱研究"", 《北京航空航天大学学报》 * |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112666003A (en) * | 2020-12-04 | 2021-04-16 | 中国航发北京航空材料研究院 | Accelerated test method for simulating coupling effect of carrier-based platform multi-element environmental factors |
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Application publication date: 20170222 |