CN204575503U - A kind of proving installation of simulating aviation component Service Environment - Google Patents
A kind of proving installation of simulating aviation component Service Environment Download PDFInfo
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- CN204575503U CN204575503U CN201520211441.6U CN201520211441U CN204575503U CN 204575503 U CN204575503 U CN 204575503U CN 201520211441 U CN201520211441 U CN 201520211441U CN 204575503 U CN204575503 U CN 204575503U
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- control system
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- service environment
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Abstract
A kind of proving installation of simulating aviation component Service Environment, comprise power supply, master control system, salt fog generation system, test macro, environmental control system and salt-fog test box body, salt fog generation system, test macro, environmental control system are positioned at salt spray test chamber box house, it is outside that master control system is positioned at salt-fog test box body, test macro, master control system, environmental control system are connected successively, and master control system is connected with salt fog generation system.This device comparatively truly can reflect the environmental baseline in the actual Service Environment of aircraft, can also carry out accelerated test, greatly shorten test period.
Description
Technical field
The utility model belongs to material analysing equipment technical field, specifically relates to a kind of proving installation of simulating aviation component Service Environment.
Background technology
Corrosion of metal damage, throughout the every field of national economy, causes very huge economic loss.In the U.S., corrode the loss caused and account for 4.7% of its total value of production in national economy.During 11th Five-Year, China is about 2 trillion yuan owing to corroding the direct or indirect loss caused.Due to severe Service Environment, corrosion damage is more obvious in the harm of aerospace.Between 10 years of statistics U.S. 1994 to 2004, about 100,000,000 mean manhours to repairs are for solving corrosion and etching detection work every year.Average 7.6 maintenance hour/pilot time, account for 36% of the whole maintenance and inspection time, the expense being generally used for etching detection and repairing accounts for greatly 25% of total maintenance expense.And the part catastrophic failure that corrosion can cause, cause a serious accident.
The corrosion resistance of airplane parts is the important measurement index of workpiece performance always.The experiment of current research part corrosion resistance generally adopts salt spray corrosion test machine, but the Service Environment of aircraft is very complicated, comprises the high-speed air environment etc. when humidity environment when airport is parked, temperature environment, salt mist environment, flight.Can not the decay resistance of piece surface under simulated aircraft Service Environment simply by salt mist experiment machine.So developing a kind of military service performance of proving installation to research aircraft component that can be similar to aviation component Service Environment is significantly.
Summary of the invention
Based on this, the blank that the utility model is to make up conventional apparatus provides a kind of proving installation of simulating aviation component Service Environment, and this device can make aviation component carry out environmental longevity aging test in salt fog and wind environment.
Its technical scheme is as follows:
A kind of proving installation of simulating aviation component Service Environment, comprise power supply, master control system, salt fog generation system, test macro, environmental control system and salt-fog test box body, described salt fog generation system, test macro, environmental control system are positioned at described salt spray test chamber box house, it is outside that described master control system is positioned at described salt-fog test box body, described test macro, master control system, environmental control system are connected successively, and described master control system is connected with salt fog generation system.
Below the technical solution of the utility model is described further:
Described salt fog generation system comprises air compressor, air lance, suction hose, solution container, described suction hose is connected with described solution container, described air compressor is connected with described air lance, the nozzle of described air lance is perpendicular near one end of described suction hose, and the air that the nozzle of described air lance sprays directly is sprayed onto specimen surface.
Described test macro comprises Research on Automatic Measuring System of Temperature and humidity field test system.
Described environmental control system comprises temperature-adjusting heating device, water receptacle, humidity heating arrangement, and described humidity heating arrangement is positioned at water receptacle inside.
Described Research on Automatic Measuring System of Temperature is made up of temperature sensor, and described temperature sensor is equidistantly uniformly distributed on salt spray test chamber box house surface.
Described humidity field test system is made up of humidity sensor, and described humidity sensor is equidistantly uniformly distributed on salt spray test chamber box house surface.
Described temperature-adjusting heating device is positioned at salt spray test chamber box house surface surrounding.
The beneficial effects of the utility model are: can simulate preferably the salt mist environment of gas impact and air in aircraft flight.And according to the temperature humidity set, automatically can be controlled by test macro, master control system and environmental control system, the temperature humidity environment in simulated aircraft military service process.So this device comparatively truly can reflect the environmental baseline in the actual Service Environment of aircraft, can also accelerated test be carried out, greatly shorten test period.
Accompanying drawing explanation
Fig. 1 is a kind of general structure schematic diagram of simulating the proving installation of aviation component Service Environment of the utility model.
Fig. 2 is a kind of principle schematic simulating the proving installation of aviation component Service Environment of the utility model.
Description of reference numerals: 1, power supply, 2, master control system, 3, salt fog generation system, 4, environmental control system, 5, test macro, 6, salt-fog test box body, 7, air compressor, 8, air lance, 9, suction hose, 10, solution container, 11, sample, 12, temperature sensor, 13, humidity sensor, 14, temperature-adjusting heating device, 15, water receptacle, 16, humidity heating arrangement.
Embodiment
Below in conjunction with accompanying drawing, the utility model is described in detail.
A kind of proving installation of simulating aviation component Service Environment as shown in Figure 1, comprise power supply 1, master control system 2, salt fog generation system 3, environmental control system 4, test macro 5 and salt-fog test box body 6, it is inner that described salt fog generation system 3, test macro 5, environmental control system 4 are positioned at described salt-fog test box body 6, it is outside that described master control system 2 is positioned at described salt-fog test box body 6, described test macro 5, master control system 2, environmental control system 4 are connected successively, and described master control system 2 is connected with salt fog generation system 3.
A kind of proving installation of simulating aviation component Service Environment as shown in Figure 2, described salt fog generation system 3 comprises air compressor 7, air lance 8, suction hose 9, solution container 10, described suction hose 9 is connected with described solution container 10, described air compressor 7 is connected with described air lance 8, the nozzle of described air lance 8 is perpendicular near one end of described suction hose 9, and the air that the nozzle of described air lance 8 sprays directly is sprayed onto sample 11 surface.Described environmental control system 4 comprises temperature-adjusting heating device 14, water receptacle 15, humidity heating arrangement 16, and it is inner setting in water receptacle 15 that described humidity adds hot charging 16.Described test macro 5 comprises Research on Automatic Measuring System of Temperature and humidity field test system.Described Research on Automatic Measuring System of Temperature is made up of temperature sensor 12, and described temperature sensor 12 is equidistantly uniformly distributed in salt-fog test box body 6 interior surface.Described humidity field test system is made up of humidity sensor 13, and described humidity sensor 13 is equidistantly uniformly distributed in salt-fog test box body 6 interior surface.Described temperature-adjusting heating device 14 is positioned at salt-fog test box body 6 interior surface surrounding.
Principle of work of the present utility model is: the high velocity air that the gases at high pressure utilizing air compressor 7 to produce produce through the nozzle of air lance 8, negative pressure is formed on suction hose 9 top, solution in solution container 10 is sucked out through suction hose 9 under suction function, effect through high velocity air forms salt fog, the high velocity air being mingled with salt fog directly sprays to test specimen 11 surface, the salt fog in simulated aircraft flight course and the coefficient Service Environment of high velocity air.Temperature control system and moisture control system pass through the temperature humidity environment in closed-loop control simulated aircraft military service process according to the temperature humidity condition that master control system sets.
Before the use, will add in solution container 10 and prepare salt fog solution in advance, modulator approach is: every pure distilled water of 93ml, adds 5g pure sodium chloride, 1g magnesium chloride, 1g calcium sulphate.Distilled water is added in advance in water receptacle 15.
During use, first connect gas source switch and power supply, regulate air compressor pressure.Switch on power, set the temperature required and humidity of experiment on the controller, temperature is generally 35 degrees Celsius.Open salt fog generation system, after machine to be tested runs 5 minutes, put into test specimen and test.
Claims (7)
1. simulate the proving installation of aviation component Service Environment for one kind, it is characterized in that, comprise power supply, master control system, salt fog generation system, test macro, environmental control system and salt-fog test box body, described salt fog generation system, test macro, environmental control system are positioned at described salt spray test chamber box house, it is outside that described master control system is positioned at described salt-fog test box body, described test macro, master control system, environmental control system are connected successively, and described master control system is connected with salt fog generation system.
2. a kind of proving installation of simulating aviation component Service Environment according to claim 1, it is characterized in that, described salt fog generation system comprises air compressor, air lance, suction hose, solution container, described suction hose is connected with described solution container, described air compressor is connected with described air lance, the nozzle of described air lance is perpendicular near one end of described suction hose, and the air that the nozzle of described air lance sprays directly is sprayed onto specimen surface.
3. a kind of proving installation of simulating aviation component Service Environment according to claim 1, it is characterized in that, described test macro comprises Research on Automatic Measuring System of Temperature and humidity field test system.
4. a kind of proving installation of simulating aviation component Service Environment according to claim 1, is characterized in that, described environmental control system comprises temperature-adjusting heating device, water receptacle, humidity heating arrangement, and described humidity heating arrangement is positioned at water receptacle inside.
5. a kind of proving installation of simulating aviation component Service Environment according to claim 3, it is characterized in that, described Research on Automatic Measuring System of Temperature is made up of temperature sensor, and described temperature sensor is equidistantly uniformly distributed on salt spray test chamber box house surface.
6. a kind of proving installation of simulating aviation component Service Environment according to claim 3, it is characterized in that, described humidity field test system is made up of humidity sensor, and described humidity sensor is equidistantly uniformly distributed on salt spray test chamber box house surface.
7. a kind of proving installation of simulating aviation component Service Environment according to claim 4, is characterized in that, described temperature-adjusting heating device is positioned at salt spray test chamber box house surface surrounding.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201520211441.6U CN204575503U (en) | 2015-04-10 | 2015-04-10 | A kind of proving installation of simulating aviation component Service Environment |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201520211441.6U CN204575503U (en) | 2015-04-10 | 2015-04-10 | A kind of proving installation of simulating aviation component Service Environment |
Publications (1)
| Publication Number | Publication Date |
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| CN204575503U true CN204575503U (en) | 2015-08-19 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN201520211441.6U Expired - Fee Related CN204575503U (en) | 2015-04-10 | 2015-04-10 | A kind of proving installation of simulating aviation component Service Environment |
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Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106443262A (en) * | 2016-10-08 | 2017-02-22 | 浙江大学 | Online salt fog test device for spaceflight electric connector |
| CN112433131A (en) * | 2020-11-10 | 2021-03-02 | 珠海格力电器股份有限公司 | Arc analysis system, method and device |
| CN114993926A (en) * | 2022-07-19 | 2022-09-02 | 中国电器科学研究院股份有限公司 | Novel salt spray environment test system and method |
-
2015
- 2015-04-10 CN CN201520211441.6U patent/CN204575503U/en not_active Expired - Fee Related
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106443262A (en) * | 2016-10-08 | 2017-02-22 | 浙江大学 | Online salt fog test device for spaceflight electric connector |
| CN106443262B (en) * | 2016-10-08 | 2019-06-07 | 浙江大学 | A kind of online salt spray test device of Aerospace Electric Connector |
| CN112433131A (en) * | 2020-11-10 | 2021-03-02 | 珠海格力电器股份有限公司 | Arc analysis system, method and device |
| CN114993926A (en) * | 2022-07-19 | 2022-09-02 | 中国电器科学研究院股份有限公司 | Novel salt spray environment test system and method |
| CN114993926B (en) * | 2022-07-19 | 2022-12-20 | 中国电器科学研究院股份有限公司 | Novel salt spray environment test system and method |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20150819 Termination date: 20180410 |
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| CF01 | Termination of patent right due to non-payment of annual fee |