CN208672312U - The low-temp low-pressure experimental cabin of simulated altitude - Google Patents
The low-temp low-pressure experimental cabin of simulated altitude Download PDFInfo
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- CN208672312U CN208672312U CN201821433998.4U CN201821433998U CN208672312U CN 208672312 U CN208672312 U CN 208672312U CN 201821433998 U CN201821433998 U CN 201821433998U CN 208672312 U CN208672312 U CN 208672312U
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Abstract
The utility model discloses a kind of low-temp low-pressure experimental cabins of simulated altitude, the outlet of refrigeration equipment is connected by the air inlet of pipeline and experimental cabin, the inner wall of experimental cabin is equipped with pressure sensor and temperature sensor, experimental cabin is controlled to a vacuum pump by vacuum-pumping tube, the side wall of experimental cabin is connected to the first cavity, the junction of experimental cabin and the first cavity is equipped with the first electromagnet of annular, and the first iron ball is equipped in the first cavity, and the bottom in the first cavity is equipped with the second electromagnet of annular；First cavity is connect by pipeline with the second cavity, and the junction of pipeline and the second cavity is equipped with the 4th electromagnet of annular, and the second iron ball is equipped in the second cavity, and the bottom in the second cavity is equipped with the third electromagnet of annular；Second cavity is connect by connecting tube with dry air storage tank.The utility model is at low cost, and structure is simple, solves in the prior art that experimental cabin leakproofness is poor, the short problem of service life.
Description
Technical field
The utility model belongs to aero-engine detection technique field, is related to a kind of low-temp low-pressure test of simulated altitude
Cabin.
Background technique
The one kind of aviation piston engine as internal combustion engine, with the increase of aircraft altitude, environment atmospheric pressure
It is reduced with constant temperature, the air of low-temp low-pressure enters in engine, participates in acting；In order to obtain aviation piston engine in height
Empty performance data, most of way are just to be tested higher to height above sea level, and higher cost, real hypo height has office
It is sex-limited, it is difficult to obtain more test datas；The experimental cabin in partial simulation high-altitude is passed directly into standard atmospheric pressure in vacuum breaker
Air, larger to the impact force of experimental cabin, experimental cabin easy to damage shortens the working life, reduce sealing performance.Therefore one is needed
The low-temp low-pressure experimental cabin of kind simulated altitude, for detecting the performance of aero-engine.
Summary of the invention
To solve the above-mentioned problems, the utility model provides a kind of low-temp low-pressure experimental cabin of simulated altitude, at low cost, knot
Structure is simple, solves in the prior art that experimental cabin leakproofness is poor, the short problem of service life.
The utility model the technical scheme adopted is that a kind of simulated altitude low-temp low-pressure experimental cabin, refrigeration equipment
Outlet is connected by the air inlet of pipeline and experimental cabin, is equipped with the first electromagnetism on the pipeline between refrigeration equipment and experimental cabin
Valve, is equipped with filter plate at the air inlet of experimental cabin, and the inner wall of experimental cabin is equipped with pressure sensor and temperature sensor, in experimental cabin
Equipped with running support, aero-engine is installed on running support, the exhaust outlet of aero-engine passes through exhaust pipe and waste gas collection box
Connection；Experimental cabin is controlled to a vacuum pump by vacuum-pumping tube, and vacuum-pumping tube is equipped with second solenoid valve；The side wall of experimental cabin and
The junction of the connection of one cavity, experimental cabin and the first cavity is equipped with the first electromagnet of annular, is equipped with the first iron in the first cavity
Ball, the bottom level in the first cavity are equipped with the second electromagnet of annular；First cavity is connect by pipeline with the second cavity, is managed
The junction of road and the second cavity is equipped with the 4th electromagnet of annular, is equipped with the second iron ball in the second cavity, in the second cavity
Bottom level is equipped with the third electromagnet of annular；Second cavity connect by connecting tube with dry air storage tank, connecting tube with do
The caliber of dry air reservoir connecting pin is less than the caliber with the second cavity connecting pin, the pipeline between the first cavity and the second cavity
Caliber is less than the connector bore of experimental cabin and the first cavity；Pressure sensor passes through the switch of the second microcontroller and vacuum pump
Connection, temperature sensor are connect by the first microcontroller with the first solenoid valve.
The utility model is further characterized in that further, first microcontroller, the second microcontroller are all made of
C8051F020 single-chip microcontroller.
Further, the model PY210 of the pressure sensor.
Further, the model DS18B20 of the temperature sensor.
Further, the filter plate is arc.
The beneficial effects of the utility model are: refrigeration equipment is for making air be down to required temperature, cold air is through filter plate mistake
Enter in experimental cabin after filter, filter out the impurity in air, improves the air quality in experimental cabin；Start vacuum pump, so that examination
Hatch checking is hypobaric hypoxia, low temperature environment, simulated altitude environment；The atmospheric pressure in experimental cabin is detected by pressure sensor, is led to
Excess temperature sensor detects temperature, and pressure sensor is connected by the switch of the second microcontroller and vacuum pump, temperature sensor
It is connect by the first microcontroller with the first solenoid valve, for adjusting atmospheric pressure in experimental cabin and temperature to desirable value, is closed
The first solenoid valve, second solenoid valve are closed, the first electromagnet is powered, and experimental cabin is closed hypobaric hypoxia, low temperature environment, is testing
Performance detection is carried out to aero-engine in cabin；The utility model is able to detect different atmospheric pressures aero-engine at a temperature of
Performance.
After the completion of detection, third electromagnet, the second electromagnet are powered, the 4th electromagnet, the power-off of the first electromagnet, dry empty
Constant pressure and dry air in gas storage tank successively passes through connecting tube, the second cavity, the first cavity, into experimental cabin, due to along into
The caliber of the connecting tube in gas direction is gradually increased, and the pipe diameter between the first cavity and the second cavity is less than experimental cabin and first
The connector bore of cavity, during entering experimental cabin, as caliber increases, pressure is gradually reduced dry air, and existing
Have in technology and directly compare the mode that atmospheric air is passed through experimental cabin progress vacuum breaker, the utility model avoids normal atmosphere
Direct impact of the pressure to experimental cabin, extends the service life of equipment.
In addition, the air being passed through uses dry air, it is ensured that experimental cabin is in dry environment in the case where not using,
Damage of the moisture in air to experimental cabin is reduced, its leakproofness is improved.
Detailed description of the invention
In order to illustrate the embodiment of the utility model or the technical proposal in the existing technology more clearly, below will be to embodiment
Or attached drawing needed to be used in the description of the prior art is briefly described, it should be apparent that, the accompanying drawings in the following description is only
It is some embodiments of the utility model, for those of ordinary skill in the art, in the premise not made the creative labor
Under, it is also possible to obtain other drawings based on these drawings.
Fig. 1 is the structural schematic diagram of the utility model embodiment.
In figure, 1. experimental cabins, 2. refrigeration equipments, 3. running supports, 4. aero-engines, 5. exhaust pipes, 6. waste gas collection box,
7. the first solenoid valve, 8. filter plates, 9. pressure sensors, 10. first cavitys, 11. second cavitys, 12. second solenoid valves, 13.
Vacuum-pumping tube, 14. first microcontrollers, 15. vacuum pumps, 16. temperature sensors, 17. first electromagnet, 18. second electromagnet,
19. the first iron ball, 20. dry air storage tanks, 21. third electromagnet, 22. second iron balls, 23. the 4th electromagnet, 24. connections
Pipe, 25. second microcontrollers.
Specific embodiment
Below in conjunction with the utility model embodiment, the technical scheme in the embodiment of the utility model is carried out clear, complete
Site preparation description, it is clear that the described embodiments are only a part of the embodiments of the utility model, instead of all the embodiments.
Based on the embodiments of the present invention, obtained by those of ordinary skill in the art without making creative efforts
Every other embodiment, fall within the protection scope of the utility model.
The structure of the utility model embodiment, as shown in Figure 1, the outlet of refrigeration equipment 2 by pipeline and experimental cabin 1 into
Port connects, and is equipped with the first solenoid valve 7 on the pipeline between refrigeration equipment 2 and experimental cabin 1, sets at the air inlet of experimental cabin 1
There is filter plate 8, filter plate 8 is arc, to increase the contact area with air, improves filter efficiency；The inner wall of experimental cabin 1 is equipped with
Pressure sensor 9 and temperature sensor 16, experimental cabin 1 is interior to be equipped with running support 3, is equipped with aero-engine 4 on running support 3, navigates
The exhaust outlet of empty engine 4 is connect by exhaust pipe 5 with waste gas collection box 6；Experimental cabin 1 passes through vacuum-pumping tube 13 and vacuum pump 15
Connection, vacuum-pumping tube 13 are equipped with second solenoid valve 12；The side wall of experimental cabin 1 is connected to the first cavity 10, experimental cabin 1 and first
The junction of cavity 10 is equipped with the first electromagnet 17 of annular, is equipped with the first iron ball 19 in the first cavity 10, in the first cavity 10
Bottom level be equipped with annular the second electromagnet 18；First cavity 10 is connect by pipeline with the second cavity 11, pipeline and the
The junction of two cavitys 11 is equipped with the 4th electromagnet 23 of annular, is equipped with the second iron ball 22, the second cavity 11 in the second cavity 11
Interior bottom level is equipped with the third electromagnet 21 of annular；Second cavity 11 is connected by connecting tube 24 and dry air storage tank 20
It connects, the caliber of connecting tube 24 and 20 connecting pin of dry air storage tank is less than the caliber with 11 connecting pin of the second cavity, i.e., along air inlet
The caliber of the connecting tube 24 in direction is gradually increased；Pipe diameter between first cavity 10 and the second cavity 11 is less than experimental cabin 1
With the connector bore of the first cavity 10, the diameter of the diameter of the second iron ball 22 less than the first iron ball 19.
Pressure sensor 9 is connect by the second microcontroller 25 with the switch of vacuum pump 15, and temperature sensor 16 passes through the
One microcontroller 14 is connect with the first solenoid valve 7；First microcontroller 14, that the second microcontroller 25 is all made of C8051F020 is mono-
Piece machine, the speed of service are fast；The model PY210 of pressure sensor 9 spreads silicon pressure-sensitive chip using import, has shock resistance, resistance to tired
Labor, high reliablity, compact structure, feature easy for installation；The model DS18B20 of temperature sensor 16, is sealed using stainless steel
Dress, shock resistance, high reliablity.
Refrigeration equipment 2, which refers to, to freeze to the equipment of conditions of certain gas flow air inlet dynamic continuous cooling, such as expansion turbine, liquid
Nitrogen refrigeration.
The working principle of the utility model embodiment: air enters refrigeration equipment 2, and refrigeration equipment 2 is for being down to air
Required temperature, cold air enter in experimental cabin 1 after the filtering of filter plate 8, filter out the impurity in air, improve in experimental cabin 1
Air quality；Second solenoid valve 12 is opened, the 4th electromagnet 23, the first electromagnet 17 are powered, third electromagnet 21, the second electromagnetism
Iron 18 powers off, and starts vacuum pump 15, so that experimental cabin 1 is hypobaric hypoxia and low temperature environment, simulated altitude environment；It is passed by pressure
Sensor 9 detects the atmospheric pressure in experimental cabin 1, detects temperature by temperature sensor 16, pressure sensor 9 passes through the second micro-control
Device 25 processed is connect with the switch of vacuum pump 15, and temperature sensor 16 is connect by the first microcontroller 14 with the first solenoid valve 7, is used
In adjusting atmospheric pressure in experimental cabin 1 and temperature to desirable value, the first solenoid valve 7 and second solenoid valve 12, experimental cabin 1 are closed
For closed hypobaric hypoxia, low temperature environment, performance detection is carried out to aero-engine 4 in experimental cabin 1；After the completion of detection, the
Three electromagnet 21, the second electromagnet 18 are powered, the 4th electromagnet 23, the power-off of the first electromagnet 17, in dry air storage tank 20
Dry air successively passes through connecting tube 24, the second cavity 11, the first cavity 10, into experimental cabin 1, due to along airintake direction
The caliber of connecting tube 24 is gradually increased, and the pipe diameter between the first cavity 10 and the second cavity 11 is less than experimental cabin 1 and first
The connector bore of cavity 10, during entering experimental cabin 1, as caliber increases, pressure is gradually reduced dry air, with
Directly the mode that atmospheric air is passed through the progress vacuum breaker of experimental cabin 1 is compared in the prior art, the utility model avoids normally
Direct impact of the atmospheric pressure to experimental cabin 1, extends the service life of equipment.In addition, the air being passed through uses dry air, really
Experimental cabin 1 is protected in the case where not using in dry environment, damage of the reduction moisture in air to experimental cabin 1 improves it
Leakproofness extends the service life of equipment.
It should be noted that, in this document, relational terms such as first and second and the like are used merely to a reality
Body or operation are distinguished with another entity or operation, are deposited without necessarily requiring or implying between these entities or operation
In any actual relationship or order or sequence.Moreover, the terms "include", "comprise" or its any other variant are intended to
Non-exclusive inclusion, so that the process, method, article or equipment including a series of elements is not only wanted including those
Element, but also including other elements that are not explicitly listed, or further include for this process, method, article or equipment
Intrinsic element.In the absence of more restrictions, the element limited by sentence "including a ...", it is not excluded that
There is also other identical elements in process, method, article or equipment including the element.
Each embodiment in this specification is all made of relevant mode and describes, same and similar portion between each embodiment
Dividing may refer to each other, and each embodiment focuses on the differences from other embodiments.
The above is only the preferred embodiment of the utility model only, is not intended to limit the protection model of the utility model
It encloses.Any modification, equivalent substitution, improvement and etc. made within the spirit and principle of the present invention, are all contained in this reality
With in novel protection scope.
Claims (5)
1. a kind of low-temp low-pressure experimental cabin of simulated altitude, which is characterized in that the outlet of refrigeration equipment (2) passes through pipeline and test
The air inlet in cabin (1) connects, and is equipped with the first solenoid valve (7) on the pipeline between refrigeration equipment (2) and experimental cabin (1), tests
Filter plate (8) are equipped at the air inlet in cabin (1), the inner wall of experimental cabin (1) is equipped with pressure sensor (9) and temperature sensor
(16), running support (3) are equipped in experimental cabin (1), are equipped with aero-engine (4) on running support (3), aero-engine (4)
Exhaust outlet is connect by exhaust pipe (5) with waste gas collection box (6)；Experimental cabin (1) passes through vacuum-pumping tube (13) and vacuum pump (15)
Connection, vacuum-pumping tube (13) are equipped with second solenoid valve (12)；The side wall of experimental cabin (1) is connected to the first cavity (10), test
The junction of cabin (1) and the first cavity (10) is equipped with the first electromagnet (17) of annular, is equipped with the first iron in the first cavity (10)
Ball (19), the bottom level in the first cavity (10) are equipped with the second electromagnet (18) of annular；First cavity (10) passes through pipeline
It is connect with the second cavity (11), the junction of pipeline and the second cavity (11) is equipped with the 4th electromagnet (23) of annular, and second is empty
The second iron ball (22) are equipped in chamber (11), the bottom level in the second cavity (11) is equipped with the third electromagnet (21) of annular；The
Two cavitys (11) are connect by connecting tube (24) with dry air storage tank (20), and connecting tube (24) and dry air storage tank (20) are even
The caliber for connecing end is less than caliber with the second cavity (11) connecting pin, the pipeline between the first cavity (10) and the second cavity (11)
Caliber is less than the connector bore of experimental cabin (1) and the first cavity (10)；Pressure sensor (9) passes through the second microcontroller (25)
It is connect with the switch of vacuum pump (15), temperature sensor (16) is connect by the first microcontroller (14) with the first solenoid valve (7).
2. a kind of low-temp low-pressure experimental cabin of simulated altitude according to claim 1, which is characterized in that first micro-control
Device (14) processed, the second microcontroller (25) are all made of C8051F020 single-chip microcontroller.
3. a kind of low-temp low-pressure experimental cabin of simulated altitude according to claim 1, which is characterized in that the pressure sensing
The model PY210 of device (9).
4. a kind of low-temp low-pressure experimental cabin of simulated altitude according to claim 1, which is characterized in that the temperature sensing
The model DS18B20 of device (16).
5. a kind of low-temp low-pressure experimental cabin of simulated altitude according to claim 1, which is characterized in that the filter plate
It (8) is arc.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201821433998.4U CN208672312U (en) | 2018-09-03 | 2018-09-03 | The low-temp low-pressure experimental cabin of simulated altitude |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201821433998.4U CN208672312U (en) | 2018-09-03 | 2018-09-03 | The low-temp low-pressure experimental cabin of simulated altitude |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN208672312U true CN208672312U (en) | 2019-03-29 |
Family
ID=65841537
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201821433998.4U Expired - Fee Related CN208672312U (en) | 2018-09-03 | 2018-09-03 | The low-temp low-pressure experimental cabin of simulated altitude |
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| CN (1) | CN208672312U (en) |
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110346146A (en) * | 2019-07-31 | 2019-10-18 | 中国航发沈阳发动机研究所 | A kind of experimental cabin for main chamber low-temperature test |
| CN111927623A (en) * | 2020-06-22 | 2020-11-13 | 北京航空航天大学 | High-altitude ventilation and dynamic performance simulation test platform for two-stroke aviation piston engine |
| CN112198468A (en) * | 2020-09-11 | 2021-01-08 | 中国科学院金属研究所 | Waveguide method microwave dielectric material ultralow temperature complex electromagnetic parameter testing device |
| CN114509681A (en) * | 2021-12-28 | 2022-05-17 | 重庆阿泰可科技股份有限公司 | Vacuum environment test system for hydrogen-air fuel battery |
| CN115219206A (en) * | 2022-08-31 | 2022-10-21 | 中国航发四川燃气涡轮研究院 | Engine cold and hot dipping system for high and low temperature starting test of aircraft engine |
| CN116447129A (en) * | 2023-06-19 | 2023-07-18 | 成都凯天电子股份有限公司 | Device for simulating high-altitude performance of missile fuel pump and testing method thereof |
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2018
- 2018-09-03 CN CN201821433998.4U patent/CN208672312U/en not_active Expired - Fee Related
Cited By (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110346146A (en) * | 2019-07-31 | 2019-10-18 | 中国航发沈阳发动机研究所 | A kind of experimental cabin for main chamber low-temperature test |
| CN111927623A (en) * | 2020-06-22 | 2020-11-13 | 北京航空航天大学 | High-altitude ventilation and dynamic performance simulation test platform for two-stroke aviation piston engine |
| CN111927623B (en) * | 2020-06-22 | 2021-06-04 | 北京航空航天大学 | High-altitude ventilation and dynamic performance simulation test platform for two-stroke aviation piston engine |
| CN112198468A (en) * | 2020-09-11 | 2021-01-08 | 中国科学院金属研究所 | Waveguide method microwave dielectric material ultralow temperature complex electromagnetic parameter testing device |
| CN112198468B (en) * | 2020-09-11 | 2022-01-14 | 中国科学院金属研究所 | Waveguide method microwave dielectric material ultralow temperature complex electromagnetic parameter testing device |
| CN114509681A (en) * | 2021-12-28 | 2022-05-17 | 重庆阿泰可科技股份有限公司 | Vacuum environment test system for hydrogen-air fuel battery |
| CN114509681B (en) * | 2021-12-28 | 2022-10-28 | 重庆阿泰可科技股份有限公司 | Vacuum environment test system for hydrogen-air fuel battery |
| CN115219206A (en) * | 2022-08-31 | 2022-10-21 | 中国航发四川燃气涡轮研究院 | Engine cold and hot dipping system for high and low temperature starting test of aircraft engine |
| CN115219206B (en) * | 2022-08-31 | 2023-02-17 | 中国航发四川燃气涡轮研究院 | Engine cold and hot dipping system for high and low temperature starting test of aircraft engine |
| CN116447129A (en) * | 2023-06-19 | 2023-07-18 | 成都凯天电子股份有限公司 | Device for simulating high-altitude performance of missile fuel pump and testing method thereof |
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| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20190329 |