CN210983122U - Heat exchanger simulation device of airplane environment control system - Google Patents
Heat exchanger simulation device of airplane environment control system Download PDFInfo
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- CN210983122U CN210983122U CN201922265936.8U CN201922265936U CN210983122U CN 210983122 U CN210983122 U CN 210983122U CN 201922265936 U CN201922265936 U CN 201922265936U CN 210983122 U CN210983122 U CN 210983122U
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- heat exchanger
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- control system
- vacuum
- environmental control
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Abstract
The utility model relates to a simulator that uses among aircraft environmental control system ground simulation test process belongs to aircraft environmental control system experimental design field. The heat exchanger is arranged in a vacuum simulation cabin, an outlet guide pipe is arranged at a cold edge outlet of the heat exchanger, and an outlet of the outlet guide pipe extends out of the vacuum simulation cabin and is used for exhausting air from the cold edge outlet of the heat exchanger to the outside of the vacuum simulation cabin. The utility model has the advantages of as follows: the influence of high-temperature gas at the outlet of the cold edge of the heat exchanger on the temperature of the external environment of the airplane in the test process of the environmental control system can be eliminated, the authenticity of test data is improved, and the construction cost of a vacuum simulation system can be reduced.
Description
Technical Field
The utility model relates to a simulator that uses among aircraft environmental control system ground simulation test process belongs to aircraft environmental control system experimental design field.
Background
In the process of a ground simulation test of an aircraft environmental control system, the external environment (such as pressure and temperature) of the aircraft flying at high altitude is often required to be simulated, and the external environment simulation is carried out in a vacuum simulation cabin. The existing environment control system heat exchanger simulation device exhausts the cold side of the heat exchanger to the vacuum simulation cabin, and because the airflow of the cold side of the heat exchanger is very large, a large amount of high-temperature gas enters the vacuum simulation cabin, the external environment temperature of the cabin section of the airplane can be increased, so that the simulation of the external temperature of the airplane is not real, and finally the test result is influenced. In addition, a large amount of gas enters the vacuum simulation chamber, so that the air extraction capacity of the vacuum pump needs to be greatly improved, and the construction cost of the vacuum simulation system is increased.
SUMMERY OF THE UTILITY MODEL
The utility model aims at solving the problem that exists among the prior art, provide an aircraft environmental control system heat exchanger analogue means that does not influence vacuum simulation under-deck ambient temperature.
In order to achieve the above purpose, the utility model adopts the following technical scheme: the heat exchanger is arranged in a vacuum simulation cabin, an outlet guide pipe is arranged at a cold edge outlet of the heat exchanger, and an outlet of the outlet guide pipe extends out of the vacuum simulation cabin and is used for exhausting air from the cold edge outlet of the heat exchanger to the outside of the vacuum simulation cabin.
Preferably, a regulating valve is installed on the inlet duct for regulating the gas flow rate.
Preferably, the regulating valve is positioned outside the vacuum simulation cabin, so that the regulating valve is convenient for operators to regulate, the airflow pressure of the cold side inlet of the heat exchanger is increased, and the equivalent simulation of the cold side airflow of the heat exchanger is achieved.
The working principle is as follows: heating the gas from the gas source to the temperature required by the test by controlling the power of the heater, and then regulating the flow of the gas to the flow value required by the test by controlling the opening of the regulating valve; the simulated airflow enters a cold side air duct of a heat exchanger arranged in the vacuum simulation cabin through an inlet guide pipe, and is discharged out of the vacuum cabin from an outlet guide pipe after heat exchange.
Compared with the prior art, the utility model has the advantages of as follows: the influence of high-temperature gas at the outlet of the cold edge of the heat exchanger on the temperature of the external environment of the airplane in the test process of the environmental control system can be eliminated, the authenticity of test data is improved, and the construction cost of a vacuum simulation system can be reduced.
Drawings
FIG. 1 is a schematic structural diagram of an embodiment of the present invention;
in the figure, 1, a gas source; 2. a heater; 3. adjusting a valve; 4. an inlet conduit; 5. a heat exchanger; 6. an outlet conduit; 7. an aircraft cabin section; 8. a vacuum simulation cabin; 9. a vacuum pump.
Detailed Description
The present invention will be described in detail with reference to the accompanying drawing 1: a heat exchanger simulator of an aircraft environmental control system comprises an air source 1, a heater 2, a regulating valve 3, an inlet conduit 4, a heat exchanger 5 and an outlet conduit 6 which are sequentially communicated; the air source 1 provides simulated air flow, the air from the air source 1 is heated to the temperature required by the test by controlling the power of the heater 2, the regulating valve 3 is arranged on the inlet conduit 4 between the heater 2 and the heat exchanger 5, the flow of the air is regulated to the flow value required by the test by controlling the opening degree of the regulating valve, the cold side air channel of the heat exchanger 5 in the vacuum simulation cabin is communicated with the inlet conduit 4 and is used for carrying out heat exchange between the heated simulated air flow and the air in the hot side of the heat exchanger, the outlet conduit 6 is arranged at the outlet of the cold side of the heat exchanger 5, the outlet of the outlet conduit 6 extends out of the vacuum simulation cabin and is used for leading the exhaust of the cold side outlet of the heat.
Thus, the gas discharged from the cold side of the heat exchanger does not enter the vacuum simulation chamber 8, and the ambient temperature outside the aircraft cabin section 7 is not affected. After the gas discharged into the vacuum chamber is reduced, the capacity requirement of the vacuum pump 9 can be reduced, and the construction cost of the vacuum pump is saved.
The above embodiments are merely preferred embodiments of the present invention, and do not limit the present invention. It will be understood by those skilled in the art that any modification, extension, etc. made without departing from the principles of the invention are within the scope of the invention.
Claims (3)
1. The utility model provides an aircraft environmental control system heat exchanger analogue means, includes air supply, heater, entry pipe and the heat exchanger that communicates in proper order, and the heat exchanger sets up in vacuum simulation under-deck, its characterized in that: and an outlet guide pipe is arranged at the cold edge outlet of the heat exchanger, and the outlet of the outlet guide pipe extends out of the vacuum simulation cabin and is used for exhausting air from the cold edge outlet of the heat exchanger to the outside of the vacuum simulation cabin.
2. The aircraft environmental control system heat exchanger simulator of claim 1, wherein: an adjusting valve is mounted on the inlet conduit for adjusting the gas flow.
3. The aircraft environmental control system heat exchanger simulator of claim 2, wherein: the regulating valve is positioned outside the vacuum simulation cabin.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201922265936.8U CN210983122U (en) | 2019-12-17 | 2019-12-17 | Heat exchanger simulation device of airplane environment control system |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201922265936.8U CN210983122U (en) | 2019-12-17 | 2019-12-17 | Heat exchanger simulation device of airplane environment control system |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN210983122U true CN210983122U (en) | 2020-07-10 |
Family
ID=71438857
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201922265936.8U Active CN210983122U (en) | 2019-12-17 | 2019-12-17 | Heat exchanger simulation device of airplane environment control system |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN210983122U (en) |
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2019
- 2019-12-17 CN CN201922265936.8U patent/CN210983122U/en active Active
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|---|---|---|---|
| GR01 | Patent grant | ||
| GR01 | Patent grant | ||
| CP02 | Change in the address of a patent holder |
Address after: Nanchang high tech Industrial Development Zone, Jiangxi Province Patentee after: JIANGXI HONGDU AVIATION INDUSTRY GROUP Co.,Ltd. Address before: 330000 Jiangxi city in Nanchang Province, the new bridge box 460 box 5001 Patentee before: JIANGXI HONGDU AVIATION INDUSTRY GROUP Co.,Ltd. |
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| CP02 | Change in the address of a patent holder |