CN113830327A - Ventilation unit for aircraft test - Google Patents
Ventilation unit for aircraft test Download PDFInfo
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- CN113830327A CN113830327A CN202111390117.1A CN202111390117A CN113830327A CN 113830327 A CN113830327 A CN 113830327A CN 202111390117 A CN202111390117 A CN 202111390117A CN 113830327 A CN113830327 A CN 113830327A
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
- B64F5/00—Designing, manufacturing, assembling, cleaning, maintaining or repairing aircraft, not otherwise provided for; Handling, transporting, testing or inspecting aircraft components, not otherwise provided for
- B64F5/60—Testing or inspecting aircraft components or systems
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F17—STORING OR DISTRIBUTING GASES OR LIQUIDS
- F17D—PIPE-LINE SYSTEMS; PIPE-LINES
- F17D1/00—Pipe-line systems
- F17D1/02—Pipe-line systems for gases or vapours
- F17D1/04—Pipe-line systems for gases or vapours for distribution of gas
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F17—STORING OR DISTRIBUTING GASES OR LIQUIDS
- F17D—PIPE-LINE SYSTEMS; PIPE-LINES
- F17D1/00—Pipe-line systems
- F17D1/02—Pipe-line systems for gases or vapours
- F17D1/065—Arrangements for producing propulsion of gases or vapours
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F17—STORING OR DISTRIBUTING GASES OR LIQUIDS
- F17D—PIPE-LINE SYSTEMS; PIPE-LINES
- F17D3/00—Arrangements for supervising or controlling working operations
- F17D3/01—Arrangements for supervising or controlling working operations for controlling, signalling, or supervising the conveyance of a product
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F17—STORING OR DISTRIBUTING GASES OR LIQUIDS
- F17D—PIPE-LINE SYSTEMS; PIPE-LINES
- F17D3/00—Arrangements for supervising or controlling working operations
- F17D3/18—Arrangements for supervising or controlling working operations for measuring the quantity of conveyed product
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- General Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
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- Transportation (AREA)
- Aviation & Aerospace Engineering (AREA)
- Central Air Conditioning (AREA)
Abstract
The invention relates to the technical field of ventilation devices, in particular to a ventilation device for an airplane test, which comprises a plurality of groups of sub-circulating air processing systems; each group of the sub-circulating air processing systems comprises an air return system, a temperature processing system connected with the air return system and used for adjusting air, an air supply system connected with the temperature processing system and used for transmitting the adjusted air and a humidity processing system used for adjusting humidity; the invention has reasonable integral structure design, can effectively meet the air circulation treatment problem of the extreme environment of a large-scale aviation airplane climate laboratory by utilizing a plurality of groups of sub-circulation air treatment systems, can divide the laboratory into a plurality of areas by utilizing a layout division mode, and then enables a temperature field, a humidity field and a speed field to meet the test requirements of different environments by carrying out partition adjustment on a plurality of areas of airflow organization.
Description
Technical Field
The invention relates to the technical field of ventilation devices, in particular to a ventilation device for an airplane test.
Background
The airplane weather environment adaptability test is one of essential links in airplane design, and is characterized by that under the condition of indoor simulation or outdoor natural weather environment, the airplane can be made to bear the action of weather environment stress so as to obtain the weather environment ultimate capacity information of airplane, and according to the development requirements, failure criterion and test data the weather environment adaptability of said airplane can be comprehensively evaluated, and the extent of meeting the requirements of weather environment adaptability can be determined.
One of the essential factors for carrying out the aircraft climate environmental suitability test is the construction of a large aviation aircraft climate laboratory. The large-scale aviation aircraft climate laboratory can simulate the climate environments on the earth surface such as extreme low temperature, high temperature, damp and hot, snowfall, solar irradiation, ice and freezing rain, rain and freezing fog, the size of the large-scale aviation aircraft climate laboratory can meet the climate test requirements of various airplanes, and the large-scale aviation aircraft climate laboratory is an important test facility for verifying the climate environment adaptability of various industrial products such as aircrafts and the like. Due to the technical difficulty in designing and constructing large-scale climate laboratories and the high project cost, only a few countries such as the United states, the United kingdom, the Korea, Switzerland, China and the like establish large-scale climate laboratories which can meet the complete level of aircrafts at present.
The simulation of various climates in a large-scale climate laboratory is realized by a basic environment simulation system and a special environment simulation system. The basic environment simulation system is used for realizing specified temperature, humidity and pressure conditions, and is the most core, most critical and most complex environment simulation system of a climate environment laboratory; the special environment simulation system realizes snowfall, solar irradiation, ice accumulation, freezing rain and the like on the basis of the temperature, humidity and pressure conditions provided by the basic environment simulation system. The circulating air system is an important component of a basic environment simulation system of a laboratory, the temperature and the humidity of air in the laboratory are directly processed through the circulating system, the processed air is sent into an environment chamber again, the temperature and the humidity in the environment chamber are adjusted, and the target environment is realized.
At present, the domestic large climate laboratory is mainly used for climate tests of military firearms, armored vehicles, tanks, civil automobiles, train carriages and the like, such as a general assembly 32 base, a Baicheng weapon test center, a Ministry of railways four-side vehicle factory, a Changchun automobile research institute, an engineering soldier two-place and the like. The scale of the laboratory is not large, the laboratory is not a complex comprehensive environment laboratory, the air circulation in the cabin is fast, the uniformity of the temperature is easy to realize, but the air circulation ventilation device in the basic environment simulation system is simple, and the laboratory is not suitable for a large-scale climate laboratory. Air circulation ventilation apparatuses in overseas large climate laboratories such as the american maijin climate laboratory and the korean ADD environment laboratory are in a high secrecy state and cannot refer to the related art.
Aiming at large-scale climate laboratory with volume exceeding 100000 m for cultivating trees, the air circulation speed in the warehouse is slow due to overlarge laboratory volume, and the ground structure of the laboratory exceeds 5000 m in area2The concrete structure of (2) has huge heat sink. Therefore, it is a difficult design point to ensure that a large-scale climate laboratory meets various indexes of wide temperature range, high uniformity, wind speed limitation and the like of the environmental temperature.
Disclosure of Invention
In order to solve the existing problems, the invention provides a ventilating device for an airplane test.
The technical scheme of the invention is as follows: a ventilation device for an aircraft test comprises a plurality of groups of sub-circulating air processing systems;
each group of the sub-circulating air processing systems comprises an air return system for collecting and transmitting the air inside the large-scale aviation aircraft climate laboratory, a temperature processing system connected with the air return system and used for adjusting the air in the large-scale aviation aircraft climate laboratory, an air supply system connected with the temperature processing system and used for transmitting the adjusted air to the inside of the large-scale aviation aircraft climate laboratory, and a humidity processing system used for adjusting the humidity of the large-scale aviation aircraft climate laboratory;
the air return system comprises an air return pipeline and an air inlet arranged at the air inlet end of the air return pipeline;
the temperature processing system comprises an air duct cavity connected with the air outlet end of the return air pipeline and two allocation processing devices which are arranged in parallel in the air duct cavity and used for adjusting air flow;
the two allocation processing devices comprise air inlet fans, air flow buffer tubes with one ends connected with the air outlet ends of the air inlet fans, processing chambers connected with the other ends of the air flow buffer tubes and heat exchangers arranged in the processing chambers;
the treatment cavity comprises a treatment cavity body and a conversion pipeline, wherein the interior of the treatment cavity body is divided into a first treatment cavity body, a second treatment cavity body and a third treatment cavity body; air valves are arranged at the joints of the conversion pipeline and the first processing cavity, the second processing cavity and the third processing cavity; the air inlet end of the first processing cavity is connected with the other end of the air flow buffer pipe;
the heat exchanger comprises a frosting heat exchanger arranged in the first treatment cavity, a medium-temperature heat exchanger arranged in the second treatment cavity and a low-temperature heat exchanger arranged in the third treatment cavity;
the air supply system comprises an air supply pipeline and an air supply device, wherein the air supply pipeline is connected with the air outlet end of the conversion pipeline, and the air supply device is installed at the air outlet end of the air supply pipeline.
Further, still including the new trend system that can carry out purification treatment to the inside air of treatment chamber body.
Furthermore, the air supply pipeline adopts a variable cross-section design structure; the air supply pipeline adopts the variable cross-section design to adjust the pressure of each air supply outlet to keep consistent, thereby ensuring the outlet speed to be consistent and better meeting the uniformity requirement of the environmental temperature of a laboratory.
Furthermore, the air supply device adopts a swirl air port; the air supply angle of the cyclone is adjustable, so that the problem of uneven air temperature and speed in a laboratory can be solved through zone control.
Furthermore, the air duct cavity comprises an air inlet connecting pipeline connected with an air return pipeline, a processing cavity pipeline connected with the other end of the air inlet connecting pipeline and used for installing a allocating processing device, and an air supply connecting pipeline used for connecting the processing cavity pipeline with the air supply pipeline.
Furthermore, air supply connecting tube corner all is provided with the guide plate, utilizes the guide plate of corner to make the air current homogeneity better when passing through.
Furthermore, a flow meter is arranged in the air supply connecting pipeline; the flowmeter adopts a pitot tube with a heating function, and the mounting position of the pitot tube is at a position where the airflow in the air supply connecting pipeline is stable.
Further, the humidity processing system comprises a dry steam humidifier for humidifying and a rotary dehumidifier for dehumidifying; the humidity of the ambient air can be controlled within the range of 5% RH-95% RH by means of humidification or dehumidification.
Furthermore, electric tracing heat is arranged on the outer surfaces of the frosting heat exchanger, the medium-temperature heat exchanger and the low-temperature heat exchanger; the phenomenon that frost or liquid water is frozen in the pipeline can be effectively prevented by utilizing electric heat tracing.
Compared with the prior art, the invention has the beneficial effects that:
1) the ventilating device is reasonable in overall structural design, the problem of air circulation treatment in extreme environments of a large-scale aviation airplane climate laboratory can be effectively solved by utilizing the multiple groups of sub-circulation air treatment systems, the laboratory can be divided into multiple areas by utilizing a layout division mode, and then the temperature field, the humidity field and the speed field can meet different environmental test requirements through multi-area airflow organization partition adjustment;
2) the ventilation device has higher reliability, and performs air circulation treatment on a large-scale aviation aircraft climate laboratory in a mode of forming double channels by using the double-allocation treatment device; each channel can work independently and jointly, so that the unit still has working capacity when equipment in one channel fails or stops;
3) the ventilating device has higher practicability, can be applied to a large-scale aviation aircraft climate laboratory, and can effectively make up for the technical blank of China in the field.
Drawings
FIG. 1 is a schematic front view of the structure of embodiment 1 of the present invention;
FIG. 2 is a schematic front view showing a temperature processing system according to embodiment 1 of the present invention;
FIG. 3 is a schematic top view of a blending device according to embodiment 1 of the present invention;
fig. 4 is a schematic top view of an air supply system according to embodiment 1 of the present invention;
FIG. 5 is a schematic layout of a five-component cyclic air treatment system in accordance with an exemplary embodiment of the present invention;
FIG. 6 is a schematic layout of an air supply apparatus according to an exemplary embodiment of the present invention;
the air conditioner comprises a 1-air return system, a 11-air return pipeline, a 12-air inlet, a 2-air supply system, a 21-air supply pipeline, a 22-air supply device, a 3-temperature processing system, a 30-air duct cavity, a 301-air inlet connecting pipeline, a 302-processing cavity pipeline, a 303-air supply connecting pipeline, a 31-air inlet fan, a 32-air flow buffer pipe, a 33-processing cavity, a 331-first processing cavity, a 332-second processing cavity, a 333-third processing cavity, a 334-conversion pipeline, a 34-heat exchanger, a 341-frosting heat exchanger, a 342-medium temperature heat exchanger, a 343-low temperature heat exchanger, a 344-electric heat tracing and a 4-humidity processing system.
Detailed Description
Example 1
The ventilating device for the airplane test shown in figures 1 and 2 comprises 6 groups of circulating air processing systems;
each group of sub-circulating air processing systems comprises an air return system 1 for collecting and transmitting the air inside the large-scale aviation aircraft climate laboratory, a temperature processing system 3 connected with the air return system 1 and used for adjusting the air inside the large-scale aviation aircraft climate laboratory, an air supply system 2 connected with the temperature processing system 3 and used for transmitting the adjusted air to the inside of the large-scale aviation aircraft climate laboratory, and a humidity processing system 4 used for adjusting the humidity of the large-scale aviation aircraft climate laboratory;
as shown in fig. 1, the air return system 1 includes an air return duct 11 and an air inlet 12 disposed at an air inlet end of the air return duct 11;
as shown in fig. 2 and 3, the temperature processing system 3 includes an air duct cavity 30 connected to the air outlet end of the return air duct 11, and two blending processing devices installed in parallel inside the air duct cavity 30 for adjusting the air flow; the two allocation processing devices respectively comprise an air inlet fan 31, an air flow buffer tube 32 with one end connected with the air outlet end of the air inlet fan 31, a processing cavity 33 connected with the other end of the air flow buffer tube 32 and a heat exchanger 34 arranged in the processing cavity 33;
the processing chamber 33 includes a processing chamber body divided into a first processing chamber 331, a second processing chamber 332, and a third processing chamber 333, and a switching pipe 334 connected to the first processing chamber 331, the second processing chamber 332, and the third processing chamber 333, respectively; air valves are arranged at the joints of the conversion pipeline 334, the first processing cavity 331, the second processing cavity 332 and the third processing cavity 333; the air inlet end of the first processing cavity 331 is connected with the other end of the air flow buffer tube 32;
the heat exchanger 34 includes a frosting heat exchanger 341 installed inside the first process chamber 331, a medium temperature heat exchanger 342 installed inside the second process chamber 332, and a low temperature heat exchanger 343 installed inside the third process chamber 333;
as shown in fig. 1, the air supply system 2 includes an air supply duct 21 having an air inlet end connected to an air outlet end of the conversion duct 334, and an air supply device 22 installed at the air outlet end of the air supply duct 21; as shown in fig. 4, the air supply duct 21 adopts a variable cross-section design structure, and the air supply device 22 adopts a swirl tuyere;
as shown in fig. 1 and 2, the air duct cavity 30 includes an air inlet connecting duct 301 connected to the return air duct 11, a processing chamber duct 302 connected to the other end of the air inlet connecting duct 301 and used for installing a blending processing device, and an air supply connecting duct 303 used for connecting the processing chamber duct 302 with the air supply duct 21; flow deflectors are arranged at the corners of the air supply connecting pipeline 303; a flowmeter is arranged in the air supply connecting pipeline 303;
as shown in fig. 3, electric tracing 344 is installed on the outer surfaces of the frosting heat exchanger 341, the medium temperature heat exchanger 342, and the low temperature heat exchanger 343.
Still including the new trend system that can carry out purification treatment to the inside air of treatment chamber body.
Wherein the humidity processing system 4 comprises a dry steam humidifier for humidification and a rotary dehumidifier for dehumidification.
It should be noted that: two allocation processing devices are arranged in the air duct cavity 30 and can be used in a low-temperature large-load environment, because the environment has a high requirement on the heat load of a temperature processing system, and the temperature after being processed by a heat exchanger is far lower than-10 ℃ after the simulation of a snow-falling environment at the temperature of-10 ℃ is realized by taking a snow-falling test as an example; in general, the left channel and the right channel run simultaneously in the same state and have independent working capacity, so that when equipment in one channel breaks down or stops, the allocation processing device still has the working capacity to improve the reliability of the allocation processing device;
in addition, the embodiment further includes related control devices and other accessory devices, and the other accessory devices specifically include conventional structural members in the field, such as an access door, an incubator, a support frame, and the like, which are not described herein again.
Example 2
The difference from the embodiment 1 is that 8 groups of sub-circulation air processing systems are included;
still including the new trend system that can carry out purification treatment to the inside air of treatment chamber body.
Application example
Taking the existing large-scale aviation aircraft climate laboratory in the research institute as an example, the laboratory parameters are as follows:
1) a laboratory volume exceeding 100000 m, laboratory effective size being: width 72m, depth 60m, height 22 m;
2) the main technical indexes of the laboratory part are as follows: temperature range: minus 55 ℃ to minus 74 ℃; cooling rate: cooling to-55 deg.C at normal temperature for 24 hr; the heating rate is as follows: the temperature is raised to +74 ℃ at 8 hours; the device can simulate complex climate environments such as high temperature, low temperature, solar irradiation, rain, snow fall, freezing rain, freezing cloud/ice and the like; under various environmental conditions, the temperature fluctuation does not exceed 3 ℃.
The large aircraft climate laboratory was now assembled using the solution proposed in example 1:
this experimental ventilation unit of aircraft includes five groups of sub-circulation wind processing systems: as shown in fig. 5, for the building structure depth design index of 60m in the laboratory, five groups of sub-circulating air treatment systems can fully cover the laboratory by arranging a layout form of one group of sub-circulating air treatment systems at intervals of 12 m; aiming at the uniformity requirements of the wind speed and the temperature of a laboratory, the structure of a sub-circulating air treatment system is combined, and air adopts an up-feeding and down-returning mode; as shown in fig. 6, one air supply device 22 is arranged at an interval of 12m of the air supply duct 21, and 6 air supply devices 22 are arranged in total, so that the design index of the building structure length of a laboratory 72m is realized; in addition, the air supply pipeline 21 adopts a variable cross-section rectangular design, the height is uniformly set to 1550mm, and the width of the pipeline where each air supply outlet is located is 1900mm, 2700mm, 3300mm, 3600mm, 4500mm and 5100mm respectively; the design can realize the pressure quality guarantee consistency of 6 air supply outlets, thereby ensuring the air speed consistency of the air outlets and better meeting the requirement of the uniformity of the environmental temperature of a laboratory; the air supply pipeline 21 adopts a cyclone air port as an air supply device, and the air supply angle of the cyclone is adjustable; thus, the five groups of sub-circulating air processing systems divide the laboratory into 30 airflow organization units of 12m multiplied by 12m, and the problems of the air temperature and the speed uniformity of the laboratory are solved through zone control;
the frosting heat exchanger 341 adopts an LM-8 frosting heat exchanger, is mainly used for dehumidifying air in high-humidity low-temperature tests such as rain, snow, freezing rain and the like, adopts a variable-pitch design and is sequentially set to be 24mm, 12mm and 6 mm; the 24mm distance between the windward sides can ensure that the air resistance is not too large under the condition of frosting so as to protect the performances of the medium-temperature heat exchanger 342 and the low-temperature heat exchanger 343, and meanwhile, the heat exchanger is also used for cooling or heating air under the normal test working condition of more than-25 ℃;
the middle-temperature heat exchanger 342 adopts an LM-8 middle-high heat exchanger and is used for cooling or heating air in a test at the temperature of more than 25 ℃ below zero;
the low-temperature heat exchanger 343 adopts a CH2CL2 low-temperature heat exchanger and is used for cooling air under the test working conditions of minus 25 ℃ to minus 55 ℃;
the product parameters of the LM-8 frosting heat exchanger, the LM-8 middle-high heat exchanger and the CH2CL2 low-temperature heat exchanger are as follows:
LM-8 frosting heat exchanger: the length is multiplied by the height, the row is multiplied by 2.4m by 3m by 6m, and the chip distance is 24mm +12mm +6 mm;
LM-8 medium-high heat exchanger: the length is multiplied by the height, the row is multiplied by 2.4m by 3m by 6m, and the chip distance is 6 mm;
CH2CL2 low temperature heat exchanger: the length X height X row is 2.4m X3 m X14 m, and the chip pitch is 6 mm.
The air inlet fan 31 is used for driving circulating air to flow, and the air flow of each air supply device 22 can be adjusted by controlling the working frequency, so that the air flow organization required by each test working condition is realized; in addition, the two allocation processing devices share a set of humidity processing system to realize the control of the humidity environment of the laboratory;
the flowmeter adopts a pitot tube with a heating function and is arranged at a position where the airflow of the pipeline is relatively stable; for example, 30 flow meters are specifically configured, and the air flow in the pipeline is analyzed by calculating an average value of data measured by the 30 flow meters;
in addition, the air inlet 12, the air supply device 22, the air outlet of the frosting heat exchanger 341, the air outlet of the medium temperature heat exchanger 342 and the air outlet of the low temperature heat exchanger 343 are respectively provided with two temperature and humidity sensors at the central positions for monitoring the working state of each sub-circulating air processing system;
after the design of the main components is completed, other accessory equipment, such as an air valve, an access door, an insulation can, a support frame and the like, is designed or configured according to the requirements of the system operation principle, the system control, the equipment maintenance, the fire fighting and the like.
The laboratory was run as follows:
1) when the laboratory is to realize the environmental temperature in the range of-25 ℃ to +74 ℃:
the air valve is opened, and the air inlet fan 31 is started to enable air in the laboratory to enter the processing cavity 33 from the air return pipeline 11 and the air inlet connecting pipeline 301 through the laboratory air inlet 12; then obtaining heat or cold through the LM-8 frosting heat exchanger and the LM-8 medium temperature heat exchanger; the humidity of the processed air is increased through a dry steam humidifier, and the air enters the laboratory again from the air supply swirler through the air supply connecting pipeline 303 and the air supply pipeline 21; continuously circulating in the mode until the target temperature and humidity are reached;
2) when the laboratory is to realize the environmental temperature within the range of-55 ℃ to-25 ℃:
opening an air valve, starting an air inlet fan 31 to enable air in the laboratory to enter a treatment cavity 33 from an air return pipeline 11 and an air inlet connecting pipeline 301 through a laboratory air inlet 12, and then obtaining cold energy through an LM-8 frosting heat exchanger and a CH2CL2 low-temperature heat exchanger; the humidity of the processed air is increased through a dry steam humidifier, and the air enters the laboratory again from the air supply swirler through the air supply connecting pipeline 303 and the air supply pipeline 21; continuously circulating in the mode until the target temperature and humidity are reached;
3) for tests with large heat loads such as snowfall, freezing rain, freezing fog and the like:
an air valve is opened, an air inlet fan 31 is started, so that air in the laboratory enters a treatment cavity 33 from an air return pipeline 11 and an air inlet connecting pipeline 301 through a laboratory air inlet 12, and cold energy is obtained through an LM-8 frosting heat exchanger, an LM-8 medium-temperature heat exchanger and a CH2CL2 low-temperature heat exchanger in sequence; re-enter the laboratory from the air supply swirler through the air supply connecting pipeline 303 and the air supply pipeline 21; the humidity of the treated air is adjusted by a humidity treatment system 4; and continuously circulating in the mode until the target temperature and humidity are reached.
Claims (9)
1. A ventilation device for an aircraft test is characterized by comprising a plurality of groups of sub-circulating air treatment systems;
each group of the sub-circulating air processing systems comprises an air return system (1) used for collecting and transmitting air inside a large-scale aviation aircraft climate laboratory, a temperature processing system (3) connected with the air return system (1) and used for adjusting the air inside the large-scale aviation aircraft climate laboratory, an air supply system (2) connected with the temperature processing system (3) and used for transmitting the adjusted air to the inside of the large-scale aviation aircraft climate laboratory, and a humidity processing system (4) used for adjusting the humidity of the large-scale aviation aircraft climate laboratory;
the air return system (1) comprises an air return pipeline (11) and an air inlet (12) arranged at the air inlet end of the air return pipeline (11);
the temperature processing system (3) comprises an air duct cavity (30) connected with the air outlet end of the air return pipeline (11) and two allocation processing devices which are arranged in the air duct cavity (30) in parallel and used for adjusting air flow;
the two allocation processing devices respectively comprise an air inlet fan (31), an air flow buffer tube (32) with one end connected with the air outlet end of the air inlet fan (31), a processing cavity (33) connected with the other end of the air flow buffer tube (32) and a heat exchanger (34) arranged in the processing cavity (33);
the processing cavity (33) comprises a processing cavity body and a conversion pipeline (334), wherein the processing cavity body is internally divided into a first processing cavity body (331), a second processing cavity body (332) and a third processing cavity body (333), and the conversion pipeline (334) is respectively connected with the first processing cavity body (331), the second processing cavity body (332) and the third processing cavity body (333); air valves are arranged at the joints of the conversion pipeline (334) and the first processing cavity (331), the second processing cavity (332) and the third processing cavity (333); the air inlet end of the first processing cavity (331) is connected with the other end of the air flow buffer pipe (32);
the heat exchanger (34) comprises a frosting heat exchanger (341) installed inside the first process chamber (331), a medium temperature heat exchanger (342) installed inside the second process chamber (332), and a low temperature heat exchanger (343) installed inside the third process chamber (333);
and the air supply system (2) comprises an air supply pipeline (21) with an air inlet end connected with an air outlet end of the conversion pipeline (334) and an air supply device (22) arranged at the air outlet end of the air supply pipeline (21).
2. The ventilating device for the aircraft test as recited in claim 1, further comprising a fresh air system capable of purifying the air inside the chamber body.
3. An aircraft test ventilation device as claimed in claim 1, characterized in that said supply duct (21) is of variable cross-section design.
4. An aircraft test ventilation device as claimed in claim 1, characterized in that the air supply device (22) is a swirl nozzle.
5. A ventilating device for aircraft testing according to claim 1, wherein the duct chamber (30) comprises an air inlet connecting duct (301) connected to the return air duct (11), a treatment chamber duct (302) connected to the other end of the air inlet connecting duct (301) and used for installing a deployment processing device, and an air supply connecting duct (303) used for connecting the treatment chamber duct (302) with the air supply duct (21).
6. An aircraft test ventilation device as claimed in claim 5, wherein a baffle is provided at each corner of the supply air connecting duct (303).
7. An aircraft test ventilation device as claimed in claim 5, characterized in that a flow meter is arranged in the supply connection duct (303).
8. An aircraft test ventilation device as claimed in claim 1, characterized in that the moisture management system (4) comprises a dry steam humidifier for humidification and a rotary dehumidifier for dehumidification.
9. The ventilating device for the aircraft test as claimed in claim 1, wherein the frosting heat exchanger (341), the medium temperature heat exchanger (342) and the low temperature heat exchanger (343) are provided with electric tracing heat (344) on the outer surfaces thereof.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111390117.1A CN113830327A (en) | 2021-11-23 | 2021-11-23 | Ventilation unit for aircraft test |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111390117.1A CN113830327A (en) | 2021-11-23 | 2021-11-23 | Ventilation unit for aircraft test |
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| CN113830327A true CN113830327A (en) | 2021-12-24 |
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| CN202111390117.1A Pending CN113830327A (en) | 2021-11-23 | 2021-11-23 | Ventilation unit for aircraft test |
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Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN108150229A (en) * | 2016-12-02 | 2018-06-12 | 通用电气公司 | Control system and method |
| CN108168893A (en) * | 2017-12-13 | 2018-06-15 | 中国飞机强度研究所 | A kind of interior aircraft engine running experience compensated with air system |
| CN110006118A (en) * | 2019-03-29 | 2019-07-12 | 中国飞机强度研究所 | A kind of large-scale synthesis climatizer air treatment system |
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2021
- 2021-11-23 CN CN202111390117.1A patent/CN113830327A/en active Pending
Patent Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108150229A (en) * | 2016-12-02 | 2018-06-12 | 通用电气公司 | Control system and method |
| CN108168893A (en) * | 2017-12-13 | 2018-06-15 | 中国飞机强度研究所 | A kind of interior aircraft engine running experience compensated with air system |
| CN110006118A (en) * | 2019-03-29 | 2019-07-12 | 中国飞机强度研究所 | A kind of large-scale synthesis climatizer air treatment system |
Non-Patent Citations (1)
| Title |
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| 马建军等: "大型综合气候实验室基础环境模拟系统设计", 《装备环境工程》 * |
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Application publication date: 20211224 |