CN102179140A - Drying system used in airplane - Google Patents
Drying system used in airplane Download PDFInfo
- Publication number
- CN102179140A CN102179140A CN2011100300252A CN201110030025A CN102179140A CN 102179140 A CN102179140 A CN 102179140A CN 2011100300252 A CN2011100300252 A CN 2011100300252A CN 201110030025 A CN201110030025 A CN 201110030025A CN 102179140 A CN102179140 A CN 102179140A
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- Prior art keywords
- air
- dehumidifying
- time
- upstream end
- aircraft
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- 238000001035 drying Methods 0.000 title claims abstract description 22
- 239000011229 interlayer Substances 0.000 claims abstract description 14
- 238000011144 upstream manufacturing Methods 0.000 claims description 37
- 239000002912 waste gas Substances 0.000 claims description 30
- 238000001816 cooling Methods 0.000 claims description 29
- 230000000740 bleeding effect Effects 0.000 claims description 4
- 239000007789 gas Substances 0.000 claims description 4
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 abstract description 16
- 239000010410 layer Substances 0.000 abstract description 9
- 238000007791 dehumidification Methods 0.000 abstract description 6
- 238000009413 insulation Methods 0.000 abstract description 6
- 238000009825 accumulation Methods 0.000 abstract description 2
- 238000005057 refrigeration Methods 0.000 abstract 3
- 238000004519 manufacturing process Methods 0.000 abstract 1
- 238000005265 energy consumption Methods 0.000 description 5
- 230000000694 effects Effects 0.000 description 4
- 238000010586 diagram Methods 0.000 description 3
- 238000005516 engineering process Methods 0.000 description 3
- 238000000034 method Methods 0.000 description 3
- 238000004378 air conditioning Methods 0.000 description 2
- 230000001276 controlling effect Effects 0.000 description 2
- 230000007423 decrease Effects 0.000 description 2
- 238000010438 heat treatment Methods 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000009833 condensation Methods 0.000 description 1
- 230000005494 condensation Effects 0.000 description 1
- 230000007797 corrosion Effects 0.000 description 1
- 238000005260 corrosion Methods 0.000 description 1
- 238000005530 etching Methods 0.000 description 1
- 238000000605 extraction Methods 0.000 description 1
- 239000000446 fuel Substances 0.000 description 1
- 239000011810 insulating material Substances 0.000 description 1
- 239000007788 liquid Substances 0.000 description 1
- 230000007774 longterm Effects 0.000 description 1
- 238000012423 maintenance Methods 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 230000001105 regulatory effect Effects 0.000 description 1
- 125000006850 spacer group Chemical group 0.000 description 1
- 239000003643 water by type Substances 0.000 description 1
Images
Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D13/00—Arrangements or adaptations of air-treatment apparatus for aircraft crew or passengers, or freight space
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B01—PHYSICAL OR CHEMICAL PROCESSES OR APPARATUS IN GENERAL
- B01D—SEPARATION
- B01D53/00—Separation of gases or vapours; Recovering vapours of volatile solvents from gases; Chemical or biological purification of waste gases, e.g. engine exhaust gases, smoke, fumes, flue gases, aerosols
- B01D53/26—Drying gases or vapours
- B01D53/265—Drying gases or vapours by refrigeration (condensation)
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B01—PHYSICAL OR CHEMICAL PROCESSES OR APPARATUS IN GENERAL
- B01D—SEPARATION
- B01D2259/00—Type of treatment
- B01D2259/45—Gas separation or purification devices adapted for specific applications
- B01D2259/4566—Gas separation or purification devices adapted for specific applications for use in transportation means
- B01D2259/4575—Gas separation or purification devices adapted for specific applications for use in transportation means in aeroplanes or space ships
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D13/00—Arrangements or adaptations of air-treatment apparatus for aircraft crew or passengers, or freight space
- B64D13/06—Arrangements or adaptations of air-treatment apparatus for aircraft crew or passengers, or freight space the air being conditioned
- B64D2013/0603—Environmental Control Systems
- B64D2013/0662—Environmental Control Systems with humidity control
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/50—On board measures aiming to increase energy efficiency
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- Chemical & Material Sciences (AREA)
- Engineering & Computer Science (AREA)
- Oil, Petroleum & Natural Gas (AREA)
- Thermal Sciences (AREA)
- Analytical Chemistry (AREA)
- General Chemical & Material Sciences (AREA)
- Physics & Mathematics (AREA)
- Chemical Kinetics & Catalysis (AREA)
- Health & Medical Sciences (AREA)
- General Health & Medical Sciences (AREA)
- Pulmonology (AREA)
- Aviation & Aerospace Engineering (AREA)
- Central Air Conditioning (AREA)
- Drying Of Gases (AREA)
Abstract
In order to control the production of cold condensate within an aircraft, the invention proposes a drying system comprising: the refrigeration assembly is provided with an air inlet end for primary dehumidification and an air outlet end for primary dehumidification, and the refrigeration assembly is used for carrying out primary dehumidification on fresh air entering from the air inlet end for primary dehumidification so as to reduce the absolute humidity of the fresh air; the heat exchanger is provided with an exhaust gas inlet end, an exhaust gas outlet end, a secondary dehumidified air inlet end and a secondary dehumidified air outlet end, the exhaust gas inlet end is communicated with the electronic equipment cabin, and the heat exchanger is used for carrying out heat exchange on hot exhaust gas exhausted by the electronic equipment cabin and cold fresh air exhausted by the refrigeration assembly so as to carry out secondary dehumidification and reduce the relative humidity of the hot exhaust gas and the cold fresh air to obtain dry air; a distribution line for delivering dry air into the fuselage sandwich, and a control assembly. By the aid of the drying system, accumulation of condensed water or ice in the heat and sound insulation layer of the airplane can be reduced, and heat insulation performance of the interlayer of the airplane is improved.
Description
Technical field
The present invention relates to a kind of drying system that is used in the aircraft.More particularly, the present invention relates to a kind of drying system in the aircraft of being used for that reduces energy consumption.
Background technology
Aircraft in flight course, per hour approximately breathe out steam of 100 grams of every passenger, and these steam run into after the cold mechanism of aircraft cooling rapidly and form condensed water, therefore, are very surprising in long-term formed in-flight condensed water quantity.The result, after condensed water is absorbed by the heat insulation layer in the fuselage and miscellaneous equipment, the weight that makes aircraft is increased more than half ton (condensation water quantity is mainly relevant with passengers quantity, the aircraft method of operation, regional climate), and the weight that increases will cause higher fuel consume, and environment is caused negative influence.Worse, a large amount of condensed waters can cause heat insulation layer damage and then etching machine body structure and damage electrical equipment that reduced the service life of aircraft.In addition, liquid water droplets flows into main cabin or driving cabin, also is that the passenger and crew is undesirable.
Apparently, or the generation of control condensed water, or the condensed water that forms is handled is the method that solves the problems of the technologies described above.In the prior art, the aircraft that has is controlled the generation of condensed water by installing drying system additional, but mostly be special drying system, to the processing of heating that dehumidifies of air in the cabin, this will cause the increase of airplane equipment weight, can strengthen the power consumption of aircraft simultaneously, thereby cause the increase of aircraft energy consumption, promptly this dehumidification mode is to be based upon on the basis that makes the increase of aircraft energy consumption.
Summary of the invention
In order to reduce aircraft energy consumption, a kind of new drying system that the present invention proposes on the basis that makes full use of the aircraft existing equipment as much as possible.Electronic equipment on the aircraft need cool off air and cool off keeping its normal operation, and the generation used heat that will heat up behind the air cooling electronic apparatus, in the prior art, basically, the air that all these is had used heat is directly discharged aircraft.Yet in the present invention, these used heat heat the fresh air that cooling assembly generates by heat exchanger, thereby reduce the relative humidity of fresh air.Because existing cooling assembly equipment itself just has except that water function, the humidity of the fresh air of cooling assembly outlet is very low, and behind the heat temperature raising of over-heat-exchanger, humidity will be lower again, drying capacity is enhanced, and has improved rate of energy on the aircraft simultaneously.
Particularly, the invention discloses a kind of drying system that is used in the aircraft, it comprises: cooling assembly, heat exchanger, distribution circuit and Control Component.Wherein, cooling assembly has the air upstream end of dehumidifying for the first time and the air outlet side that dehumidifies for the first time, reduces its absolute humidity thereby described cooling assembly is used for that the fresh air that the air upstream end from the described dehumidifying first time enters is carried out the dehumidifying first time; Heat exchanger, has the waste gas upstream end, the waste gas outlet side, the air upstream end of dehumidifying and the air outlet side of dehumidifying for the second time for the second time, described waste gas upstream end is communicated with electronics bay, described waste gas outlet side is communicated with the outside of aircraft, the air upstream end of described second time of dehumidifying is communicated with the air outlet side of the described dehumidifying first time, thereby described heat exchanger is used for the waste gas of the heat that will enter from described waste gas upstream end and be discharged by described waste gas outlet side and enters and carry out heat exchange by the fresh air of the air outlet side discharge of the described dehumidifying second time and carry out dehumidifying the second time and obtain dry air to reduce its relative humidity from the air upstream end of the described dehumidifying second time; Distribution circuit is used for the dry air that the air outlet side of the described dehumidifying second time is discharged is transported in the fuselage interlayer; Control Component is used for controlling at least according to different operating modes one of them person of the efficient of the flow of described dry air and described heat exchanger.
Preferably, described Control Component is used to control the exhaust gas flow of the waste gas upstream end of described heat exchanger.
Preferably, described Control Component is used to control the flow of described dry air.
More preferably, arbitrary place in the position between the air upstream end of the air outlet side of the position of the air upstream end of described first time of dehumidifying, the position on the described distribution circuit, the described first time of dehumidifying and the described second time of dehumidifying and the position of described waste gas upstream end is provided with flow control valve, and described Control Component is realized flow-control to described dry air via described flow control valve.
Particularly, described distribution circuit is arranged in the lateral region and/or the top area of aircraft.
Particularly, described aircraft has bilge portion, and air bleeding valve is located at described bilge portion, and the dry air that is used for being transported in the fuselage interlayer is discharged.
By described drying system, the present invention can reach following beneficial technical effects: reduce or eliminate the accumulation of interior condensed water of the adiabatic sound insulating layer of aircraft or ice; Utilize the used heat in the electronic equipment exhaust, improve the aircraft energy utilization rate, strengthen the aircraft economy; Reduce the fuselage corrosion, reduce the electric fault and the short circuit phenomenon of aircraft, improve aircraft safety; Strengthen the adiabatic heat-insulation effect of aircraft interlayer, reduce the aircraft air-conditioning system thermal force, reduce the aircraft energy consumption, improve the economy and the comfortableness of aircraft.
Description of drawings
Fig. 1 is the schematic diagram of drying system of the present invention;
Fig. 2 is an airframe interlayer gap schematic diagram.
The specific embodiment
As shown in Figure 1, it shows the schematic diagram of drying system of the present invention, and wherein, described drying system 10 is made up of cooling assembly 1, heat exchanger 2, distribution circuit 3 and Control Component 4.Described cooling assembly 1 has the air upstream end 11 of dehumidifying for the first time and the air outlet side 12 of dehumidifying for the first time, thereby it is used for the fresh air that the air upstream end 11 from the described dehumidifying first time enters carried out dehumidifying first time reducing its absolute humidity.Described heat exchanger 2 has the air upstream end 23 of waste gas upstream end 21, waste gas outlet side 22, dehumidifying for the second time and the air outlet side 24 that dehumidifies for the second time.Wherein, described waste gas upstream end 21 is connected with electronics bay 5, described waste gas outlet side 22 communicates with the aircraft external world, the air upstream end 23 of the described dehumidifying second time communicates with the air outlet side 12 of the dehumidifying first time of cooling assembly 1, and the air outlet side 24 of the described dehumidifying second time is communicated with distribution circuit 3.Described distribution circuit 3 has an end 31 of the dry air of air outlet side 24 discharges that receive the described dehumidifying second time, and described dry air is transported to the other end 32 in the fuselage interlayer, the described other end 32 is provided with near the fuselage interlayer of aircraft, and described distribution circuit 3 is used for dry gas is assigned to the preposition place and forms air-flow in the airframe interlayer.Described Control Component 4, be used for according to different operating mode control cooling assembly 1 and heat exchanger 2, more preferably, control one of them person of the efficient of the flow of described dry air and described heat exchanger 2 at least, more preferably, can control the efficient of the flow and the heat exchanger 2 of dry air simultaneously.More specifically, described Control Component 4 is single-chip microcomputer (SCM) or CPU (CPU) or the programmable logic controller (PLC) any controllers that can realize data operation and disposal ability such as (PLC), it can control the flow of dry air to satisfy need of work via flow control valve, the exhaust gas flow that can control also that waste gas upstream end 21 via heat exchanger 2 enters and be discharged by waste gas outlet side 22 is controlling the efficient of described heat exchanger 2, thereby the power that also can control described cooling assembly 1 and described heat exchanger 2 in addition reaches the parameters such as temperature and humidity of regulating the final dry air that flows out.Preferably, position between the air upstream end 23 of the air outlet side 12 of the position of the air upstream end 11 of dehumidifying first time of described cooling assembly 1, the position on the described distribution circuit 3, the described first time of dehumidifying and the described second time of dehumidifying (promptly, position between cooling assembly 1 and the heat exchanger 2), in the position of described waste gas upstream end 21 (being the position between heat exchanger 2 and the described electronics bay 5), a flow control valve can be set respectively also can only flow control valve be set in some or certain several position.Described flow control valve also can be manually operated, is preferably controlled automatically by above-mentioned Control Component 4.
As everyone knows, all has de-watering apparatus in the cooling assembly 1 in the aircraft, therefore, when entering cooling assembly 1 after can reduce the absolute humidity of fresh air widely by the de-watering apparatus of described cooling assembly 1 from the air upstream end 11 of dehumidifying for the first time from the fresh air of engine.What like this, the air outlet side 12 of the dehumidifying first time of cooling assembly 1 was discharged is exactly the lower fresh air of humidity.In the present invention, described heat exchanger 2 is used for and will discharges from the air outlet side 12 of dehumidifying first time of cooling assembly 1 and enter the cold relatively fresh air of heat exchanger 2 and carry out exchange heat from the waste gas of the relatively hot of heat exchanger 2 that electronics bay 5 is discharged and entered from waste gas upstream end 21 from the air upstream end 23 that dehumidifies for the second time.From the cold fresh air of cooling assembly 1 behind over-heat-exchanger 2, because temperature raises after the heat exchange, thereby the relative water capacity of fresh air will decrease, what therefore, discharge from the air outlet side 24 of dehumidifying second time of heat exchanger 2 is exactly absolute humidity and all lower dry air of relative humidity.Described dry air is transported to those by distribution circuit 3 needs dry aircraft passenger compartment zone as zones such as top, main cabin, main cabin sidewall spacers.Simultaneously, discharge aircraft through the waste gas after the heat exchange via waste gas outlet side 22.
More preferably, can control the efficient of heat exchanger 2, obtain the temperature dry air different with relative humidity by the extraction flow from electronics bay 5 on control heat exchanger 2 hot limits.Simultaneously also can be according to temperature, damp condition in external condition and the cabin different, the flow of control dry air.
More preferably, in order to alleviate the weight of aircraft, distribution circuit 3 can be made up of the pipeline of lighter weight, and is arranged in the top area of aircraft from front to back, and the central authorities of the as far as possible close aircraft in its position are with the uniformity of guaranteeing that control air distributes.
Below, describe how forming the protection air-flow in conjunction with Fig. 2.
Fuselage outer side structure and inside sidewalls structure have formed fuselage sandwich, as shown in Figure 2, it shows a kind of fuselage sandwich that is made of airframe structure 6, trim panel 7, adiabatic sound insulating layer 8 substantially, wherein, is formed with gap 9 between trim panel 7 and the adiabatic sound insulating layer 8.
In the prior art, the passenger and crew is in the main cabin behind the exhalation humid air, this humid air can enter the top area and the sidewall areas in main cabin by the slit, and from the top or lateral region flow to gap 9, the adiabatic sound insulating layer 8 that humid air and temperature are lower contacts with airframe structure 6 and forms condensed water.
In the present invention, after delivering to top, main cabin or lateral region equably by distribution circuit 3 dry air that temperature and humidity is all comparatively suitable, because air bleeding valve is located at the bilge portion of aircraft usually, like this, the pressure of aircraft cabin bottom can be a little less than the top area in main cabin, therefore, the gap 9 of dry air between trim panel 7 and adiabatic sound insulating layer 8 flows into the trigonum, participate in the recirculation except that a part of dry air enters recirculation regions, all the other dry airs are finally discharged out of my cabin by the air bleeding valve of bilge portion.The dry air that temperature is higher, humidity is lower in the gap of fuselage interlayer, formed one deck play " heat-insulation layer " effect protection air-flow fuselage outer side structure and the higher inside sidewalls structure of temperature that temperature is lower keep apart; thereby; avoided humid air directly directly to contact with fuselage outer side structure (as covering, long purlin etc.); therefore, prevent the temperature decline and the generation condensed water of humid air effectively.As previously mentioned, the top, main cabin that distribution circuit 3 is arranged in aircraft only is more excellent scheme, and in fact, distribution circuit 3 also can be arranged in the both sides, main cabin of aircraft, and more preferably, distribution circuit 3 can also be arranged in the both sides, main cabin and the main cabin top area of aircraft simultaneously.
Principle of the present invention is as follows: utilize the fresh air of the higher characteristics heating of electronics bay delivery temperature from cooling assembly, reduction is from the relative humidity of the fresh air of cooling assembly, make this part fresh air dry more and obtain dry air, again this part dry air is fed in the gap of the lower fuselage interlayer of temperature, prevent the generation of condensed water.At this, need to prove that in the prior art, the cooling assembly of aircraft itself just has except that water function, the present invention has utilized this function of cooling assembly just, does not need special dehydrating unit.Simultaneously, utilized used heat in the electronics bay exhaust to heat fresh air from cooling assembly.Like this, not only obtain dry air, also improved capacity usage ratio.The higher dry air of temperature enters in the aircraft interlayer, can improve the heat-insulating property of aircraft interlayer, reduces the thermal force of aircraft air-conditioning system.
The present invention can be achieved as follows technique effect: keep the aircraft cabin inner drying, alleviate aircraft weight, prolong heat-insulating material life-span, reduce airplane fault and reduce aircraft maintenance work.Simultaneously, also effectively utilized the high-temp waste gas that cooling electronic apparatus produced.
Technology contents of the present invention and technical characterstic disclose as above, yet are appreciated that under creative ideas of the present invention, those skilled in the art can make various changes and modifications to said structure, but all belongs to protection scope of the present invention.The description of above-mentioned embodiment is exemplary rather than restrictive, and protection scope of the present invention is determined by claim.
Claims (6)
1. one kind is used for the interior drying system of aircraft, comprising:
Cooling assembly has the air upstream end of dehumidifying for the first time and the air outlet side that dehumidifies for the first time, reduces its absolute humidity thereby described cooling assembly is used for that the fresh air that the air upstream end from the described dehumidifying first time enters is carried out the dehumidifying first time;
Heat exchanger, has the waste gas upstream end, the waste gas outlet side, the air upstream end of dehumidifying and the air outlet side of dehumidifying for the second time for the second time, described waste gas upstream end is communicated with electronics bay, described waste gas outlet side is communicated with the outside of aircraft, the air upstream end of described second time of dehumidifying is communicated with the air outlet side of the described dehumidifying first time, thereby described heat exchanger is used for the waste gas of the heat that will enter from described waste gas upstream end and be discharged by described waste gas outlet side and enters and carry out heat exchange by the fresh air of the air outlet side discharge of the described dehumidifying second time and carry out dehumidifying the second time and obtain dry air to reduce its relative humidity from the air upstream end of the described dehumidifying second time;
Distribution circuit is used for the dry air that the air outlet side of the described dehumidifying second time is discharged is transported in the fuselage interlayer, and
Control Component is used for controlling at least according to different operating modes one of them person of the efficient of the flow of described dry air and described heat exchanger.
2. drying system according to claim 1, described Control Component are used to control the exhaust gas flow of the waste gas upstream end of described heat exchanger.
3. drying system according to claim 1, wherein, described Control Component is used to control the flow of described dry air.
4. drying system according to claim 3, wherein, the arbitrary place in the position of the position between the air upstream end of the air outlet side of the position of the air upstream end of described first time of dehumidifying, the position on the described distribution circuit, the described first time of dehumidifying and the described second time of dehumidifying, described waste gas upstream end is provided with flow control valve.
5. drying system according to claim 1, wherein, described distribution circuit is arranged in the lateral region and/or the top area of aircraft.
6. drying system according to claim 1, described aircraft has bilge portion, and air bleeding valve is located at described bilge portion, and the dry air that is used for being transported in the fuselage interlayer is discharged.
Priority Applications (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2011100300252A CN102179140B (en) | 2011-01-27 | 2011-01-27 | Drying system used in airplane |
| PCT/CN2011/079648 WO2012100542A1 (en) | 2011-01-27 | 2011-09-14 | Dehumidification system for use in airplanes |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2011100300252A CN102179140B (en) | 2011-01-27 | 2011-01-27 | Drying system used in airplane |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN102179140A true CN102179140A (en) | 2011-09-14 |
| CN102179140B CN102179140B (en) | 2013-05-01 |
Family
ID=44565542
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN2011100300252A Active CN102179140B (en) | 2011-01-27 | 2011-01-27 | Drying system used in airplane |
Country Status (2)
| Country | Link |
|---|---|
| CN (1) | CN102179140B (en) |
| WO (1) | WO2012100542A1 (en) |
Cited By (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103204242A (en) * | 2013-03-25 | 2013-07-17 | 大连理工大学 | Double air channel wall for airplane |
| CN104071327A (en) * | 2014-06-05 | 2014-10-01 | 江苏科技大学 | Parallel type temperature control system and control method for stratospheric airship |
| CN104097779A (en) * | 2013-04-03 | 2014-10-15 | 空中客车作业有限公司 | Aircraft air-conditioining system |
| CN104260891A (en) * | 2014-09-23 | 2015-01-07 | 中国商用飞机有限责任公司 | Method and system for ventilating and heating aircraft cargo compartment |
| CN104802996A (en) * | 2014-01-24 | 2015-07-29 | 波音公司 | Dehumidification system for use in a vehicle and method of assembling thereof |
| CN105984305A (en) * | 2015-01-30 | 2016-10-05 | 观致汽车有限公司 | Drying and ventilating device and system for high-pressure system of vehicle |
| CN110960964A (en) * | 2019-12-21 | 2020-04-07 | 铜陵万华禾香板业有限公司 | Method and device for dehumidifying compressed air of glue applying system |
| CN113734447A (en) * | 2016-04-22 | 2021-12-03 | 哈米尔顿森德斯特兰德公司 | Environmental control system with dual channel secondary heat exchanger and cabin pressure assist |
| CN113955123A (en) * | 2021-12-09 | 2022-01-21 | 中国商用飞机有限责任公司 | Aircraft dehumidification system |
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- 2011-09-14 WO PCT/CN2011/079648 patent/WO2012100542A1/en active Application Filing
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| CN1060270A (en) * | 1990-08-17 | 1992-04-15 | 联合技术股份有限公司 | The environmental control system condensing circulation |
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Cited By (14)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103204242A (en) * | 2013-03-25 | 2013-07-17 | 大连理工大学 | Double air channel wall for airplane |
| CN104097779A (en) * | 2013-04-03 | 2014-10-15 | 空中客车作业有限公司 | Aircraft air-conditioining system |
| US10343781B2 (en) | 2013-04-03 | 2019-07-09 | Airbus Operations Gmb | Aircraft cooling system |
| US9988151B2 (en) | 2014-01-24 | 2018-06-05 | The Boeing Company | Dehumidification system for use in a vehicle and method of assembling thereof |
| CN104802996A (en) * | 2014-01-24 | 2015-07-29 | 波音公司 | Dehumidification system for use in a vehicle and method of assembling thereof |
| CN104071327A (en) * | 2014-06-05 | 2014-10-01 | 江苏科技大学 | Parallel type temperature control system and control method for stratospheric airship |
| CN104071327B (en) * | 2014-06-05 | 2016-03-30 | 江苏科技大学 | Stratospheric Airship Parallel Temperature Control System and Control Method |
| CN104260891A (en) * | 2014-09-23 | 2015-01-07 | 中国商用飞机有限责任公司 | Method and system for ventilating and heating aircraft cargo compartment |
| CN104260891B (en) * | 2014-09-23 | 2016-08-24 | 中国商用飞机有限责任公司 | Method and system for ventilating and heating aircraft cargo compartment |
| CN105984305A (en) * | 2015-01-30 | 2016-10-05 | 观致汽车有限公司 | Drying and ventilating device and system for high-pressure system of vehicle |
| CN113734447A (en) * | 2016-04-22 | 2021-12-03 | 哈米尔顿森德斯特兰德公司 | Environmental control system with dual channel secondary heat exchanger and cabin pressure assist |
| CN113734447B (en) * | 2016-04-22 | 2024-01-02 | 哈米尔顿森德斯特兰德公司 | Environmental control system using dual channel secondary heat exchanger and cabin pressure assist |
| CN110960964A (en) * | 2019-12-21 | 2020-04-07 | 铜陵万华禾香板业有限公司 | Method and device for dehumidifying compressed air of glue applying system |
| CN113955123A (en) * | 2021-12-09 | 2022-01-21 | 中国商用飞机有限责任公司 | Aircraft dehumidification system |
Also Published As
| Publication number | Publication date |
|---|---|
| WO2012100542A1 (en) | 2012-08-02 |
| CN102179140B (en) | 2013-05-01 |
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