CN102398684A - Carbon dioxide concentration control system for closed capsule of manned spacecraft - Google Patents
Carbon dioxide concentration control system for closed capsule of manned spacecraft Download PDFInfo
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- CN102398684A CN102398684A CN2010102853439A CN201010285343A CN102398684A CN 102398684 A CN102398684 A CN 102398684A CN 2010102853439 A CN2010102853439 A CN 2010102853439A CN 201010285343 A CN201010285343 A CN 201010285343A CN 102398684 A CN102398684 A CN 102398684A
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- carbon dioxide
- closed
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- control system
- concentration control
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Abstract
The invention discloses a carbon dioxide concentration control system for a closed capsule of a manned spacecraft. The carbon dioxide concentration control system comprises a carbon dioxide extraction device, a carbon dioxide transmission channel, an electrolyzer and a power supply device, wherein the carbon dioxide extraction device is arranged in a gas flowing system of the closed capsule, one end of the carbon dioxide transmission channel is connected with the carbon dioxide extraction device, the electrolyzer is connected with the other end of the carbon dioxide transmission channel and is capable of solidifying carbon dioxide, and the power supply device is used for supplying electric power for the electrolyzer. In the carbon dioxide concentration control system disclosed by the invention, after carbon dioxide in the gas flowing system of the closed capsule is collected, the collected carbon dioxide is solidified into an organic matter through reduction reaction, so that carbon dioxide in the gas flowing system can be removed directly, and the concentration of carbon dioxide in the closed capsule is reduced further; therefore, the long-term control on carbon dioxide concentration can be realized.
Description
Technical field
The present invention relates to gas concentration control technology field, relate in particular to a kind of manned spacecraft closed in space carbon dioxide concentration control system.
Background technology
The length that realizes manned spacecraft is apart from interplanetary travel; Cosmonaut's carbon-dioxide processing that metabolism produces in closed in space is the problem that must solve; But will the gas concentration lwevel of closed in space be controlled in the human body tolerance range, otherwise the safety that will endanger the cosmonaut.
When manned spacecraft moves near earth space; The control of gas concentration lwevel can be adopted short-term solution in the closed in space; Absorb the CO2 in the closed in space through the CO2 in the carbon dioxide absorber absorption closed in space or through carbon-dioxide absorbent; Replenish new adsorbent or absorbent through the emission delivery ship afterwards, and will contain carbon-dioxide adsorbent or absorbent is transported ground back, realize closed in space's concentration of carbon dioxide control.
But when manned spacecraft is grown flying of distance far awayly; Be limited to launching condition or economic consideration and can't launch delivery ship; At this moment; Can't replenish new adsorbent or absorbent, and also can't transport containing carbon-dioxide adsorbent or absorbent, above-mentioned short-term solution can not satisfy manned spacecraft requirement to closed in space's gas concentration lwevel control in the long-distance flight process.
Summary of the invention
In view of this, the object of the present invention is to provide a kind of manned spacecraft closed in space carbon dioxide concentration control system, can be at the gas concentration lwevel in the medium-term and long-term control of the manned spacecraft long-distance flight process closed in space.
For realizing above-mentioned purpose, the present invention provides following technical scheme:
A kind of manned spacecraft closed in space carbon dioxide concentration control system comprises: be arranged at the carbon dioxide draw device in the gas flow system of said closed in space; One end and said carbon dioxide draw device bonded assembly CO2 transmission path; Be connected with the other end of said CO2 transmission path, curable carbon-dioxide electrolytic cell; Can be said electrolytic cell provides the electric supply installation of electric energy.
Preferably, the cathode material of said electrolytic cell is one or more in copper, tin and the chromium, and anode material is a nickel, and battery acid is a sodium sulphaste.
Preferably; Said carbon dioxide draw device is: admission port is positioned at said closed in space gas flow system, air extractor duct and said CO2 transmission path bonded assembly cylindrical shell, between said admission port and said air extractor duct, is provided with and only holds polypropylene screen or the polyethylene film that CO2 passes through.
Preferably, said carbon dioxide draw device comprises: the carbon dioxide collecting device of built-in carbon dioxide absorber or absorbent; Can discharge carbon-dioxide device for releasing carbon dioxide in said adsorbent or the absorbent; Can the adsorbent in the said carbon dioxide collecting device or absorbent be transferred to first transmitting device of said device for releasing carbon dioxide; Can the adsorbent in the said device for releasing carbon dioxide or absorbent be transferred to second transmitting device of said carbon dioxide collecting device.
Preferably, also comprise: fuel cell, and the 3rd transmitting device that can the organic matter in the said electrolytic cell be transferred to said fuel cell.
Preferably, also comprise: the four-way that connects said electrolytic cell and said fuel cell.
Preferably, also comprise: organic matter memory storage, and the 5th transmitting device that can the organic matter in the said electrolytic cell be transferred to said organic matter memory storage.
Preferably, said electric supply installation comprises photoemissive element and energy-storage battery.
This shows; Beneficial effect of the present invention is: in carbon dioxide concentration control system disclosed by the invention; After the CO2 in collecting closed in space's gas flow system, the CO2 of collecting is cured as organic matter, directly eliminates the CO2 in the gas flow system through reduction reaction; And then reduce the gas concentration lwevel in the closed in space, realize long-term control to gas concentration lwevel.
Description of drawings
In order to be illustrated more clearly in the embodiment of the invention; To do simple introduction to the accompanying drawing of required use among the embodiment below; Obviously, the accompanying drawing in describing below only is some embodiments of the present invention, for those of ordinary skills; Under the prerequisite of not paying creative work, can also obtain other accompanying drawing according to these accompanying drawings.
Fig. 1 is the structural representation of the disclosed manned spacecraft of the embodiment of the invention one closed in space carbon dioxide concentration control system;
Fig. 2 is the structural representation of the disclosed manned spacecraft of the embodiment of the invention two closed in space carbon dioxide concentration control system;
Fig. 3 is the structural representation of the disclosed manned spacecraft of the embodiment of the invention three closed in space carbon dioxide concentration control system;
Fig. 4 is the structural representation of the disclosed manned spacecraft of the embodiment of the invention four closed in space carbon dioxide concentration control system;
Fig. 5 is the structural representation of the disclosed manned spacecraft of the embodiment of the invention five closed in space carbon dioxide concentration control system.
The specific embodiment
To combine the accompanying drawing in the embodiment of the invention below, the technical scheme in the embodiment of the invention is carried out clear, intactly description, obviously, described embodiment only is the present invention's part embodiment, rather than whole embodiment.Based on the embodiment among the present invention, those of ordinary skills are not making under the creative work prerequisite, and the every other embodiment that is obtained belongs to protection domain of the present invention.
The invention discloses a kind of manned spacecraft closed in space carbon dioxide concentration control system, can be at the gas concentration lwevel in the medium-term and long-term control of the manned spacecraft long-distance flight process closed in space.
Embodiment one
Referring to Fig. 1, Fig. 1 is the structural representation of the disclosed manned spacecraft of the embodiment of the invention one closed in space carbon dioxide concentration control system.
This control system comprises: carbon dioxide draw device 11, CO2 transmission path 12, electrolytic cell 13 and electric supply installation 14.
Wherein, Carbon dioxide draw device 11 is arranged in the gas flow system 15 of closed in space; Gas flow system 15 is under the effect of its engine installation 16; Make that the gas that is in the closed in space under agravic or the microgravity is flowed, carbon dioxide draw device 11 is used for extracting the CO2 of gas flow system 15; The two ends of CO2 transmission path 12 are connected with electrolytic cell 13 with carbon dioxide draw device 11 respectively; The CO2 that carbon dioxide draw device 11 obtains can get in the electrolytic cell 13 through CO2 transmission path 12, and the reaction of CO2 generation reduction curing forms organic molecules such as formic acid, methyl alcohol and formaldehyde in electrolytic cell 13; Electric supply installation 14 is electrolytic cell 13 power supplies, guarantees the carrying out of carbon dioxide reduction curing reaction.
In the foregoing description one disclosed carbon dioxide concentration control system; After the CO2 in collecting closed in space's gas flow system; Through reduction reaction the CO2 of collecting is cured as organic matter; Eliminate the CO2 in the gas flow system, and then reduce the gas concentration lwevel in the closed in space, realize control gas concentration lwevel.
Embodiment two
Referring to Fig. 2, Fig. 2 is the structural representation of the disclosed manned spacecraft of the embodiment of the invention two closed in space carbon dioxide concentration control system.
This control system comprises: carbon dioxide collecting device 21, device for releasing carbon dioxide 22, first transmitting device 23, second transmitting device 24, CO2 transmission path 25, electrolytic cell 26 and electric supply installation 27.
Wherein, Carbon dioxide collecting device 21 is arranged in the gas flow system of closed in space; In carbon dioxide collecting device 21, be placed with carbon dioxide absorber or absorbent; Adsorbable or absorb the CO2 in the gas flow system; Be adsorbed with carbon-dioxide adsorbent afterwards or be absorbed with carbon-dioxide absorbent and transfer in the device for releasing carbon dioxide 22 through first transmitting device 23; Device for releasing carbon dioxide 22 discharges the CO2 in adsorbent or the absorbent, and transfers in the electrolytic cell 26 through the CO2 transmission path 25 that is attached thereto and to be cured as organic matter, and the adsorbent after the release of carbon dioxide or absorbent turn back in the carbon dioxide collecting device 21 through second transmitting device 24 in the device for releasing carbon dioxide 22; Again absorbing carbon dioxide, electric supply installation 27 are the reduction reaction power supply in the electrolytic cell 26.
In force, the absorbent in the carbon dioxide collecting device 21 can adopt ammoniacal liquor, monoethanolamine, tetraethylenepentamine or other to contain the material of amine groups.
When the absorbent in the carbon dioxide collecting device 21 was ammoniacal liquor, ammoniacal liquor absorbed the CO2 in the gas flow system, and its chemical equation is: NH
3H
2O+CO
2→ NH
4HCO
3Afterwards; Being absorbed with carbon-dioxide ammoniacal liquor gets in the device for releasing carbon dioxide 22 through first transmitting device 23; Pressure in the device for releasing carbon dioxide 22 is low than the pressure in the carbon dioxide collecting device 21, temperature is high than the temperature in the carbon dioxide collecting device 21, and the CO2 that absorb in the ammoniacal liquor this moment is released, and its chemical equation is: NH
4HCO
3→ NH
3H
2O+CO
2↑.Ammoniacal liquor after the release of carbon dioxide returns in the carbon dioxide collecting device 21 through second transmitting device 24, is used for absorbing carbon dioxide once more, has realized the recycle of ammoniacal liquor.
It is to be noted material that monoethanolamine, tetraethylenepentamine or other contain amine groups all can with the CO2 absorbing carbon dioxide that reacts, after changing reaction conditions, reversible process takes place discharges the CO2 that absorbs, can repeated usage.
Adsorbent in the carbon dioxide collecting device 21 can be calcium oxide, alundum (Al, magnesia or active carbon.
CO2 in the gas flow system is adsorbed by the solid adsorbent in the carbon dioxide collecting device 21; Be adsorbed with carbon-dioxide solid adsorbent afterwards and get into device for releasing carbon dioxide 22 through first transmitting device 23; Under the condition of low-voltage high-temperature; The CO2 that is adsorbed in the solid adsorbent is released, and the solid adsorbent after the release of carbon dioxide returns carbon dioxide collecting device 21 through second transmitting device 24, is used for absorbing carbon dioxide once more.
In the foregoing description two disclosed carbon dioxide concentration control systems; Adsorbent in carbon dioxide collecting device and the device for releasing carbon dioxide and absorbent can be recycled and reused for carbon-dioxide extraction and release; Under the situation that new adsorbent and absorbent are not provided, can accomplish carbon-dioxide extraction for a long time; Through electrolytic cell CO2 is cured as organic matter; Eliminate the CO2 in the gas flow system, and then reduce the gas concentration lwevel in the closed in space, realize control gas concentration lwevel.
Embodiment three
Referring to Fig. 3, Fig. 3 is the structural representation of the embodiment of the invention three disclosed carbon dioxide draw devices.
The carbon dioxide draw device is a tube structure; This cylindrical shell 31 has admission port 311 and air extractor duct 312, and wherein, admission port 311 is positioned at the gas flow system 32 of closed in space; Air extractor duct 312 is connected with an end of CO2 transmission path 33; The other end of CO2 transmission path 33 is connected with electrolytic cell 34, between the admission port 311 of cylindrical shell 31 and air extractor duct 312, is provided with and only holds polypropylene screen or the polyethylene film 313 that CO2 passes through, and electric supply installation 35 is used to electrolytic cell 34 power supplies.
Gas in closed in space's gas flow system gets into after the cylindrical shell 31; Owing between admission port 311 and air extractor duct 312, be provided with and only hold polypropylene screen or the polyethylene film 313 that CO2 passes through; This causes other gases in the air flow system to be intercepted; Have only CO2 to get in the electrolytic cell 34 through air extractor duct 312 and CO2 transmission path 33 successively, the reduction reaction takes place under the effect of electrolytic cell 34 be cured as organic matter.
In the foregoing description three disclosed carbon dioxide concentration control systems; Only need to be provided with and only hold polypropylene screen or the polyethylene film that CO2 passes through and to accomplish carbon-dioxide extraction; Through reduction reaction CO2 is cured as organic matter afterwards, eliminates the CO2 in the gas flow system, and then reduce the gas concentration lwevel in the closed in space; Realization is to the control of gas concentration lwevel; Be that with the difference of embodiment two disclosed carbon dioxide concentration control systems need not just to accomplish the control to gas concentration lwevel by adsorbent, system architecture is simpler.
Embodiment four
Referring to Fig. 4, Fig. 4 is the structural representation of the embodiment of the invention four disclosed carbon dioxide draw devices.
This control system comprises: carbon dioxide draw device 41, CO2 transmission path 42, electrolytic cell 43, electric supply installation 44, fuel cell 45, the 3rd transmitting device 46 and the 4th transmission path 47.
Wherein, carbon dioxide draw device 41 is arranged in the gas flow system 48 of closed in space, is used for extracting the CO2 of gas flow system 48; The two ends of CO2 transmission path 42 are connected with electrolytic cell 43 with carbon dioxide draw device 41 respectively; The CO2 that carbon dioxide draw device 41 obtains can get in the electrolytic cell 43 through CO2 transmission path 42, and the reaction of CO2 generation reduction curing forms organic molecules such as formic acid, methyl alcohol and formaldehyde in electrolytic cell 43; Electric supply installation 44 is electrolytic cell 43 power supplies, guarantees the carrying out of carbon dioxide reduction curing reaction; The organic molecules such as formic acid, methyl alcohol and formaldehyde that generate in the electrolytic cell 43; Can transfer in the fuel cell 45 through the 3rd transmitting device 46; Fuel cell 45 with organic molecule act as a fuel, with air as oxidizer; Convert chemical power to electric energy, this electric energy can be the engine installation 49 or the power supply of the Lighting System in the manned spacecraft of electrolytic cell 43, gas flow system 48.
Preferably, the 4th transmission path 47 is set between fuel cell 45 and electrolytic cell 43.Fuel cell 45 can produce CO2 in course of reaction; If directly with carbon-dioxide emission in closed in space; Then CO2 just can be extracted and then solidify after only entering into gas flow system 48; This can cause the increase of the carbon dioxide content in the closed in space, in fuel cell 45 and electrolytic cell 43, the 4th transmission path 47 is set after, the CO2 that fuel cell 45 produces can directly get in the electrolytic cells 43 through the 4th transmission path 47 and be cured.
The embodiment of the invention four disclosed carbon dioxide concentration control systems; The organic matter that fuel cell can utilize CO2 to solidify and produce produces electric energy; Engine installation 49 or the power supply of the Lighting System in the manned spacecraft for electrolytic cell 43, gas flow system 48 have reduced the demand of system to external electric energy.
Embodiment five
Referring to Fig. 5, Fig. 5 is the structural representation of the embodiment of the invention five disclosed carbon dioxide draw devices.
This control system comprises: carbon dioxide draw device 51, CO2 transmission path 52, electrolytic cell 53, electric supply installation 54, fuel cell 55, the 3rd transmitting device 56, the 4th transmission path 57, organic matter memory storage 58 and the 5th transmitting device 59.
The difference of embodiment five disclosed carbon dioxide concentration control systems and embodiment four disclosed carbon dioxide concentration control systems is, further is provided with: organic matter memory storage 58 and the 5th transmission path 59.And the function of carbon dioxide draw device 51, CO2 transmission path 52, electrolytic cell 53, electric supply installation 54, fuel cell 55, the 3rd transmission path 56 and the 4th transmission path 57 is consistent with the function of each device in the embodiment four disclosed carbon dioxide concentration control systems, repeats no more at this.
When fuel cell 55 can't all utilize when producing large amount of organic in the electrolytic cell 53; Will in electrolytic cell 53, produce remaining organic matter; Can transfer to organic matter memory storage 56 with remaining organic matter this moment through the 5th transmitting device 59, stored by organic matter memory storage 56.
In the disclosed carbon dioxide concentration control system of various embodiments of the present invention; Electric supply installation can be made up of photoemissive element and energy-storage battery; Photoemissive element can directly convert luminous energy into engine installation or the power supply of the Lighting System in the manned spacecraft that electric energy is electrolytic cell, gas flow system; When producing dump energy, can it be stored in the energy-storage battery, energy-storage battery can be lead-acid battery, nickel-cadmium cell or lithium ion battery.Wherein photoemissive element is positioned at the outside of manned spacecraft, be convenient to receive luminous energy, and energy-storage battery can be positioned over the outside of manned spacecraft, also can be positioned over the inside of manned spacecraft.
In force, the negative electrode of electrolytic cell can adopt in nickel, gold, titanium, zirconium, copper, tin and the chromium one or more to process, and anode can adopt nickel to process, and battery acid is selected sodium sulphaste or natrium carbonate for use.From the metallo-cost consideration, the manufacturing materials of cathode of electrolytic tank is preferably one or more in copper, tin and the chromium among the present invention.
Each embodiment adopts the mode of going forward one by one to describe in this specification sheets, and what each embodiment stressed all is and the difference of other embodiment that identical similar part is mutually referring to getting final product between each embodiment.For the disclosed device of embodiment, because it is corresponding with the embodiment disclosed method, so description is fairly simple, relevant part is partly explained referring to method and is got final product.
Claims (8)
1. a manned spacecraft closed in space carbon dioxide concentration control system is characterized in that, comprising:
Be arranged at the interior carbon dioxide draw device of gas flow system of said closed in space;
One end and said carbon dioxide draw device bonded assembly CO2 transmission path;
Be connected with the other end of said CO2 transmission path, curable carbon-dioxide electrolytic cell;
Can be said electrolytic cell provides the electric supply installation of electric energy.
2. manned spacecraft according to claim 1 closed in space carbon dioxide concentration control system is characterized in that the cathode material of said electrolytic cell is one or more in copper, tin and the chromium, and anode material is a nickel, and battery acid is a sodium sulphaste.
3. manned spacecraft according to claim 2 closed in space carbon dioxide concentration control system is characterized in that said carbon dioxide draw device is:
Admission port is positioned at said closed in space gas flow system, air extractor duct and said CO2 transmission path bonded assembly cylindrical shell, between said admission port and said air extractor duct, is provided with and only holds polypropylene screen or the polyethylene film that CO2 passes through.
4. manned spacecraft according to claim 2 closed in space carbon dioxide concentration control system is characterized in that said carbon dioxide draw device comprises:
The carbon dioxide collecting device of built-in carbon dioxide absorber or absorbent;
Can discharge carbon-dioxide device for releasing carbon dioxide in said adsorbent or the absorbent;
Can the adsorbent in the said carbon dioxide collecting device or absorbent be transferred to first transmitting device of said device for releasing carbon dioxide;
Can the adsorbent in the said device for releasing carbon dioxide or absorbent be transferred to second transmitting device of said carbon dioxide collecting device.
5. manned spacecraft according to claim 1 closed in space carbon dioxide concentration control system is characterized in that, also comprises: fuel cell, and the 3rd transmitting device that can the organic matter in the said electrolytic cell be transferred to said fuel cell.
6. manned spacecraft according to claim 5 closed in space carbon dioxide concentration control system is characterized in that, also comprises: the four-way that connects said electrolytic cell and said fuel cell.
7. manned spacecraft according to claim 6 closed in space carbon dioxide concentration control system; It is characterized in that; Also comprise: organic matter memory storage, and the 5th transmitting device that can the organic matter in the said electrolytic cell be transferred to said organic matter memory storage.
8. manned spacecraft according to claim 1 closed in space carbon dioxide concentration control system is characterized in that said electric supply installation comprises photoemissive element and energy-storage battery.
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201010285343.9A CN102398684B (en) | 2010-09-15 | 2010-09-15 | Carbon dioxide concentration control system for closed capsule of manned spacecraft |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201010285343.9A CN102398684B (en) | 2010-09-15 | 2010-09-15 | Carbon dioxide concentration control system for closed capsule of manned spacecraft |
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| CN102398684A true CN102398684A (en) | 2012-04-04 |
| CN102398684B CN102398684B (en) | 2014-04-30 |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112357126A (en) * | 2021-01-11 | 2021-02-12 | 中国人民解放军国防科技大学 | Harmful gas removing unit storage device |
Citations (6)
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|---|---|---|---|---|
| US3471384A (en) * | 1965-08-11 | 1969-10-07 | Borg Warner | Electrolytic method of oxygen generation |
| DE3838508A1 (en) * | 1988-11-12 | 1990-05-17 | Erno Raumfahrttechnik Gmbh | Controlling the carbon dioxide concentration of space stations |
| DE4333504A1 (en) * | 1993-10-01 | 1995-04-06 | Dornier Gmbh | Process for O2 recovery from life support systems |
| JPH08133200A (en) * | 1994-11-08 | 1996-05-28 | Mitsubishi Heavy Ind Ltd | Continuous carbon removing system |
| JP2004261757A (en) * | 2003-03-04 | 2004-09-24 | Suga Test Instr Co Ltd | Environmental purification and circulation type water electrolysis apparatus |
| CN201961538U (en) * | 2010-09-15 | 2011-09-07 | 苏州大学 | Airtight cabin carbon dioxide concentration control system of manned spacecraft |
-
2010
- 2010-09-15 CN CN201010285343.9A patent/CN102398684B/en not_active Expired - Fee Related
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3471384A (en) * | 1965-08-11 | 1969-10-07 | Borg Warner | Electrolytic method of oxygen generation |
| DE3838508A1 (en) * | 1988-11-12 | 1990-05-17 | Erno Raumfahrttechnik Gmbh | Controlling the carbon dioxide concentration of space stations |
| DE4333504A1 (en) * | 1993-10-01 | 1995-04-06 | Dornier Gmbh | Process for O2 recovery from life support systems |
| JPH08133200A (en) * | 1994-11-08 | 1996-05-28 | Mitsubishi Heavy Ind Ltd | Continuous carbon removing system |
| JP2004261757A (en) * | 2003-03-04 | 2004-09-24 | Suga Test Instr Co Ltd | Environmental purification and circulation type water electrolysis apparatus |
| CN201961538U (en) * | 2010-09-15 | 2011-09-07 | 苏州大学 | Airtight cabin carbon dioxide concentration control system of manned spacecraft |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112357126A (en) * | 2021-01-11 | 2021-02-12 | 中国人民解放军国防科技大学 | Harmful gas removing unit storage device |
| CN112357126B (en) * | 2021-01-11 | 2021-03-30 | 中国人民解放军国防科技大学 | Harmful gas removing unit storage device |
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| Publication number | Publication date |
|---|---|
| CN102398684B (en) | 2014-04-30 |
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