CN105438501A - Space station aqueous-based propulsion system based on hydrogen arc thruster and hydrogen oxygen engine - Google Patents
Space station aqueous-based propulsion system based on hydrogen arc thruster and hydrogen oxygen engine Download PDFInfo
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- CN105438501A CN105438501A CN201510860374.5A CN201510860374A CN105438501A CN 105438501 A CN105438501 A CN 105438501A CN 201510860374 A CN201510860374 A CN 201510860374A CN 105438501 A CN105438501 A CN 105438501A
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- 239000001301 oxygen Substances 0.000 title claims abstract description 245
- 229910052760 oxygen Inorganic materials 0.000 title claims abstract description 245
- UFHFLCQGNIYNRP-UHFFFAOYSA-N Hydrogen Chemical compound [H][H] UFHFLCQGNIYNRP-UHFFFAOYSA-N 0.000 title claims abstract description 225
- 239000001257 hydrogen Substances 0.000 title claims abstract description 217
- 229910052739 hydrogen Inorganic materials 0.000 title claims abstract description 217
- QVGXLLKOCUKJST-UHFFFAOYSA-N atomic oxygen Chemical compound [O] QVGXLLKOCUKJST-UHFFFAOYSA-N 0.000 title claims abstract description 131
- 150000002431 hydrogen Chemical class 0.000 title claims abstract description 17
- 239000007789 gas Substances 0.000 claims abstract description 47
- 239000002351 wastewater Substances 0.000 claims abstract description 25
- 238000004065 wastewater treatment Methods 0.000 claims description 18
- 239000003638 chemical reducing agent Substances 0.000 claims description 17
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 claims description 17
- 238000005868 electrolysis reaction Methods 0.000 claims description 12
- 238000001914 filtration Methods 0.000 claims description 5
- JEGUKCSWCFPDGT-UHFFFAOYSA-N h2o hydrate Chemical compound O.O JEGUKCSWCFPDGT-UHFFFAOYSA-N 0.000 claims description 5
- 239000003380 propellant Substances 0.000 abstract description 10
- 230000007547 defect Effects 0.000 abstract description 4
- 229910001882 dioxygen Inorganic materials 0.000 description 11
- 239000002912 waste gas Substances 0.000 description 11
- MYMOFIZGZYHOMD-UHFFFAOYSA-N Dioxygen Chemical compound O=O MYMOFIZGZYHOMD-UHFFFAOYSA-N 0.000 description 10
- 238000011282 treatment Methods 0.000 description 4
- 238000000034 method Methods 0.000 description 3
- WFPZPJSADLPSON-UHFFFAOYSA-N dinitrogen tetraoxide Chemical compound [O-][N+](=O)[N+]([O-])=O WFPZPJSADLPSON-UHFFFAOYSA-N 0.000 description 2
- 239000000203 mixture Substances 0.000 description 2
- 238000011144 upstream manufacturing Methods 0.000 description 2
- 239000012267 brine Substances 0.000 description 1
- 230000006837 decompression Effects 0.000 description 1
- 230000007812 deficiency Effects 0.000 description 1
- 239000000446 fuel Substances 0.000 description 1
- 230000007774 longterm Effects 0.000 description 1
- 238000012423 maintenance Methods 0.000 description 1
- HDZGCSFEDULWCS-UHFFFAOYSA-N monomethylhydrazine Chemical compound CNN HDZGCSFEDULWCS-UHFFFAOYSA-N 0.000 description 1
- -1 polyoxy Polymers 0.000 description 1
- 230000001105 regulatory effect Effects 0.000 description 1
- HPALAKNZSZLMCH-UHFFFAOYSA-M sodium;chloride;hydrate Chemical compound O.[Na+].[Cl-] HPALAKNZSZLMCH-UHFFFAOYSA-M 0.000 description 1
- 239000000243 solution Substances 0.000 description 1
Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G1/00—Cosmonautic vehicles
- B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
- B64G1/40—Arrangements or adaptations of propulsion systems
- B64G1/402—Propellant tanks; Feeding propellants
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- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Remote Sensing (AREA)
- Aviation & Aerospace Engineering (AREA)
- Electrolytic Production Of Non-Metals, Compounds, Apparatuses Therefor (AREA)
Abstract
The invention relates to a space station aqueous-based propulsion system based on a hydrogen arc thruster and a hydrogen oxygen engine. The space station aqueous-based propulsion system comprises a waste water processing and electrolyzing module (1), a hydrogen-oxygen storage module (2), a hydrogen-oxygen supplying module (3), a hydrogen arc thrustor module (4) and a hydrogen-oxygen engine module (5). The space station aqueous-based propulsion system disclosed by the invention meets two requirements that exhaust gas and waste water are effectively processed in a manned space station and propellants are saved, and besides, the hudrogen arc thrustor module (4) is led for adjusting the proportion of oxygen to hydrogen, which are consumed by the whole system, so that the defect that a conventional aqueous-based propulsion system is difficult to completely and effectively utilize the oxygen and the hydrogen of which the mixing ratio of the oxygen to the hydrogen being 4 or less, which are generated by exhaust gas and waste water in the conventional space station, is overcome, the effective utilization of the exhaust gas and the waste water of the space station is realized, and 25% or more of the propellants can be saved for the space station each year.
Description
Technical field
The present invention relates to space station propulsion system, particularly a kind of water base propulsion system in space station based on hydrogen Arcjet and oxyhydrogen engine.
Background technology
Space station is the spacecraft of China at the maximum-norm ground, and wind area is comparatively large, and runs on low orbit, and in order to overcome outer space atmospherical drag, orbit keeping height, needs to consume a large amount of propellants.The satellite propulsion system of existing space station continues to use traditional bipropellant propulsion system based on methyl hydrazine/dinitrogen tetroxide, needs every year more than the normal operation of 3000kg propellant for space station.
Simultaneously, manned space station provides the necessary water of existence and oxygen to give long-term operation on orbit cosmonaut, space station produces the hydrogen or oxygen gas of certain pressure by water electrolysis system brine electrolysis, wherein, oxygen is mainly used in the oxygen atmosphere maintaining space station, ensure that astronaut breathes, hydrogen is discharged after treatment as waste gas.At present, can produce a large amount of astronaut's sanitary wastewater and electrolytic waste gas (hydrogen) in the operational process of space station, these waste water and waste gas are not only difficult to be utilized, but also need to expend extra resource and carry out treatment and discharge to it.
In order to solve the problem that propellant expenditure in orbit huge and space station waste gas waste water in space station is difficult to effectively utilize, need to propose a kind ofly to produce the propulsion system of thrust by efficiency utilization hydrogen or oxygen gas.The hydrogen or oxygen gas ratio produced due to space station waste gas waste water is in addition lower than hydrogen-oxygen equivalence ratio 1:8, and namely few and the two ratio of hydrogen polyoxy gas is not fixed.Therefore need propulsion system can have multiple type of service to hydrogen or oxygen gas, this consumption ratio of hydrogen or oxygen gas can be adjusted to a certain extent.
Summary of the invention
The technical matters that the present invention solves is: overcome the deficiencies in the prior art, provide a kind of water base propulsion system in space station based on hydrogen Arcjet and oxyhydrogen engine, can space efficient station waste gas and waste water, and provide in orbit required thrust for space station, can be space station and save propellant more than 25% every year.
Technical solution of the present invention is: based on the water base propulsion system in space station of hydrogen Arcjet and oxyhydrogen engine, comprise wastewater treatment and electrolytic module, hydrogen-oxygen memory module, hydrogen-oxygen supplying module, hydrogen Arcjet module, gas hydrogen-oxygen engine block, wherein
Wastewater treatment and electrolytic module, comprise waterwater entrance, the first oxygen outlet, the first hydrogen outlet, filter element, electrolysis cells; Waterwater entrance receives space station waste water and delivers to filter element, filter element delivers to electrolysis cells after filtering waste water, electrolysis cells carries out electrolysis to the waste water after filtration and obtains oxygen, hydrogen, oxygen is delivered to hydrogen-oxygen memory module through the first oxygen outlet, hydrogen is delivered to hydrogen-oxygen memory module through the first hydrogen outlet;
Hydrogen-oxygen memory module, comprises the first oxygen intake, the second oxygen outlet, the first hydrogen inlet, the second hydrogen outlet, oxygen device for filling, high-pressure oxygen cylinder, hydrogen device for filling, High Pressure Hydrogen gas cylinder, first oxygen intake receives oxygen, and oxygen is delivered to High Pressure Hydrogen gas cylinder through oxygen device for filling, first hydrogen inlet receives hydrogen, and hydrogen is delivered to High Pressure Hydrogen gas cylinder through hydrogen device for filling, oxygen device for filling regulates the first oxygen intake or high-pressure oxygen cylinder air pressure, the first oxygen intake place oxygen pneumatic is made to be greater than oxygen pneumatic in high-pressure oxygen cylinder and lower than the specified storage air pressure of high-pressure oxygen cylinder, hydrogen device for filling regulates the first hydrogen inlet or High Pressure Hydrogen gas cylinder air pressure, the first hydrogen inlet place hydrogen gas pressure is made to be greater than oxygen pneumatic in High Pressure Hydrogen gas cylinder and lower than the specified storage air pressure of High Pressure Hydrogen gas cylinder, high-pressure oxygen cylinder stores oxygen, and oxygen is delivered to hydrogen-oxygen supplying module through the second oxygen outlet, High Pressure Hydrogen gas cylinder hydrogen gas storage, and hydrogen is delivered to hydrogen-oxygen supplying module through the second hydrogen outlet,
Hydrogen-oxygen supplying module, comprises the second oxygen intake, oxygen pressure reducer, trioxid outlet, the second hydrogen inlet, hydrogen pressure reducer, the 3rd hydrogen outlet, the 4th hydrogen outlet;
Second oxygen intake delivers to oxygen pressure reducer after receiving oxygen, oxygen is carried out step-down by oxygen pressure reducer, obtain the oxygen after step-down and deliver to trioxid outlet, oxygen is delivered to gas hydrogen-oxygen engine block by trioxid outlet, second hydrogen inlet delivers to hydrogen pressure reducer after receiving hydrogen, hydrogen is carried out step-down by hydrogen pressure reducer, obtain the hydrogen after step-down and deliver to the 3rd hydrogen outlet, the 4th hydrogen outlet respectively, hydrogen is delivered to gas hydrogen-oxygen engine block by the 3rd hydrogen outlet, and hydrogen is delivered to hydrogen Arcjet module by the 4th hydrogen outlet;
Hydrogen Arcjet module, comprises the 3rd hydrogen inlet, hydrogen Arcjet branch road; 3rd hydrogen inlet delivers to hydrogen Arcjet branch road after receiving hydrogen, hydrogen Arcjet branch road comprises flow controller, hydrogen Arcjet, flow controller receives external flow instruction, the hydrogen flowing quantity delivering to hydrogen Arcjet is controlled according to flow instruction, hydrogen Arcjet produces the thrust of momentum wheel unloading and the posture position control being used for space station, wherein, hydrogen Arcjet branch road is at least 2; Described flow instruction comprises the hydrogen flowing quantity being delivered to hydrogen Arcjet;
Gas hydrogen-oxygen engine block, comprises trioxid entrance, the 4th hydrogen inlet, oxyhydrogen engine branch road; Trioxid entrance delivers to oxyhydrogen engine branch road after receiving oxygen, 4th hydrogen inlet delivers to oxyhydrogen engine branch road after receiving hydrogen, oxyhydrogen engine in oxyhydrogen engine branch road produces the high hold thrust being used for space station, and wherein, oxyhydrogen engine branch road is at least 2.
The oxygen that in described gas hydrogen-oxygen engine block, oxyhydrogen engine needs and hydrogen weight ratio are 4-8.
The specified storage air pressure of described high-pressure oxygen cylinder or High Pressure Hydrogen gas cylinder is 2-15MPa.
The air pressure of the oxygen after described step-down or the hydrogen after step-down is 1.4MPa-1.6MPa.
The present invention's advantage is compared with prior art:
(1) the present invention is by reasonable disposition wastewater treatment and electrolytic module, hydrogen-oxygen memory module, hydrogen-oxygen supplying module, hydrogen Arcjet module, gas hydrogen-oxygen engine block, form the water base propulsion system in space station based on hydrogen Arcjet and oxyhydrogen engine, meet space station and effectively process waste gas and waste water, save propellant these two demands, solve the space station fuel make up cycle of design at present partially short problem;
(2) the present invention introduces hydrogen Arcjet module, the oxygen regulating whole system to consume by the power of hydrogen Arcjet in configuration hydrogen Arcjet module, quantity and work capacity and hydrogen ratio, overcoming existing water base propulsion system uses merely the gas hydrogen-oxygen thruster of mixture ratio 4-8 to be difficult to the mixture ratio of current space station waste gas waste water generation to be less than the oxygen of 4 and the defect of the fully effective utilization of hydrogen, has the oxygen of energy efficiency utilization different proportion and the advantage of hydrogen;
(3) in the present invention, hydrogen Arcjet module unloads for the momentum wheel of space station, the high precision of posture position controls, gas hydrogen-oxygen engine block keeps for the height of space station, overcoming existing water base propulsion system needs the gas hydrogen-oxygen driving engine adopting different thrust magnitude to complete all tasks, the defect that the specific impulse caused is on the low side, thruster design difficulty is large, solves the design challenges of the space gas hydrogen-oxygen driving engine that accurate low thrust works long hours;
(4) present invention achieves the effective utilization to space station waste gas and waste water, produce the maintenance thrust in-orbit needed for space station, can be space station every year and save propellant more than 25% propellant.
Accompanying drawing explanation
Fig. 1 is the water base propulsion system structure figure in space station that the present invention is based on hydrogen Arcjet and oxyhydrogen engine;
Fig. 2 is wastewater treatment of the present invention and electrolytic module constructional drawing;
Fig. 3 is hydrogen-oxygen memory module configuration figure of the present invention;
Fig. 4 is hydrogen-oxygen supplying module constructional drawing of the present invention;
Fig. 5 is gas hydrogen-oxygen engine block of the present invention;
Fig. 6 is hydrogen Arcjet module of the present invention.
Detailed description of the invention
Be difficult to be utilized for a large amount of sanitary wastewater produced in the operational process of space station and electrolytic waste gas (hydrogen) and need to expend extra resource carries out treatment and discharge defect to it, the present invention proposes a kind of water base propulsion system in space station based on hydrogen Arcjet and oxyhydrogen engine, this system produces hydrogen and oxygen by electrolytic treatments waste water, the discarded Hydrogen collection of the hydrogen or oxygen gas produce electrolysis wastewater and the discharge of space station life support system gets up to be supplied to the gentle hydrogen-oxygen driving engine of hydrogen Arcjet, wherein, hydrogen Arcjet utilizes hydrogen to produce thrust, gas hydrogen-oxygen driving engine utilizes hydrogen or oxygen gas to produce thrust.Present system is combinationally used by the gentle hydrogen-oxygen driving engine of hydrogen Arcjet, the waste gas of manned space station and waste water is made to obtain efficiency utilization, for space station provides considerable power in orbit, according to estimation, this system can be space station every year and saves propellant more than 25%, greatly reduces the independent operating cost of manned space station.
The water base propulsion system in space station based on hydrogen Arcjet and oxyhydrogen engine comprises wastewater treatment and electrolytic module, hydrogen-oxygen memory module, hydrogen-oxygen supplying module, hydrogen Arcjet module, gas hydrogen-oxygen engine block.Wastewater treatment and electrolytic module utilize space station wastewater electrolytic to produce hydrogen or oxygen gas.The hydrogen that space station is discarded by hydrogen-oxygen memory module and the hydrogen or oxygen gas produced by waste water and electrolytic module are collected, and store with certain pressure.The high voltage hydrogen-oxygen gas that hydrogen-oxygen memory module stores by hydrogen-oxygen supplying module, by decompression and flow control, is supplied to the gentle hydrogen-oxygen engine block of hydrogen Arcjet module according to certain pressure and flow.Hydrogen Arcjet module utilizes hydrogen to produce thrust.Gas hydrogen-oxygen engine block utilizes hydrogen and oxygen to produce thrust.
With reference to the accompanying drawings present system is described in detail below.
The water base propulsion system in space station based on hydrogen Arcjet and oxyhydrogen engine comprises as shown in Figure 1: wastewater treatment and electrolytic module 1, hydrogen-oxygen memory module 2, hydrogen-oxygen supplying module 3, hydrogen Arcjet module 4, gas hydrogen-oxygen engine block 5, wherein, the wastewater treatment of wastewater treatment and electrolytic module 1 and electrolytic module oxygen outlet 8 are connected with the hydrogen-oxygen memory module oxygen intake 9 of hydrogen-oxygen memory module 2.The wastewater treatment of wastewater treatment and electrolytic module 1 and electrolytic module hydrogen outlet 7 are connected with the hydrogen-oxygen memory module hydrogen inlet 16 of hydrogen-oxygen memory module 2.The hydrogen-oxygen memory module oxygen outlet 12 of hydrogen-oxygen memory module 2 is connected with the hydrogen-oxygen supplying module oxygen intake 17 of hydrogen-oxygen supplying module 3.The hydrogen-oxygen memory module hydrogen outlet 13 of hydrogen-oxygen memory module 2 is connected with the hydrogen-oxygen supplying module hydrogen inlet 23 of hydrogen-oxygen supplying module 3.The hydrogen-oxygen supplying module oxygen outlet 19 of hydrogen-oxygen supplying module 3 is connected with the gas hydrogen-oxygen engine block oxygen intake 24 of gas hydrogen-oxygen engine block 5.First hydrogen-oxygen supplying module hydrogen outlet 20 of hydrogen-oxygen supplying module 3 is connected with the gas hydrogen-oxygen engine block hydrogen inlet 26 of gas hydrogen-oxygen engine block 5.Second hydrogen-oxygen supplying module hydrogen outlet 21 of hydrogen-oxygen supplying module 3 is connected with the hydrogen Arcjet module hydrogen inlet 27 of hydrogen Arcjet module 4.
(1) wastewater treatment and electrolytic module.
Wastewater treatment and electrolytic module 1 are as shown in Figure 2.Receive waste water by wastewater treatment and electrolytic module waterwater entrance 6, by filtering and electrolysis, produce hydrogen and oxygen, hydrogen is exported by wastewater treatment and electrolytic module hydrogen outlet 7, and oxygen is by exporting by wastewater treatment and electrolytic module oxygen outlet 8.
(2) hydrogen-oxygen memory module
Hydrogen-oxygen memory module 2 as shown in Figure 3,9 is hydrogen-oxygen memory module oxygen intake, 10 is oxygen device for filling, 11 is high-pressure oxygen cylinder, 12 is hydrogen-oxygen memory module oxygen outlet, and 13 is hydrogen-oxygen memory module hydrogen outlet, and 14 is High Pressure Hydrogen gas cylinder, 15 is hydrogen device for filling, and 16 is hydrogen-oxygen memory module hydrogen inlet.Oxygen is received by hydrogen-oxygen memory module oxygen intake 9, by oxygen device for filling 10, oxygen filling is entered high-pressure oxygen cylinder 11, high-pressure oxygen cylinder 11 stores high pressure oxygen, stores pressure 2-15MPa, and high pressure oxygen is exported by hydrogen-oxygen memory module oxygen outlet 12 by high-pressure oxygen cylinder 11.Hydrogen is received by hydrogen-oxygen memory module hydrogen inlet 16, by hydrogen device for filling 15, hydrogen is filled into High Pressure Hydrogen gas cylinder 14, High Pressure Hydrogen gas cylinder 14 stores high pressure oxygen, stores pressure 2-15MPa, and high pressure hydrogen is exported by hydrogen-oxygen memory module hydrogen outlet 13 by High Pressure Hydrogen gas cylinder 14.
Device for filling is used for upstream hydrogen or carrier of oxygen to be filled to high-pressure gas bottle, this device is nursed one's health by pressure on the one hand, ensure that hydrogen or carrier of oxygen pressure are higher than gaseous tension in gas cylinder, simultaneously lower than the specified storage pressure of gas cylinder, enable hydrogen or oxygen gas filling air inlet bottle, control on the other hand oppositely to reveal, ensure that gas cylinder internal memory storing gas oppositely can not be leaked to upstream components.
(3) hydrogen-oxygen supplying module
Hydrogen-oxygen supplying module 3 as shown in Figure 4,17 is hydrogen-oxygen supplying module oxygen intake, 18 is oxygen pressure reducer, 19 is hydrogen-oxygen supplying module oxygen outlet, 20 is the first hydrogen-oxygen supplying module hydrogen outlet, 21 is the second hydrogen-oxygen supplying module hydrogen outlet, and 22 is hydrogen regulator, and 23 is hydrogen-oxygen supplying module hydrogen inlet.Receive high pressure oxygen by hydrogen-oxygen supplying module oxygen intake 17, high pressure oxygen to be reduced pressure to 1.4MPa-1.6MPa by oxygen pressure reducer 18, by hydrogen-oxygen supplying module oxygen outlet 19, low oxygen is exported.
Hydrogen-oxygen supplying module 3 receives high pressure hydrogen by hydrogen-oxygen supplying module hydrogen inlet 23, high pressure hydrogen to be reduced pressure to 1.4MPa-1.6MPa by hydrogen pressure reducer 22, by the first hydrogen-oxygen supplying module hydrogen outlet 20 and the second hydrogen-oxygen supplying module hydrogen outlet 21, low pressure hydrogen is exported.
Hydrogen-oxygen supplying module comprises an oxygen branch and Liang Ge hydrogen branch, oxygen to be reduced pressure to after pressure needed for gas hydrogen-oxygen engine operation by pressure reducer and is supplied to gas hydrogen-oxygen engine block by oxygen branch, hydrogen branch is supplied to gas hydrogen-oxygen engine block by a pressure reducer road after pressure needed for gas hydrogen-oxygen engine operation of being reduced pressure to by hydrogen, and another road is supplied to hydrogen Arcjet module.
(4) hydrogen Arcjet module
As shown in Figure 5,24 is gas hydrogen-oxygen engine block oxygen intake to hydrogen Arcjet module 4, and 25 is gas hydrogen-oxygen driving engine, and 26 is gas hydrogen-oxygen engine block hydrogen inlet.By hydrogen Arcjet module hydrogen inlet 27 inputting hydrogen, and be divided into multiple branch road and supply to downstream.A branch road comprises a tiny flow quantity controller 28 and a hydrogen Arcjet 29, and numbers of branches is determined according to the actual propelling demand in space station.The tiny flow quantity controller 28 of each branch road accurately controls hydrogen flowing quantity, feeds hydrogen gas to hydrogen Arcjet 29 according to demand.
(5) gas hydrogen-oxygen engine block
As shown in Figure 6,27 is hydrogen Arcjet module hydrogen inlet to gas hydrogen-oxygen engine block 5, and 28 is tiny flow quantity controller, and 29 is hydrogen Arcjet.Input oxygen by gas hydrogen-oxygen engine block oxygen intake 24, by gas hydrogen-oxygen engine block hydrogen inlet 26 inputting hydrogen, and form multiple branch road respectively and be supplied to gas hydrogen-oxygen driving engine 25.Each oxygen branch road and the corresponding gas hydrogen-oxygen driving engine 25 of hydrogen branch road, gas hydrogen-oxygen driving engine 25 uses as precise tracking, and thrust and quantity advance demand to determine by space station.
The content be not described in detail in specification sheets of the present invention belongs to the known technology of those skilled in the art.
Claims (4)
1. based on the water base propulsion system in space station of hydrogen Arcjet and oxyhydrogen engine, it is characterized in that comprising wastewater treatment and electrolytic module (1), hydrogen-oxygen memory module (2), hydrogen-oxygen supplying module (3), hydrogen Arcjet module (4), gas hydrogen-oxygen engine block (5), wherein
Wastewater treatment and electrolytic module (1), comprise waterwater entrance (6), the first oxygen outlet (8), the first hydrogen outlet (7), filter element, electrolysis cells; Waterwater entrance (6) receives space station waste water and delivers to filter element, filter element delivers to electrolysis cells after filtering waste water, electrolysis cells carries out electrolysis to the waste water after filtration and obtains oxygen, hydrogen, oxygen is delivered to hydrogen-oxygen memory module (2) through the first oxygen outlet (8), hydrogen is delivered to hydrogen-oxygen memory module (2) through the first hydrogen outlet (7);
Hydrogen-oxygen memory module (2), comprises the first oxygen intake (9), the second oxygen outlet (12), the first hydrogen inlet (16), the second hydrogen outlet (13), oxygen device for filling (10), high-pressure oxygen cylinder (11), hydrogen device for filling (15), High Pressure Hydrogen gas cylinder (14), first oxygen intake (9) receives oxygen, and oxygen is delivered to High Pressure Hydrogen gas cylinder (14) through oxygen device for filling (10), first hydrogen inlet (16) receives hydrogen, and hydrogen is delivered to High Pressure Hydrogen gas cylinder (14) through hydrogen device for filling (15), oxygen device for filling (10) regulates the first oxygen intake (9) or high-pressure oxygen cylinder (11) air pressure, the first oxygen intake (9) place oxygen pneumatic is made to be greater than high-pressure oxygen cylinder (11) interior oxygen pneumatic and lower than the specified storage air pressure of high-pressure oxygen cylinder (11), hydrogen device for filling (15) regulates the first hydrogen inlet (16) or High Pressure Hydrogen gas cylinder (14) air pressure, the first hydrogen inlet (16) place hydrogen gas pressure is made to be greater than High Pressure Hydrogen gas cylinder (14) interior oxygen pneumatic and lower than the specified storage air pressure of High Pressure Hydrogen gas cylinder (14), high-pressure oxygen cylinder (11) stores oxygen, and oxygen is delivered to hydrogen-oxygen supplying module (3) through the second oxygen outlet (12), High Pressure Hydrogen gas cylinder (14) hydrogen gas storage, and hydrogen is delivered to hydrogen-oxygen supplying module (3) through the second hydrogen outlet (13),
Hydrogen-oxygen supplying module (3) comprises the second oxygen intake (17), oxygen pressure reducer (18), trioxid outlet (19), the second hydrogen inlet (23), hydrogen pressure reducer (22), the 3rd hydrogen outlet (20), the 4th hydrogen outlet (21);
Second oxygen intake (17) delivers to oxygen pressure reducer (18) after receiving oxygen, oxygen is carried out step-down by oxygen pressure reducer (18), obtain the oxygen after step-down and deliver to trioxid outlet (19), oxygen is delivered to gas hydrogen-oxygen engine block (5) by trioxid outlet (19), second hydrogen inlet (23) delivers to hydrogen pressure reducer (22) after receiving hydrogen, hydrogen is carried out step-down by hydrogen pressure reducer (22), obtain the hydrogen after step-down and deliver to the 3rd hydrogen outlet (20) respectively, 4th hydrogen outlet (21), hydrogen is delivered to gas hydrogen-oxygen engine block (5) by the 3rd hydrogen outlet (20), hydrogen is delivered to hydrogen Arcjet module by the 4th hydrogen outlet (21),
Hydrogen Arcjet module (4), comprises the 3rd hydrogen inlet (27), hydrogen Arcjet branch road; 3rd hydrogen inlet (27) delivers to hydrogen Arcjet branch road after receiving hydrogen, hydrogen Arcjet branch road comprises flow controller (28), hydrogen Arcjet (29), flow controller (28) receives external flow instruction, the hydrogen flowing quantity delivering to hydrogen Arcjet (29) is controlled according to flow instruction, hydrogen Arcjet (29) produces the thrust of momentum wheel unloading and the posture position control being used for space station, wherein, hydrogen Arcjet branch road is at least 2; Described flow instruction comprises the hydrogen flowing quantity being delivered to hydrogen Arcjet (29);
Gas hydrogen-oxygen engine block (5), comprises trioxid entrance (24), the 4th hydrogen inlet (26), oxyhydrogen engine branch road; Trioxid entrance (24) delivers to oxyhydrogen engine branch road after receiving oxygen, 4th hydrogen inlet (26) delivers to oxyhydrogen engine branch road after receiving hydrogen, oxyhydrogen engine (25) in oxyhydrogen engine branch road produces the high hold thrust being used for space station, wherein, oxyhydrogen engine branch road is at least 2.
2. the water base propulsion system in space station based on hydrogen Arcjet and oxyhydrogen engine according to claim 1, is characterized in that: the oxygen that in described gas hydrogen-oxygen engine block (5), oxyhydrogen engine (25) needs and hydrogen weight ratio are 4-8.
3. the water base propulsion system in space station based on hydrogen Arcjet and oxyhydrogen engine according to claim 1 and 2, is characterized in that: described high-pressure oxygen cylinder (11) or the specified storage air pressure of High Pressure Hydrogen gas cylinder (14) are 2-15MPa.
4. the water base propulsion system in space station based on hydrogen Arcjet and oxyhydrogen engine according to claim 1 and 2, is characterized in that: the air pressure of the oxygen after described step-down or the hydrogen after step-down is 1.4MPa-1.6MPa.
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Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110127089A (en) * | 2019-05-10 | 2019-08-16 | 北京控制工程研究所 | A kind of water base propulsion system and method applied to high rail satellite |
| CN111005848A (en) * | 2019-10-31 | 2020-04-14 | 西安空间无线电技术研究所 | Working medium supply system and method for space electrochemical composite thruster |
| CN111452998A (en) * | 2020-04-16 | 2020-07-28 | 北京控制工程研究所 | Water-based propulsion system optimal efficiency determination method based on multi-target optimization |
| CN113174606A (en) * | 2021-04-14 | 2021-07-27 | 西安航天动力研究所 | Moon base energy supply and application system based on photolysis water hydrogen production technology |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPH03224897A (en) * | 1990-01-26 | 1991-10-03 | Ishikawajima Harima Heavy Ind Co Ltd | Energy supply system for spacecraft |
| US5116000A (en) * | 1989-12-18 | 1992-05-26 | Aerospatiale Societe Nationale Industrielle | Adaptable system for storing liquid under pressure and spacecraft propellant storage applications thereof |
| RU2310768C2 (en) * | 2005-10-07 | 2007-11-20 | Открытое акционерное общество "Ракетно-космическая корпорация "Энергия" им. С.П. Королева" | Impulse-action rocket solar oxygen-hydrogen propulsion plant |
| CN101220481A (en) * | 2007-09-26 | 2008-07-16 | 哈尔滨工业大学 | Method for producing solar water-based high pressure high purity oxyhydrogen fuel for space vehicle |
| CN102935899A (en) * | 2012-09-11 | 2013-02-20 | 中国航天员科研训练中心 | Cooling, heating and power integrated system based on fuel cell and hydrogen storage device of fuel cell for extravehicular spacesuit |
| CN104828262A (en) * | 2015-04-30 | 2015-08-12 | 北京控制工程研究所 | Low-pressure liquefied gas thrust generating method for spacecraft |
-
2015
- 2015-11-30 CN CN201510860374.5A patent/CN105438501B/en active Active
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5116000A (en) * | 1989-12-18 | 1992-05-26 | Aerospatiale Societe Nationale Industrielle | Adaptable system for storing liquid under pressure and spacecraft propellant storage applications thereof |
| JPH03224897A (en) * | 1990-01-26 | 1991-10-03 | Ishikawajima Harima Heavy Ind Co Ltd | Energy supply system for spacecraft |
| RU2310768C2 (en) * | 2005-10-07 | 2007-11-20 | Открытое акционерное общество "Ракетно-космическая корпорация "Энергия" им. С.П. Королева" | Impulse-action rocket solar oxygen-hydrogen propulsion plant |
| CN101220481A (en) * | 2007-09-26 | 2008-07-16 | 哈尔滨工业大学 | Method for producing solar water-based high pressure high purity oxyhydrogen fuel for space vehicle |
| CN102935899A (en) * | 2012-09-11 | 2013-02-20 | 中国航天员科研训练中心 | Cooling, heating and power integrated system based on fuel cell and hydrogen storage device of fuel cell for extravehicular spacesuit |
| CN104828262A (en) * | 2015-04-30 | 2015-08-12 | 北京控制工程研究所 | Low-pressure liquefied gas thrust generating method for spacecraft |
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110127089A (en) * | 2019-05-10 | 2019-08-16 | 北京控制工程研究所 | A kind of water base propulsion system and method applied to high rail satellite |
| CN111005848A (en) * | 2019-10-31 | 2020-04-14 | 西安空间无线电技术研究所 | Working medium supply system and method for space electrochemical composite thruster |
| CN111452998A (en) * | 2020-04-16 | 2020-07-28 | 北京控制工程研究所 | Water-based propulsion system optimal efficiency determination method based on multi-target optimization |
| CN111452998B (en) * | 2020-04-16 | 2021-08-10 | 北京控制工程研究所 | Water-based propulsion system optimal efficiency determination method based on multi-target optimization |
| CN113174606A (en) * | 2021-04-14 | 2021-07-27 | 西安航天动力研究所 | Moon base energy supply and application system based on photolysis water hydrogen production technology |
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| CN105438501B (en) | 2017-08-29 |
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