CN105438501B - The water base propulsion system in space station based on hydrogen Arcjet and oxyhydrogen engine - Google Patents
The water base propulsion system in space station based on hydrogen Arcjet and oxyhydrogen engine Download PDFInfo
- Publication number
- CN105438501B CN105438501B CN201510860374.5A CN201510860374A CN105438501B CN 105438501 B CN105438501 B CN 105438501B CN 201510860374 A CN201510860374 A CN 201510860374A CN 105438501 B CN105438501 B CN 105438501B
- Authority
- CN
- China
- Prior art keywords
- hydrogen
- oxygen
- pressure
- module
- inlet
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Active
Links
- 239000001257 hydrogen Substances 0.000 title claims abstract description 278
- 229910052739 hydrogen Inorganic materials 0.000 title claims abstract description 278
- UFHFLCQGNIYNRP-UHFFFAOYSA-N Hydrogen Chemical compound [H][H] UFHFLCQGNIYNRP-UHFFFAOYSA-N 0.000 title claims abstract description 263
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 title claims abstract description 21
- 239000001301 oxygen Substances 0.000 claims abstract description 276
- 229910052760 oxygen Inorganic materials 0.000 claims abstract description 276
- QVGXLLKOCUKJST-UHFFFAOYSA-N atomic oxygen Chemical compound [O] QVGXLLKOCUKJST-UHFFFAOYSA-N 0.000 claims abstract description 195
- 239000002351 wastewater Substances 0.000 claims abstract description 27
- 238000004065 wastewater treatment Methods 0.000 claims abstract description 19
- 239000007789 gas Substances 0.000 claims abstract description 11
- 238000005868 electrolysis reaction Methods 0.000 claims description 29
- 150000002431 hydrogen Chemical class 0.000 claims description 23
- 239000003638 chemical reducing agent Substances 0.000 claims description 7
- 230000006837 decompression Effects 0.000 claims description 3
- 238000012423 maintenance Methods 0.000 claims description 3
- 239000002912 waste gas Substances 0.000 abstract description 11
- 239000003380 propellant Substances 0.000 abstract description 7
- 230000007547 defect Effects 0.000 abstract description 2
- 229910001882 dioxygen Inorganic materials 0.000 description 11
- MYMOFIZGZYHOMD-UHFFFAOYSA-N Dioxygen Chemical compound O=O MYMOFIZGZYHOMD-UHFFFAOYSA-N 0.000 description 8
- 238000010586 diagram Methods 0.000 description 4
- 239000000446 fuel Substances 0.000 description 4
- WFPZPJSADLPSON-UHFFFAOYSA-N dinitrogen tetraoxide Chemical compound [O-][N+](=O)[N+]([O-])=O WFPZPJSADLPSON-UHFFFAOYSA-N 0.000 description 2
- 239000010840 domestic wastewater Substances 0.000 description 2
- 238000000034 method Methods 0.000 description 2
- 238000011144 upstream manufacturing Methods 0.000 description 2
- 239000002699 waste material Substances 0.000 description 2
- 230000007812 deficiency Effects 0.000 description 1
- 238000001914 filtration Methods 0.000 description 1
- 230000007774 longterm Effects 0.000 description 1
- HDZGCSFEDULWCS-UHFFFAOYSA-N monomethylhydrazine Chemical compound CNN HDZGCSFEDULWCS-UHFFFAOYSA-N 0.000 description 1
- 230000004083 survival effect Effects 0.000 description 1
Classifications
-
- 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
Landscapes
- 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
Description
技术领域technical field
本发明涉及空间站推进系统，特别是一种基于氢电弧推力器和氢氧发动机的空间站水基推进系统。The invention relates to a space station propulsion system, in particular to a space station water-based propulsion system based on a hydrogen arc thruster and a hydrogen-oxygen engine.
背景技术Background technique
空间站是中国在研的最大规模的航天器，迎风面积较大，且在低轨道上运行，为了克服外层空间大气阻力，维持轨道高度，需要消耗大量的推进剂。现有的空间站的卫星推进系统沿用传统的基于甲基肼/四氧化二氮的双组元推进系统，每年需要超过3000kg推进剂用于空间站的正常运行。The space station is the largest spacecraft under development in China. It has a large windward area and operates in a low orbit. In order to overcome the atmospheric resistance of outer space and maintain the orbital altitude, it needs to consume a large amount of propellant. The satellite propulsion system of the existing space station follows the traditional dual-component propulsion system based on methylhydrazine/nitrogen tetroxide, which needs more than 3000kg of propellant for the normal operation of the space station every year.
同时，载人空间站为了给长期在轨工作宇航员提供生存必须的水和氧气，空间站通过水电解系统电解水产生一定压力的氢氧气体，其中，氧气主要用于维持空间站的氧气环境，保证航天员呼吸，氢气作为废气经过处理后排出。目前，空间站运行过程中会产生大量航天员生活废水和电解废气(氢气)，这些废水和废气不仅难以得到利用，而且还需要耗费额外的资源对其进行处理和排放。At the same time, in order to provide the long-term on-orbit astronauts with the necessary water and oxygen for survival, the space station electrolyzes water through the water electrolysis system to generate hydrogen and oxygen gas at a certain pressure. Among them, the oxygen is mainly used to maintain the oxygen environment of the space station and ensure the safety of spaceflight. The personnel breathes, and the hydrogen gas is discharged as waste gas after treatment. At present, during the operation of the space station, a large amount of domestic waste water and electrolytic waste gas (hydrogen gas) will be generated. These waste water and waste gas are not only difficult to use, but also need to consume additional resources to treat and discharge them.
为了解决空间站在轨运行推进剂消耗巨大和空间站废气废水难以有效利用的问题，需要提出一种能够高效利用氢氧气体产生推力的推进系统。另外由于空间站废气废水产生的氢氧气体比例低于氢氧当量比1：8，即氢气多氧气少且二者比例并不固定。因此需要推进系统能够对氢氧气体有多种使用形式，可以在一定程度上调整氢氧气体的消耗比例。In order to solve the problems of the huge consumption of propellant in orbital operation of the space station and the difficulty in effectively utilizing waste gas and waste water of the space station, it is necessary to propose a propulsion system that can efficiently use hydrogen and oxygen gas to generate thrust. In addition, because the hydrogen-oxygen gas ratio produced by the space station waste water is lower than the hydrogen-oxygen equivalent ratio of 1:8, that is, there is more hydrogen than oxygen and the ratio of the two is not fixed. Therefore, the propulsion system needs to be able to use hydrogen and oxygen in various forms, and the consumption ratio of hydrogen and oxygen can be adjusted to a certain extent.
发明内容Contents of the invention
本发明解决的技术问题是：克服现有技术的不足，提供了一种基于氢电弧推力器和氢氧发动机的空间站水基推进系统，能够高效利用空间站废气和废水，并为空间站提供在轨运行所需的推力，可为空间站每年节省推进燃料25％以上。The technical problem solved by the present invention is: to overcome the deficiencies of the prior art, to provide a space station water-based propulsion system based on hydrogen arc thrusters and hydrogen-oxygen engines, which can efficiently utilize space station waste gas and waste water, and provide space stations with on-orbit operation The required thrust can save more than 25% of propulsion fuel for the space station every year.
本发明的技术解决方案是：基于氢电弧推力器和氢氧发动机的空间站水基推进系统，包括废水处理及电解模块、氢氧存储模块、氢氧供给模块、氢电弧推力器模块、气氢气氧发动机模块，其中The technical solution of the present invention is: a space station water-based propulsion system based on hydrogen arc thrusters and hydrogen-oxygen engines, including wastewater treatment and electrolysis modules, hydrogen and oxygen storage modules, hydrogen and oxygen supply modules, hydrogen arc thruster modules, gas hydrogen and oxygen engine module, where
废水处理及电解模块，包括废水入口、第一氧气出口、第一氢气出口，过滤单元、电解单元；废水入口接收空间站废水送至过滤单元，过滤单元对废水进行过滤后送至电解单元，电解单元对过滤后的废水进行电解得到氧气、氢气，将氧气经第一氧气出口送至氢氧存储模块，将氢气经第一氢气出口送至氢氧存储模块；Wastewater treatment and electrolysis module, including waste water inlet, first oxygen outlet, first hydrogen outlet, filter unit, and electrolysis unit; the waste water inlet receives space station waste water and sends it to the filter unit, which filters the waste water and sends it to the electrolysis unit, the electrolysis unit Electrolyzing the filtered wastewater to obtain oxygen and hydrogen, sending the oxygen to the hydrogen-oxygen storage module through the first oxygen outlet, and sending the hydrogen to the hydrogen-oxygen storage module through the first hydrogen outlet;
氢氧存储模块，包括第一氧气入口、第二氧气出口、第一氢气入口、第二氢气出口、氧充填装置、高压氧气瓶、氢充填装置、高压氢气瓶；第一氧气入口接收氧气，并将氧气经氧充填装置送至高压氢气瓶，第一氢气入口接收氢气，并将氢气经氢充填装置送至高压氢气瓶，氧充填装置调节第一氧气入口或高压氧气瓶气压，使第一氧气入口处氧气气压大于高压氧气瓶内氧气气压且低于高压氧气瓶额定存储气压，氢充填装置调节第一氢气入口或高压氢气瓶气压，使第一氢气入口处氢气气压大于高压氢气瓶内氧气气压且低于高压氢气瓶额定存储气压，高压氧气瓶存储氧气，并将氧气经第二氧气出口送至氢氧供给模块，高压氢气瓶存储氢气，并将氢气经第二氢气出口送至氢氧供给模块；The oxygen hydrogen storage module includes a first oxygen inlet, a second oxygen outlet, a first hydrogen inlet, a second hydrogen outlet, an oxygen filling device, a high-pressure oxygen cylinder, a hydrogen filling device, and a high-pressure hydrogen cylinder; the first oxygen inlet receives oxygen, and The oxygen is sent to the high-pressure hydrogen cylinder through the oxygen filling device, the first hydrogen inlet receives hydrogen, and the hydrogen is sent to the high-pressure hydrogen cylinder through the hydrogen filling device, and the oxygen filling device adjusts the pressure of the first oxygen inlet or the high-pressure oxygen cylinder to make the first oxygen The oxygen pressure at the inlet is greater than the oxygen pressure in the high-pressure oxygen cylinder and lower than the rated storage pressure of the high-pressure oxygen cylinder. The hydrogen filling device adjusts the first hydrogen inlet or the pressure of the high-pressure hydrogen cylinder so that the hydrogen pressure at the first hydrogen inlet is greater than the oxygen pressure in the high-pressure hydrogen cylinder. And lower than the rated storage pressure of the high-pressure hydrogen cylinder, the high-pressure oxygen cylinder stores oxygen, and sends the oxygen to the hydrogen-oxygen supply module through the second oxygen outlet, and the high-pressure hydrogen cylinder stores hydrogen, and sends the hydrogen to the hydrogen-oxygen supply through the second hydrogen outlet module;
氢氧供给模块，包括第二氧气入口、氧减压器、第三氧气出口、第二氢气入口、氢减压器、第三氢气出口、第四氢气出口；The oxygen hydrogen supply module includes a second oxygen inlet, an oxygen decompressor, a third oxygen outlet, a second hydrogen inlet, a hydrogen decompressor, a third hydrogen outlet, and a fourth hydrogen outlet;
第二氧气入口接收氧气后送至氧减压器，氧减压器将氧气进行降压，得到降压后的氧气并送至第三氧气出口，第三氧气出口将氧气送至气氢气氧发动机模块，第二氢气入口接收氢气后送至氢减压器，氢减压器将氢气进行降压，得到降压后的氢气并分别送至第三氢气出口、第四氢气出口，第三氢气出口将氢气送至气氢气氧发动机模块，第四氢气出口将氢气送至氢电弧推力器模块；The second oxygen inlet receives oxygen and sends it to the oxygen decompressor, and the oxygen decompressor decompresses the oxygen to obtain the depressurized oxygen and sends it to the third oxygen outlet, and the third oxygen outlet sends the oxygen to the hydrogen-oxygen engine Module, the second hydrogen inlet receives hydrogen and sends it to the hydrogen decompressor, and the hydrogen decompressor decompresses the hydrogen to obtain the depressurized hydrogen and sends it to the third hydrogen outlet, the fourth hydrogen outlet, and the third hydrogen outlet respectively The hydrogen is sent to the hydrogen-oxygen engine module, and the fourth hydrogen outlet sends the hydrogen to the hydrogen arc thruster module;
氢电弧推力器模块，包括第三氢气入口、氢电弧推力器支路；第三氢气入口接收氢气后送至氢电弧推力器支路，氢电弧推力器支路包括流量控制器、氢电弧推力器，流量控制器接收外部流量指令，根据流量指令控制送至氢电弧推力器的氢气流量，氢电弧推力器产生用于空间站的动量轮卸载及姿态位置控制的推力，其中，氢电弧推力器支路为至少2个；所述的流量指令包括输送至氢电弧推力器的氢气流量；The hydrogen arc thruster module includes a third hydrogen inlet and a hydrogen arc thruster branch; the third hydrogen inlet receives hydrogen and sends it to the hydrogen arc thruster branch, and the hydrogen arc thruster branch includes a flow controller and a hydrogen arc thruster , the flow controller receives the external flow command, and controls the flow of hydrogen gas sent to the hydrogen arc thruster according to the flow command, and the hydrogen arc thruster generates thrust for the momentum wheel unloading and attitude position control of the space station, wherein, the hydrogen arc thruster branch It is at least 2; the flow command includes the hydrogen flow delivered to the hydrogen arc thruster;
气氢气氧发动机模块，包括第三氧气入口、第四氢气入口、氢氧发动机支路；第三氧气入口接收氧气后送至氢氧发动机支路，第四氢气入口接收氢气后送至氢氧发动机支路，氢氧发动机支路中的氢氧发动机产生用于空间站的高度保持的推力，其中，氢氧发动机支路为至少2个。The gas-hydrogen-oxygen engine module includes the third oxygen inlet, the fourth hydrogen inlet, and the hydrogen-oxygen engine branch; the third oxygen inlet receives oxygen and sends it to the hydrogen-oxygen engine branch, and the fourth hydrogen inlet receives hydrogen and sends it to the hydrogen-oxygen engine In the branch circuit, the hydrogen-oxygen engine in the hydrogen-oxygen engine branch generates thrust for maintaining the altitude of the space station, wherein there are at least two hydrogen-oxygen engine branches.
所述的气氢气氧发动机模块中氢氧发动机需要的氧气和氢气重量比为4-8。The weight ratio of oxygen and hydrogen required by the hydrogen-oxygen engine in the hydrogen-oxygen engine module is 4-8.
所述的高压氧气瓶或高压氢气瓶的额定存储气压为2-15MPa。The rated storage pressure of the high-pressure oxygen cylinder or high-pressure hydrogen cylinder is 2-15MPa.
所述的降压后的氧气或降压后的氢气的气压为1.4MPa-1.6MPa。The pressure of the decompressed oxygen or decompressed hydrogen is 1.4MPa-1.6MPa.
本发明与现有技术相比的优点在于：The advantage of the present invention compared with prior art is:
(1)本发明通过合理配置废水处理及电解模块、氢氧存储模块、氢氧供给模块、氢电弧推力器模块、气氢气氧发动机模块，形成基于氢电弧推力器和氢氧发动机的空间站水基推进系统，满足了空间站有效处理废气和废水，节省推进燃料这两项需求，解决了目前设计的空间站燃料补给周期偏短的问题；(1) The present invention forms a water-based space station based on hydrogen arc thrusters and hydrogen-oxygen engines by rationally configuring wastewater treatment and electrolysis modules, hydrogen-oxygen storage modules, hydrogen-oxygen supply modules, hydrogen-arc thruster modules, and gas-hydrogen-oxygen engine modules. The propulsion system satisfies the two needs of the space station to effectively treat exhaust gas and waste water and save propellant fuel, and solves the problem of the short fuel supply cycle of the currently designed space station;
(2)本发明引入氢电弧推力器模块，通过配置氢电弧推力器模块中氢电弧推力器的功率、数量和工作量来调节整个系统消耗的氧气和氢气比例，克服了现有水基推进系统单纯使用混合比4-8的气氢气氧推力器难以将目前空间站废气废水产生的混合比小于4的氧气和氢气完全有效利用的缺陷，具有能高效利用不同比例的氧气和氢气的优点；(2) The present invention introduces the hydrogen arc thruster module, and adjusts the ratio of oxygen and hydrogen consumed by the entire system by configuring the power, quantity and workload of the hydrogen arc thruster in the hydrogen arc thruster module, which overcomes the existing water-based propulsion system Simply using gas-hydrogen-oxygen thrusters with a mixing ratio of 4-8 is difficult to fully and effectively utilize the oxygen and hydrogen produced by waste water from space stations with a mixing ratio of less than 4, and has the advantage of being able to efficiently utilize oxygen and hydrogen in different proportions;
(3)本发明中氢电弧推力器模块用于空间站的动量轮卸载、姿态位置的高精度控制，气氢气氧发动机模块用于空间站的高度保持，克服了现有水基推进系统需要采用不同推力量级的气氢气氧发动机完成所有任务，导致的比冲偏低、推力器设计难度大的缺陷，解决了精确小推力长时间工作的空间气氢气氧发动机的设计难题；(3) In the present invention, the hydrogen arc thruster module is used for the unloading of the momentum wheel of the space station and the high-precision control of the attitude position, and the gas-hydrogen-oxygen engine module is used for the height maintenance of the space station, which overcomes the need to use different thrusts in the existing water-based propulsion system The large-scale gas-hydrogen-oxygen engine completes all tasks, resulting in low specific impulse and difficult design of thrusters, which solves the design problem of space gas-hydrogen-oxygen engines that work for a long time with precise low thrust;
(4)本发明实现了对空间站废气和废水的有效利用，产生空间站所需的在轨维持推力，每年可为空间站节省推进剂25％以上推进剂。(4) The present invention realizes the effective utilization of waste gas and waste water of the space station, generates the on-orbit maintenance thrust required by the space station, and can save more than 25% propellant for the space station every year.
附图说明Description of drawings
图1为本发明基于氢电弧推力器和氢氧发动机的空间站水基推进系统结构图；Fig. 1 is the structural diagram of the space station water-based propulsion system based on the hydrogen arc thruster and the hydrogen-oxygen engine of the present invention;
图2为本发明废水处理及电解模块结构图；Fig. 2 is the structural diagram of wastewater treatment and electrolysis module of the present invention;
图3为本发明氢氧存储模块结构图；Fig. 3 is the structural diagram of hydrogen and oxygen storage module of the present invention;
图4为本发明氢氧供给模块结构图；Fig. 4 is a structural diagram of the hydrogen and oxygen supply module of the present invention;
图5为本发明气氢气氧发动机模块；Fig. 5 is the gas-hydrogen-oxygen engine module of the present invention;
图6为本发明氢电弧推力器模块。Fig. 6 is a hydrogen arc thruster module of the present invention.
具体实施方式detailed description
针对空间站运行过程中产生的大量生活废水和电解废气(氢气)难以得到利用且需要耗费额外的资源对其进行处理和排放的缺陷，本发明提出一种基于氢电弧推力器和氢氧发动机的空间站水基推进系统，该系统通过电解处理废水产生氢气和氧气，将电解废水产生的氢氧气体和空间站生保系统排放的废弃氢气收集起来供给到氢电弧推力器和气氢气氧发动机，其中，氢电弧推力器利用氢气产生推力，气氢气氧发动机利用氢氧气体产生推力。本发明系统通过氢电弧推力器和气氢气氧发动机的组合使用，使载人空间站的废气和废水得到高效利用，为空间站提供可观的在轨运行动力，根据估算，该系统每年可为空间站节省推进燃料25％以上，大大降低载人空间站的独立运行成本。Aiming at the defects that a large amount of domestic wastewater and electrolytic waste gas (hydrogen) generated during the operation of the space station are difficult to be utilized and require additional resources to process and discharge them, the present invention proposes a space station based on a hydrogen arc thruster and a hydrogen-oxygen engine The water-based propulsion system, which generates hydrogen and oxygen by electrolytically treating wastewater, collects the hydrogen-oxygen gas produced by electrolysis of wastewater and the waste hydrogen discharged from the life support system of the space station, and supplies them to the hydrogen-arc thruster and hydrogen-oxygen engine. Among them, the hydrogen-arc thrust The engine uses hydrogen to generate thrust, and the hydrogen-oxygen engine uses hydrogen and oxygen gas to generate thrust. The system of the present invention makes efficient use of the waste gas and waste water of the manned space station through the combined use of the hydrogen arc thruster and the gas-hydrogen-oxygen engine, and provides the space station with considerable power for on-orbit operation. According to estimates, the system can save propulsion fuel for the space station every year More than 25%, greatly reducing the independent operation cost of the manned space station.
基于氢电弧推力器和氢氧发动机的空间站水基推进系统包括废水处理及电解模块、氢氧存储模块、氢氧供给模块、氢电弧推力器模块、气氢气氧发动机模块。废水处理及电解模块利用空间站废水电解产生氢氧气体。氢氧存储模块将空间站废弃的氢气和由废水及电解模块产生的氢氧气体收集，并以一定压力存储。氢氧供给模块将氢氧存储模块存储的高压氢氧气体通过减压和流量控制，按照一定的压力和流量供给到氢电弧推力器模块和气氢气氧发动机模块。氢电弧推力器模块利用氢气产生推力。气氢气氧发动机模块利用氢气和氧气产生推力。The space station water-based propulsion system based on hydrogen arc thrusters and hydrogen-oxygen engines includes wastewater treatment and electrolysis modules, hydrogen-oxygen storage modules, hydrogen-oxygen supply modules, hydrogen-arc thruster modules, and gas-hydrogen-oxygen engine modules. The wastewater treatment and electrolysis module uses the electrolysis of waste water on the space station to generate hydrogen and oxygen gas. The hydrogen-oxygen storage module collects the waste hydrogen of the space station and the hydrogen-oxygen gas produced by the waste water and the electrolysis module, and stores them under a certain pressure. The hydrogen and oxygen supply module supplies the high-pressure hydrogen and oxygen gas stored in the hydrogen and oxygen storage module to the hydrogen arc thruster module and the hydrogen and oxygen engine module according to a certain pressure and flow through decompression and flow control. The hydrogen arc thruster module uses hydrogen to generate thrust. The hydrogen-oxygen engine module uses hydrogen and oxygen to generate thrust.
下面根据附图对本发明系统进行详细说明。The system of the present invention will be described in detail below according to the accompanying drawings.
基于氢电弧推力器和氢氧发动机的空间站水基推进系统如图1所示包括：废水处理及电解模块1、氢氧存储模块2、氢氧供给模块3、氢电弧推力器模块4、气氢气氧发动机模块5，其中，废水处理及电解模块1的废水处理及电解模块氧气出口8与氢氧存储模块2的氢氧存储模块氧气入口9相连。废水处理及电解模块1的废水处理及电解模块氢气出口7与氢氧存储模块2的氢氧存储模块氢气入口16相连。氢氧存储模块2的氢氧存储模块氧气出口12与氢氧供给模块3的氢氧供给模块氧气入口17相连。氢氧存储模块2的氢氧存储模块氢气出口13与氢氧供给模块3的氢氧供给模块氢气入口23相连。氢氧供给模块3的氢氧供给模块氧气出口19与气氢气氧发动机模块5的气氢气氧发动机模块氧气入口24相连。氢氧供给模块3的第一氢氧供给模块氢气出口20与气氢气氧发动机模块5的气氢气氧发动机模块氢气入口26相连。氢氧供给模块3的第二氢氧供给模块氢气出口21与氢电弧推力器模块4的氢电弧推力器模块氢气入口27相连。The space station water-based propulsion system based on hydrogen arc thrusters and hydrogen-oxygen engines is shown in Figure 1, including: wastewater treatment and electrolysis module 1, hydrogen and oxygen storage module 2, hydrogen and oxygen supply module 3, hydrogen arc thruster module 4, gas hydrogen Oxygen engine module 5 , wherein the wastewater treatment and electrolysis module oxygen outlet 8 of the wastewater treatment and electrolysis module 1 is connected to the hydrogen and oxygen storage module oxygen inlet 9 of the hydrogen and oxygen storage module 2 . The wastewater treatment and electrolysis module hydrogen outlet 7 of the wastewater treatment and electrolysis module 1 is connected to the hydrogen oxygen storage module hydrogen inlet 16 of the hydrogen oxygen storage module 2 . The hydrogen and oxygen storage module oxygen outlet 12 of the hydrogen and oxygen storage module 2 is connected with the hydrogen and oxygen supply module oxygen inlet 17 of the hydrogen and oxygen supply module 3 . The oxygen hydrogen storage module hydrogen outlet 13 of the hydrogen oxygen storage module 2 is connected with the hydrogen oxygen supply module hydrogen inlet 23 of the hydrogen oxygen supply module 3 . The hydrogen and oxygen supply module oxygen outlet 19 of the hydrogen and oxygen supply module 3 is connected with the hydrogen and oxygen engine module oxygen inlet 24 of the hydrogen and oxygen engine module 5 . The first hydrogen and oxygen supply module hydrogen outlet 20 of the hydrogen and oxygen supply module 3 is connected with the hydrogen and oxygen engine module hydrogen inlet 26 of the hydrogen and oxygen engine module 5 . The hydrogen gas outlet 21 of the second hydrogen and oxygen supply module of the hydrogen and oxygen supply module 3 is connected with the hydrogen gas inlet 27 of the hydrogen arc thruster module of the hydrogen arc thruster module 4 .
(1)废水处理及电解模块。(1) Wastewater treatment and electrolysis module.
废水处理及电解模块1如图2所示。通过废水处理及电解模块废水入口6接收废水，通过过滤和电解，产生氢气和氧气，氢气通过废水处理及电解模块氢气出口7输出，氧气通过通过废水处理及电解模块氧气出口8输出。The wastewater treatment and electrolysis module 1 is shown in FIG. 2 . The waste water is received through the waste water treatment and electrolysis module waste water inlet 6, through filtration and electrolysis, hydrogen and oxygen are produced, the hydrogen is output through the waste water treatment and electrolysis module hydrogen outlet 7, and the oxygen is output through the waste water treatment and electrolysis module oxygen outlet 8.
(2)氢氧存储模块(2) Oxygen hydrogen storage module
氢氧存储模块2如图3所示，9为氢氧存储模块氧气入口，10为氧充填装置，11为高压氧气瓶，12为氢氧存储模块氧气出口，13为氢氧存储模块氢气出口，14为高压氢气瓶，15为氢充填装置，16为氢氧存储模块氢气入口。通过氢氧存储模块氧气入口9接收氧气，通过氧充填装置10将氧气充填入高压氧气瓶11，高压氧气瓶11存储高压氧气，存储压力2-15MPa，高压氧气瓶11通过氢氧存储模块氧气出口12将高压氧气输出。通过氢氧存储模块氢气入口16接收氢气，通过氢充填装置15将氢气充填入高压氢气瓶14，高压氢气瓶14存储高压氧气，存储压力2-15MPa，高压氢气瓶14通过氢氧存储模块氢气出口13将高压氢气输出。Hydroxygen storage module 2 as shown in Figure 3, 9 is the oxygen inlet of the hydrogen-oxygen storage module, 10 is the oxygen filling device, 11 is the high-pressure oxygen cylinder, 12 is the oxygen outlet of the hydrogen-oxygen storage module, and 13 is the hydrogen outlet of the hydrogen-oxygen storage module, 14 is a high-pressure hydrogen cylinder, 15 is a hydrogen filling device, and 16 is a hydrogen inlet of a hydrogen-oxygen storage module. Oxygen is received through the oxygen inlet 9 of the hydrogen-oxygen storage module, and oxygen is filled into the high-pressure oxygen cylinder 11 through the oxygen filling device 10. The high-pressure oxygen cylinder 11 stores high-pressure oxygen with a storage pressure of 2-15 MPa. The high-pressure oxygen cylinder 11 passes through the oxygen outlet of the hydrogen-oxygen storage module. 12 output high pressure oxygen. Hydrogen is received through the hydrogen inlet 16 of the hydrogen-oxygen storage module, and hydrogen is filled into the high-pressure hydrogen cylinder 14 through the hydrogen filling device 15. The high-pressure hydrogen cylinder 14 stores high-pressure oxygen, and the storage pressure is 2-15MPa. The high-pressure hydrogen cylinder 14 passes through the hydrogen outlet of the hydrogen-oxygen storage module. 13 output high-pressure hydrogen.
充填装置用于将上游氢或氧气体充填到高压气瓶，该装置一方面通过压力调理，保证氢或氧气体压力高于气瓶内气体压力，同时低于气瓶额定存储压力，使氢氧气体能够充填进气瓶，另一方面控制反向泄露，保证气瓶内存储气体不会反向泄露到上游部件。The filling device is used to fill the upstream hydrogen or oxygen gas into the high-pressure gas cylinder. On the one hand, the device ensures that the hydrogen or oxygen gas pressure is higher than the gas pressure in the gas cylinder through pressure regulation, and at the same time lower than the rated storage pressure of the gas cylinder, so that the hydrogen and oxygen gas The body can fill the air cylinder, and on the other hand, control the reverse leakage to ensure that the gas stored in the cylinder will not leak back to the upstream components.
(3)氢氧供给模块(3) Hydrogen and oxygen supply module
氢氧供给模块3如图4所示，17为氢氧供给模块氧气入口，18为氧减压器，19为氢氧供给模块氧气出口，20为第一氢氧供给模块氢气出口，21为第二氢氧供给模块氢气出口，22为氢气减压器，23为氢氧供给模块氢气入口。通过氢氧供给模块氧气入口17接收高压氧气，通过氧减压器18将高压氧气减压到1.4MPa-1.6MPa，通过氢氧供给模块氧气出口19将低压氧气输出。Hydrogen and oxygen supply module 3 as shown in Figure 4, 17 is the oxygen inlet of hydrogen and oxygen supply module, 18 is the oxygen pressure reducer, 19 is the oxygen outlet of hydrogen and oxygen supply module, 20 is the hydrogen outlet of the first hydrogen and oxygen supply module, and 21 is the first 22 is the hydrogen pressure reducer, and 23 is the hydrogen inlet of the hydrogen and oxygen supply module. The high-pressure oxygen is received through the oxygen inlet 17 of the hydrogen-oxygen supply module, the high-pressure oxygen is decompressed to 1.4MPa-1.6MPa through the oxygen pressure reducer 18, and the low-pressure oxygen is output through the oxygen outlet 19 of the hydrogen-oxygen supply module.
氢氧供给模块3通过氢氧供给模块氢气入口23接收高压氢气，通过氢减压器22将高压氢气减压到1.4MPa-1.6MPa，通过第一氢氧供给模块氢气出口20和第二氢氧供给模块氢气出口21将低压氢气输出。The oxygen hydrogen supply module 3 receives high-pressure hydrogen through the hydrogen inlet 23 of the oxygen hydrogen supply module, decompresses the high-pressure hydrogen to 1.4MPa-1.6MPa through the hydrogen pressure reducer 22, and passes through the hydrogen outlet 20 of the first hydrogen oxygen supply module and the second hydrogen oxygen The hydrogen outlet 21 of the supply module outputs the low-pressure hydrogen.
氢氧供给模块包括一个氧气分支和两个氢气分支，氧气分支通过减压器将氧气减压到气氢气氧发动机工作所需压力后供给到气氢气氧发动机模块，氢气分支通过减压器将氢气减压到气氢气氧发动机工作所需压力后一路供给到气氢气氧发动机模块，另一路供给到氢电弧推力器模块。The hydrogen and oxygen supply module includes an oxygen branch and two hydrogen branches. The oxygen branch decompresses the oxygen to the pressure required for the hydrogen and oxygen engine to work through the pressure reducer and then supplies it to the hydrogen and oxygen engine module. After depressurizing to the pressure required for the hydrogen-oxygen engine to work, one path is supplied to the hydrogen-oxygen engine module, and the other path is supplied to the hydrogen arc thruster module.
(4)氢电弧推力器模块(4) Hydrogen arc thruster module
氢电弧推力器模块4如图5所示，24为气氢气氧发动机模块氧气入口，25为气氢气氧发动机，26为气氢气氧发动机模块氢气入口。通过氢电弧推力器模块氢气入口27输入氢气，并分成多个支路向下游供给。一个支路包括一个微小流量控制器28和一个氢电弧推力器29，分支数量根据空间站实际推进需求确定。各个支路的微小流量控制器28精确控制氢气流量，按照需求将氢气供给到氢电弧推力器29。The hydrogen arc thruster module 4 is as shown in Figure 5, 24 is the oxygen inlet of the hydrogen-oxygen engine module, 25 is the hydrogen-oxygen engine, and 26 is the hydrogen inlet of the hydrogen-oxygen engine module. The hydrogen gas is input through the hydrogen gas inlet 27 of the hydrogen arc thruster module, and is divided into multiple branches and supplied downstream. One branch includes a micro-flow controller 28 and a hydrogen arc thruster 29, and the number of branches is determined according to the actual propulsion requirements of the space station. The tiny flow controllers 28 of each branch precisely control the hydrogen flow, and supply the hydrogen to the hydrogen arc thruster 29 according to the demand.
(5)气氢气氧发动机模块(5) Hydrogen and oxygen engine module
气氢气氧发动机模块5如图6所示，27为氢电弧推力器模块氢气入口，28为微小流量控制器，29为氢电弧推力器。通过气氢气氧发动机模块氧气入口24输入氧气，通过气氢气氧发动机模块氢气入口26输入氢气，并分别形成多个支路供给到气氢气氧发动机25。每一个氧气支路和氢气支路对应一个气氢气氧发动机25，气氢气氧发动机25作为轨控发动机使用，推力和数量由空间站推进需求确定。The gas-hydrogen-oxygen engine module 5 is as shown in Figure 6, 27 is the hydrogen inlet of the hydrogen arc thruster module, 28 is a micro flow controller, and 29 is the hydrogen arc thruster. Oxygen is input through the oxygen inlet 24 of the hydrogen-oxygen engine module, hydrogen is input through the hydrogen inlet 26 of the hydrogen-oxygen engine module, and a plurality of branches are respectively formed to supply to the hydrogen-oxygen engine 25 . Each oxygen branch and hydrogen branch corresponds to a gas-hydrogen-oxygen engine 25, and the gas-hydrogen-oxygen engine 25 is used as an orbit control engine, and the thrust and quantity are determined by the propulsion requirements of the space station.
本发明说明书中未作详细描述的内容属本领域技术人员的公知技术。The content that is not described in detail in the description of the present invention belongs to the well-known technology of those skilled in the art.
Claims (4)
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510860374.5A CN105438501B (en) | 2015-11-30 | 2015-11-30 | The water base propulsion system in space station based on hydrogen Arcjet and oxyhydrogen engine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510860374.5A CN105438501B (en) | 2015-11-30 | 2015-11-30 | The water base propulsion system in space station based on hydrogen Arcjet and oxyhydrogen engine |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN105438501A CN105438501A (en) | 2016-03-30 |
| CN105438501B true CN105438501B (en) | 2017-08-29 |
Family
ID=55549242
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201510860374.5A Active CN105438501B (en) | 2015-11-30 | 2015-11-30 | The water base propulsion system in space station based on hydrogen Arcjet and oxyhydrogen engine |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN105438501B (en) |
Families Citing this family (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110127089B (en) * | 2019-05-10 | 2021-02-05 | 北京控制工程研究所 | A water-based propulsion system and method for high-orbit satellites |
| CN111005848A (en) * | 2019-10-31 | 2020-04-14 | 西安空间无线电技术研究所 | A space electrochemical composite thruster working medium supply system and method |
| 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 |
| CN115649492B (en) * | 2022-10-28 | 2025-05-02 | 中国运载火箭技术研究院 | A cryogenic propellant integrated fluid system based on energy-fluid matching design |
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 | Preparation method of solar water-based high-pressure high-purity hydrogen-oxygen fuel for space vehicles |
| 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 | Preparation method of solar water-based high-pressure high-purity hydrogen-oxygen fuel for space vehicles |
| 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 |
Also Published As
| Publication number | Publication date |
|---|---|
| CN105438501A (en) | 2016-03-30 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN105438501B (en) | The water base propulsion system in space station based on hydrogen Arcjet and oxyhydrogen engine | |
| CN110127089B (en) | A water-based propulsion system and method for high-orbit satellites | |
| WO2022135110A1 (en) | Mixed pressurization multistage filling hydrogenation device | |
| CN202063261U (en) | Gas-powered rocket and gas-powered rocket system | |
| CN107762663B (en) | Space propulsion system integrating propulsion and replenishment functions | |
| CN113174606A (en) | Moon base energy supply and application system based on photolysis water hydrogen production technology | |
| CN107878783A (en) | A kind of power supply propulsion system based on regeneratable fuel cell | |
| CN112501632A (en) | Research of rail-controlled engine system based on solar water electrolysis | |
| EP2699714A1 (en) | A combined magnetohydrodynamic and electrochemical method and facility for namely electric power generation | |
| US20160083855A1 (en) | Method for operating a high-pressure electrolysis system, high-pressure electrolysis system and hydrogen filling station comprising a high-pressure electrolysis system | |
| CN102030314B (en) | Oxygen generator | |
| CN207999295U (en) | A kind of compressed air electric energy storing system | |
| CN110925032B (en) | Lunar pneumatic power generation method based on propelling residual resource secondary utilization | |
| CN203442476U (en) | Air-supply circulating system of air engine | |
| CN111927648A (en) | An integrated power system for orbit and attitude control based on non-toxic and environmentally friendly propellant | |
| CN117366471A (en) | Application system for replacing ash hydrogen in thermal power plant | |
| CN203883078U (en) | Quickly started methanol fuel power supply system | |
| CN116529473A (en) | Spacecraft with low-thrust and high-thrust propulsion systems | |
| CN103539084A (en) | Nitrogen system | |
| CN106545934A (en) | A kind of deep-sea space station equipment compartment cooling system and its control method | |
| RU2018129983A (en) | The method of acceleration to a given interplanetary orbit and a reusable transport and energy module | |
| CN108278493B (en) | Natural gas oxygen pipeline network cooperative control management system | |
| CN112141365B (en) | On-orbit service module based on ground test interface | |
| CN104743665A (en) | Experimental device for microbiological treatment of urine wastewater | |
| CN202876648U (en) | Denitration process system |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |