CN110127089B - Water-based propulsion system and method applied to high-orbit satellite - Google Patents
Water-based propulsion system and method applied to high-orbit satellite Download PDFInfo
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- CN110127089B CN110127089B CN201910389491.6A CN201910389491A CN110127089B CN 110127089 B CN110127089 B CN 110127089B CN 201910389491 A CN201910389491 A CN 201910389491A CN 110127089 B CN110127089 B CN 110127089B
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- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 title claims abstract description 148
- 238000000034 method Methods 0.000 title claims abstract description 15
- 239000001301 oxygen Substances 0.000 claims abstract description 287
- 229910052760 oxygen Inorganic materials 0.000 claims abstract description 287
- 239000012528 membrane Substances 0.000 claims abstract description 63
- 230000003068 static effect Effects 0.000 claims abstract description 62
- 239000007789 gas Substances 0.000 claims abstract description 45
- 238000002156 mixing Methods 0.000 claims abstract description 17
- 239000001257 hydrogen Substances 0.000 claims description 244
- 229910052739 hydrogen Inorganic materials 0.000 claims description 244
- QVGXLLKOCUKJST-UHFFFAOYSA-N atomic oxygen Chemical compound [O] QVGXLLKOCUKJST-UHFFFAOYSA-N 0.000 claims description 236
- UFHFLCQGNIYNRP-UHFFFAOYSA-N Hydrogen Chemical compound [H][H] UFHFLCQGNIYNRP-UHFFFAOYSA-N 0.000 claims description 209
- 150000002431 hydrogen Chemical class 0.000 claims description 34
- 230000001143 conditioned effect Effects 0.000 claims description 21
- 239000008367 deionised water Substances 0.000 claims description 13
- 229910021641 deionized water Inorganic materials 0.000 claims description 13
- 241000283690 Bos taurus Species 0.000 claims description 8
- 238000001816 cooling Methods 0.000 claims description 6
- 239000000126 substance Substances 0.000 claims description 5
- 230000005855 radiation Effects 0.000 claims description 4
- 239000000112 cooling gas Substances 0.000 claims description 3
- 230000007774 longterm Effects 0.000 description 5
- 230000003750 conditioning effect Effects 0.000 description 4
- 238000005868 electrolysis reaction Methods 0.000 description 4
- 238000005516 engineering process Methods 0.000 description 4
- 238000001035 drying Methods 0.000 description 3
- 230000000737 periodic effect Effects 0.000 description 3
- MYMOFIZGZYHOMD-UHFFFAOYSA-N Dioxygen Chemical compound O=O MYMOFIZGZYHOMD-UHFFFAOYSA-N 0.000 description 2
- 238000010586 diagram Methods 0.000 description 2
- 229910001882 dioxygen Inorganic materials 0.000 description 2
- 230000001141 propulsive effect Effects 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000002485 combustion reaction Methods 0.000 description 1
- 230000000295 complement effect Effects 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 238000010891 electric arc Methods 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
- 239000000203 mixture Substances 0.000 description 1
- 230000001105 regulatory effect Effects 0.000 description 1
- 238000000926 separation method Methods 0.000 description 1
- 238000006467 substitution reaction Methods 0.000 description 1
- 238000011144 upstream manufacturing Methods 0.000 description 1
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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
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- B64G1/402—Propellant tanks; Feeding propellants
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Abstract
The invention discloses a water-based propulsion system and method applied to a high-orbit satellite, wherein the system comprises a power supply, a water tank, a static water supply proton exchange membrane electrolytic cell, an oxyhydrogen management system, a hundred-Newton-level hydrogen-oxygen orbit control engine and a Newton-level hydrogen-oxygen attitude control engine. The invention solves the problems that the oxyhydrogen gas is difficult to manage in space environment for a long time and the oxyhydrogen gas with equivalent mixing ratio is difficult to utilize efficiently, and improves the engineering practicability of the oxyhydrogen propulsion system in a space flight platform.
Description
Technical Field
The invention belongs to the technical field of space propulsion, and particularly relates to a water-based propulsion system and method applied to a high-orbit satellite.
Background
Oxyhydrogen propulsion is currently the highest form of chemical propulsion.
The water-based propulsion technology is based on a proton exchange membrane water electrolysis cell (SPE), a space gas hydrogen oxygen engine and a hydrogen electric arc thruster. The technology generates oxyhydrogen gas by electrolyzing water and supplies the oxyhydrogen gas to an engine to generate thrust. The technology enables the space flight platform to generate chemical thrust with specific impulse over 360s on the track only by carrying low-pressure water, has the characteristics of high specific impulse, greenness, no pollution, safe storage, low cost and the like, and meets the development requirements of space tasks on the propulsion technology at the present stage.
However, the application of the water-based propulsion system to the satellite platform has the following problems:
(1) oxyhydrogen gas electrolyzed by a traditional electrolytic cell is mixed with water, and an additional water-gas separation device, a drying device and the like are needed, so that the traditional electrolytic cell is not suitable for being used on a satellite platform.
(2) The pressure of oxyhydrogen gas electrolyzed by the electrolytic cell is limited. If the electrolyzed gas is directly stored in the gas cylinder, the gas quality which can be stored by the gas cylinder in one electrolysis period is less, and the total thrust which can be obtained by the satellite platform in one period is severely limited. If the electrolyzed gas is stored in the gas cylinder after being pressurized by the booster pump, the quality of the gas which can be stored in the gas cylinder in one electrolysis period can be greatly improved. However, the booster pump is a vulnerable part, and is not suitable for being frequently used as a main matching part of the satellite platform.
(3) The oxygen and hydrogen electrolyzed by the water-based propulsion system is 8: 1, only in a mixing ratio of 8: 1 can ensure that the electrolyzed oxyhydrogen gas is fully utilized. And the traditional hydrogen-oxygen engine has a design mixing ratio of 4: about 1, designed as 8: the conventional 1 mixing ratio oxyhydrogen engine has difficulty in supporting a long-term stable operation. There is no clear water-based propulsion system engine complement internationally.
Disclosure of Invention
The technical problem solved by the invention is as follows: the defects of the prior art are overcome, the water-based propulsion system and the water-based propulsion method applied to the high-orbit satellite are provided, the problem of engineering practicability of the water-based propulsion system in the high-orbit satellite is solved, and the propulsion specific impulse of the high-orbit satellite can reach more than 360 s.
The purpose of the invention is realized by the following technical scheme: according to one aspect of the present invention, there is provided a water-based propulsion system for use with an elevated earth satellite, comprising: the system comprises a power supply, a water tank, a static water supply proton exchange membrane electrolytic cell, an oxygen-hydrogen management system, a hundred-Newton grade hydrogen-oxygen rail control engine and a Newton grade hydrogen-oxygen attitude control engine; the system comprises a power supply, a water tank, a hydrogen inlet, an oxygen inlet, a hydrogen outlet, a hydrogen inlet, an oxygen outlet, a hydrogen path, an oxygen path, a hydrogen path and an oxygen path, wherein the power supply and the water tank are respectively connected with a static water supply proton exchange membrane electrolytic cell; the power supply supplies power to the static water supply proton exchange membrane electrolytic cell; the water tank supplies low-pressure deionized water for the static water supply proton exchange membrane electrolytic cell; the static water supply proton exchange membrane electrolytic cell directly electrolyzes low-pressure deionized water into high-pressure hydrogen and high-pressure oxygen by using electric energy and supplies the high-pressure hydrogen and the high-pressure oxygen to the hydrogen and oxygen management system respectively; the hydrogen and oxygen management system stores high-pressure hydrogen and high-pressure oxygen into a high-pressure gas cylinder, conditions the high-pressure hydrogen into preset pressure and preset flow rate, and then respectively supplies the preset pressure and the preset flow rate to the hundred-Newton-level hydrogen and oxygen rail control engine and the Newton-level hydrogen and oxygen attitude control engine, and conditions the high-pressure oxygen into preset pressure and preset flow rate, and then respectively supplies the preset pressure and the preset flow rate to the hundred-Newton-level hydrogen and oxygen rail control engine and the Newton-level hydrogen and oxygen attitude control engine; the hundred-Newton grade hydrogen-oxygen rail control engine generates steady-state rail control thrust according to the conditioned high-pressure hydrogen and the conditioned high-pressure oxygen; the cattle-grade hydrogen oxygen attitude control engine generates pulse attitude control thrust according to the conditioned high-pressure hydrogen and the conditioned high-pressure oxygen. The method comprises the following steps of regulating high-pressure hydrogen into preset pressure and preset flow, and then respectively supplying the preset pressure and the preset flow to a hundred-Newton-level hydrogen-oxygen rail control engine and a Newton-level hydrogen-oxygen attitude control engine: the method comprises the steps of conditioning high-pressure hydrogen into rated hydrogen inlet pressure of a hundred-Newton-level hydrogen-oxygen rail-controlled engine and rated hydrogen flow of the hundred-Newton-level hydrogen-oxygen rail-controlled engine, supplying the conditioned high-pressure hydrogen to the hundred-Newton-level hydrogen-oxygen rail-controlled engine, conditioning the high-pressure hydrogen into rated hydrogen inlet pressure of the bovine-level hydrogen-oxygen attitude-control engine and rated hydrogen flow of the bovine-level hydrogen-oxygen attitude-control engine, and supplying the conditioned high-pressure hydrogen to the bovine-level hydrogen-oxygen attitude-control engine; after being conditioned into preset pressure and preset flow, the high-pressure oxygen is respectively supplied to a hundred-Newton hydrogen oxygen rail control engine and a Newton hydrogen oxygen attitude control engine, and the method specifically comprises the following steps: the method comprises the steps of conditioning high-pressure oxygen into rated oxygen inlet pressure of a hundred-Newton grade hydrogen-oxygen rail-controlled engine and rated oxygen flow of the hundred-Newton grade hydrogen-oxygen rail-controlled engine, supplying the conditioned high-pressure oxygen to the hundred-Newton grade hydrogen-oxygen rail-controlled engine, conditioning the high-pressure oxygen into rated oxygen inlet pressure of the bovine grade hydrogen-oxygen attitude-control engine and rated oxygen flow of the bovine grade hydrogen-oxygen attitude-control engine, and supplying the conditioned high-pressure oxygen to the bovine grade hydrogen-oxygen attitude-control engine.
In the above water-based propulsion system for high-orbit satellites, the hydrogen and oxygen management system comprises a hydrogen direct filling module, a hydrogen pump pressurization module, a high-pressure hydrogen cylinder, a hydrogen path pressure flow control module, an oxygen direct filling module, an oxygen pump pressurization module, a high-pressure oxygen cylinder and an oxygen path pressure flow control module; the hydrogen path of the static water supply proton exchange membrane electrolytic cell is divided into two paths which are respectively connected with the hydrogen direct filling module and the hydrogen pump pressurizing module; the hydrogen direct filling module is connected with the hydrogen pump pressurizing module in parallel and then connected with the high-pressure hydrogen cylinder; the high-pressure hydrogen cylinder is connected with the hydrogen path pressure flow control module; an oxygen path of the static water supply proton exchange membrane electrolytic cell is divided into two paths which are respectively connected with an oxygen direct filling module and an oxygen pump pressurizing module; the oxygen direct filling module is connected with the oxygen pump pressurizing module in parallel and then connected with the high-pressure oxygen cylinder; the high-pressure oxygen cylinder is connected with the oxygen path pressure flow control module.
In the water-based propulsion system applied to the high orbit satellite, the static water supply proton exchange membrane electrolytic cell receives 0.1MPa low-pressure deionized water provided by the water tank, and the electric energy of the power supply directly electrolyzes high-pressure hydrogen and high-pressure oxygen with the pressure of more than 3 MPa.
In the water-based propulsion system applied to the high-orbit satellite, the static water supply proton exchange membrane electrolytic cell electrolyzes high-pressure hydrogen, and when the storage pressure of a high-pressure hydrogen bottle is required to be not more than the highest pressure hydrogen which can be electrolyzed by the static water supply proton exchange membrane electrolytic cell, the high-pressure hydrogen bottle is directly filled by the hydrogen direct filling module; when the storage pressure of the high-pressure hydrogen cylinder is required to exceed the highest pressure of the static water supply proton exchange membrane electrolytic cell, the hydrogen is filled into the high-pressure hydrogen cylinder after being further pressurized by the hydrogen pump pressurizing module.
In the water-based propulsion system applied to the high orbit satellite, the static water supply proton exchange membrane electrolytic cell electrolyzes high-pressure oxygen, and when the storage pressure of a high-pressure oxygen cylinder is required to be not more than the highest pressure oxygen which can be electrolyzed by the static water supply proton exchange membrane electrolytic cell, the high-pressure oxygen cylinder is directly filled by the oxygen direct filling module; when the storage pressure of the high-pressure oxygen cylinder is required to exceed the highest pressure of the static water supply proton exchange membrane electrolytic cell capable of electrolyzing oxygen, the high-pressure oxygen cylinder is filled with the oxygen through an oxygen pump pressurizing module after further pressurization.
In the above water-based propulsion system applied to the high orbit satellite, the volume ratio of the high-pressure hydrogen cylinder to the high-pressure oxygen cylinder is 2: 1.
in the above water-based propulsion system applied to the high orbit satellite, the hundred-newton grade hydrogen-oxygen orbit control engine has a mixing ratio of 8: 1, the hydrogen-oxygen rail-controlled engine with vortex cooling gas takes steady-state ignition as a main working mode.
In the above water-based propulsion system applied to the high orbit satellite, the mixture ratio of the cattle-grade hydrogen-oxygen attitude control engine is 8: 1, the air film and radiation cooling air hydrogen oxygen attitude control engine takes pulse ignition as a main working mode.
According to another aspect of the present invention, there is also provided a water-based propulsion method for an elevated earth satellite, the method comprising the steps of: a power supply is used for supplying power to the static water supply proton exchange membrane electrolytic cell; supplying low-pressure deionized water to the static water supply proton exchange membrane electrolytic cell by using a water tank; the static water supply proton exchange membrane electrolytic cell directly electrolyzes low-pressure deionized water into high-pressure hydrogen and high-pressure oxygen by using electric energy and supplies the high-pressure hydrogen and the high-pressure oxygen to the hydrogen and oxygen management system respectively; the hydrogen and oxygen management system stores high-pressure hydrogen and high-pressure oxygen into a high-pressure gas cylinder, conditions the high-pressure hydrogen into preset pressure and preset flow rate, and then respectively supplies the preset pressure and the preset flow rate to the hundred-Newton-level hydrogen and oxygen rail control engine and the Newton-level hydrogen and oxygen attitude control engine, and conditions the high-pressure oxygen into preset pressure and preset flow rate, and then respectively supplies the preset pressure and the preset flow rate to the hundred-Newton-level hydrogen and oxygen rail control engine and the Newton-level hydrogen and oxygen attitude control engine; the hundred-Newton grade hydrogen-oxygen rail control engine generates steady-state rail control thrust according to the conditioned high-pressure hydrogen and the conditioned high-pressure oxygen; the cattle-grade hydrogen oxygen attitude control engine generates pulse attitude control thrust according to the conditioned high-pressure hydrogen and the conditioned high-pressure oxygen.
In the above water-based propulsion method applied to the high orbit satellite, the hydrogen and oxygen management system comprises a hydrogen direct filling module, a hydrogen pump pressurization module, a high-pressure hydrogen cylinder, a hydrogen path pressure flow control module, an oxygen direct filling module, an oxygen pump pressurization module, a high-pressure oxygen cylinder and an oxygen path pressure flow control module; the hydrogen path of the static water supply proton exchange membrane electrolytic cell is divided into two paths which are respectively connected with the hydrogen direct filling module and the hydrogen pump pressurizing module; the hydrogen direct filling module is connected with the hydrogen pump pressurizing module in parallel and then connected with the high-pressure hydrogen cylinder; the high-pressure hydrogen cylinder is connected with the hydrogen path pressure flow control module; an oxygen path of the static water supply proton exchange membrane electrolytic cell is divided into two paths which are respectively connected with an oxygen direct filling module and an oxygen pump pressurizing module; the oxygen direct filling module is connected with the oxygen pump pressurizing module in parallel and then connected with the high-pressure oxygen cylinder; the high-pressure oxygen cylinder is connected with the oxygen path pressure flow control module.
Compared with the prior art, the invention has the following beneficial effects:
(1) the existing water electrolysis related system mainly adopts a traditional electrolytic cell, needs a series of auxiliary facilities such as a water circulating pump, a booster pump, a drying device and the like, and is not suitable for a satellite platform. The static water supply proton exchange membrane electrolytic cell is introduced to serve as the electrolytic device of the water-based propulsion system, so that the water-based propulsion system can electrolyze high-pressure hydrogen and oxygen which can be directly stored by using low-pressure deionized water, the water-based propulsion system does not need a complex water circulation device, a long-life supercharging device and a drying device, and the on-orbit service life, reliability and practicability of the system are greatly improved.
(2) The existing water-based propulsion system is generally matched with a booster pump, and electrolyzed gas is stored in a high-pressure gas cylinder after being boosted. Because the booster pump is difficult to realize the on-orbit work of high reliability and long service life, the design state is difficult to meet the long-term on-orbit use requirement of the satellite platform. The invention provides a design of connecting a gas direct filling module and a gas pump pressurizing module which are connected in parallel at an outlet of an electrolytic cell aiming at the use characteristics of a satellite platform on a propulsion system. During the long-term on-orbit working period of the satellite, the electrolyzed gas is directly filled into the high-pressure gas cylinder through the hydrogen direct filling module (7) for the periodic use of the satellite. During the short-term orbit transfer of the satellite or when the orbit needs orbit maneuvering, the electrolyzed gas is further pressurized by the gas pump pressurizing module and then stored in the high-pressure gas cylinder, so that the system can provide more propelling capacity in one period. The design can meet the propulsion requirements of short-term orbital transfer and long-term on-orbit flight of the high-orbit satellite platform, avoids the requirements on overhigh long service life and reliability of the booster pump in the water-based propulsion system, and greatly improves the feasibility and the practicability of the water-based propulsion system on the high-orbit satellite platform.
(3) Existing water-based propulsion system designs do not explicitly address the volumetric state of the oxyhydrogen gas cylinder in the system. The volume ratio of the high-pressure hydrogen cylinder to the high-pressure oxygen cylinder configured in the system is 2: 1, simultaneously the mass mixing ratio of the rail control engine and the attitude control engine is 8: the design can ensure that the proportion of oxyhydrogen gas stored and consumed by the system is consistent with that of oxyhydrogen gas electrolyzed by the electrolytic cell all the time, can ensure that the electrolyzed oxyhydrogen gas is fully utilized, and can ensure that the pressure of a hydrogen cylinder and an oxygen cylinder, and the pressure of the cathode of the electrolytic cell and the pressure of the anode of the electrolytic cell are always kept in a relative balance state in the running process of the system.
(4) The existing water-based propulsion system mainly comprises 8 parts of matched mixing ratio: 1 conventional hydrogen-oxygen engine. Because the weight ratio of 8: 1, the oxyhydrogen combustion temperature is too high, and the oxyhydrogen engine in the traditional design state is difficult to adapt to 8: 1, it is difficult to stably operate for a long period of time. The invention introduces a mixing ratio of 8: 1, mixing ratio of vortex cooling hydrogen-oxygen engine of 8: 1 is used in a conventional hydrogen-oxygen engine. The former can satisfy the requirement of the satellite for long-term stable ignition work, and the latter can satisfy the requirement of short-term pulse ignition work, thus solving the design problem of the engine matched with the water-based propulsion system.
Drawings
Various other advantages and benefits will become apparent to those of ordinary skill in the art upon reading the following detailed description of the preferred embodiments. The drawings are only for purposes of illustrating the preferred embodiments and are not to be construed as limiting the invention. Also, like reference numerals are used to refer to like parts throughout the drawings. In the drawings:
FIG. 1 is a block diagram of a water-based propulsion system for high earth orbit satellites provided by an embodiment of the present invention;
FIG. 2 is a block diagram of a hydrogen and oxygen management system provided by an embodiment of the invention.
Detailed Description
Exemplary embodiments of the present disclosure will be described in more detail below with reference to the accompanying drawings. While exemplary embodiments of the present disclosure are shown in the drawings, it should be understood that the present disclosure may be embodied in various forms and should not be limited to the embodiments set forth herein. Rather, these embodiments are provided so that this disclosure will be thorough and complete, and will fully convey the scope of the disclosure to those skilled in the art. It should be noted that the embodiments and features of the embodiments may be combined with each other without conflict. The present invention will be described in detail below with reference to the embodiments with reference to the attached drawings.
The invention provides a water-based propulsion system applied to a high orbit satellite, which comprises a power supply, a water tank, a static water supply proton exchange membrane electrolytic cell, an oxyhydrogen management system, a hundred-Newton-level hydrogen-oxygen orbit control engine and a Newton-level hydrogen-oxygen attitude control engine. The system generates high-pressure hydrogen and oxygen by electrolyzing water through a static water supply proton exchange membrane electrolytic cell, stores the electrolyzed hydrogen and oxygen through an oxygen-hydrogen management system, and supplies the hydrogen and oxygen to a hundred-Newton-level hydrogen-oxygen rail control engine and a Newton-level hydrogen-oxygen attitude control engine to generate steady-state rail control thrust and pulse attitude control thrust required by a satellite. The water-based propulsion system applied to the high orbit satellite solves the problems that the oxyhydrogen gas is difficult to manage in the space environment for a long time and the oxyhydrogen gas with equivalent mixing ratio is difficult to utilize efficiently, and improves the engineering practicability of the oxyhydrogen propulsion system on a space flight platform.
The system of the invention is explained in detail below with reference to the drawings.
A water-based propulsion system for high earth orbit satellites, as shown in figure 1, comprising: the device comprises a power supply 1, a water tank 5, a static water supply proton exchange membrane electrolytic cell 2, an oxygen-hydrogen management system 3, a hundred-Newton level hydrogen-oxygen rail control engine 4 and a Newton level hydrogen-oxygen attitude control engine 6. The power supply 1 is electrically connected with the static water supply proton exchange membrane electrolytic cell 2 and supplies power to the static water supply proton exchange membrane electrolytic cell 2. The water tank 5 is connected with a water supply interface of the static water supply proton exchange membrane electrolytic cell 2 and provides low-pressure deionized water of about 0.1MPa for the static water supply proton exchange membrane electrolytic cell 2. The static water supply proton exchange membrane electrolytic cell 2 utilizes electric energy to electrolyze deionized water, and can directly electrolyze high-pressure hydrogen and oxygen with over 3MPa and extremely low water content. The hydrogen outlet of the static water supply proton exchange membrane electrolytic cell 2 is connected with the hydrogen inlet of the hydrogen-oxygen management system 3, and the electrolyzed high-pressure hydrogen is input into the hydrogen-oxygen management system 3. An oxygen outlet of the static water supply proton exchange membrane electrolytic cell 2 is connected with an oxygen inlet of the hydrogen and oxygen management system 3, and the electrolyzed high-pressure oxygen is input into the hydrogen and oxygen management system 3. The hydrogen and oxygen management system 3 stores hydrogen and oxygen electrolyzed by the static water supply proton exchange membrane electrolytic cell 2, and supplies the stored high-pressure hydrogen and high-pressure oxygen to the hundred-Newton hydrogen and oxygen orbit control engine 4 and the Newton hydrogen and oxygen attitude control engine 6 after pressure and flow control when the satellite needs, so as to generate thrust required by the satellite. The hundred-Newton grade hydrogen-oxygen rail-controlled engine 4 is a vortex cooling hydrogen-oxygen engine capable of stably igniting and working for a long time. The hydrogen inlet and the oxygen inlet of the engine are respectively connected with the hydrogen outlet and the oxygen outlet of the hydrogen and oxygen management system 3, and the hydrogen and the oxygen supplied by the hydrogen and oxygen management system 3 are utilized to generate steady-state rail control thrust. The engine design mixing ratio is 8: 1, namely, according to the mass ratio of 8: 1, standard volume ratio 2: the ratio of 1 consumes oxyhydrogen gas. The ox-level hydrogen-oxygen attitude control engine 6 is a traditional air film and radiation cooling hydrogen-oxygen engine and can be ignited in a pulse mode to generate attitude control thrust. The hydrogen inlet and the oxygen inlet of the engine are respectively connected with the hydrogen outlet and the oxygen outlet of the hydrogen-oxygen management system 3, and the hydrogen and the oxygen supplied by the hydrogen-oxygen management system 3 are utilized to generate pulse attitude control thrust. The engine mixing ratio is 8: 1, namely, according to the mass ratio of 8: 1, standard volume ratio 2: the ratio of 1 consumes oxyhydrogen gas.
As shown in FIG. 2, the hydrogen and oxygen management system 3 is divided into a hydrogen path and an oxygen path.
And a hydrogen inlet of the hydrogen gas path is connected with a parallel structure consisting of a hydrogen direct filling module 7 and a hydrogen pump pressurizing module 8. The downstream of the parallel connection structure formed by the hydrogen direct filling module 7 and the hydrogen pump pressurizing module 8 is connected with the inlet of a high-pressure hydrogen cylinder 9. The outlet of the high-pressure hydrogen cylinder 9 is connected with the inlet of the hydrogen path pressure flow control module 10. The outlet of the hydrogen circuit pressure flow control module 10 is the hydrogen inlet of the hydrogen and oxygen management system. During satellite conventional in-orbit operation, water-based propulsion systems are primarily used to provide position-preserving thrust on a periodic basis, with less oxyhydrogen gas required for the propulsion system. Therefore, during the normal operation of the satellite, the hydrogen inlet of the hydrogen and oxygen management system 3 is directly communicated with the high-pressure hydrogen cylinder 9 through the hydrogen direct filling module 7, and the high-pressure hydrogen electrolyzed by the static water supply proton exchange membrane electrolytic cell 2 directly enters the high-pressure hydrogen cylinder 9 for storage. At this time, the highest pressure of the hydrogen stored in the high-pressure hydrogen cylinder 9 in one period of the water-based propulsion system does not exceed the pressure of the hydrogen electrolyzed by the static water supply proton exchange membrane electrolytic cell 2, and the stored hydrogen quantity is relatively small. During a short time of satellite orbital transfer or orbital maneuver, the water-based propulsion system needs to provide as much oxyhydrogen gas as possible at a time to provide steady thrust for satellite orbital transfer that lasts longer and is more propulsive. At this time, a hydrogen inlet of the hydrogen and oxygen management system 3 is communicated with the high-pressure hydrogen cylinder 9 through the hydrogen pump pressurizing module 8, and the high-pressure hydrogen electrolyzed by the static water supply proton exchange membrane electrolytic cell 2 enters the high-pressure hydrogen cylinder 9 for storage after being further pressurized by the hydrogen pump pressurizing module 8. At this time, the highest pressure of hydrogen stored in the high-pressure hydrogen cylinder 9 in one period of the water-based propulsion system is the highest pressure which can be provided by the hydrogen pump pressurizing module 8 and is far higher than the pressure of hydrogen electrolyzed by the static water supply proton exchange membrane electrolytic cell 2, and the amount of stored hydrogen is greatly increased.
And an oxygen inlet of the oxygen gas path is connected with a parallel structure consisting of an oxygen direct filling module 12 and an oxygen pump pressurizing module 11. The downstream of the parallel connection structure formed by the oxygen direct filling module 12 and the oxygen pump pressurizing module 11 is connected with the inlet of a high-pressure oxygen cylinder 13. The outlet of the high-pressure oxygen bottle 13 is connected with the inlet of the oxygen path pressure flow control module 14. The outlet of the oxygen path pressure flow control module 14 is the hydrogen inlet of the hydrogen and oxygen management system. During satellite conventional in-orbit operation, water-based propulsion systems are primarily used to provide position-preserving thrust on a periodic basis, with less oxyhydrogen gas required for the propulsion system. Therefore, during the normal operation of the satellite, the oxygen inlet of the hydrogen and oxygen management system 3 is directly communicated with the high-pressure oxygen cylinder 13 through the oxygen direct filling module 12, and the high-pressure oxygen electrolyzed by the static water supply proton exchange membrane electrolytic cell 2 directly enters the high-pressure oxygen cylinder 13 for storage. At this time, the highest pressure of oxygen stored in the high-pressure oxygen cylinder 13 in one period of the water-based propulsion system does not exceed the pressure of hydrogen electrolyzed by the static water supply proton exchange membrane electrolytic cell 2, and the stored oxygen amount is relatively small. During a short time of satellite orbital transfer or orbital maneuver, the water-based propulsion system needs to provide as much oxyhydrogen gas as possible at a time to provide steady thrust for satellite orbital transfer that lasts longer and is more propulsive. At this time, an oxygen inlet of the oxyhydrogen management system 3 is communicated with the high-pressure oxygen cylinder 13 through the oxygen pump pressurizing module 11, and the high-pressure oxygen electrolyzed by the static water supply proton exchange membrane electrolytic cell 2 enters the high-pressure oxygen cylinder 13 for storage after being further pressurized by the oxygen pump pressurizing module 11. At this time, the highest pressure of oxygen stored in the hyperbaric oxygen cylinder 13 in one period of the water-based propulsion system is the highest pressure which can be provided by the oxygen pump pressurizing module 11 and is far higher than the pressure of oxygen electrolyzed by the static water supply proton exchange membrane electrolytic cell 2, and the amount of stored oxygen is greatly increased.
In the hydrogen and oxygen management system 3, the volume ratio of the high-pressure hydrogen cylinder 9 to the high-pressure oxygen cylinder 13 is designed to be 2: 1. the mass ratio of hydrogen to oxygen electrolyzed by the static water supply proton exchange membrane electrolytic cell 2 is 8: 1, volume ratio under standard state is 2: 1, therefore, volume ratio 2: the high-pressure hydrogen cylinder 9 and the high-pressure oxygen cylinder 13 of the device 1 are matched with the amount of oxyhydrogen gas electrolyzed by the upstream static water supply proton exchange membrane electrolytic cell 2. The mass mixing ratio of the hundred-Newton grade hydrogen-oxygen orbital control engine 4 and the bovine grade hydrogen-oxygen attitude control engine 6 which are configured by the water-based propulsion system applied to the high orbit satellite is 8: 1, ensuring that the whole system is also mixed according to the volume ratio of 2: 1 consumption of oxyhydrogen gas. Therefore, the volume ratio 2 of the high-pressure hydrogen cylinder 9 to the high-pressure oxygen cylinder 13: the design of 1 can ensure that the gas production pressure and the storage pressure of the hydrogen gas circuit and the oxygen gas circuit are always kept basically consistent in the using process of the system.
In the hydrogen and oxygen management system, a hydrogen path pressure and flow control module 10 is used for adjusting the high-pressure hydrogen stored in a high-pressure hydrogen cylinder 9 to proper pressure and flow according to the requirements of a hundred-newton-level hydrogen and oxygen rail control engine 4 and a newton-level hydrogen and oxygen attitude control engine 6. The oxygen path pressure flow control module 14 is used for adjusting the high-pressure oxygen stored in the high-pressure oxygen cylinder 13 to proper pressure and flow according to the requirements of the hundred-newton grade hydrogen oxygen rail control engine 4 and the newton grade hydrogen oxygen attitude control engine 6.
The above-described embodiments are merely preferred embodiments of the present invention, and general changes and substitutions by those skilled in the art within the technical scope of the present invention are included in the protection scope of the present invention.
Claims (5)
1. A water-based propulsion system for use with an elevated earth satellite, comprising: the device comprises a power supply (1), a water tank (5), a static water supply proton exchange membrane electrolytic cell (2), an oxyhydrogen management system (3), a hundred-Newton-level hydrogen-oxygen rail-controlled engine (4) and a Newton-level hydrogen-oxygen attitude-controlled engine (6); wherein the content of the first and second substances,
the power supply (1) and the water tank (5) are respectively connected with the static water supply proton exchange membrane electrolytic cell (2), a hydrogen circuit and an oxygen circuit of the static water supply proton exchange membrane electrolytic cell (2) are respectively connected with a hydrogen inlet and an oxygen inlet of the hydrogen and oxygen management system (3), a hydrogen circuit outlet and an oxygen circuit outlet of the hydrogen and oxygen management system (3) are respectively connected with a hydrogen inlet and an oxygen inlet of the hundred-Newton hydrogen and oxygen rail-controlled engine (4), and a hydrogen circuit outlet and an oxygen circuit outlet of the hydrogen and oxygen management system (3) are respectively connected with a hydrogen inlet and an oxygen inlet of the bovine hydrogen and oxygen attitude-controlled engine (6);
the power supply (1) supplies power to the static water supply proton exchange membrane electrolytic cell (2);
the water tank (5) supplies low-pressure deionized water for the static water supply proton exchange membrane electrolytic cell (2);
the static water supply proton exchange membrane electrolytic cell (2) directly electrolyzes low-pressure deionized water into high-pressure hydrogen and high-pressure oxygen by using electric energy and supplies the high-pressure hydrogen and the high-pressure oxygen to the hydrogen and oxygen management system (3) respectively;
the hydrogen and oxygen management system (3) stores high-pressure hydrogen and high-pressure oxygen into a high-pressure gas cylinder, conditions the high-pressure hydrogen into preset pressure and preset flow rate, and then respectively supplies the preset pressure and the preset flow rate to the hundred-Newton grade hydrogen and oxygen rail control engine (4) and the Newton grade hydrogen and oxygen attitude control engine (6), and conditions the high-pressure oxygen into preset pressure and preset flow rate, and then respectively supplies the preset pressure and the preset flow rate to the hundred-Newton grade hydrogen and oxygen rail control engine (4) and the Newton grade hydrogen and oxygen attitude control engine (6);
the hundred-Newton grade hydrogen-oxygen rail control engine (4) generates steady rail control thrust according to the conditioned high-pressure hydrogen and the conditioned high-pressure oxygen;
the cattle-grade hydrogen oxygen attitude control engine (6) generates pulse attitude control thrust according to the conditioned high-pressure hydrogen and the conditioned high-pressure oxygen;
the hydrogen and oxygen management system (3) comprises a hydrogen direct filling module (7), a hydrogen pump pressurizing module (8), a high-pressure hydrogen cylinder (9), a hydrogen path pressure and flow control module (10), an oxygen direct filling module (12), an oxygen pump pressurizing module (11), a high-pressure oxygen cylinder (13) and an oxygen path pressure and flow control module (14); wherein the content of the first and second substances,
a hydrogen circuit of the static water supply proton exchange membrane electrolytic cell (2) is divided into two paths which are respectively connected with a hydrogen direct filling module (7) and a hydrogen pump pressurizing module (8);
the hydrogen direct filling module (7) is connected with the hydrogen pump pressurizing module (8) in parallel and then is connected with the high-pressure hydrogen cylinder (9);
the high-pressure hydrogen cylinder (9) is connected with the hydrogen path pressure flow control module (10);
an oxygen circuit of the static water supply proton exchange membrane electrolytic cell (2) is divided into two paths and is respectively connected with an oxygen direct filling module (12) and an oxygen pump pressurizing module (11);
the oxygen direct filling module (12) is connected with the oxygen pump pressurizing module (11) in parallel and then is connected with the high-pressure oxygen cylinder (13);
the high-pressure oxygen bottle (13) is connected with the oxygen path pressure flow control module (14);
the static water supply proton exchange membrane electrolytic cell (2) receives 0.1MPa low-pressure deionized water provided by the water tank (5), and the electric energy of the power supply (1) directly electrolyzes high-pressure hydrogen and high-pressure oxygen with the pressure of more than 3 MPa;
the hundred-Newton grade hydrogen-oxygen rail-controlled engine (4) has a mixing ratio of 8: 1, the vortex cooling gas hydrogen-oxygen rail control engine takes steady-state ignition as a main working form;
the cattle-grade hydrogen oxygen attitude control engine (6) has a mixing ratio of 8: 1, the air film and radiation cooling air hydrogen oxygen attitude control engine takes pulse ignition as a main working mode.
2. The water-based propulsion system for high earth orbit satellites as claimed in claim 1, wherein: the static water supply proton exchange membrane electrolytic cell (2) electrolyzes high-pressure hydrogen, and when the storage pressure of the high-pressure hydrogen bottle (9) is required to be not more than the highest pressure hydrogen which can be electrolyzed by the static water supply proton exchange membrane electrolytic cell (2), the hydrogen is directly filled into the high-pressure hydrogen bottle (9) through a hydrogen direct filling module (7); when the high-pressure hydrogen cylinder (9) is required to store hydrogen with the pressure exceeding the highest pressure capable of being electrolyzed by the static water supply proton exchange membrane electrolytic cell (2), a hydrogen pump pressurization module (8) is selected to be filled into the high-pressure hydrogen cylinder (9) after further pressurization.
3. The water-based propulsion system for high earth orbit satellites as claimed in claim 1, wherein: the static water supply proton exchange membrane electrolytic cell (2) electrolyzes high-pressure oxygen, and when the storage pressure of the high-pressure oxygen bottle (13) is required to be not more than the highest pressure oxygen which can be electrolyzed by the static water supply proton exchange membrane electrolytic cell (2), the high-pressure oxygen bottle (13) is directly filled with oxygen through an oxygen direct filling module (12); when the storage pressure of the high-pressure oxygen cylinder (13) is required to exceed the highest pressure of the static water supply proton exchange membrane electrolytic cell (2) capable of electrolyzing oxygen, the high-pressure oxygen cylinder (13) is filled with the oxygen after further pressurization by the oxygen pump pressurization module (11).
4. The water-based propulsion system for high earth orbit satellites as claimed in claim 1, wherein: the volume ratio of the high-pressure hydrogen cylinder (9) to the high-pressure oxygen cylinder (13) is 2: 1.
5. a water-based propulsion method for high earth orbit satellites, comprising the steps of:
a power supply (1) is used for supplying power to a static water supply proton exchange membrane electrolytic cell (2);
a water tank (5) is used for supplying low-pressure deionized water for the static water supply proton exchange membrane electrolytic cell (2);
the static water supply proton exchange membrane electrolytic cell (2) directly electrolyzes low-pressure deionized water into high-pressure hydrogen and high-pressure oxygen by using electric energy and supplies the high-pressure hydrogen and the high-pressure oxygen to the hydrogen and oxygen management system (3) respectively;
the hydrogen and oxygen management system (3) stores high-pressure hydrogen and high-pressure oxygen into a high-pressure gas cylinder, conditions the high-pressure hydrogen into preset pressure and preset flow rate, and then respectively supplies the preset pressure and the preset flow rate to the hundred-Newton grade hydrogen and oxygen rail control engine (4) and the Newton grade hydrogen and oxygen attitude control engine (6), and conditions the high-pressure oxygen into preset pressure and preset flow rate, and then respectively supplies the preset pressure and the preset flow rate to the hundred-Newton grade hydrogen and oxygen rail control engine (4) and the Newton grade hydrogen and oxygen attitude control engine (6);
the hundred-Newton grade hydrogen-oxygen rail control engine (4) generates steady rail control thrust according to the conditioned high-pressure hydrogen and the conditioned high-pressure oxygen;
the cattle-grade hydrogen oxygen attitude control engine (6) generates pulse attitude control thrust according to the conditioned high-pressure hydrogen and the conditioned high-pressure oxygen;
the hydrogen and oxygen management system (3) comprises a hydrogen direct filling module (7), a hydrogen pump pressurizing module (8), a high-pressure hydrogen cylinder (9), a hydrogen path pressure and flow control module (10), an oxygen direct filling module (12), an oxygen pump pressurizing module (11), a high-pressure oxygen cylinder (13) and an oxygen path pressure and flow control module (14); wherein the content of the first and second substances,
a hydrogen circuit of the static water supply proton exchange membrane electrolytic cell (2) is divided into two paths which are respectively connected with a hydrogen direct filling module (7) and a hydrogen pump pressurizing module (8);
the hydrogen direct filling module (7) is connected with the hydrogen pump pressurizing module (8) in parallel and then is connected with the high-pressure hydrogen cylinder (9);
the high-pressure hydrogen cylinder (9) is connected with the hydrogen path pressure flow control module (10);
an oxygen circuit of the static water supply proton exchange membrane electrolytic cell (2) is divided into two paths and is respectively connected with an oxygen direct filling module (12) and an oxygen pump pressurizing module (11);
the oxygen direct filling module (12) is connected with the oxygen pump pressurizing module (11) in parallel and then is connected with the high-pressure oxygen cylinder (13);
the high-pressure oxygen bottle (13) is connected with the oxygen path pressure flow control module (14);
the hundred-Newton grade hydrogen-oxygen rail-controlled engine (4) has a mixing ratio of 8: 1, the vortex cooling gas hydrogen-oxygen rail control engine takes steady-state ignition as a main working form;
the cattle-grade hydrogen oxygen attitude control engine (6) has a mixing ratio of 8: 1, the air film and radiation cooling air hydrogen oxygen attitude control engine takes pulse ignition as a main working mode.
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