CN116696606A - Exhaust device of propellant storage tank of carrier rocket - Google Patents
Exhaust device of propellant storage tank of carrier rocket Download PDFInfo
- Publication number
- CN116696606A CN116696606A CN202310979788.4A CN202310979788A CN116696606A CN 116696606 A CN116696606 A CN 116696606A CN 202310979788 A CN202310979788 A CN 202310979788A CN 116696606 A CN116696606 A CN 116696606A
- Authority
- CN
- China
- Prior art keywords
- gas
- propellant
- manifold
- tank
- fixedly connected
- 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.)
- Granted
Links
- 239000003380 propellant Substances 0.000 title claims abstract description 47
- 239000007788 liquid Substances 0.000 claims abstract description 39
- 238000000926 separation method Methods 0.000 claims abstract description 15
- 239000003463 adsorbent Substances 0.000 claims description 3
- 238000013022 venting Methods 0.000 claims 7
- 238000007872 degassing Methods 0.000 claims 1
- 238000000034 method Methods 0.000 description 4
- 230000002745 absorbent Effects 0.000 description 3
- 239000002250 absorbent Substances 0.000 description 3
- 230000006978 adaptation Effects 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 239000012071 phase Substances 0.000 description 2
- RZVHIXYEVGDQDX-UHFFFAOYSA-N 9,10-anthraquinone Chemical compound C1=CC=C2C(=O)C3=CC=CC=C3C(=O)C2=C1 RZVHIXYEVGDQDX-UHFFFAOYSA-N 0.000 description 1
- 235000015842 Hesperis Nutrition 0.000 description 1
- 235000012633 Iberis amara Nutrition 0.000 description 1
- 230000000712 assembly Effects 0.000 description 1
- 238000000429 assembly Methods 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 238000007599 discharging Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 238000002309 gasification Methods 0.000 description 1
- 238000010438 heat treatment Methods 0.000 description 1
- 239000007791 liquid phase Substances 0.000 description 1
- 230000005855 radiation Effects 0.000 description 1
- 238000009423 ventilation Methods 0.000 description 1
- 239000002699 waste material Substances 0.000 description 1
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 description 1
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K9/00—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
- F02K9/42—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof using liquid or gaseous propellants
- F02K9/60—Constructional parts; Details not otherwise provided for
Abstract
The invention provides an exhaust device of a propellant storage tank of a carrier rocket, which comprises: a gas collection manifold; at least 4 gas-taking clam shells fixedly connected with the gas-collecting manifold are fixedly connected with an exhaust flange of the gas-collecting manifold; and the gas in the propellant storage tank enters the gas collecting manifold through the gas taking clam shell to carry out gas-liquid separation on the gas, and the separated gas is discharged out of the propellant storage tank through the exhaust flange. According to the scheme, the liquid propellant can be effectively separated from the exhaust gas, and the influence of liquid-clamping exhaust on the flying attitude of the carrier rocket is prevented.
Description
Technical Field
The invention relates to the technical field of carrier rockets, in particular to an exhaust device of a propellant storage tank of a carrier rocket.
Background
In the flying process of the liquid carrier rocket, the propellant in the storage tank can be continuously evaporated under the physical heating actions of solar radiation, pneumatic heat and the like, and frequent exhaust operation is required to be carried out on the storage tank in order to avoid the structural damage of the tank body or the change of the supply parameters caused by excessive pressure. On the other hand, the rocket is often faced with complex load environments such as weightlessness, vibration and the like due to flight control requirements in the flight process, at the moment, the gas phase and the liquid phase in the storage tank are highly mixed, if direct exhaust is carried out, a large amount of liquid propellant is discharged, so that the propellant waste is caused, the normal track entering of the rocket is influenced, the phenomenon of rapid gasification in the liquid propellant discharging process can occur, the rocket posture is disturbed, and the posture control difficulty is improved.
Disclosure of Invention
The invention provides an exhaust device of a propellant storage tank of a carrier rocket, which aims to solve the problem that the normal flight attitude of the rocket is influenced by gas-liquid two-phase mixing exhaust in the propellant storage tank of the carrier rocket.
In order to solve the technical problems, the technical scheme of the invention is as follows:
an exhaust device for a propellant tank of a launch vehicle, comprising:
a gas collection manifold;
at least 4 gas-taking clam shells fixedly connected with the gas collecting manifold;
an exhaust flange fixedly connected with the gas collecting manifold;
and the gas in the propellant storage tank enters the gas collecting manifold through the gas taking clam shell to carry out gas-liquid separation on the gas, and the separated gas is discharged out of the propellant storage tank through the exhaust flange.
Optionally, at least 4 connecting pipelines are arranged on the gas collecting manifold, and the at least 4 connecting pipelines are communicated with the gas collecting manifold;
wherein, the first connecting pipeline is fixedly connected with the end part of the gas collecting manifold;
the second connecting pipeline, the third connecting pipeline and the fourth connecting pipeline are vertically fixed on the side wall of the gas collecting manifold.
Optionally, the gas collecting manifold has an inner diameter near one end of the first connecting pipe that is smaller than an inner diameter near one end of the exhaust method.
Optionally, an included angle between the second connecting pipeline, the third connecting pipeline and the fourth connecting pipeline is 120 degrees.
Optionally, the air taking clam shell comprises an upper shell and a lower shell, and a circular seam inlet is formed between the upper shell and the lower shell.
Optionally, the at least 4 gas-taking clam shells are fixedly connected with the gas collecting manifold through the at least 4 connecting pipelines;
wherein the first air taking clam shell is fixedly connected with the first connecting pipeline;
the second gas-taking clam shell is fixedly connected with the second connecting pipeline;
the third air taking clam shell is fixedly connected with the third connecting pipeline;
the fourth air taking clam shell is fixedly connected with the fourth connecting pipeline.
Optionally, filter screen assemblies are arranged inside the at least 4 connecting pipelines.
Optionally, swirl vanes are arranged in the gas collecting manifold.
Optionally, a groove is formed in one end, close to the exhaust flange, of the gas collection manifold.
Optionally, a leakage absorbent is arranged in the groove.
The scheme of the invention at least comprises the following beneficial effects:
the scheme of the invention comprises the following steps: a gas collection manifold; at least 4 gas-taking clam shells fixedly connected with the gas-collecting manifold are fixedly connected with an exhaust flange of the gas-collecting manifold; and the gas in the propellant storage tank enters the gas collecting manifold through the gas taking clam shell to carry out gas-liquid separation on the gas, and the separated gas is discharged out of the propellant storage tank through the exhaust flange. According to the scheme, the liquid propellant can be effectively separated from the exhaust gas, excessive loss of the propellant is avoided, reliable exhaust of the low-temperature propellant storage tank of the carrier rocket under a complex overload condition can be realized, and the influence of liquid-clamping exhaust on the flight attitude of the carrier rocket is prevented.
Drawings
FIG. 1 is a schematic diagram of an exhaust apparatus for a propellant tank of a launch vehicle according to an embodiment of the present invention;
FIG. 2 is a longitudinal cross-sectional view of an exhaust apparatus provided by an embodiment of the present invention;
FIG. 3 is a cross-sectional view of an exhaust apparatus provided by an embodiment of the present invention;
fig. 4 is a schematic structural view of a gas-taking clam shell according to an embodiment of the present invention.
Reference numerals illustrate:
1. a gas collection manifold; 11. a first connecting pipe; 12. a second connecting pipe; 13. a third connecting pipe; 14. a fourth connecting pipe; 21. an upper housing; 22. a lower housing; 23. a circular seam inlet; 211. a first air taking clam shell; 212. a second air-taking clam shell; 213. thirdly, taking air clam shells; 214. fourth, taking a gas clam shell; 3. an exhaust flange; 4. a screen assembly; 5. swirl vanes; 6. and (3) a leakage adsorbent.
Detailed Description
Exemplary embodiments of the present invention will be described in more detail below with reference to the accompanying drawings. While exemplary embodiments of the present invention are shown in the drawings, it should be understood that the present invention 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 invention to those skilled in the art.
As shown in fig. 1 to 3, an embodiment of the present invention proposes an exhaust device of a propellant tank of a carrier rocket, comprising:
a gas collecting manifold 1;
at least 4 gas-taking clam shells fixedly connected with the gas collecting manifold 1;
an exhaust flange 3 fixedly connected with the gas collecting manifold 1;
the gas in the propellant storage tank enters the gas collecting manifold 1 through the gas taking clam shell to carry out gas-liquid separation on the gas, and the separated gas is discharged out of the propellant storage tank through the exhaust flange 3.
In this embodiment, when the tank needs to be exhausted, the gas in the propellant tank enters the device from the annular slot inlets 23 of the 4 gas-taking clam shells, the droplets mixed in the gas are separated by the filter screen assembly 4 and then enter the gas collecting manifold 1, then the droplets are separated from the gas flow by the centrifugal action of the swirl vanes 5, and the gas is discharged from the tank from the exhaust flange 3.
The device utilizes the filter screen water-proof ventilation and gas-liquid centrifugal separation principle, can effectively separate the liquid propellant from the exhaust gas, avoids excessive loss of the propellant, can realize reliable exhaust of the low-temperature propellant storage tank of the carrier rocket under the complex overload condition, and prevents the influence of liquid-clamping exhaust on the flight attitude of the carrier rocket.
In an alternative embodiment of the present invention, at least 4 connecting pipes are provided on the gas collecting manifold 1, and the at least 4 connecting pipes are communicated with the gas collecting manifold 1;
wherein, the first connecting pipeline 11 is fixedly connected with the end part of the gas collecting manifold 1;
the second connecting pipe 12, the third connecting pipe 13 and the fourth connecting pipe 14 are vertically fixed on the side wall of the gas collecting manifold 1.
In this embodiment, the first connecting pipe 11 is installed at the top of the gas collecting manifold 1, and the second connecting pipe 12, the third connecting pipe 13, and the fourth connecting pipe 14 are installed tangentially along the cross section of the gas collecting manifold 1.
After entering the gas collecting manifold 1 from the top and tangential directions, the air flow forms axial air flow and tangential air flow, the two air flows are combined to form a low-speed rotational flow, and part of liquid drops are thrown onto the inner wall of the gas collecting manifold 1, so that the liquid drops flow down along the inner wall, and the primary separation of gas and liquid is realized.
In an alternative embodiment of the present invention, the inner diameter of the gas collecting manifold 1 near the end of the first connecting pipe 11 is smaller than the inner diameter near the end of the exhaust flange 3.
In this embodiment, the structure of the gas collecting manifold 1 is designed such that the radius of the upper portion is smaller than that of the lower portion, so that the pressure in the gas collecting manifold 1 can be reduced, and insufficient gas-liquid separation caused by too high airflow velocity under high pressure is avoided.
In an alternative embodiment of the present invention, as shown in fig. 4, the gas-taking clam shell includes an upper shell 21 and a lower shell 22, and a circular seam inlet 23 is formed between the upper shell 21 and the lower shell 22.
In this embodiment, a clamshell type gas-taking structure is adopted, the gas-taking clamshell is composed of two spherical shells under mountain, a gap is reserved between the upper shell 21 and the lower shell 22 to form the circular seam inlet 23, and a large volume of liquid clusters can be effectively prevented from entering through the circular seam inlet 23 to form a first measure of gas-liquid separation.
As shown in fig. 3, in an alternative embodiment of the present invention, the at least 4 gas-taking clam shells are fixedly connected with the gas collecting manifold 1 through the at least 4 connecting pipes;
wherein, the first air intake clam shell 211 is fixedly connected with the first connecting pipeline 11;
the second gas-taking clam shell 212 is fixedly connected with the second connecting pipeline 12;
the third air-taking clam shell 213 is fixedly connected with the third connecting pipeline 13;
the fourth gas-taking clam shell 214 is fixedly connected with the fourth connecting pipe 14.
In an alternative embodiment of the present invention, the included angle between the second connecting pipe 12, the third connecting pipe 13 and the fourth connecting pipe 14 is 120 degrees.
In the above embodiment, the first connecting pipe 11 is disposed at the top of the gas collecting manifold 1, and the second connecting pipe 12, the third connecting pipe 13, and the fourth connecting pipe 14 are vertically disposed in the tangential direction of the gas collecting manifold 1;
the included angle between the second connecting pipeline 12, the third connecting pipeline 13 and the fourth connecting pipeline 14 is 120 degrees, so that the tangential direction air intake is ensured to be uniform, the cyclone inside the air collecting manifold 1 is stable, and the gas-liquid rotation and separation caused by the influence of turbulent flow are avoided, and the damage to an exhaust device is avoided.
In an alternative embodiment of the invention, the at least 4 connecting pipes are each provided with a screen assembly 4 inside.
In this embodiment, the filter screen assembly 4 is installed at a connection port of the connection pipe and the air taking clam shell;
the filter screen assembly 4 is used as an exhaust device and is used as a second measure of gas-liquid separation, the resistance of liquid flowing through the filter screen is far greater than that of gas by utilizing the surface tension effect of the liquid, and the liquid can be blocked by the filter screen to separate liquid drops mixed in the gas again.
In an alternative embodiment of the present invention, as shown in fig. 2, the gas collecting manifold 1 is provided with swirl vanes 5 inside.
In this embodiment, the swirl blades 5 are disposed inside the gas collecting manifold 1, parallel to the inner diameter direction of the gas collecting manifold 1, and at a height lower than the positions of the second connecting pipe 12, the third connecting pipe 13, and the fourth connecting pipe 14;
the low-speed rotational flow passes through a rotational flow channel formed by the rotational flow blades 5, so that the rotational flow speed is accelerated, the rotational flow is further enhanced, and the low-speed rotational flow is converted into high-speed rotational flow;
the high-speed rotational flow generates larger centrifugal force, and the mass of liquid drops is far greater than that of gas, so that the liquid drops are gathered on the inner wall of the gas collecting manifold 1, and then the liquid drops are separated from the gas flow, so that a third measure of gas-liquid separation is formed.
In an alternative embodiment of the present invention, as shown in fig. 2, a groove is disposed in the gas collecting manifold 1 near one end of the exhaust flange 3.
In an alternative embodiment of the invention, a leakage absorbent 6 is arranged in the groove.
In the above embodiment, the leakage absorbent 6 is disposed in a groove below the cyclone blade 5 and is attached to the inner wall of the gas collecting manifold 1.
When the separated liquid drops flow down along the inner wall of the gas collecting manifold 1, the liquid drops are adsorbed after contacting with the leaked liquid adsorbent 6, so that the gas and the liquid are completely separated, and the separated liquid is ensured not to be mixed with the gas again.
In an alternative embodiment of the present invention, the center of the exhaust flange 3 is provided with an exhaust port, and the pure gas without liquid is discharged from the propellant storage tank through the exhaust port after gas-liquid separation, so as to realize high-purity exhaust of the propellant storage tank.
The exhaust device of the propellant storage tank of the carrier rocket provided by the embodiment of the invention can realize reliable exhaust of the propellant storage tank of the carrier rocket under the complex overload condition. The device utilizes filter screen water proof ventilative and gas-liquid centrifugal separation principle, can be effectual with liquid propellant from the exhaust gas separation, avoid the excessive loss of propellant, in addition, the device can prevent the influence of double-deck liquid exhaust to carrier rocket flight gesture.
While the foregoing is directed to the preferred embodiments of the present invention, it will be appreciated by those skilled in the art that various modifications and adaptations can be made without departing from the principles of the present invention, and such modifications and adaptations are intended to be comprehended within the scope of the present invention.
Claims (10)
1. An exhaust apparatus for a propellant tank of a launch vehicle, comprising:
a gas collecting manifold (1);
at least 4 gas-taking clam shells fixedly connected with the gas collecting manifold (1);
an exhaust flange (3) fixedly connected with the gas collecting manifold (1);
the gas in the propellant storage tank enters the gas collecting manifold (1) through the gas taking clam shell, gas-liquid separation is carried out on the gas, and the separated gas is discharged out of the propellant storage tank through the exhaust flange (3).
2. A device for exhausting a tank of propellant for a launch vehicle according to claim 1, wherein said manifold (1) is provided with at least 4 connecting ducts, said at least 4 connecting ducts being in communication with said manifold (1);
wherein, the first connecting pipeline (11) is fixedly connected with the end part of the gas collecting manifold (1);
the second connecting pipeline (12), the third connecting pipeline (13) and the fourth connecting pipeline (14) are vertically fixed on the side wall of the gas collecting manifold (1).
3. A device for venting a tank of a propellant for a launch vehicle according to claim 2, wherein the internal diameter of the manifold (1) near the end of the first connecting duct (11) is smaller than the internal diameter near the end of the venting flange (3).
4. A device for venting a tank of a propellant for a launch vehicle according to claim 2, wherein the angle between said second connecting duct (12), said third connecting duct (13) and said fourth connecting duct (14) is 120 degrees.
5. A device for venting a propellant tank of a launch vehicle according to claim 1, wherein said degassing clam shell comprises an upper shell (21) and a lower shell (22), said upper shell (21) and said lower shell (22) defining a circular seam inlet (23) therebetween.
6. A device for venting a tank of a propellant for a launch vehicle according to claim 2, wherein said at least 4 gas-extracting clam shells are fixedly connected to said gas collection manifold (1) by means of said at least 4 connecting pipes;
wherein the first air taking clam shell (211) is fixedly connected with the first connecting pipeline (11);
the second air taking clam shell (212) is fixedly connected with the second connecting pipeline (12);
the third air taking clam shell (213) is fixedly connected with the third connecting pipeline (13);
the fourth air taking clam shell (214) is fixedly connected with the fourth connecting pipeline (14).
7. A device for venting a tank of a propellant for a launch vehicle according to claim 2, wherein said at least 4 connecting ducts are internally provided with a screen assembly (4).
8. A device for exhausting a tank of propellant for a launch vehicle according to claim 1, wherein said manifold (1) is internally provided with swirl vanes (5).
9. A device for exhausting a tank of propellant for a vehicle according to claim 1, characterized in that the manifold (1) is internally provided with a recess near one end of the exhaust flange (3).
10. A device for venting a propellant tank of a launch vehicle according to claim 9, wherein a liquid-leaking adsorbent (6) is provided in the recess.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202310979788.4A CN116696606B (en) | 2023-08-07 | 2023-08-07 | Exhaust device of propellant storage tank of carrier rocket |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202310979788.4A CN116696606B (en) | 2023-08-07 | 2023-08-07 | Exhaust device of propellant storage tank of carrier rocket |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN116696606A true CN116696606A (en) | 2023-09-05 |
| CN116696606B CN116696606B (en) | 2023-10-27 |
Family
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202310979788.4A Active CN116696606B (en) | 2023-08-07 | 2023-08-07 | Exhaust device of propellant storage tank of carrier rocket |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN116696606B (en) |
Citations (16)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3425234A (en) * | 1966-01-28 | 1969-02-04 | Georges Jean Henri Trepaud | Tanks for liquefied gases |
| GB1568275A (en) * | 1976-12-06 | 1980-05-29 | Hughes Aircraft Co | Liquid vapour separator |
| JPH034907A (en) * | 1989-05-30 | 1991-01-10 | Mitsubishi Oil Co Ltd | System for removing gases in liquids |
| US6073450A (en) * | 1999-03-04 | 2000-06-13 | Boeing North American | Combined diffuser and recirculation manifold in a propellant tank |
| CN201553157U (en) * | 2009-09-28 | 2010-08-18 | 北京控制工程研究所 | Storage tank plate-type propellant management device |
| KR101409939B1 (en) * | 2013-01-16 | 2014-06-20 | 한국항공우주연구원 | Ultra low temperature liquid propellant collecting apparatus for reigniting propulsion engine of rocket |
| CN104089177A (en) * | 2014-06-24 | 2014-10-08 | 北京控制工程研究所 | Exhaust passage for bubble trap of surface tension tank |
| CN105035363A (en) * | 2015-08-25 | 2015-11-11 | 中国人民解放军国防科学技术大学 | Storage tank exhaust device and model selection method of storage tank exhaust device |
| CN105889145A (en) * | 2014-12-11 | 2016-08-24 | 西安航天发动机厂 | Liquid accumulator with micro-pressure response function |
| CN107327355A (en) * | 2017-07-28 | 2017-11-07 | 北京宇航系统工程研究所 | A kind of spacecraft propulsion agent management method |
| CN108704392A (en) * | 2018-05-29 | 2018-10-26 | 中国人民解放军国防科技大学 | Centrifugal force inertia cascade gas-liquid separator |
| CN108883424A (en) * | 2016-04-06 | 2018-11-23 | 东京滤器株式会社 | Oil eliminator |
| CN110052109A (en) * | 2019-05-15 | 2019-07-26 | 北京控制工程研究所 | A kind of gas-liquid separation device for satellite booster agent tank |
| JP2019132142A (en) * | 2018-01-29 | 2019-08-08 | 国立大学法人室蘭工業大学 | Pressurization gas supply device and propulsion device for satellite using the same |
| CN114275193A (en) * | 2021-11-12 | 2022-04-05 | 西安交通大学 | Net curtain type on-orbit filling system and method for low-temperature propellant and low-temperature storage tank |
| CN218266078U (en) * | 2022-10-20 | 2023-01-10 | 重庆鑫源动力制造有限公司 | Exhaust manifold assembly |
-
2023
- 2023-08-07 CN CN202310979788.4A patent/CN116696606B/en active Active
Patent Citations (16)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3425234A (en) * | 1966-01-28 | 1969-02-04 | Georges Jean Henri Trepaud | Tanks for liquefied gases |
| GB1568275A (en) * | 1976-12-06 | 1980-05-29 | Hughes Aircraft Co | Liquid vapour separator |
| JPH034907A (en) * | 1989-05-30 | 1991-01-10 | Mitsubishi Oil Co Ltd | System for removing gases in liquids |
| US6073450A (en) * | 1999-03-04 | 2000-06-13 | Boeing North American | Combined diffuser and recirculation manifold in a propellant tank |
| CN201553157U (en) * | 2009-09-28 | 2010-08-18 | 北京控制工程研究所 | Storage tank plate-type propellant management device |
| KR101409939B1 (en) * | 2013-01-16 | 2014-06-20 | 한국항공우주연구원 | Ultra low temperature liquid propellant collecting apparatus for reigniting propulsion engine of rocket |
| CN104089177A (en) * | 2014-06-24 | 2014-10-08 | 北京控制工程研究所 | Exhaust passage for bubble trap of surface tension tank |
| CN105889145A (en) * | 2014-12-11 | 2016-08-24 | 西安航天发动机厂 | Liquid accumulator with micro-pressure response function |
| CN105035363A (en) * | 2015-08-25 | 2015-11-11 | 中国人民解放军国防科学技术大学 | Storage tank exhaust device and model selection method of storage tank exhaust device |
| CN108883424A (en) * | 2016-04-06 | 2018-11-23 | 东京滤器株式会社 | Oil eliminator |
| CN107327355A (en) * | 2017-07-28 | 2017-11-07 | 北京宇航系统工程研究所 | A kind of spacecraft propulsion agent management method |
| JP2019132142A (en) * | 2018-01-29 | 2019-08-08 | 国立大学法人室蘭工業大学 | Pressurization gas supply device and propulsion device for satellite using the same |
| CN108704392A (en) * | 2018-05-29 | 2018-10-26 | 中国人民解放军国防科技大学 | Centrifugal force inertia cascade gas-liquid separator |
| CN110052109A (en) * | 2019-05-15 | 2019-07-26 | 北京控制工程研究所 | A kind of gas-liquid separation device for satellite booster agent tank |
| CN114275193A (en) * | 2021-11-12 | 2022-04-05 | 西安交通大学 | Net curtain type on-orbit filling system and method for low-temperature propellant and low-temperature storage tank |
| CN218266078U (en) * | 2022-10-20 | 2023-01-10 | 重庆鑫源动力制造有限公司 | Exhaust manifold assembly |
Non-Patent Citations (2)
| Title |
|---|
| 刘展: "低温推进剂长期在轨压力管理技术研究进展", 宇航学报, vol. 35, no. 3, pages 254 - 261 * |
| 刘桢: "运载火箭上面级微重力环境下的推进剂管理", 导弹与航天运载技术, no. 4, pages 20 - 26 * |
Also Published As
| Publication number | Publication date |
|---|---|
| CN116696606B (en) | 2023-10-27 |
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