CN114412662A - Liquid level stabilizing device of oxidant box and oxyhydrogen rocket - Google Patents
Liquid level stabilizing device of oxidant box and oxyhydrogen rocket Download PDFInfo
- Publication number
- CN114412662A CN114412662A CN202210072546.2A CN202210072546A CN114412662A CN 114412662 A CN114412662 A CN 114412662A CN 202210072546 A CN202210072546 A CN 202210072546A CN 114412662 A CN114412662 A CN 114412662A
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- Prior art keywords
- box
- room
- gasbag
- rocket
- tank
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- 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
- F02K9/605—Reservoirs
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02E—REDUCTION OF GREENHOUSE GAS [GHG] EMISSIONS, RELATED TO ENERGY GENERATION, TRANSMISSION OR DISTRIBUTION
- Y02E60/00—Enabling technologies; Technologies with a potential or indirect contribution to GHG emissions mitigation
- Y02E60/30—Hydrogen technology
- Y02E60/32—Hydrogen storage
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- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Filling Or Discharging Of Gas Storage Vessels (AREA)
Abstract
The application discloses liquid level stabilising arrangement and oxyhydrogen rocket of oxidant case relates to rocket technical field, includes: the box, liquid oxygen is equipped with in the inside of box, and the inside top of box is equipped with fills room and gasbag, the gasbag wraps up in the cover fill the room, be used for with fill the room seal in the gasbag, place solid-state inert gas in the room of filling, the outer wall of filling the room is equipped with a plurality of through-hole. The application can reduce the shaking of liquid oxygen in the box body, and improves the flight stability of the oxyhydrogen rocket.
Description
Technical Field
The application relates to the technical field of rockets, in particular to a liquid level stabilizing device of an oxidant tank and an oxyhydrogen rocket.
Background
The oxyhydrogen rocket is a space rocket adopting liquid hydrogen and liquid oxygen as fuels, the oxyhydrogen engine is used for providing launching power for the space rocket, the oxyhydrogen engine is one of the trends of the world rocket engine technology development, and the mastery of the oxyhydrogen engine technology is one of the signs of the state becoming the strong country of space flight. The development of a high-thrust oxyhydrogen engine is a development trend of liquid rocket engine technology at home and abroad. However, as the rocket rises to burn the fuel ceaselessly, the liquid oxygen in the oxidant tank of the oxyhydrogen rocket is gradually reduced, so that the liquid level of the liquid oxygen in the oxidant tank body is reduced, the liquid oxygen shakes in the tank body to be larger and larger as the fuel burns, and the integral flight of the oxyhydrogen rocket is influenced to a certain extent.
Disclosure of Invention
The present application is directed to solving at least one of the problems in the prior art. Therefore, the liquid level stabilizing device of the oxidant tank and the oxyhydrogen rocket can reduce the shaking of liquid oxygen in the tank body and improve the flight stability of the oxyhydrogen rocket.
In a first aspect, the present application provides a level stabilizing device for an oxidant tank, comprising:
the box, liquid oxygen is equipped with in the inside of box, and the inside top of box is equipped with fills room and gasbag, the gasbag wraps up in the cover fill the room, be used for with fill the room seal in the gasbag, place solid-state inert gas in the room of filling, the outer wall of filling the room is equipped with a plurality of through-hole.
The liquid level stabilizing device of the oxidant tank in the embodiment of the first aspect of the application has at least the following beneficial effects: through the fixed filling chamber that is equipped with in top at the box, be equipped with solid-state inert gas in the filling chamber, the gasbag wraps up in the cover filling chamber, thereby realize sealed gasbag's effect, the inside liquid oxygen as the combustion improver that is equipped with of box, at the in-process of burning, the liquid level of liquid oxygen descends gradually, and the temperature in the box also improves thereupon, thereby make the solid-state inert gas who is located the filling chamber melt, along with it vaporize, liquid or gas are through flowing out at the through-hole department, the realization is to the gas filled effect of gasbag, thereby make the gasbag swell, make the bottom of gasbag push down the liquid level, thereby reduce the rocking of liquid oxygen in the box, thereby the stability of oxyhydrogen rocket flight has been improved.
According to some embodiments of the first aspect of the present application, the solid inert gas is solid argon.
According to some embodiments of the first aspect of the present application, the filling chamber is fixed to the inner top end of the tank by welding.
According to some embodiments of the first aspect of the present application, a cross-section of the airbag in an inflated state matches a cross-section of the tank.
According to some embodiments of the first aspect of the present application, the bottom end of the bladder is planar.
According to some embodiments of the first aspect of the present application, the tank is made of an aluminum alloy.
In a second aspect, the present application also provides a hydrogen-oxygen rocket including a level stabilizer for an oxidizer tank as described in any one of the embodiments of the first aspect.
The oxyhydrogen rocket according to the embodiment of the second aspect of the application has at least the following beneficial effects: through the fixed filling chamber that is equipped with in top at the box, be equipped with solid-state inert gas in the filling chamber, the gasbag wraps up in the cover filling chamber, thereby realize sealed gasbag's effect, the inside liquid oxygen as the combustion improver that is equipped with of box, at the in-process of burning, the liquid level of liquid oxygen descends gradually, and the temperature in the box also improves thereupon, thereby make the solid-state inert gas who is located the filling chamber melt, along with it vaporize, liquid or gas are through flowing out at the through-hole department, the realization is to the gas filled effect of gasbag, thereby make the gasbag swell, make the bottom of gasbag push down the liquid level, thereby reduce the rocking of liquid oxygen in the box, thereby the stability of oxyhydrogen rocket flight has been improved.
Additional aspects and advantages of the present application will be set forth in part in the description which follows and, in part, will be obvious from the description, or may be learned by practice of the present application.
Drawings
Additional aspects and advantages of the present application will become apparent and readily appreciated from the following description of the embodiments, taken in conjunction with the accompanying drawings of which:
fig. 1 is a schematic cross-sectional view of a level stabilizing device of an oxidant tank of some embodiments of the present application.
The reference numbers are as follows:
a case 110; an air bag 120; a filling chamber 130; and a through hole 131.
Detailed Description
Reference will now be made in detail to embodiments of the present application, examples of which are illustrated in the accompanying drawings, wherein like or similar reference numerals refer to the same or similar elements or elements having the same or similar function throughout. The embodiments described below with reference to the drawings are exemplary only for the purpose of explaining the present application and are not to be construed as limiting the present application.
In the description of the present application, it is to be understood that the positional descriptions, such as the directions of up, down, front, rear, left, right, etc., referred to herein are based on the directions or positional relationships shown in the drawings, and are only for convenience of description and simplification of description, and do not indicate or imply that the referred device or element must have a specific direction, be constructed and operated in a specific direction, and thus, should not be construed as limiting the present application.
In the description of the present application, if there is a description to the first, only for the purpose of distinguishing technical features, it is not to be understood as indicating or implying relative importance or implicitly indicating the number of technical features indicated or implicitly indicating the precedence of the technical features indicated.
In the description of the present application, unless otherwise expressly limited, terms such as set, mounted, connected and the like should be construed broadly, and those skilled in the art can reasonably determine the specific meaning of the terms in the present application by combining the detailed contents of the technical solutions.
In a first aspect, and with reference to fig. 1, the present application provides a level stabilizing apparatus for an oxidizer tank, comprising: the liquid oxygen is filled in the box body 110, the top end of the inside of the box body 110 is provided with a filling chamber 130 and an air bag 120, the air bag 120 is wrapped on the filling chamber 130 and used for sealing the filling chamber 130 in the air bag 120, solid inert gas is placed in the filling chamber 130, and the outer wall of the filling chamber 130 is provided with a plurality of through holes 131. The filling chamber 130 is fixedly arranged at the top of the box body 110, solid inert gas is arranged in the filling chamber 130, and the air bag 120 is wrapped in the filling chamber 130, so that the effect of sealing the air bag 120 is realized, liquid oxygen serving as a combustion improver is filled in the box body 110, the liquid level of the liquid oxygen gradually drops in the combustion process, the temperature in the box body 110 is also increased, so that the solid inert gas in the filling chamber 130 is melted and vaporized, the liquid or the gas flows out from the through hole 131, the air bag 120 is inflated, the air bag 120 expands, the liquid level is pressed at the bottom of the air bag 120, the shaking of the liquid oxygen in the box body 110 is reduced, and the stability of hydrogen and oxygen flight is improved.
It will be appreciated that the solid inert gas is solid argon, wherein argon has a melting point of-189.2 deg.C and a boiling point of-185.7 deg.C, and oxygen has a melting point of-218.4 deg.C and a boiling point of-183 deg.C, and the temperature of oxygen when charged into the tank 110 is much lower than that of argon, thus ensuring that argon does not rapidly change to liquid and gaseous states; when the temperature of the oxyhydrogen rocket rises during launching, a gap is formed between the liquid level of the liquid oxygen and the top of the box body 110, and the argon gas is vaporized to fill the air bag 120. From the practical point of view, liquid oxygen is generally filled at the last moment before the launching of the oxyhydrogen rocket, so that the temperature of the liquid oxygen can be ensured to be low enough, in order to seek a slight increase in density, more oxidant is filled under the same volume to improve the carrying capacity and ensure the success rate of the rocket.
It will be appreciated that the filling chamber 130 is fixed to the inner top end of the case 110 by welding. Through the mode of welding for filling chamber 130 fixes more firmly, prevents that filling chamber 130 from droing to in the gasbag 120, causes the destruction to gasbag 120, wherein, the top of box 110 can be equipped with the dodge gate, can place solid-state argon to filling chamber 130 through opening the dodge gate, simultaneously, because the fuel tank in the oxyhydrogen rocket is disposable, can just place solid-state argon according to filling chamber 130 before, do not limit this in this application, the technical field of the institute designs according to practical application.
With continued reference to fig. 1, it can be understood that the cross section of the airbag 120 in the inflated state matches the cross section of the box body 110, so as to better ensure that the bottom of the airbag 120 moves downward when the airbag 120 is inflated, and also avoid the liquid oxygen from shaking in the gap between the airbag 120 and the inner wall of the box body 110, thereby further ensuring the liquid level stability of the liquid oxygen.
With continued reference to fig. 1, it can be understood that the bottom end of the air bag 120 is a plane, so as to better fix the liquid level on the same horizontal position, reduce the sloshing of the liquid oxygen, and further ensure the liquid level stability of the liquid oxygen.
It can be understood that the box body 110 is made of aluminum alloy, has certain rigidity and reduces the mass of the box body, and is more beneficial to launching the oxyhydrogen rocket.
In a second aspect, the present application also provides an oxyhydrogen rocket including a level stabilizer for an oxidizer tank of any one of the embodiments of the first aspect. The filling chamber 130 is fixedly arranged at the top of the box body 110, solid inert gas is arranged in the filling chamber 130, and the air bag 120 is wrapped in the filling chamber 130, so that the effect of sealing the air bag 120 is realized, liquid oxygen serving as a combustion improver is filled in the box body 110, the liquid level of the liquid oxygen gradually drops in the combustion process, the temperature in the box body 110 is also increased, so that the solid inert gas in the filling chamber 130 is melted and vaporized, the liquid or the gas flows out from the through hole 131, the air bag 120 is inflated, the air bag 120 expands, the liquid level is pressed at the bottom of the air bag 120, the shaking of the liquid oxygen in the box body 110 is reduced, and the stability of hydrogen and oxygen flight is improved.
The embodiments of the present application have been described in detail with reference to the drawings, but the present application is not limited to the embodiments, and various changes can be made without departing from the spirit of the present application within the knowledge of those skilled in the art.
Claims (7)
1. A liquid level stabilizing device for an oxidizer tank, comprising:
the box, liquid oxygen is equipped with in the inside of box, and the inside top of box is equipped with fills room and gasbag, the gasbag wraps up in the cover fill the room, be used for with fill the room seal in the gasbag, place solid-state inert gas in the room of filling, the outer wall of filling the room is equipped with a plurality of through-hole.
2. The tank level stabilizer of claim 1, wherein the solid inert gas is solid argon.
3. The tank level stabilizer according to claim 1, wherein said filling chamber is fixed to an inner top end of said tank body by welding.
4. The fluid level stabilizer for an oxidizer tank as set forth in claim 1, wherein a cross section of the bladder in an inflated state matches a cross section of the tank body.
5. The level stabilizing device of the oxidizer tank of claim 1, wherein the bottom end of the bladder is planar.
6. The apparatus of claim 1, wherein the housing is made of aluminum alloy.
7. A hydrogen-oxygen rocket, comprising the level stabilizer of the oxidizer tank of any one of claims 1 to 6.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210072546.2A CN114412662B (en) | 2022-01-21 | 2022-01-21 | Liquid level stabilizing device of oxidant box and oxyhydrogen rocket |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210072546.2A CN114412662B (en) | 2022-01-21 | 2022-01-21 | Liquid level stabilizing device of oxidant box and oxyhydrogen rocket |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN114412662A true CN114412662A (en) | 2022-04-29 |
| CN114412662B CN114412662B (en) | 2023-05-02 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202210072546.2A Active CN114412662B (en) | 2022-01-21 | 2022-01-21 | Liquid level stabilizing device of oxidant box and oxyhydrogen rocket |
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| CN (1) | CN114412662B (en) |
Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPH04201697A (en) * | 1990-11-30 | 1992-07-22 | Mitsubishi Heavy Ind Ltd | Sloshing damping device in liquid fuel rocket propellant tank |
| US20150008235A1 (en) * | 2013-07-08 | 2015-01-08 | Esmaeil Khoshsepehr | Apparatus and method to limit slosh and ullage in a liquid container |
| CN204213627U (en) * | 2014-11-14 | 2015-03-18 | 河南科技学院 | A kind of use for laboratory shielding gas source of the gas transmitter |
| CN110469427A (en) * | 2019-08-14 | 2019-11-19 | 重庆零壹空间科技集团有限公司 | A kind of method and structure of vertical withdrawal liquid rocket propulsion system anti-shake |
| CN112407338A (en) * | 2020-11-24 | 2021-02-26 | 北京宇航系统工程研究所 | Propellant storage tank shaking damping device adapting to large-amplitude change of temperature difference and internal pressure |
| CN112431692A (en) * | 2020-11-17 | 2021-03-02 | 中国人民解放军战略支援部队航天工程大学 | Cooperation air-breathing liquid rocket engine propellant supply system |
| CN113464314A (en) * | 2021-06-30 | 2021-10-01 | 航天科工火箭技术有限公司 | Anti-shaking device and liquid rocket |
-
2022
- 2022-01-21 CN CN202210072546.2A patent/CN114412662B/en active Active
Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPH04201697A (en) * | 1990-11-30 | 1992-07-22 | Mitsubishi Heavy Ind Ltd | Sloshing damping device in liquid fuel rocket propellant tank |
| US20150008235A1 (en) * | 2013-07-08 | 2015-01-08 | Esmaeil Khoshsepehr | Apparatus and method to limit slosh and ullage in a liquid container |
| CN204213627U (en) * | 2014-11-14 | 2015-03-18 | 河南科技学院 | A kind of use for laboratory shielding gas source of the gas transmitter |
| CN110469427A (en) * | 2019-08-14 | 2019-11-19 | 重庆零壹空间科技集团有限公司 | A kind of method and structure of vertical withdrawal liquid rocket propulsion system anti-shake |
| CN112431692A (en) * | 2020-11-17 | 2021-03-02 | 中国人民解放军战略支援部队航天工程大学 | Cooperation air-breathing liquid rocket engine propellant supply system |
| CN112407338A (en) * | 2020-11-24 | 2021-02-26 | 北京宇航系统工程研究所 | Propellant storage tank shaking damping device adapting to large-amplitude change of temperature difference and internal pressure |
| CN113464314A (en) * | 2021-06-30 | 2021-10-01 | 航天科工火箭技术有限公司 | Anti-shaking device and liquid rocket |
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| CN114412662B (en) | 2023-05-02 |
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