CN111924141A - Moon surface low-temperature propellant nondestructive storage device - Google Patents
Moon surface low-temperature propellant nondestructive storage device Download PDFInfo
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- CN111924141A CN111924141A CN202010824455.0A CN202010824455A CN111924141A CN 111924141 A CN111924141 A CN 111924141A CN 202010824455 A CN202010824455 A CN 202010824455A CN 111924141 A CN111924141 A CN 111924141A
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- 239000003380 propellant Substances 0.000 title claims abstract description 43
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- 239000007788 liquid Substances 0.000 claims abstract description 107
- 239000007789 gas Substances 0.000 claims abstract description 70
- VNWKTOKETHGBQD-UHFFFAOYSA-N methane Chemical compound C VNWKTOKETHGBQD-UHFFFAOYSA-N 0.000 claims abstract description 32
- MYMOFIZGZYHOMD-UHFFFAOYSA-N Dioxygen Chemical compound O=O MYMOFIZGZYHOMD-UHFFFAOYSA-N 0.000 claims abstract description 19
- 238000009413 insulation Methods 0.000 claims abstract description 16
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G1/00—Cosmonautic vehicles
- B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
- B64G1/40—Arrangements or adaptations of propulsion systems
- B64G1/402—Propellant tanks; Feeding propellants
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- 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)
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- Combustion & Propulsion (AREA)
- Remote Sensing (AREA)
- Aviation & Aerospace Engineering (AREA)
- Filling Or Discharging Of Gas Storage Vessels (AREA)
Abstract
A moon surface low-temperature propellant nondestructive storage device comprises a low-temperature liquid storage tank and a gas container, wherein the low-temperature liquid storage tank is fixed on the moon surface through a support leg, and the gas container is fixed on the low-temperature liquid storage tank through a low-heat-conduction connecting rod; the top of the low-temperature liquid storage tank is provided with a first connecting pipe, the bottom of the gas container is provided with a second connecting pipe, the connecting pipe is provided with a stop valve, and the first connecting pipe is communicated with the second connecting pipe through a low heat conduction pipe; the outer surface of the low-temperature liquid storage tank is covered with a plurality of layers of heat insulation layers, the bottom of the low-temperature liquid storage tank is provided with a liquid filling valve and a liquid draining valve, the top of the low-temperature liquid storage tank is provided with a first pressure increasing pipe, and the top of the low-temperature liquid storage tank is provided with a first safety valve and a first pressure releasing valve; the top of the gas container is provided with a second pressure increasing pipe, the second pressure increasing pipe is provided with a second pressure reducing valve and a second check valve, and the top of the gas container is provided with a second safety valve and a second pressure relief valve; the invention realizes the lunar surface zero-evaporation storage of liquid oxygen and liquid methane, and has the advantages of simple structure, reliable equipment operation and the like.
Description
Technical Field
The invention belongs to the technical field of aerospace low-temperature propellant storage, and particularly relates to a moon surface low-temperature propellant nondestructive storage device.
Background
The moon is a celestial body closest to the earth, has abundant resources and energy sources, and is also the most ideal technical verification base for people to move to deep space. Lunar exploration has drawn attention and research into the united states, russia, europe, the sun, the seal and the Chinese aerospace world, and lunar bases have been planned and built to serve various needs. In the foreseeable future, manned ground-moon commutes will be more frequent, even reaching "flights". The propellant required for the take-off of a spacecraft from the moon must meet the long-term storage capacity at the moon.
Compared with the conventional propellant, the low-temperature propellant comprises the combination of liquid hydrogen/liquid oxygen, liquid methane/liquid oxygen, liquid oxygen/kerosene and the like, has the performance advantages of high thrust and high specific impulse, and plays a more important role in future aerospace exploration. In comparison, the boiling point of liquid methane/liquid oxygen is close, the space management and application can be carried out by adopting a unified technology, and the control difficulty is far lower than that of liquid hydrogen. Therefore, liquid methane/liquid oxygen is considered to be the main power fuel for supporting the next day-to-day, lunar exploration.
The boiling points of the low-temperature liquid oxygen and the liquid methane for spaceflight are far lower than that of the normal-temperature environment, wherein the boiling point of the liquid oxygen under normal pressure is 90.1K, and the boiling point of the liquid methane is 111.5K. When the low-temperature propellant is stored on the ground, on orbit and on the surface of the moon, the heating and vaporization of the liquid propellant can be inevitably caused by environmental heat invasion, and the propellant loss is caused. The mission suitability of a space probe vehicle depends to a large extent on the total amount of propellant available. Therefore, reducing the amount of evaporative loss of the cryogenic propellant, even to achieve lossless storage, is key to support future deep space exploration.
The surface of the moon is free of atmosphere, and the moon rotates for a circle approximately equal to 28 days of the earth, wherein 14 days of the moon and 14 days of the moon at night. The surface temperature during the monthly day was as high as 120 ℃ and the monthly night was reduced to-180 ℃. When the low-temperature propellant is stored in the moon and day environment, the high-temperature environment can cause severe heating and vaporization loss of the low-temperature propellant, the high-temperature duration is long, the vaporization loss is far greater than the ground working condition, and the low-temperature propellant carried to the surface of the moon can be excessively lost and cannot support the subsequent space missions.
The existing lunar exploration task is short, and the future development lunar activities of human beings must be carried out for a long time, such as alternating multi-month day/night. How to realize the high-efficient storage of low temperature liquid oxygen and liquid methane under the special thermal environment of the moon becomes one of the technical problems that need to be solved. No relevant literature publication is found at present.
Disclosure of Invention
In order to overcome the defects of the prior art, the invention aims to provide a moon surface low-temperature propellant nondestructive storage device, which realizes the lunar surface zero-evaporation storage of liquid oxygen and liquid methane by utilizing the thermodynamic characteristics of the liquid oxygen and liquid methane propellants and the special thermal environment of the moon surface, and has the advantages of simple structure, reliable equipment operation, no need of energy supply and the like.
In order to achieve the aim, the invention adopts the technical scheme that:
a moon surface low-temperature propellant nondestructive storage device comprises a low-temperature liquid storage tank 1 and a gas container 2, wherein the low-temperature liquid storage tank 1 is fixed on the moon surface through a support leg 21, and the gas container 2 is fixed on the low-temperature liquid storage tank 1 through a low-heat-conduction connecting rod 22;
the top of the low-temperature liquid storage tank 1 is provided with a first connecting pipe 3, the bottom of the gas container 2 is provided with a second connecting pipe 4, the first connecting pipe 3 is provided with a first stop valve 6, the second connecting pipe 4 is provided with a second stop valve 7, and the first connecting pipe 3 is communicated with the second connecting pipe 4 through a low heat conduction pipe 5;
the outer surface of the low-temperature liquid storage tank 1 is covered with a plurality of layers of heat insulation layers 8, the bottom of the low-temperature liquid storage tank 1 is respectively provided with a liquid filling valve 9 and a liquid drain valve 10, the top of the low-temperature liquid storage tank 1 is provided with a first pressure increasing pipe 11, the first pressure increasing pipe 11 is provided with a first pressure reducing valve 12 and a first check valve 13, and the top of the low-temperature liquid storage tank 1 is simultaneously provided with a first safety valve 14 and a first pressure relief valve 15;
the top of the gas container 2 is provided with a second pressure increasing pipe 16, the second pressure increasing pipe 16 is provided with a second pressure reducing valve 17 and a second check valve 18, and the top of the gas container 2 is simultaneously provided with a second safety valve 19 and a second pressure relief valve 20.
The low-temperature liquid storage tank 1 is made of stainless steel or aluminum alloy materials, liquid methane and liquid oxygen are stored in the low-temperature liquid storage tank 1, the liquid filling rate is less than 98%, the wall thickness is 1-5 mm, and the pressure resistance is greater than 0.5 MPa; the first pressure increasing pipe 11, the first safety valve 14 and the first pressure relief valve 15 are respectively communicated with an air pillow area of the low-temperature liquid storage tank 1.
The gas container 2 is made of stainless steel, aluminum alloy or copper, the wall thickness is 1-5 mm, and the pressure resistance is more than 0.5 MPa.
The first connecting pipe 3 is welded at the top of the low-temperature liquid storage tank 1, and the pipe wall material is the same as that of the low-temperature liquid storage tank 1; the second connecting pipe 4 is welded at the bottom of the gas container 2, and the pipe wall material is the same as that of the gas container 2.
The first stop valve 6 and the second stop valve 7 are low-temperature ball valves.
The low heat conduction pipe 5 is processed by S-epoxy resin or graphite epoxy resin, two ends of the low heat conduction pipe 5 are respectively connected with the first connecting pipe 3 and the second connecting pipe 4 through threads or flanges, and the length of the low heat conduction pipe 5 is larger than 0.2 m.
The first connecting pipe 3, the second connecting pipe 4 and the low heat conduction pipe 5 realize the circulation of fluid between the low-temperature liquid storage tank 1 and the gas container 2, and the surfaces of the first connecting pipe 3, the second connecting pipe 4 and the low heat conduction pipe 5 comprise a plurality of layers of heat insulation layers 8.
The multilayer heat insulation layer 8 is formed by alternately arranging a metal reflecting screen and a non-metal spacer, the metal reflecting screen is an aluminum foil, a double-sided aluminum plated polyester film or a single-sided aluminum plated polyester film, and the non-metal spacer is a glass fiber or a nylon net.
The first check valve 13 is directed toward the cryogenic liquid storage tank 1, and the second check valve 18 is directed toward the gas container 2.
The support legs 21 and the low heat conduction connecting rods 22 are made of invar steel or 304 stainless steel, and the surfaces of the support legs and the low heat conduction connecting rods are wrapped by multiple layers of heat insulation layers 8.
The invention has the beneficial effects that:
the invention utilizes day and night in-situ thermal environment conditions on the lunar surface, combines thermodynamic characteristics of low-temperature liquid oxygen and liquid methane, and condenses the liquid propellant lost by lunar day and night again through the design of the low-temperature propellant storage container structure, thereby realizing long-term lossless storage of the lunar surface of the low-temperature propellant.
Compared with the traditional low-temperature storage tank, the introduction of the gas container 2 does not bring more heat loss to the low-temperature liquid storage tank 1, and the heat leakage loss caused by gas heat conduction and pipe wall heat conduction in the daytime is smaller. Because gas container 2 does not adopt adiabatic processing during the night, can reach thermal equilibrium with the night cold background in short time, superheated gas takes place the heat transfer that condenses with cold wall contact in the gas container 2, and the condensate flows back to low temperature liquid storage tank 1 under the lunar surface action of gravity, and cold wall is fully contacted with gas all the time, can guarantee that gas fully condenses.
The device has excellent applicability to future lunar exploration, the liquid oxygen/liquid methane combination is the most potential propellant, the applicable object of the invention is just lunar surface storage of the liquid oxygen and the liquid methane, and the liquid oxygen can be prepared in situ on the lunar surface. In addition, the device has no moving part, simple structure and no additional energy input in the running process, and has important value for future lunar exploration and resource development.
Drawings
FIG. 1 is a schematic structural diagram of the present invention.
Detailed Description
The present invention will be described in detail below with reference to the accompanying drawings.
Referring to fig. 1, the nondestructive storage device for the low-temperature propellant on the lunar surface comprises a low-temperature liquid storage tank 1 and a gas container 2, wherein the low-temperature liquid storage tank 1 is fixed on the lunar surface through a support leg 21, and the gas container 2 is fixed on the low-temperature liquid storage tank 1 through a low-heat-conduction connecting rod 22;
the top of the low-temperature liquid storage tank 1 is provided with a first connecting pipe 3, the bottom of the gas container 2 is provided with a second connecting pipe 4, the first connecting pipe 3 is provided with a first stop valve 6, the second connecting pipe 4 is provided with a second stop valve 7, and the first connecting pipe 3 is communicated with the second connecting pipe 4 through a low heat conduction pipe 5;
the outer surface of the low-temperature liquid storage tank 1 is covered with a plurality of layers of heat insulation layers 8, the bottom of the low-temperature liquid storage tank 1 is respectively provided with a liquid filling valve 9 and a liquid drain valve 10, the top of the low-temperature liquid storage tank 1 is provided with a first pressure increasing pipe 11, the first pressure increasing pipe 11 is provided with a first pressure reducing valve 12 and a first check valve 13, and the top of the low-temperature liquid storage tank 1 is simultaneously provided with a first safety valve 14 and a first pressure relief valve 15;
the top of the gas container 2 is provided with a second pressure increasing pipe 16, the second pressure increasing pipe 16 is provided with a second pressure reducing valve 17 and a second check valve 18, and the top of the gas container 2 is simultaneously provided with a second safety valve 19 and a second pressure relief valve 20.
The low-temperature liquid storage tank 1 is made of stainless steel or aluminum alloy materials, liquid methane and liquid oxygen are stored in the low-temperature liquid storage tank 1, the liquid filling rate is less than 98%, the wall thickness is 1-5 mm, and the pressure resistance is greater than 0.5 MPa; the first pressure increasing pipe 11, the first safety valve 14 and the first pressure relief valve 15 are respectively communicated with an air pillow area of the low-temperature liquid storage tank 1.
The gas container 2 is made of stainless steel, aluminum alloy or copper, the wall thickness is 1-5 mm, the pressure resistance is greater than 0.5MPa, and the surface is not wrapped by a heat insulating material.
The first connecting pipe 3 is welded at the top of the low-temperature liquid storage tank 1, and the pipe wall material is the same as that of the low-temperature liquid storage tank 1; the second connecting pipe 4 is welded at the bottom of the gas container 2, and the pipe wall material is the same as that of the gas container 2; the first stop valve 6 and the second stop valve 7 are low-temperature ball valves.
The low heat conduction pipe 5 is processed by S-epoxy resin or graphite epoxy resin, two ends of the low heat conduction pipe 5 are respectively connected with the first connecting pipe 3 and the second connecting pipe 4 through threads or flanges, and the length of the low heat conduction pipe 5 is larger than 0.2 m.
The first connecting pipe 3, the second connecting pipe 4 and the low heat conduction pipe 5 realize the circulation of fluid between the low-temperature liquid storage tank 1 and the gas container 2, and the surfaces of the first connecting pipe 3, the second connecting pipe 4 and the low heat conduction pipe 5 comprise a plurality of layers of heat insulation layers 8.
The multilayer heat insulation layer 8 is formed by alternately arranging a metal reflecting screen and a non-metal spacer, the metal reflecting screen is an aluminum foil, a double-sided aluminum plated polyester film or a single-sided aluminum plated polyester film, and the non-metal spacer is a glass fiber or a nylon net.
The first check valve 13 is directed toward the cryogenic liquid storage tank 1, and the second check valve 18 is directed toward the gas container 2.
The support legs 21 and the low heat conduction connecting rods 22 are made of invar steel or 304 stainless steel, and the surfaces of the support legs and the low heat conduction connecting rods are wrapped by multiple layers of heat insulation layers 8.
The working principle of the invention is as follows:
the low-temperature liquid storage tank 1 and the gas container 2 are both launched by the earth, and the equipment is assembled on the surface of the moon; before the assembly of the moon, the first stop valve 6 and the second stop valve 7 are closed, the low-temperature liquid storage tank 1 carrying low-temperature propellant is fixed on the moon by the support legs 21, the gas container 2 is fixed above the low-temperature liquid storage tank 1 by the low heat conduction connecting rod 22, and the connection of a fluid pipeline consisting of the first connecting pipe 3, the second connecting pipe 4 and the low heat conduction pipe 5 is ensured; the first and second shut-off valves 6 and 7 are used to close the cryogenic liquid storage tank 1 and the gas container 2 before assembly and to maintain the required container seal from the ground to before assembly.
After the low-temperature liquid storage tank 1 and the gas container 2 are assembled, the first stop valve 6 and the second stop valve 7 are opened, the flow channel connection of the low-temperature liquid storage tank 1 and the gas container 2 is realized, and the long-term storage of the low-temperature liquid oxygen and the liquid methane can be realized. Wherein, the liquid filling valve 9 is used for replenishing liquid propellant, and the liquid drain valve 10 is used for supplying or draining the liquid propellant. When the liquid is normally supplied, the pressurized gas is communicated with the first pressurizing pipe 11, and the low-temperature liquid storage tank 1 is pressurized through the first reducing valve 12 and the first check valve 13 to establish the required liquid supply pressure; first relief valve 14 is used for overpressure venting of cryogenic liquid tank 1 and first relief valve 15 is used for active relief. The second pressure increasing pipe 16, the second pressure reducing valve 17, and the second check valve 18 are used to supplement gas to the gas container 2, the second safety valve 19 is used to exhaust the gas container 2 in an emergency, and the second pressure reducing valve 20 is used to actively reduce pressure.
In the moon and day, the temperature of the lunar surface rises, the low-temperature propellant in the low-temperature liquid storage tank 1 gradually rises and gasifies under the heat invasion of the lunar surface environment, the temperature rise and gasification of the liquid propellant are slow due to the heat protection of the multilayer heat insulation layer 8, and the pressure of the low-temperature liquid storage tank 1 slowly rises; the gas container 2 is not protected by heat insulation, so that the temperature of the wall surface and the internal gas of the gas container 2 is increased quickly and is balanced with the surrounding thermal environment in a short time, and then, the temperature of the gas container 2 is not changed obviously any more, and the whole device is stable. At this time, a large temperature difference exists at two ends of a fluid pipeline consisting of the first connecting pipe 3, the second connecting pipe 4 and the low heat conduction pipe 5, and heat is transferred from the upper end of the second connecting pipe 4 to the lower end of the first connecting pipe 3; because the whole system reaches a quasi-steady state, the airflow speed in the fluid pipeline is low, and the heat conduction effect through the gas is extremely small. In addition, the low heat conduction pipe 5 greatly inhibits the axial heat conduction along the pipe wall, and the whole pipeline system is wrapped by the multiple layers of heat insulation layers 8, so that the local heat leakage through the fluid passage is small in the daytime, and the obvious temperature rise or gasification loss of the propellant in the low-temperature liquid storage tank 1 cannot be caused. As the monthly day rest time continues, the pressure gradually rises throughout the apparatus and the low temperature propellant boil-off gas is stored primarily in the gas container 2.
At night, the lunar surface reaches a low temperature environment of nearly-180 ℃ in a short time and keeps basically stable. Because the gas container 2 does not have adiabatic parcel and be the metal material, the metal wall can be cooled down to the lunar surface temperature in the short time, and the metal wall is cooled down to the gaseous continuous cooling in the gas container 2. At the beginning, the pressure in the gas container 2 is high, the corresponding condensation temperature of the internal gas is also relatively high, and the temperature of the metal wall is lower than the condensation temperature of the gas, so that the propellant vapor is condensed on the inner wall surface of the gas container 2, the condensed liquid flows back to the low-temperature liquid storage tank 1 under the action of the lunar surface gravity, and the recovery of the vapor is realized. In addition, under the gravity of the moon surface, the inner surface of the gas container 2 can be always kept in contact with the steam, and the continuous condensation process is realized. As the condensation continues, the pressure within the entire device gradually decreases, ultimately resulting in long-term non-destructive storage of the cryogenic propellant.
It should be noted that during the month, heat is transferred from the moon to the gas container 2, and the temperature of the gas container 2 does not change after thermal equilibrium is reached. Therefore, although the monthly time is long, the heat cannot be continuously and stably transferred to the gas container 2, and the heat transferred to the gas container 2 over the monthly time is limited; and when the moon is night, the wall surface temperature of the gas container 2 is always kept at a lower level, and the heat can be continuously absorbed from the internal fluid, so that the fluid is cooled and condensed and recovered.
Claims (10)
1. A moon surface low-temperature propellant nondestructive storage device comprises a low-temperature liquid storage tank (1) and a gas container (2), and is characterized in that: the low-temperature liquid storage tank (1) is fixed on the moon surface through a support leg (21), and the gas container (2) is fixed on the low-temperature liquid storage tank (1) through a low heat conduction connecting rod (22);
the top of the low-temperature liquid storage tank (1) is provided with a first connecting pipe (3), the bottom of the gas container (2) is provided with a second connecting pipe (4), the first connecting pipe (3) is provided with a first stop valve (6), the second connecting pipe (4) is provided with a second stop valve (7), and the first connecting pipe (3) and the second connecting pipe (4) are communicated through a low heat conduction pipe (5);
the outer surface of the low-temperature liquid storage tank (1) is covered with a plurality of layers of heat insulation layers (8), the bottom of the low-temperature liquid storage tank (1) is respectively provided with a liquid filling valve (9) and a liquid drainage valve (10), the top of the low-temperature liquid storage tank (1) is provided with a first pressure increasing pipe (11), the first pressure increasing pipe (11) is provided with a first pressure reducing valve (12) and a first check valve (13), and the top of the low-temperature liquid storage tank (1) is simultaneously provided with a first safety valve (14) and a first pressure reducing valve (15);
the top of the gas container (2) is provided with a second pressure increasing pipe (16), the second pressure increasing pipe (16) is provided with a second pressure reducing valve (17) and a second check valve (18), and the top of the gas container (2) is simultaneously provided with a second safety valve (19) and a second pressure relief valve (20).
2. The moon surface low-temperature propellant nondestructive storage device according to claim 1, wherein: the low-temperature liquid storage tank (1) is made of stainless steel or aluminum alloy materials, liquid methane and liquid oxygen are stored in the low-temperature liquid storage tank (1), the liquid filling rate is less than 98%, the wall thickness is 1-5 mm, and the pressure resistance is greater than 0.5 MPa; the first pressure increasing pipe (11), the first safety valve (14) and the first pressure relief valve (15) are respectively communicated with an air pillow area of the low-temperature liquid storage tank (1).
3. The moon surface low-temperature propellant nondestructive storage device according to claim 1, wherein: the gas container (2) is made of stainless steel, aluminum alloy or copper, the wall thickness is 1-5 mm, and the pressure resistance is greater than 0.5 MPa.
4. The moon surface low-temperature propellant nondestructive storage device according to claim 1, wherein: the first connecting pipe (3) is welded at the top of the low-temperature liquid storage tank (1), and the pipe wall material is the same as that of the low-temperature liquid storage tank (1); the second connecting pipe (4) is welded at the bottom of the gas container (2), and the pipe wall material is the same as that of the gas container (2).
5. The moon surface low-temperature propellant nondestructive storage device according to claim 1, wherein: the first stop valve (6) and the second stop valve (7) are low-temperature ball valves.
6. The moon surface low-temperature propellant nondestructive storage device according to claim 1, wherein: the low heat conduction pipe (5) is processed by S-epoxy resin or graphite epoxy resin, two ends of the low heat conduction pipe (5) are respectively connected with the first connecting pipe (3) and the second connecting pipe (4) through threads or flanges, and the length of the low heat conduction pipe (5) is larger than 0.2 m.
7. The moon surface low-temperature propellant nondestructive storage device according to claim 1, wherein: the low-temperature liquid storage tank is characterized in that the first connecting pipe (3), the second connecting pipe (4) and the low heat conduction pipe (5) realize the circulation of fluid between the low-temperature liquid storage tank (1) and the gas container (2), and the surfaces of the first connecting pipe (3), the second connecting pipe (4) and the low heat conduction pipe (5) comprise multiple layers of heat insulation layers (8).
8. The moon surface low-temperature propellant nondestructive storage device according to claim 1, wherein: the multilayer heat insulation layer (8) is formed by alternately arranging a metal reflecting screen and a non-metal spacer, the metal reflecting screen is an aluminum foil, a double-sided aluminum plated polyester film or a single-sided aluminum plated polyester film, and the non-metal spacer is a glass fiber or a nylon net.
9. The moon surface low-temperature propellant nondestructive storage device according to claim 1, wherein: the first check valve (13) flows towards the low-temperature liquid storage tank (1), and the second check valve (18) flows towards the gas container (2).
10. The moon surface low-temperature propellant nondestructive storage device according to claim 1, wherein: the supporting legs (21) and the low-heat-conduction connecting rods (22) are made of invar steel or 304 stainless steel, and the surfaces of the supporting legs and the low-heat-conduction connecting rods are wrapped by multiple layers of heat insulation layers (8).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010824455.0A CN111924141B (en) | 2020-08-17 | 2020-08-17 | Moon surface low-temperature propellant nondestructive storage device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010824455.0A CN111924141B (en) | 2020-08-17 | 2020-08-17 | Moon surface low-temperature propellant nondestructive storage device |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN111924141A true CN111924141A (en) | 2020-11-13 |
| CN111924141B CN111924141B (en) | 2022-12-09 |
Family
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114252344A (en) * | 2021-12-20 | 2022-03-29 | 北京星际荣耀空间科技股份有限公司 | Low-temperature hydraulic testing device and method for pressure container without heat insulation layer |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US7559508B1 (en) * | 2006-12-07 | 2009-07-14 | Taylor Thomas C | Propellant depot in space |
| CN110159914A (en) * | 2019-05-06 | 2019-08-23 | 上海宇航系统工程研究所 | Adapt to the cryogenic liquid storage evaporation control system and control method of moonscape |
| CN110726321A (en) * | 2019-09-29 | 2020-01-24 | 西安交通大学 | Phase change energy storage and supply system utilizing large temperature difference between day and night on lunar surface |
| CN110758776A (en) * | 2019-10-28 | 2020-02-07 | 西安交通大学 | Low-temperature propellant on-orbit zero-evaporation passive heat-insulation storage tank |
-
2020
- 2020-08-17 CN CN202010824455.0A patent/CN111924141B/en active Active
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US7559508B1 (en) * | 2006-12-07 | 2009-07-14 | Taylor Thomas C | Propellant depot in space |
| CN110159914A (en) * | 2019-05-06 | 2019-08-23 | 上海宇航系统工程研究所 | Adapt to the cryogenic liquid storage evaporation control system and control method of moonscape |
| CN110726321A (en) * | 2019-09-29 | 2020-01-24 | 西安交通大学 | Phase change energy storage and supply system utilizing large temperature difference between day and night on lunar surface |
| CN110758776A (en) * | 2019-10-28 | 2020-02-07 | 西安交通大学 | Low-temperature propellant on-orbit zero-evaporation passive heat-insulation storage tank |
Non-Patent Citations (2)
| Title |
|---|
| 朱洪来等: "低温推进剂在轨贮存与管理技术研究", 《载人航天》 * |
| 王磊等: "长期在轨贮存低温推进剂过冷度获取方案研究", 《航空动力学报》 * |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114252344A (en) * | 2021-12-20 | 2022-03-29 | 北京星际荣耀空间科技股份有限公司 | Low-temperature hydraulic testing device and method for pressure container without heat insulation layer |
| CN114252344B (en) * | 2021-12-20 | 2023-04-18 | 北京星际荣耀空间科技股份有限公司 | Low-temperature hydraulic testing device and method for pressure container without heat insulation layer |
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| CN111924141B (en) | 2022-12-09 |
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