CN114922744A - Force-bearing type low-temperature common-bottom storage tank for spacecraft - Google Patents
Force-bearing type low-temperature common-bottom storage tank for spacecraft Download PDFInfo
- Publication number
- CN114922744A CN114922744A CN202210343951.3A CN202210343951A CN114922744A CN 114922744 A CN114922744 A CN 114922744A CN 202210343951 A CN202210343951 A CN 202210343951A CN 114922744 A CN114922744 A CN 114922744A
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- Prior art keywords
- storage tank
- ring
- common
- connecting ring
- spacecraft
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- 239000007788 liquid Substances 0.000 claims description 19
- 239000003380 propellant Substances 0.000 claims description 15
- 238000009987 spinning Methods 0.000 claims description 9
- 238000009413 insulation Methods 0.000 claims description 6
- 238000003801 milling Methods 0.000 claims description 4
- 239000000126 substance Substances 0.000 claims description 2
- 239000007787 solid Substances 0.000 description 9
- MYMOFIZGZYHOMD-UHFFFAOYSA-N Dioxygen Chemical compound O=O MYMOFIZGZYHOMD-UHFFFAOYSA-N 0.000 description 5
- 239000001257 hydrogen Substances 0.000 description 5
- 229910052739 hydrogen Inorganic materials 0.000 description 5
- UFHFLCQGNIYNRP-UHFFFAOYSA-N Hydrogen Chemical compound [H][H] UFHFLCQGNIYNRP-UHFFFAOYSA-N 0.000 description 4
- 229910000838 Al alloy Inorganic materials 0.000 description 3
- 230000009286 beneficial effect Effects 0.000 description 3
- 239000000463 material Substances 0.000 description 3
- 239000004642 Polyimide Substances 0.000 description 2
- 239000000956 alloy Substances 0.000 description 2
- 230000008878 coupling Effects 0.000 description 2
- 238000010168 coupling process Methods 0.000 description 2
- 238000005859 coupling reaction Methods 0.000 description 2
- 238000001704 evaporation Methods 0.000 description 2
- 230000008020 evaporation Effects 0.000 description 2
- 229920001721 polyimide Polymers 0.000 description 2
- 230000002787 reinforcement Effects 0.000 description 2
- 238000007789 sealing Methods 0.000 description 2
- 238000003466 welding Methods 0.000 description 2
- 235000015842 Hesperis Nutrition 0.000 description 1
- 235000012633 Iberis amara Nutrition 0.000 description 1
- 229920005830 Polyurethane Foam Polymers 0.000 description 1
- 230000001133 acceleration Effects 0.000 description 1
- 238000009835 boiling Methods 0.000 description 1
- 239000002131 composite material Substances 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 238000011010 flushing procedure Methods 0.000 description 1
- 239000006260 foam Substances 0.000 description 1
- 238000005242 forging Methods 0.000 description 1
- 150000002431 hydrogen Chemical class 0.000 description 1
- 230000005486 microgravity Effects 0.000 description 1
- 231100000956 nontoxicity Toxicity 0.000 description 1
- 239000011496 polyurethane foam Substances 0.000 description 1
- 230000005855 radiation Effects 0.000 description 1
- 238000005507 spraying Methods 0.000 description 1
Images
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
- F02K9/605—Reservoirs
-
- 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
Abstract
The application relates to the field of storage tanks for spacecrafts, and particularly discloses a bearing type low-temperature common-bottom storage tank for a spacecraft, which comprises a front storage tank, a common-bottom storage tank and a rear storage tank which are sequentially connected from top to bottom, wherein the front storage tank comprises a front seal head, a column section and a rear seal head which are sequentially welded; the rear storage box comprises a rear storage box end enclosure; the rear end enclosure is provided with a mounting hole coaxial with the rear end enclosure, the common bottom is connected to the mounting hole of the rear end enclosure, the common bottom is in a spherical crown shape with a convex middle part, and the rear storage tank end enclosure is connected to the mounting hole of the rear end enclosure and is positioned below the common bottom. The common-bottom storage tank can effectively bear internal pressure load and transfer external system load, thereby greatly reducing the system weight and improving the structural efficiency.
Description
Technical Field
The application relates to the technical field of storage tanks, in particular to a bearing type low-temperature common-bottom storage tank for a spacecraft, which is particularly suitable for low-temperature propulsion aircrafts, low-temperature landers, low-temperature upper-level large-scale high-performance spacecrafts and the like.
Background
The low-temperature propellant combination of liquid hydrogen/liquid oxygen and the like is the first-choice propellant for deep space exploration due to high specific flushing, no toxicity and no pollution. The application of the propellant is difficult due to the low boiling point and the harsh thermal and mechanical environment of the space. As a storage carrier for cryogenic propellants, cryogenic tanks are an important component of propulsion systems as well as spacecraft.
In the related art, the conventional storage tank is generally a serial structure of an upper storage tank, a common bottom and a lower storage tank, the upper storage tank generally comprises an upper seal head and an upper cylinder body section which are directly welded, the lower storage tank comprises a lower cylinder body section and a lower seal head which are directly welded, and the common bottom is connected between the upper cylinder body section and the lower cylinder body section. This structure has the following disadvantages:
the series structure increases the height and slenderness ratio of the storage tank, is not beneficial to the layout of the storage tank in the system, even possibly increases the total height and diameter ratio of spacecrafts such as rockets and the like, and is not beneficial to the flying stability of the spacecrafts.
Disclosure of Invention
In order to effectively reduce the height of a spacecraft storage box, the application discloses a force-bearing type low-temperature common-bottom storage box for a spacecraft.
The technical scheme is as follows:
a force-bearing type low-temperature common-bottom storage tank for a spacecraft comprises a front storage tank, a common-bottom and a rear storage tank which are sequentially connected from top to bottom, wherein the front storage tank comprises a front seal head, a column section and a rear seal head which are sequentially welded; the rear storage box comprises a rear storage box end enclosure; the rear end enclosure is provided with a mounting hole coaxial with the rear end enclosure, the bottom of the rear end enclosure is connected to the mounting hole of the rear end enclosure, the bottom of the rear end enclosure is in a spherical crown shape with the middle protruding upwards, and the rear storage tank end enclosure is connected to the mounting hole of the rear end enclosure and located below the bottom of the rear end enclosure.
And the top of the front seal head is provided with a port flange. The diameter of the inlet flange is generally not less than 450mm, and the lower end of the inlet flange is welded with the front seal head.
The front storage tank also comprises a front storage tank management device used for conveying the non-aerated liquid in the front storage tank, and the rear storage tank also comprises a rear storage tank management device used for conveying the non-aerated liquid in the rear storage tank.
The front seal head and the rear seal head are generally in an ellipsoidal shape and are welded at 4-8 circumferential equal parts.
The common-bottom connecting ring is arranged at the common bottom and comprises a first connecting ring, a second connecting ring, a third connecting ring, a fourth connecting ring and a fifth connecting ring, one end of the first connecting ring, the second connecting ring, the third connecting ring, the fourth connecting ring and the fifth connecting ring are integrally connected and sequentially arranged, the first connecting ring is connected with the mounting hole of the rear head, the second connecting ring is connected with the common bottom, and the third connecting ring is connected with the rear storage tank head. The fourth connecting ring is connected with the engine frame, and the fifth connecting ring is welded with the front storage box management device.
The end socket of the rear storage tank is in an ellipsoid shape with the same shape and surface size as the rear end socket, and the first connecting ring and the third connecting ring have the same shape and surface as the rear end socket.
The second connecting ring and the fourth connecting ring have the same profile with the common bottom.
Preceding storage box still includes preceding Y shape ring and back Y shape ring, and preceding Y shape ring includes the solid fixed ring of first fixed ring, second and the solid fixed ring of third, and first fixed ring is connected with preceding head, and the solid fixed ring of second is connected with the column segment. The third retaining ring is welded to other fittings, for example the third retaining ring may be welded to the load converter. The back Y-shaped ring comprises a first ring, a second ring and a third ring, the first ring is connected with the back end socket, the second ring is connected with the column section, and the third ring is welded with the front storage tank management device. The third fixed ring, the first fixed ring, the column section, the second ring and the third ring are coaxial.
The common-bottom connecting ring, the front Y-shaped ring and the rear Y-shaped ring are all integrally forged pieces.
Specifically, the front Y-ring is typically machined using a forged ring. The rear Y-ring is typically machined using a forged ring. The common-bottom connecting ring is generally formed by a ring forging machine.
The column section adopts a wall plate reinforcement structure which is machined or chemically milled and is usually formed by welding at 4-8 equal parts in the circumferential direction. The wall plate reinforcement structure comprises an inner layer which is a thin-wall skin and an outer layer which is a grid structure.
The common bottom is divided into three layers along the radius direction of the spherical crown, the upper layer is formed by spinning or superplastic forming with the propellant compatible plate in the upper storage tank, the lower layer is formed by spinning or superplastic forming with the propellant compatible plate in the lower storage tank, and the middle layer is a heat insulation layer. The insulating layer is typically 20-50mm thick.
Specifically, to the end storage tank is altogether gone up to liquid hydrogen/liquid oxygen, the aluminum alloy material is all compatible with liquid hydrogen and liquid oxygen, so upper strata and lower floor are the aluminum alloy material, upper strata and lower floor body coupling are provided with between upper strata and the lower floor and fill the chamber, and the insulating layer is located and fills the intracavity.
The heat insulation layer is made of any one of polyimide and polyurethane foam. The material of the thermal insulation layer is preferably polyimide.
Through the arrangement of the common-bottom structure, the common-bottom rigidity is improved, and the common-bottom bearing capacity is ensured. And the volume of the upper and lower storage tanks is changed by adjusting the size of the common bottom to meet the requirement of the mixing ratio of the engine.
The end enclosure of the rear storage tank is formed by spinning or superplastic forming of a plate compatible with the propellant in the lower storage tank.
The front storage tank management devices are composed of guide plates and liquid accumulators, the number of the front storage tank management devices is three, and the three front storage tank management devices are uniformly distributed along the axial included angle of 120 degrees, so that liquid which is not aerated in the upper storage tank can be conveyed to the engine under different working conditions. The upper part of the liquid accumulator is welded on the rear Y-shaped ring, the lower part of the liquid accumulator is welded on the common-bottom connecting ring, and the rest part of the liquid accumulator is welded on the outer wall of the storage tank.
The rear storage tank management device is composed of a guide plate and a liquid accumulator, the guide plate is uniformly distributed along the circumferential direction with an included angle of 90 degrees, and the condition that liquid which is not aerated in the upper storage tank can be conveyed to the engine under different working conditions is guaranteed. The rear storage box management device is arranged at the bottom of the rear storage box end enclosure.
In summary, the present application at least includes the following beneficial technical effects:
(1) the common-bottom storage tank is integrated in a simple outer envelope of the ellipsoidal head and the column section, so that the space configuration pressure of the spacecraft is effectively reduced, and meanwhile, the specific surface area of the storage tank is reduced, and the evaporation capacity of the low-temperature storage tank is conveniently controlled;
(2) the column section of the common-bottom storage tank adopts a skin reinforced structure, so that the specific rigidity of the storage tank is effectively improved, and the normal operation under a complex and strict mechanical environment is ensured;
(3) the combination of the liquid hydrogen and liquid oxygen management devices effectively meets the requirement that the spacecraft supplies the engine with large flow respectively under different microgravity and high acceleration environments;
(4) the low-temperature common-bottom storage tank is simple in appearance structure, convection heat transfer can be effectively reduced through outer-layer foam spraying, the low-temperature common-bottom storage tank can be applied to high-efficiency low-temperature upper-level carrying, radiation heat transfer can be greatly reduced through composite variable-density multi-layer heat insulation implementation, and the low-temperature common-bottom storage tank can be applied to a deep space exploration task of space track transfer.
Drawings
FIG. 1 is a schematic view of the overall structure of a common sump tank in an embodiment of the present invention;
FIG. 2 is a schematic view of the front Y-ring in the co-bottom bin of the present invention;
FIG. 3 is a rear Y-ring schematic view of the common floor tank of the present invention;
FIG. 4 is a schematic view of a bottom-shared attachment ring in the bottom-shared storage tank of the present invention;
description of reference numerals: 1. a population flange; 2. a front end enclosure;
3. a front Y-shaped ring; 301. a first retaining ring; 302. a second retaining ring; 303. a third fixing ring;
4. a column section; 5. sharing the bottom;
6. a rear Y-shaped ring; 601. a first ring; 602. a second ring; 603. a third ring;
7. sealing the end;
9. a common-bottom connecting ring; 901. a first connecting ring; 902. a second connection ring; 903. a fifth connecting ring; 904. a third connecting ring; 905. a fourth connecting ring;
10. sealing the end of the rear storage tank; 11. and a rear storage box management device.
Detailed Description
The present application is described in further detail below with reference to the following figures and specific examples:
the embodiment of the application discloses a force-bearing type low-temperature common-bottom storage tank for a spacecraft.
Referring to fig. 1, the force-bearing type low-temperature common-bottom storage tank for the spacecraft comprises a front storage tank, a common bottom 5 and a rear storage tank which are sequentially connected from top to bottom, wherein the common bottom 5 is connected between the front storage tank and the rear storage tank through a common-bottom connecting ring 9.
Referring to fig. 2 and 3, the front storage tank comprises a front seal head 2, a front Y-shaped ring 3, a column section 4, a rear Y-shaped ring 6 and a rear seal head 7 which are welded in sequence. Preceding Y shape ring 3 includes first solid fixed ring 301, the solid fixed ring of second 302 and the solid fixed ring of third 303, and first solid fixed ring 301 is connected with preceding head 2, and the solid fixed ring of second 302 is connected with column section 4, the solid fixed ring of third 303 with load converter welding. The rear Y-shaped ring 6 comprises a first ring 601, a second ring 602 and a third ring 603, wherein the first ring 601 is connected with the rear end socket 7, and the second ring 602 is connected with the column section 4. The third stationary ring 303, the first stationary ring 301, the column section 4, the second ring 602 and the third ring 603 are coaxial.
Referring to fig. 1 and 4, the rear tank comprises a rear tank head 10, the rear tank head 10 is ellipsoidal with the same size as the rear head 7, and the rear tank head 10 is formed by spinning or superplastic forming of a plate material compatible with the propellant in the lower tank. The rear end enclosure 7 is provided with a mounting hole coaxial with the rear end enclosure 7, the common bottom connecting ring 9 is connected to the mounting hole of the rear end enclosure 7, the common bottom 5 and the rear storage tank end enclosure 10 are both connected to the common bottom connecting ring 9, and the rear storage tank end enclosure 10 is connected to the mounting hole of the rear end enclosure 7 and is located below the common bottom 5.
The common-bottom connecting ring 9 comprises a first connecting ring 901, a second connecting ring 902, a third connecting ring 904, a fourth connecting ring 905 and a fifth connecting ring 903, wherein one end of the first connecting ring 901 is integrally connected with one end of the rear end enclosure 7, the third connecting ring 904 is connected with the common bottom 5, and the fifth connecting ring 903 is sequentially arranged on the common bottom connecting ring 904. The first connecting ring 901 and the third connecting ring 904 are in the same profile as the rear head 7. The second 902 and fourth 905 attachment rings are of the same profile as the common base 5.
The common bottom connecting ring 9, the front Y-shaped ring 3 and the rear Y-shaped ring 6 are all integrally forged pieces.
The column section is of a wall plate reinforced structure, the inner layer is a thin-wall skin, the outer layer is of a grid structure, and the column section is usually formed by thick plate milling or chemical milling.
Referring to fig. 4, the common bottom 5 is in a spherical crown shape with a convex middle part, the common bottom 5 is divided into three layers along the radius direction of the spherical crown, the upper layer adopts a propellant compatible plate in an upper storage tank for spinning or superplastic forming, the lower layer adopts a propellant compatible plate in a lower storage tank for spinning or superplastic forming, and the middle layer is a heat insulation layer. In this embodiment, the low temperature propellant in the upper storage tank is liquid hydrogen, the low temperature propellant in the lower storage tank is liquid oxygen, the material of upper strata and lower floor is the aluminum alloy, upper strata and lower floor body coupling are provided with between upper strata and the lower floor and fills the chamber, and the insulating layer is located and fills the intracavity.
The front storage tank also comprises a front storage tank management device used for conveying the non-aerated liquid in the front storage tank, and the rear storage tank also comprises a rear storage tank management device 11 used for conveying the non-aerated liquid in the rear storage tank. The front tank management device is connected to the third ring 603 and the rear tank management device 11 is provided at the bottom of the rear tank head 10.
The implementation principle of the application is as follows: the front storage tank and the rear storage tank are uniquely designed, so that the common-bottom 5 storage tank only has one column section 4 included by the front storage tank, and the common-bottom storage tank can have a larger diameter; and furthermore, the connection structure of each part of the common-bottom storage tank, the common-bottom structure, the column section 4 structure and the like are arranged, so that the common-bottom storage tank can be thicker in diameter, and the strength of the common-bottom storage tank is ensured. Through the setting of this application, the liquid in the last storage tank flows through the back storage tank management device 11 of last storage tank outer wall, need not set up more extra outflow pipeline, and the outside simple structure of total end storage tank effectively reduces spacecraft space configuration pressure, reduces the storage tank specific surface area simultaneously and is convenient for low temperature storage tank evaporation capacity control.
The invention has not been described in detail and is within the skill of the art.
The above are preferred embodiments of the present application, and the scope of protection of the present application is not limited thereto, so: all equivalent changes made according to the structure, shape and principle of the present application shall be covered by the protection scope of the present application.
Claims (10)
1. A force-bearing type low-temperature common-bottom storage box for a spacecraft is characterized in that: comprises a front storage box, a common bottom (5) and a rear storage box which are connected in sequence from top to bottom,
the front storage box comprises a front seal head (2), a column section (4) and a rear seal head (7) which are welded in sequence; the rear storage tank comprises a rear storage tank end enclosure (10);
the rear end enclosure (7) is provided with a mounting hole coaxial with the rear end enclosure (7), the common bottom (5) is connected to the mounting hole of the rear end enclosure (7), the common bottom (5) is in a spherical crown shape with a convex middle part, and the rear storage tank end enclosure (10) is connected to the mounting hole of the rear end enclosure (7) and is positioned below the common bottom (5).
2. The force-bearing type low-temperature common-bottom storage tank for the spacecraft of claim 1, which is characterized in that: the common-bottom connecting ring (9) is arranged on the common bottom (5), the common-bottom connecting ring (9) comprises a first connecting ring (901), a second connecting ring (902), a third connecting ring (904), a fourth connecting ring (905) and a fifth connecting ring (903), one end of the first connecting ring (901), one end of the second connecting ring (902), one end of the third connecting ring (904), one end of the fourth connecting ring (905) and one end of the fifth connecting ring (903) are integrally connected and are sequentially arranged, the first connecting ring (901) is connected with a mounting hole of the rear end enclosure (7), the second connecting ring (902) is connected with the common bottom (5), and the third connecting ring (904) is connected with the rear end enclosure (10).
3. The force-bearing type low-temperature common-bottom storage tank for the spacecraft of claim 1, which is characterized in that: the rear storage tank seal head (10) is in an ellipsoid shape with the same surface size as the rear seal head (7), and the first connecting ring (901) and the third connecting ring (904) are in the same surface size as the rear seal head (7).
4. The force-bearing type low-temperature common-bottom storage tank for the spacecraft of claim 1, which is characterized in that: the second connecting ring (902) and the fourth connecting ring (905) are in the same profile with the common bottom (5).
5. The force-bearing type low-temperature common-bottom storage tank for the spacecraft of claim 2, which is characterized in that: the front storage box further comprises a front Y-shaped ring (3) and a rear Y-shaped ring (6), the front Y-shaped ring (3) comprises a first fixing ring (301), a second fixing ring (302) and a third fixing ring (303), the first fixing ring (301) is connected with the front seal head (2), the second fixing ring (302) is connected with the column section (4), the rear Y-shaped ring (6) comprises a first ring (601), a second ring (602) and a third ring (603), the first ring (601) is connected with the rear seal head (7), and the second ring (602) is connected with the column section (4); the third fixed ring (303), the first fixed ring (301), the column section (4), the second ring (602) and the third ring (603) are coaxial.
6. The force-bearing type low-temperature common-bottom storage tank for the spacecraft of claim 5, which is characterized in that: the common-bottom connecting ring (9), the front Y-shaped ring (3) and the rear Y-shaped ring (6) are all integrated forged pieces.
7. The force-bearing type low-temperature common-bottom storage tank for the spacecraft of claim 1, which is characterized in that: the column section (4) is of a wall plate reinforced structure, the inner layer is a thin-wall skin, the outer layer is of a grid structure, and the column section is usually formed by milling or chemical milling of a thick plate machine.
8. The force-bearing type low-temperature common-bottom storage tank for the spacecraft of claim 1, which is characterized in that: the common bottom (5) is divided into three layers along the radius direction of the spherical crown, the upper layer is formed by spinning or superplastic forming with the compatible plate of the propellant in the upper storage tank, the lower layer is formed by spinning or superplastic forming with the compatible plate of the propellant in the lower storage tank, and the middle layer is a heat insulation layer.
9. The force-bearing type low-temperature common-bottom storage tank for the spacecraft of claim 1, which is characterized in that: the rear storage tank end socket (10) is formed by spinning or superplastic forming of a plate compatible with a propellant in the lower storage tank.
10. The force-bearing type low-temperature common-bottom storage tank for the spacecraft of claim 1, which is characterized in that: the front storage tank also comprises a front storage tank management device used for conveying the non-aerated liquid in the front storage tank, the front storage tank management device is connected to the fifth connecting ring (903), and the rear storage tank also comprises a rear storage tank management device (11) used for conveying the non-aerated liquid in the rear storage tank.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210343951.3A CN114922744A (en) | 2022-03-31 | 2022-03-31 | Force-bearing type low-temperature common-bottom storage tank for spacecraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210343951.3A CN114922744A (en) | 2022-03-31 | 2022-03-31 | Force-bearing type low-temperature common-bottom storage tank for spacecraft |
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| Publication Number | Publication Date |
|---|---|
| CN114922744A true CN114922744A (en) | 2022-08-19 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202210343951.3A Pending CN114922744A (en) | 2022-03-31 | 2022-03-31 | Force-bearing type low-temperature common-bottom storage tank for spacecraft |
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Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| FR1276533A (en) * | 1960-11-15 | 1961-11-17 | United Aircraft Corp | System for supplying liquid propellants and regulating the engine of a rocket |
| CN104648696A (en) * | 2014-12-11 | 2015-05-27 | 上海空间推进研究所 | Metal propellant storage tank for spaceflight and manufacturing method thereof |
| CN106742074A (en) * | 2016-12-20 | 2017-05-31 | 江苏豪然喷射成形合金有限公司 | Ultra lightweighting spacecraft propulsion agent tank |
| US20180281992A1 (en) * | 2015-04-22 | 2018-10-04 | Keystone Engineering Company | Center of mass control of liquid tanks for spacecraft use |
| CN112282968A (en) * | 2020-10-09 | 2021-01-29 | 北京宇航***工程研究所 | Low-temperature common-bottom storage tank for conveying propellant in inner |
-
2022
- 2022-03-31 CN CN202210343951.3A patent/CN114922744A/en active Pending
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| FR1276533A (en) * | 1960-11-15 | 1961-11-17 | United Aircraft Corp | System for supplying liquid propellants and regulating the engine of a rocket |
| CN104648696A (en) * | 2014-12-11 | 2015-05-27 | 上海空间推进研究所 | Metal propellant storage tank for spaceflight and manufacturing method thereof |
| US20180281992A1 (en) * | 2015-04-22 | 2018-10-04 | Keystone Engineering Company | Center of mass control of liquid tanks for spacecraft use |
| CN106742074A (en) * | 2016-12-20 | 2017-05-31 | 江苏豪然喷射成形合金有限公司 | Ultra lightweighting spacecraft propulsion agent tank |
| CN112282968A (en) * | 2020-10-09 | 2021-01-29 | 北京宇航***工程研究所 | Low-temperature common-bottom storage tank for conveying propellant in inner |
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