WO2015165133A1 - 一种用于空间飞行器中推进剂贮箱的蓄液器 - Google Patents
一种用于空间飞行器中推进剂贮箱的蓄液器 Download PDFInfo
- Publication number
- WO2015165133A1 WO2015165133A1 PCT/CN2014/077866 CN2014077866W WO2015165133A1 WO 2015165133 A1 WO2015165133 A1 WO 2015165133A1 CN 2014077866 W CN2014077866 W CN 2014077866W WO 2015165133 A1 WO2015165133 A1 WO 2015165133A1
- Authority
- WO
- WIPO (PCT)
- Prior art keywords
- accumulator
- liquid
- base
- mesh
- blade
- Prior art date
Links
- 239000003380 propellant Substances 0.000 title claims abstract description 34
- 239000007788 liquid Substances 0.000 claims abstract description 102
- 238000005192 partition Methods 0.000 claims abstract description 31
- 229910001069 Ti alloy Inorganic materials 0.000 claims description 3
- 239000000956 alloy Substances 0.000 claims description 3
- 238000009434 installation Methods 0.000 claims 5
- 238000003825 pressing Methods 0.000 abstract description 9
- 238000007599 discharging Methods 0.000 abstract description 5
- 230000005486 microgravity Effects 0.000 description 10
- 230000001133 acceleration Effects 0.000 description 8
- 238000009825 accumulation Methods 0.000 description 4
- 238000001595 flow curve Methods 0.000 description 4
- 238000006073 displacement reaction Methods 0.000 description 2
- 239000012530 fluid Substances 0.000 description 2
- 238000000034 method Methods 0.000 description 2
- 238000000926 separation method Methods 0.000 description 2
- 230000002159 abnormal effect Effects 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000005540 biological transmission Effects 0.000 description 1
- 230000007423 decrease Effects 0.000 description 1
- 230000007812 deficiency Effects 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 239000007791 liquid phase Substances 0.000 description 1
- 230000014759 maintenance of location Effects 0.000 description 1
- 239000012071 phase Substances 0.000 description 1
- 239000007787 solid Substances 0.000 description 1
Classifications
-
- 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
-
- 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
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F17—STORING OR DISTRIBUTING GASES OR LIQUIDS
- F17C—VESSELS FOR CONTAINING OR STORING COMPRESSED, LIQUEFIED OR SOLIDIFIED GASES; FIXED-CAPACITY GAS-HOLDERS; FILLING VESSELS WITH, OR DISCHARGING FROM VESSELS, COMPRESSED, LIQUEFIED, OR SOLIDIFIED GASES
- F17C13/00—Details of vessels or of the filling or discharging of vessels
- F17C13/008—Details of vessels or of the filling or discharging of vessels for use under microgravity conditions
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F17—STORING OR DISTRIBUTING GASES OR LIQUIDS
- F17C—VESSELS FOR CONTAINING OR STORING COMPRESSED, LIQUEFIED OR SOLIDIFIED GASES; FIXED-CAPACITY GAS-HOLDERS; FILLING VESSELS WITH, OR DISCHARGING FROM VESSELS, COMPRESSED, LIQUEFIED, OR SOLIDIFIED GASES
- F17C2270/00—Applications
- F17C2270/01—Applications for fluid transport or storage
- F17C2270/0186—Applications for fluid transport or storage in the air or in space
- F17C2270/0194—Applications for fluid transport or storage in the air or in space for use under microgravity conditions, e.g. space
Definitions
- the present invention relates to an accumulator for space fluid management, particularly for use in a propellant tank in a spacecraft.
- Propellant tanks are widely used in various space vehicles such as satellites, spacecraft, space stations, and launch vehicles because of their high reliability and long life in weightless environments.
- the core technology of the propellant tank is its internal propellant management unit (referred to as PMD).
- PMD internal propellant management unit
- PMD's management capabilities are key indicators of tank performance.
- the goal of the PMD design is that the PMD can deliver liquid reliably and bubble-free at all times.
- the PMD of the propellant tank used in spacecraft, especially on satellites is a net type, which is a capillary element for collecting propellant, and the propellant is transported by the pipeline to the liquid port end of the propellant tank.
- the limitations of this type of propellant management device have gradually emerged, which has become an unfavorable factor restricting the development of satellite industry.
- the mesh type PMD has the following disadvantages: For example, the capillary network structure has low strength, is easy to be damaged, is easy to be contaminated, and has low reliability. At the same time, it is necessary to set a complicated fluid transmission channel, resulting in a large weight of the propellant management device and a slow filling speed. .
- the propellant tank is required to not only accumulate propellant in various microgravity environments under normal working conditions, but also to store in the extreme cases of various abnormal conditions.
- Adequate propellant such as when the Z-direction (axial) rotational angular velocity is large, and the reverse acceleration is large (the satellite also appears when rotating along the X and Y axes), it can ensure sufficient liquid storage. Therefore, it is necessary to use a new type of accumulator which is simple in structure, high in reliability, large in liquid storage, low in use of the screen, and mainly in the form of a plate structure.
- the accumulators have been disclosed in various embodiments, and some accumulators are disclosed, which are also suitable for use in propellant tanks, as disclosed in U.S. Patent No. 4, 559, 565, issued to s.
- An accumulator is described, for example, in US Pat. No. 4,553, 565 A, in which the liquid storage and the separation of the gas phase from the liquid phase are effected by means of a plurality of radially spaced vanes.
- the disadvantages are: small liquid storage, in some extremes that may occur Under the circumstances (such as large axial angular velocity of the tank, large reverse acceleration or large lateral acceleration, etc.), it is impossible to ensure sufficient liquid storage without air entrapment.
- a spherical crown-like accumulator is also described in DE 100 40 755 A1, in which an inner cone-shaped plate is arranged in the accumulator, and some screen collectors and several guides are arranged in appropriate areas according to the requirements of the on-track operating conditions.
- the flow blade has the disadvantages of: the structure is complicated, the sieve is used more, and the liquid storage amount is small.
- the technical problem of the present invention is to overcome the deficiencies of the prior art and provide an accumulator for a propellant tank in a spacecraft, which has excellent performance, simple structure, high reliability, large liquid storage capacity, and micro Gravity environment work has strong adaptability, can repeatedly fill the liquid in the accumulator and discharge liquid from the accumulator, the liquid filling and discharging speed is large, and the ground can be repeatedly filled.
- An accumulator for a propellant tank in a spacecraft comprising an air duct, a cover plate, a casing, a blade, a strut, a base, a channel window platen, a passage window mesh, an accumulator mesh, a fixed block and a storage Liquid mesh platen;
- the pillar includes a center pillar, an upper support disc and a lower support disc; the upper support disc and the lower support disc are coaxially connected by a central column, the upper support disc is located at the top of the center pillar, and the lower support disc is located at the lower part of the center pillar and the bottom of the center pillar
- the end passes through the lower support disc; the upper support disc and the lower support disc of the strut are radially distributed with a plurality of mounting seams, and the mounting seams of the upper support discs are in one-to-one correspondence with the mounting seams on the lower support disc, each of the groups a corresponding mounting slot is inserted with a blade, and the blade is fixedly connected with the mounting seam;
- the base is a cylindrical structure with an upper and lower opening, and has a circular partition with a plurality of through holes therein, and the base has a plurality of passage windows on the wall below the circular partition, and the passage window mesh is covered
- the base is located outside the cylindrical wall below the circular partition, covering all the passage windows, and the passage window pressing plate will pass the passage
- the window mesh is fixed on the wall of the base;
- the accumulator mesh and the accumulator mesh plate with a plurality of through holes are sequentially placed above the circular partition in the base, and the edges of the accumulator mesh and the edges of the accumulator mesh plate are The circular partition is fixedly connected;
- the outer casing is a truncated-shaped thin-walled structure with open ends, the open end of the small diameter is fixed at the top end of the base, the blade and the pillar are integrally formed inside the outer casing, and the pillar passes through the bottom end of the lower support plate and the base Circular partitions are fixedly connected;
- the cover plate is fixed on the open end of the outer diameter of the outer casing, and the whole of the blade and the pillar is enclosed inside the outer casing, and the fixing block fixes the air guiding pipe on the cover plate, and the discharge block is used for discharging the liquid when the liquid is filled on the ground.
- a plurality of through holes are distributed in the vane for liquid circulation and trapping gas in the accumulator and between the vanes, and a plurality of angled regions are formed between the vanes for liquid guiding and accumulating.
- a gap between the edge of the blade and the outer casing communicates with a gap between the edge of the blade and the cover. There is no gap between the accumulator mesh, the accumulator mesh platen and the circular partition of the base, and the through hole on the accumulator mesh plate and the through hole on the circular partition --correspond.
- the circular partition inside the base and the base are integrated.
- the cover plate is a rotating body thin-walled structure in which the side wall is concave toward the central axis, and is opened up and down.
- the height of the cover is greater than or equal to half the height of the outer casing, and a gap is provided between the open end of the cover having a small diameter and the upper support disk at the top end of the strut.
- the channel window mesh and the accumulator mesh are both titanium alloy materials.
- the accumulator main body structure of the present invention comprises a cover plate, an outer casing, a base and an integral structure composed of blades and struts (small liquid storage) as compared with the accumulator described in US Pat. No. 4,986,398 A and DE 100 40 755 A1.
- the structure is simple, and the accumulator of the present invention has a higher structural strength due to the concentrated distribution of the main structures, and the use of the contaminated mesh-collected collector and piping described in US Pat. No. 4,986,398 A and DE 100 40 755 A1 is not used.
- the accumulator of the invention has higher reliability.
- the accumulator of the present invention is formed by a side wall to a cover plate of a rotating body thin-walled structure of the inner shaft IHJ and a casing of a truncated-shaped thin-walled structure which is open at both ends.
- the enclosed structure and the built-in integral structure consisting of blades and struts with through-holes provide a wide range of functions for large liquid storage and microgravity environments, even in extreme operating conditions such as tank shafts. In the case of a large angular velocity of rotation, a large reverse acceleration, or a large lateral acceleration, it is possible to ensure a sufficient amount of liquid that is not trapped.
- the accumulator of the present invention is completed in a short time by the channel window driven by the angle gap between the blades and the gap between the blade and the cover plate and the outer casing when the liquid inside the liquid is discharged quickly.
- the external liquid pool of the accumulator fills the accumulator with liquid, ensuring sufficient liquid retention in the accumulator.
- the accumulator mesh and the channel window mesh of the accumulator of the present invention have a small amount of use and a concentrated distribution, and are easy to realize a large liquid filling and discharging speed. And the ground repeat feature.
- Figure 1 is a cross-sectional view of the accumulator of the present invention
- Figure 2 is an exploded view of the accumulator of the present invention
- Figure 3 is a schematic structural view of a small and medium-sized accumulator according to the present invention.
- Figure 4 is a flow curve of the accumulator when the liquid is discharged in a microgravity environment
- Figure 5 is a flow curve of an accumulator filled with liquid in a microgravity environment.
- Figure 6 is a schematic structural view of a pillar of the present invention.
- Figure 7 is a schematic structural view of a base of the present invention.
- Figure 8 is a schematic view showing the structure of the passage window pressing plate of the present invention.
- the present invention provides an accumulator for a propellant tank in a spacecraft, comprising an air duct 1, a cover plate 2, a casing 3, a blade 4, a strut 5, a base 6, and a passage.
- Window platen 7, channel window mesh 8, accumulator mesh 9, fixed block 10 and accumulator mesh plate 11; the passage window mesh 8 and the accumulator mesh 9 are both titanium alloy materials.
- the pillar 5 includes a center pillar 51, an upper support disk 52 and a lower support disk 53; the upper support disk 52 and the lower support disk 53 are coaxially connected by a center pillar 51, and the upper support disk 52 is located at the center pillar 51.
- the top and bottom support discs 53 are located at the lower portion of the center post 51 and the bottom end of the center post 51 passes through the lower support disc 53; the upper support disc 52 and the lower support disc 53 of the strut 5 are radially distributed with a plurality of mounting seams and upper
- the mounting seams of the support discs 52 correspond one-to-one with the mounting seams on the lower support discs 53.
- Each of the sets of corresponding mounting seams is provided with a vane 4 to which the vane 4 is fixedly attached.
- a plurality of through holes are distributed in the vane 4 for liquid circulation and trapping of gas in the accumulator and between the vanes 4.
- a plurality of angled regions are formed between the vanes 4 for liquid flow and accumulation.
- the gap between the edge of the blade 4 and the outer casing 3 communicates with the gap between the edge of the blade 4 and the cover 2.
- the base 6 is a cylindrical structure which is open at the top and bottom, and has a circular partition having a plurality of through holes therein, and a circular partition inside the base 6 and the base 6 are integrated.
- the base 6 has a plurality of passage windows on the wall of the cylinder below the circular partition, the passage window mesh
- the passage window pressing plate 7 is a cylindrical thin-walled structure which is open at the top and bottom, and has a plurality of through holes on its side wall.
- the through hole on the channel window platen 7 should be one to one of the channel windows on the wall below the circular partition in the base 6. correspond.
- the accumulator web 9 and the accumulator web press plate 11 with a plurality of through holes are sequentially placed on the circular partition in the base 6, and the edge of the accumulator web 9 and the accumulator web press plate 11 The edges are fixedly connected to the circular partition; the reservoir web 9, the reservoir web pressing plate 11 and the circular partition in the base 6 are seamless, and the accumulator mesh
- the through hole on the pressure plate 11 corresponds to the through hole on the circular partition plate.
- the outer casing 3 is a truncated-shaped thin-walled structure having open ends, and an open end having a small diameter is fixed to the top end of the base 6, and the whole formed by the vane 4 and the strut 5 is placed inside the outer casing 3, and the strut 5 passes through the lower support plate 53.
- the bottom end is fixedly connected with the circular partition of the base 6; the whole formed by the blade 4 and the pillar 5 is a small accumulator, as shown in FIG. 3;
- the cover plate 2 is fixed on the open end of the outer casing 3 having a large diameter, and the whole of the blade 4 and the pillar 5 is enclosed inside the outer casing 3, and the fixing block 10 fixes the air pipe 1 to the cover plate 2 for the accumulator
- the gas in the angular space 15 formed by the cover 2 and the outer casing 3 is discharged when the ground is filled with liquid.
- the cover plate 2 is a rotating body thin-walled structure in which a side wall is recessed toward a central axis thereof, and is opened up and down.
- the height of the cover 2 is greater than or equal to half the height of the outer casing 3, and a gap is left between the open end of the cover 2 having a small diameter and the upper support disk 52 at the top end of the post 5.
- the accumulator of the present invention is usually located at the outlet of the propellant tank in the spacecraft, by means of which the angular space formed by the outer casing 3 and the inner wall surface 13 of the tank at the outlet of the propellant tank 14 and the angular space 15 formed by the cover 2 and the outer casing 3, to achieve effective separation of the driving gas and liquid and to accumulate sufficient liquid without trapping at the liquid outlet of the propellant tank.
- a bubble-free liquid pool 12 is formed in the base 6 through the accumulator web 8 and the passage window web 9, which ensures that no gas collects directly on the accumulator web 9, and does not It affects the flow of liquid in the accumulator, ensuring reliable and bubble-free liquid accumulation and displacement in any working condition and at all times.
- the accumulator of the present invention realizes a wide range of functions of a large liquid storage capacity and a microgravity environment by means of the angled space 15 and the built-in small accumulator structure, even in some extreme conditions that may occur, such as When the axial rotation angular velocity of the tank is large, the reverse acceleration is large, or the lateral acceleration is large, etc., it is possible to ensure sufficient liquid storage without air entrapment, and at the same time repeatedly fill the liquid in the accumulator and refill the liquid. The function of draining liquid in the accumulator.
- Figure 4 shows the flow curve of the accumulator when it is draining liquid in a microgravity environment.
- the accumulator is substantially filled with liquid, and the driving gas is trapped and collected on the open end of the cover plate 2 having a small diameter above the small accumulator to form a small air chamber 16.
- the liquid accumulated in the small accumulator under the action of the driving gas flows through the accumulator web 9 (indicated by arrow 15) into the liquid bath 12.
- the liquid accumulated in the angular space 15 flows along the blade 4 to the bottom of the small accumulator under surface tension.
- the air chamber 16 in the accumulator becomes larger and larger, and the air chamber first expands along the inner wall surface of the cover 2, and then expands along the outer casing 3 and the vane 4 until the liquid in the accumulator Substantially emptied, at which point the air chamber is substantially in the shape of the air chamber 19 in Fig. 5; at the same time, the outer casing 3 of the accumulator and the inner wall surface 13 of the tank are formed at the outlet of the propellant tank.
- the liquid in the angled space 14 flows through the passage window web 8 (indicated by arrow 18) under the action of the drive gas into the liquid bath 12.
- Figure 5 shows the flow curve of the accumulator when filling the liquid in a microgravity environment.
- the liquid is substantially evacuated in the accumulator, and the air chamber 19 formed by the driving gas substantially occupies the entire inner chamber of the accumulator, and is only stored in the lower portion of the small accumulator and the angle space 15 in the accumulator. Leave a small amount of liquid.
- the liquid accumulated in the angular space 14 at the liquid outlet of the propellant tank formed in the outer casing 3 of the accumulator and the inner wall surface 13 of the tank rapidly flows through the passage window mesh 8 (through The arrow 20 enters the liquid pool 12 and then flows through the accumulator web 9 into the small accumulator.
- the gas in the accumulator is squeezed from the open end of the cover plate 2 (shown by arrow 21), and the gas chamber 19 is continuously reduced until the entire accumulator is substantially filled with liquid.
- the air chamber 19 generally changes to the shape of the air chamber 16 in FIG.
- a solid accumulator is prepared, the volume of the accumulator is 7.25L, the maximum liquid storage capacity is 7.2L, and the effective liquid storage capacity can reach 6.98L.
- the accumulator is filled in the microgravity space environment. The liquid takes less than 720 s at a time, and the maximum discharge speed is not less than 12 ml/s in a lateral acceleration (0.001 g) space environment.
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- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Remote Sensing (AREA)
- Aviation & Aerospace Engineering (AREA)
- Filling Or Discharging Of Gas Storage Vessels (AREA)
- Supply Devices, Intensifiers, Converters, And Telemotors (AREA)
Abstract
Description
Claims
Priority Applications (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
CA2922998A CA2922998C (en) | 2014-04-29 | 2014-05-20 | Hydraulic accumulator for propellant tank in spacecraft |
US15/023,266 US9643741B2 (en) | 2014-04-29 | 2014-05-20 | Hydraulic accumulator for propellant tank in spacecraft |
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
CN201410178837.5A CN103950557B (zh) | 2014-04-29 | 2014-04-29 | 一种用于空间飞行器中推进剂贮箱的蓄液器 |
CN201410178837.5 | 2014-04-29 |
Publications (1)
Publication Number | Publication Date |
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WO2015165133A1 true WO2015165133A1 (zh) | 2015-11-05 |
Family
ID=51327955
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
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PCT/CN2014/077866 WO2015165133A1 (zh) | 2014-04-29 | 2014-05-20 | 一种用于空间飞行器中推进剂贮箱的蓄液器 |
Country Status (4)
Country | Link |
---|---|
US (1) | US9643741B2 (zh) |
CN (1) | CN103950557B (zh) |
CA (1) | CA2922998C (zh) |
WO (1) | WO2015165133A1 (zh) |
Families Citing this family (17)
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---|---|---|---|---|
US9970389B2 (en) * | 2014-03-06 | 2018-05-15 | The Boeing Company | Antivortex device and method of assembling thereof |
CN104533662B (zh) * | 2014-12-21 | 2016-06-01 | 北京工业大学 | 一种厚度不均匀带孔叶片的推进剂管理装置 |
CN104691786B (zh) * | 2015-01-07 | 2016-08-24 | 北京控制工程研究所 | 一种用于推进剂贮箱中的推进剂管理装置 |
US10611503B2 (en) * | 2015-04-22 | 2020-04-07 | Keystone Engineering Company | Center of mass control of liquid tanks for spacecraft use |
CN105346734B (zh) * | 2015-11-20 | 2018-03-23 | 上海空间推进研究所 | 一种可排气式表面张力贮箱 |
CN105642453B (zh) * | 2016-03-23 | 2018-02-13 | 北京航天动力研究所 | 一种高压大流量微重力离心气液分离装置 |
US10065751B2 (en) * | 2016-04-05 | 2018-09-04 | Orbital Atk, Inc. | Liquid storage tanks and systems and propulsion systems for space vehicles and related methods |
CN105854353B (zh) * | 2016-04-05 | 2018-02-06 | 中国空间技术研究院 | 一种新型ehd空间燃料贮箱气液相分离管理系统 |
CN106394932B (zh) * | 2016-09-23 | 2018-10-26 | 北京空间飞行器总体设计部 | 一种具有高水平微重力环境的返回式卫星 |
EP3702290A4 (en) * | 2017-10-26 | 2021-08-04 | Japan Aerospace Exploration Agency | LIQUID BEHAVIOR SUPPRESSION DEVICE |
US11092111B1 (en) | 2018-12-10 | 2021-08-17 | United Launch Alliance, L.L.C. | Vapor retention device |
CN111232250B (zh) * | 2020-01-17 | 2021-10-29 | 上海空间推进研究所 | 一种板式表面张力贮箱 |
CN112610361B (zh) * | 2020-12-29 | 2021-10-29 | 上海空间推进研究所 | 一种用于嵌入式承力贮箱的推进剂管理装置 |
US11939086B2 (en) * | 2021-02-17 | 2024-03-26 | The Boeing Company | Fuel tanks and reusable launch vehicles comprising these fuel tanks |
CN113247311B (zh) * | 2021-06-07 | 2022-09-27 | 上海空间推进研究所 | 一种柱形隔膜 |
CN114044169B (zh) * | 2021-10-21 | 2023-07-07 | 上海空间推进研究所 | 一种可补加的张力式推进剂贮箱及其制备方法 |
CN114455104B (zh) * | 2022-04-13 | 2022-07-12 | 北京凌空天行科技有限责任公司 | 一种液体飞行器推进剂贮箱消能器及推进装置 |
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2014
- 2014-04-29 CN CN201410178837.5A patent/CN103950557B/zh active Active
- 2014-05-20 CA CA2922998A patent/CA2922998C/en active Active
- 2014-05-20 US US15/023,266 patent/US9643741B2/en active Active
- 2014-05-20 WO PCT/CN2014/077866 patent/WO2015165133A1/zh active Application Filing
Patent Citations (5)
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US4976398A (en) * | 1988-11-02 | 1990-12-11 | Erno Raumfahrttechnik Gmbh | Fuel tank for aggressive liquid fuels |
US5279323A (en) * | 1991-12-19 | 1994-01-18 | Lockheed Missiles & Space Company, Inc. | Liquid management apparatus for spacecraft |
US20030056838A1 (en) * | 2001-09-21 | 2003-03-27 | Grayson Gary D. | Variable-gravity anti-vortex and vapor-ingestion-suppression device |
CN201553157U (zh) * | 2009-09-28 | 2010-08-18 | 北京控制工程研究所 | 贮箱板式推进剂管理装置 |
CN102518939A (zh) * | 2011-12-20 | 2012-06-27 | 北京控制工程研究所 | 一种板式推进剂管理装置的蓄液器 |
Also Published As
Publication number | Publication date |
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CN103950557A (zh) | 2014-07-30 |
US9643741B2 (en) | 2017-05-09 |
US20160311559A1 (en) | 2016-10-27 |
CN103950557B (zh) | 2016-05-04 |
CA2922998C (en) | 2016-10-04 |
CA2922998A1 (en) | 2015-11-05 |
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