CN107152606A - A kind of space cryogenic propellant tank - Google Patents
A kind of space cryogenic propellant tank Download PDFInfo
- Publication number
- CN107152606A CN107152606A CN201710374300.XA CN201710374300A CN107152606A CN 107152606 A CN107152606 A CN 107152606A CN 201710374300 A CN201710374300 A CN 201710374300A CN 107152606 A CN107152606 A CN 107152606A
- Authority
- CN
- China
- Prior art keywords
- tank
- vertical tube
- collector
- heat insulating
- cryogenic propellant
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Pending
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Classifications
-
- 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
- F17C1/00—Pressure vessels, e.g. gas cylinder, gas tank, replaceable cartridge
- F17C1/12—Pressure vessels, e.g. gas cylinder, gas tank, replaceable cartridge with provision for thermal insulation
-
- 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
- F17C2203/00—Vessel construction, in particular walls or details thereof
- F17C2203/03—Thermal insulations
- F17C2203/0304—Thermal insulations by solid means
- F17C2203/0329—Foam
- F17C2203/0333—Polyurethane
-
- 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
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Filling Or Discharging Of Gas Storage Vessels (AREA)
Abstract
The invention discloses a kind of space cryogenic propellant tank, including：Tank housing, blade, vertical tube, drain pipe, collector, heat insulating construction, blast pipe, air exhaust combination valve and pressure inlet；Heat insulating construction is evenly coated at tank hull outside；One end of tank enclosure interior is provided with blade, vertical tube and collector；Collector one end is on the inwall of tank housing；The other end of collector is provided with vertical tube；Around vertical tube some blades are uniformly distributed with radial；Provided with the drain pipe for passing heat insulating construction below collector；The other end of tank enclosure interior is provided with blast pipe and pressure inlet through tank housing and heat insulating construction；Blast pipe, which is located on the port on the outside of heat insulating construction, is additionally provided with air exhaust combination valve.The present invention realizes propellant positioning and managed, it is ensured that the not gas enclosure supply of propellant, and air cushion can be positioned at into fixed position, facilitates tank exhaust；Propellant lamination problem under cryogenic propellant storage for a long time and microgravity environment can also effectively be solved.
Description
Technical field
The present invention relates to propellant tank field, and in particular to one kind can apply to satellite, Upper Stage, airship, interspace
Detector and the cryogenic propellant tank of space station.
Background technology
Propellant tank is progress Propellant Management control in spacecraft dynamical system, is embodied as engine and provides not gas enclosure
The device of propellant.Propellant is divided into normal temperature propellant and cryogenic propellant, and the design and application of normal temperature propellant tank are more
Maturation, the characteristics of cryogenic propellant is due to its high-performance and environmental protection, the developing direction as Future Spacecraft dynamical system.
But due to low boiling point, easily evaporate, it is difficult to store, while becoming in spacecraft in the flight course such as rail, motor-driven, track holding, push away
Enter agent layering and non-directional problem is serious, normal temperature propellant tank design can not solve these problems, so as to greatly limit
Application of the cryogenic propellant in the long-term in-orbit aerial mission in space is made.
The content of the invention
The present invention is in order to solve the above technical problems, propose a kind of passive solar heat protection and vertical tube-blade surface tension force managing device
The cryogenic propellant tank being combined.
Above-mentioned technical problem is solved, the invention provides a kind of space cryogenic propellant tank, including：Tank housing,
Blade, vertical tube, drain pipe, collector, heat insulating construction, blast pipe, air exhaust combination valve and pressure inlet；
The heat insulating construction is evenly coated at the tank hull outside；
One end of the tank enclosure interior is provided with the blade, vertical tube and collector；Described collector one end is located at institute
On the inwall for stating tank housing；The collector other end is provided with the vertical tube；It is uniformly distributed around the vertical tube with radial
There are some blades；
Provided with the drain pipe for passing the heat insulating construction below the collector；
The other end of the tank enclosure interior is provided with blast pipe and supercharging through the tank housing and heat insulating construction
Pipe；The blast pipe, which is located on the port on the outside of heat insulating construction, is additionally provided with the air exhaust combination valve.
Further, space cryogenic propellant tank as the aforementioned, the tank housing for metal material spherical or
Ball column construction.
Further, space cryogenic propellant tank as the aforementioned, the heat insulating construction is moulded including polyurethane foam
The bed of material and thermal insulation layer, the inner surface of the polyurethane foam plastic layer are coated on the tank housing outer surface；The polyurethane
The outer surface of foam layer is coated with the thermal insulation layer.
Further, space cryogenic propellant tank as the aforementioned, the thermal insulation layer is by being outside to inside followed successively by mutually
The reflecting layer of adhesion and wall composition, the material in the reflecting layer is that aluminium foil, Kapton and polyimides of aluminizing are thin
Film one of which, the material of the wall is reticulated and loose shape fibrous material one of which.
Further, space cryogenic propellant tank as the aforementioned, the air exhaust combination valve includes diaphragm valve and row
Air valve；Described diaphragm valve one end connects the port of the blast pipe, and the other end connects the air bleeding valve.
Further, space cryogenic propellant tank as the aforementioned, the blade is that a kind of profile is multi-section circular arc
The metal material thin slice constituted with SPL.
Further, space cryogenic propellant tank as the aforementioned, the vane thickness is 0.1mm~2mm, described
Blade quantity is 8~64.
Further, space cryogenic propellant tank as the aforementioned, the vertical tube is arranged on the tank housing
Axial location, is a kind of angular metal material hollow tube of back taper wide at the top and narrow at the bottom；The narrower one end of the standpipe bubbler openings and institute
State collector adaptation connection.
Further, space cryogenic propellant tank as the aforementioned, the height of the vertical tube is tank body height
1/3~1/2；The angle of taper of the vertical tube is 10 °~30 °.
Further, space cryogenic propellant tank as the aforementioned, the metal material is aluminium alloy.
Beneficial effects of the present invention：
1st, vertical tube-blade surface tension force managing device is used inside tank, propellant positioning is on the one hand realized and manages,
The not gas enclosure supply of propellant is ensure that, gas is on the one hand positioned at fixed position, tank exhaust is facilitated.
2nd, heat insulating construction is used outside tank, inside uses vertical tube-blade surface tension force managing device, with reference to tank exhaust
Technology, can effectively solve cryogenic propellant storage and propellant lamination problem for a long time.
Brief description of the drawings
Fig. 1 is the space cryogenic propellant tank structure chart in an embodiment of the present invention；
Fig. 2 is the space cryogenic propellant tank structure chart in another embodiment of the invention；
Fig. 3 is the blade construction figure in the space cryogenic propellant tank of an embodiment of the present invention；
Fig. 4 is the structure chart of the heat insulating construction in the space cryogenic propellant tank of an embodiment of the present invention.
Embodiment
For the object, technical solutions and advantages of the present invention are more clearly understood, below in conjunction with specific embodiment, and reference
Accompanying drawing, the present invention is described in more detail.
Embodiment 1, as shown in figure 1, the present invention provides a kind of space cryogenic propellant tank, including：Tank housing 1,
Blade 2, vertical tube 3, drain pipe 4, collector 5, heat insulating construction 6, blast pipe 7, air exhaust combination valve 8 and pressure inlet 9；The adiabatic knot
Structure 6 is evenly coated at the outside of tank housing 1；One end inside the tank housing 1 is provided with the blade 2, vertical tube 3 and receipts
Storage 5；Described one end of collector 5 is on the inwall of the tank housing 1；The other end of collector 5 is provided with the vertical tube
3；Around the vertical tube 3 some blades 2 are evenly distributed with radial；The lower section of collector 5 is described exhausted provided with passing
The drain pipe 4 of heat structure 6；The other end inside the tank housing 1 is provided with through the tank housing 1 and heat insulating construction 6
Blast pipe 7 and pressure inlet 9；The blast pipe 7, which is located on the port in the outside of heat insulating construction 6, is additionally provided with the air exhaust combination valve 8.
Embodiment 2, as shown in Figures 2 and 4, the present invention provide a kind of space cryogenic propellant tank, including：Tank shell
Body 1, blade 2, vertical tube 3, drain pipe 4, collector 5, heat insulating construction 6, blast pipe 7, air exhaust combination valve 8 and pressure inlet 9；It is described exhausted
Heat structure 6 is evenly coated at the outside of tank housing 1；The inside of described one end of tank housing 1 is provided with the blade 2, vertical tube 3
With collector 5；Described one end of collector 5 is on the inwall of the tank housing 1；The other end of collector 5 is provided with described
Vertical tube 3；Around the vertical tube 3 some blades 2 are evenly distributed with radial；The lower section of collector 5, which is provided with, passes institute
State the drain pipe 4 of heat insulating construction 6；The other end inside the tank housing 1, which is provided with, runs through the tank housing 1 and heat insulating construction
6 blast pipe 7 and pressure inlet 9；The blast pipe 7, which is located on the port in the outside of heat insulating construction 6, is additionally provided with the air exhaust combination valve
8, it is preferred that the air exhaust combination valve 8 is threadedly attached on the blast pipe 7.The tank housing 1 is metal material
Spherical or ball column construction.The heat insulating construction 6 includes thermal insulation layer 13 and polyurethane foam plastic layer 12, the polyurethane foam
The inner surface of plastic layer 12 is coated on the outer surface of tank housing 1；The outer surface cladding of the polyurethane foam plastic layer 12
There is the thermal insulation layer 13.The thermal insulation layer reflecting layer 14 inter-adhesive by being outside to inside followed successively by and wall 15 are constituted, described
The material in reflecting layer 14 is the one of which of aluminium foil, Kapton and Kapton of aluminizing, the wall 15
Material is one kind in reticulated and loose shape fibrous material.The air exhaust combination valve 8 includes diaphragm valve 10 and air bleeding valve 11；
Described one end of diaphragm valve 10 connects the port of the blast pipe 7, and the other end connects the air bleeding valve 11.The blade 2 is one kind
Profile is the metal material thin slice that multi-section circular arc and SPL are constituted.The thickness of blade 2 is 0.1mm~2mm, the blade
2 quantity are 8~64.The vertical tube 3 is arranged on the axial location of tank housing 1, is that a kind of back taper wide at the top and narrow at the bottom is angular
Metal material hollow tube；The vertical tube 3 narrower one end and the collector 5 adaptation that is open is connected.The height of the vertical tube 3
For the 1/3~1/2 of the height of tank housing 1；The angle of taper of the vertical tube 3 is 10 °~30 °.It is preferred that, the metal material choosing
Select aluminium alloy.
Embodiment 3, as shown in Figures 1 and 3, the present invention provide a kind of space cryogenic propellant tank, including：Tank shell
Body 1, blade 2, vertical tube 3, drain pipe 4, collector 5, heat insulating construction 6, blast pipe 7, air exhaust combination valve 8 and pressure inlet 9；It is described exhausted
Heat structure 6 is evenly coated at the outside of tank housing 1；The inside of described one end of tank housing 1 is provided with the blade 2, vertical tube 3
With collector 5；Described one end of collector 5 is on the inwall of the tank housing 1；The other end of collector 5 is provided with described
Vertical tube 3；Around the vertical tube 3 some blades 2 are evenly distributed with radial；The lower section of collector 5, which is provided with, passes institute
State the drain pipe 4 of heat insulating construction 6；The other end inside the tank housing 1, which is provided with, runs through the tank housing 1 and heat insulating construction
6 blast pipe 7 and pressure inlet 9；The blast pipe 7, which is located on the port in the outside of heat insulating construction 6, is additionally provided with the air exhaust combination valve
8, it is preferred that the air exhaust combination valve 8 is threadedly attached on the blast pipe 7.The blade 2 is that a kind of profile is multistage
The metal material thin slice of circular arc and SPL composition.The thickness of blade 2 is 1mm, and the quantity of blade 2 is 24.It is described
Vertical tube 3 is a kind of angular metal material hollow tube of back taper wide at the top and narrow at the bottom；The vertical tube 3 be open narrower one end with it is described receive
The adaptation connection of storage 5.The height of the vertical tube 3 is the 1/3~1/2 of the height of tank housing 1；The angle of taper of the vertical tube 3 is
15°。
It is a kind of method of operation of space cryogenic propellant tank in embodiment 2 as described below：
Heat insulating construction 6 is installed outside tank housing 1, for preventing cryogenic propellant and extraneous heat exchange so that storage
Cryogenic propellant in case is in liquid condition.Meanwhile, in order to avoid causing tank pressure to exceed due to cryogenic propellant evaporation
Its design pressure, is provided with blast pipe 7 and pressure inlet 9 at the top of tank, and the outlet of blast pipe 7 is connected to air exhaust combination valve 8, is vented
Combination valve is combined by a diaphragm valve 10 and an air bleeding valve 11, with tank cryogenic propellant evaporate, tank pressure by
Edged up height, and when pressure rise is to 10 fracture pressure of diaphragm valve, diaphragm valve 10 is opened, when pressure no longer rises, air bleeding valve 11
Close；When pressure continues to rise, air bleeding valve 11 opens exhaust；After pressure drops to certain value, air bleeding valve 11 is closed automatically.
By the blade 2, vertical tube 3 and collector 5 installed inside tank housing 1, following functions can be realized：In microgravity
Under environment, using surface tension effects, cryogenic propellant is captured by blade 2 and is collected by vertical tube 3, logical from the bottom of vertical tube 3
Cross the supply engine of collector 5.Because the capture of blade 2 is acted on, within the aerial mission cycle, the liquid propellant in tank begins
It is present in eventually around vertical tube 3 and blade 2, the air cushion in tank is positioned above vertical tube always, can avoids tank will when being vented
Propellant is discharged.
Those of ordinary skills in the art should understand that：More than, described is only the specific embodiment of the present invention, and
The limitation present invention is not used in, within the spirit and principles of the invention, any modification, equivalent substitution and improvements done etc.,
It should be included within protection scope of the present invention.With inventing the technical principle being equal all within protection domain.
Claims (10)
1. a kind of space cryogenic propellant tank, it is characterised in that including：Tank housing (1), blade (2), vertical tube (3), go out
Liquid pipe (4), collector (5), heat insulating construction (6), blast pipe (7), air exhaust combination valve (8) and pressure inlet (9)；
The heat insulating construction (6) is evenly coated on the outside of the tank housing (1)；
The internal one end of the tank housing (1) is provided with the blade (2), vertical tube (3) and collector (5)；The collector (5)
One end is on the inwall of the tank housing (1)；Collector (5) other end is provided with the vertical tube (3)；The vertical tube
(3) some blades (2) are evenly distributed with radial around；
Provided with the drain pipe (4) for passing the heat insulating construction (6) below the collector (5)；
The internal other end of the tank housing (1) is provided with the blast pipe through the tank housing (1) and heat insulating construction (6)
And pressure inlet (9) (7)；The blast pipe (7), which is located on the port on the outside of heat insulating construction (6), is additionally provided with the air exhaust combination valve
(8)。
2. space cryogenic propellant tank according to claim 1, it is characterised in that the tank housing (1) is gold
Belong to the spherical or ball column construction of material.
3. space cryogenic propellant tank according to claim 1, it is characterised in that the heat insulating construction (6) includes
Polyurethane foam plastic layer (12) and thermal insulation layer (13), the inner surface of the polyurethane foam plastic layer (12) are coated on the storage
Tank shell (1) outer surface；Described polyurethane foam plastic layer (12) outer surface is coated with the thermal insulation layer (13).
4. space cryogenic propellant tank according to claim 3, it is characterised in that the thermal insulation layer (13) is by outside extremely
In be followed successively by inter-adhesive reflecting layer (14) and wall (15) composition, the material of the reflecting layer (14) is aluminium foil, polyamides
Imines film and Kapton one of which of aluminizing, the material of the wall (15) is reticulated and loose shape fiber
Material one of which.
5. space cryogenic propellant tank according to claim 1, it is characterised in that air exhaust combination valve (8) bag
Include diaphragm valve (10) and air bleeding valve (11)；Described diaphragm valve (10) one end connects the port of the blast pipe (7), other end connection
The air bleeding valve (11).
6. space cryogenic propellant tank according to claim 1, it is characterised in that the blade (2) is taken turns to be a kind of
The metal material thin slice that exterior feature constitutes for multi-section circular arc and SPL.
7. space cryogenic propellant tank according to claim 6, it is characterised in that blade (2) thickness is
0.1mm~2mm, blade (2) quantity is 8~64.
8. space cryogenic propellant tank according to claim 1, it is characterised in that the vertical tube (3) is arranged on institute
The axial location of tank housing (1) is stated, is a kind of angular metal material hollow tube of back taper wide at the top and narrow at the bottom；The vertical tube (3)
The narrower one end of opening is connected with the collector (5) adaptation.
9. space cryogenic propellant tank according to claim 8, it is characterised in that the height of the vertical tube (3) is
The 1/3~1/2 of tank housing (1) height；The angle of taper of the vertical tube (3) is 10 °~30 °.
10. the space cryogenic propellant tank according to claim 2 or 6 or 8, it is characterised in that the metal material
For aluminium alloy.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710374300.XA CN107152606A (en) | 2017-05-24 | 2017-05-24 | A kind of space cryogenic propellant tank |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710374300.XA CN107152606A (en) | 2017-05-24 | 2017-05-24 | A kind of space cryogenic propellant tank |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN107152606A true CN107152606A (en) | 2017-09-12 |
Family
ID=59793462
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201710374300.XA Pending CN107152606A (en) | 2017-05-24 | 2017-05-24 | A kind of space cryogenic propellant tank |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN107152606A (en) |
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107741373A (en) * | 2017-11-20 | 2018-02-27 | 北京宇航系统工程研究所 | A kind of tank testpieces and test method suitable for heat insulating construction cold shock experiment |
| CN109723962A (en) * | 2019-02-26 | 2019-05-07 | 重庆零壹空间航天科技有限公司 | Cryogenic propellant tank, long-term in-orbit integrated low temperature storage are for system and method |
| CN114348301A (en) * | 2021-12-20 | 2022-04-15 | 上海空间推进研究所 | Double-layer light iodine storage box utilizing molecular sieve to exhaust |
| CN114635810A (en) * | 2022-03-28 | 2022-06-17 | 上海交通大学 | Low-temperature propellant on-orbit management device suitable for complex overload |
| CN114684390A (en) * | 2022-03-31 | 2022-07-01 | 北京控制工程研究所 | Tank fluid acquisition device suitable for common-bottom tank |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| JPH10252560A (en) * | 1997-03-13 | 1998-09-22 | Ishikawajima Harima Heavy Ind Co Ltd | Supply method for gelatinized propellant and device therefor |
| CN102691592A (en) * | 2011-03-21 | 2012-09-26 | 哈米尔顿森德斯特兰德公司 | Demisable fuel supply system |
| CN104533662A (en) * | 2014-12-21 | 2015-04-22 | 北京工业大学 | Propellant managing device with blades uneven in thickness and provided with holes |
-
2017
- 2017-05-24 CN CN201710374300.XA patent/CN107152606A/en active Pending
Patent Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPH10252560A (en) * | 1997-03-13 | 1998-09-22 | Ishikawajima Harima Heavy Ind Co Ltd | Supply method for gelatinized propellant and device therefor |
| CN102691592A (en) * | 2011-03-21 | 2012-09-26 | 哈米尔顿森德斯特兰德公司 | Demisable fuel supply system |
| CN104533662A (en) * | 2014-12-21 | 2015-04-22 | 北京工业大学 | Propellant managing device with blades uneven in thickness and provided with holes |
Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107741373A (en) * | 2017-11-20 | 2018-02-27 | 北京宇航系统工程研究所 | A kind of tank testpieces and test method suitable for heat insulating construction cold shock experiment |
| CN109723962A (en) * | 2019-02-26 | 2019-05-07 | 重庆零壹空间航天科技有限公司 | Cryogenic propellant tank, long-term in-orbit integrated low temperature storage are for system and method |
| CN114348301A (en) * | 2021-12-20 | 2022-04-15 | 上海空间推进研究所 | Double-layer light iodine storage box utilizing molecular sieve to exhaust |
| CN114635810A (en) * | 2022-03-28 | 2022-06-17 | 上海交通大学 | Low-temperature propellant on-orbit management device suitable for complex overload |
| CN114635810B (en) * | 2022-03-28 | 2023-06-20 | 上海交通大学 | Low-temperature propellant on-orbit management device suitable for complex overload |
| CN114684390A (en) * | 2022-03-31 | 2022-07-01 | 北京控制工程研究所 | Tank fluid acquisition device suitable for common-bottom tank |
| CN114684390B (en) * | 2022-03-31 | 2024-07-09 | 北京控制工程研究所 | Storage tank fluid acquisition device suitable for common-bottom storage tank |
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| TA01 | Transfer of patent application right |
Effective date of registration: 20180222 Address after: 401135 Chongqing Yubei District City Longxing Zhen Ying Long Road No. 19 Applicant after: Chongqing 01 Space Technology Co. Ltd. Address before: In Beijing economic and Technological Development Zone, two street 100176 Daxing District 8 Beijing City Hospital No. 11 building B block five layer Applicant before: Beijing OneSpace Technology Co., Ltd. |
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Application publication date: 20170912 |
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