CN104533662A - Propellant managing device with blades uneven in thickness and provided with holes - Google Patents
Propellant managing device with blades uneven in thickness and provided with holes Download PDFInfo
- Publication number
- CN104533662A CN104533662A CN201410805385.9A CN201410805385A CN104533662A CN 104533662 A CN104533662 A CN 104533662A CN 201410805385 A CN201410805385 A CN 201410805385A CN 104533662 A CN104533662 A CN 104533662A
- Authority
- CN
- China
- Prior art keywords
- propellant
- blade
- tank shell
- tank
- entrance
- 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.)
- Granted
Links
Landscapes
- Toys (AREA)
Abstract
The invention provides a propellant managing device with blades uneven in thickness and provided with holes. A vertical pipe, the blades and a bottom collector are arranged in a storage tank case. The blades are installed on the vertical pipe. The vertical pipe is connected with the bottom collector. The bottom collector is installed on the lower end wall face in the storage tank case. A pressurizing opening and an exhaust opening are formed in the top of the storage tank case and arranged in the two sides of the storage tank case respectively. An inlet and a liquid outlet are formed in the bottom of the storage tank case and arranged in the two sides of the storage tank case respectively. The thicknesses of the blades are uneven and are gradually reduced from the inlet in the direction of the vertical pipe. On the basis of not additionally arranging a drive or control device, the propellant managing device can storage and supply propellants better by utilizing a simple blade structure.
Description
Technical field
The present invention designs a kind of propellant management device of in uneven thickness, hole leaf, belongs to Liquid propellant management device field.
Background technique
Along with surface tension propellant tank is widely used on satellite, airship, interstellar probe, space shuttle and space station, also obtain the achievement compared with horn of plenty about its core component propellant management device (PMD).
Present stage mainly concentrates on by elements such as screen cloth, passage, blade, centre strut, trap, groove, sponge and bubble traps by different combinations for the research of propellant management device (PMD), reach different design objects, adapt to specific aerial mission requirement.For storage propellant agent, the major function of management apparatus for providing the propellant agent of not gas enclosure and barycenter to control to motor in duty cycle, and mainly concentrates on the management role of blade to propellant agent to the control of propellant agent.Usually concentrate on quantity to the research of blade, the research of sequence, and vane thickness is on the shorter mention that affects of Propellant Management, in addition, blade structure is comparatively large on the impact of propellant management device, and quality is lighter, less on the impact of whole satellite.In sum, design a kind of propellant management device in uneven thickness, hole leaf and have important application and meaning.
Summary of the invention
The present invention devises a kind of propellant management device of in uneven thickness, hole leaf, by changing blade structure to improve its object to Propellant Management.The blade structure part of the present invention to conventional propellant management device changes, and the thickness of blade becomes uneven, upper-thin-lower-thick, makes propellant agent can better climb along blade wall like this; Blade edge is with holes simultaneously, also can alleviate the quality of management apparatus.Under identical condition, this management apparatus better can manage propellant agent, makes it be fixed near propellant management device.
Propellant management device of the present invention slightly makes improvements on the basis of the propellant management device of routine, and main structure is as follows:
The propellant management device of hole leaf in uneven thickness, this device comprises entrance 1, vertical tube 2, blade 3, boost port 4, relief opening 5, tank shell 6, end trap 7, liquid outlet 8.Vertical tube 2, blade 3, end trap 7 are arranged on the inside of tank shell 6, and blade 3 is arranged on vertical tube 2, and vertical tube 2 is connected with end trap 7, and end trap 7 is arranged on the lower end wall of tank shell 6 inside.In addition, boost port 4, relief opening 5 are installed in the top of tank shell 6, and boost port 4, relief opening 5 are separately positioned on tank shell 6 both sides; Entrance 1, liquid outlet 8 are arranged on the bottom of tank shell 6, and entrance 1, liquid outlet 8 are symmetricly set on tank shell 6 both sides respectively.The thickness of described blade 3 is uneven, and its thickness is reduced along vertical tube 2 direction gradually by entrance 1.
The blade 3 of conventional propellant management device is that thickness is uniform, and atresia on blade, the effect of this part is that propellant agent is climbed along blade under microgravity environment, can be good at being gathered near blade, is convenient to the management of propellant agent.
The working procedure of this device is as follows: propellant agent flows into from entrance 1, to enter in tank shell 6, injects pressurization gas from boost port 4.When satellite is at space motion, because gravity is almost 0, propellant agent climbs along tank shell 6 and blade 3, is attached near propellant management device.During tank work, liquid flows out from liquid outlet 8, and blade 3, as the medium of different temperatures fluid heat transfer, makes the fluid temperature gradient of management apparatus reduce, and keeps tank inner fluid homogeneous temperature.Because the outer temperature variation of, tank is violent, propellant agent is heated on liquid level and is full of saturated vapour, makes the pressure in tank constantly increase, now opens relief opening 5 and be vented.
The present invention can, on the basis not increasing extra driving or control gear, utilize simple blade structure to make propellant agent better to save and to supply propellant agent.
Accompanying drawing explanation
Fig. 1 is the three-D profile schematic diagram of the propellant management device of a kind of in uneven thickness, hole leaf of the present invention.
Fig. 2 is the cross sectional representation of the plan view of the propellant management device of a kind of in uneven thickness, hole leaf of the present invention.
Fig. 3 is the cross sectional representation of the plan view of the propellant management device of a kind of in uneven thickness, hole leaf of the present invention.
In figure: 1, entrance, 2, vertical tube, 3, blade, 4, boost port, 5, relief opening, 6, tank shell, 7, end trap, 8, liquid outlet.
Embodiment
Below in conjunction with Structure Figure, the working procedure of the propellant management device of a kind of in uneven thickness, hole leaf of invention and effect are further elaborated and are verified.
Fig. 1 is a kind of three-D profile schematic diagram of propellant management device of in uneven thickness, hole leaf.This propellant management device comprises entrance 1, vertical tube 2, blade 3, boost port 4, relief opening 5, tank shell 6, end trap 7, the several part formation of liquid outlet 8.
Before carrying out work, should open entrance 1, slowly inject propellant agent, propellant agent injects complete, closes entrance 1, opens boost port 4, injects pressurization gas, reaches desirable pressure.
During tank work, tank is in microgravity environment, propellant agent can be attached to blade 3 and tank shell 6 and near, can not block relief opening, pressurization gas is positioned at the top of tank, and when propellant agent flows out from liquid outlet 8, gas can not be discharged.Because tank is seal container, when propellant agent is heated, the gas in tank is reached capacity, opens relief opening 5, allow decompression in tank, because propellant agent is positioned at propellant management device, thus propellant agent can not be discharged from relief opening 5.This outer leafs 3, also as heat conducting medium, makes the fluid temperature gradient of management apparatus reduce, and keeps tank inner fluid homogeneous temperature.
Claims (2)
1. a propellant management device for hole leaf in uneven thickness, is characterized in that: this device comprises entrance (1), vertical tube (2), blade (3), boost port (4), relief opening (5), tank shell (6), end trap (7), liquid outlet (8); Vertical tube (2), blade (3), end trap (7) are arranged on the inside of tank shell (6), blade (3) is arranged on vertical tube (2), vertical tube (2) is connected with end trap (7), and end trap (7) is arranged on the inner lower end wall of tank shell (6); In addition, boost port (4), relief opening (5) are installed in the top of tank shell (6), and boost port (4), relief opening (5) are separately positioned on tank shell (6) both sides; Entrance (1), liquid outlet (8) are arranged on the bottom of tank shell (6), and entrance (1), liquid outlet (8) are symmetricly set on tank shell (6) both sides respectively; The thickness of described blade (3) is uneven, and its thickness is reduced along vertical tube (2) direction gradually by entrance (1).
2. the propellant management device of a kind of hole leaf in uneven thickness according to claim 1, it is characterized in that: the working procedure of this device is as follows, propellant agent flows into from entrance (1), enter in tank shell (6), inject pressurization gas from boost port (4); When satellite is at space motion, because gravity is almost 0, propellant agent climbs along tank shell (6) and blade (3), is attached near propellant management device; During tank work, liquid flows out from liquid outlet (8), and blade (3), as the medium of different temperatures fluid heat transfer, makes the fluid temperature gradient of management apparatus reduce, and keeps tank inner fluid homogeneous temperature; Because the outer temperature variation of, tank is violent, propellant agent is heated on liquid level and is full of saturated vapour, makes the pressure in tank constantly increase, now opens relief opening (5) exhaust.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410805385.9A CN104533662B (en) | 2014-12-21 | 2014-12-21 | The Propellant Management device of a kind of hole leaf in uneven thickness |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410805385.9A CN104533662B (en) | 2014-12-21 | 2014-12-21 | The Propellant Management device of a kind of hole leaf in uneven thickness |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN104533662A true CN104533662A (en) | 2015-04-22 |
| CN104533662B CN104533662B (en) | 2016-06-01 |
Family
ID=52849254
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201410805385.9A Active CN104533662B (en) | 2014-12-21 | 2014-12-21 | The Propellant Management device of a kind of hole leaf in uneven thickness |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN104533662B (en) |
Cited By (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107152606A (en) * | 2017-05-24 | 2017-09-12 | 北京零壹空间科技有限公司 | A kind of space cryogenic propellant tank |
| CN107676196A (en) * | 2017-09-12 | 2018-02-09 | 中国人民解放军战略支援部队航天工程大学 | What a kind of cover plate connected can blocking type rocket engine propellant biasing spray panel |
| CN107676194A (en) * | 2017-09-12 | 2018-02-09 | 中国人民解放军战略支援部队航天工程大学 | A kind of modularization rocket engine propellant biasing spray panel of threaded connection |
| CN107676195A (en) * | 2017-09-12 | 2018-02-09 | 中国人民解放军战略支援部队航天工程大学 | A kind of modularization rocket engine propellant biasing spray panel of cover plate connection |
| CN110282156A (en) * | 2019-05-24 | 2019-09-27 | 深圳市魔方卫星科技有限公司 | A kind of integrated cold air propulsion system and its control method |
| CN110525695A (en) * | 2019-09-06 | 2019-12-03 | 北京空间技术研制试验中心 | A kind of spacecraft propulsion developing agent storage and manage split type system |
| CN111102099A (en) * | 2019-11-18 | 2020-05-05 | 北京宇航***工程研究所 | De-swirling anti-collapse filtering integrated device |
| CN112012849B (en) * | 2020-10-15 | 2021-03-16 | 北京星际荣耀空间科技股份有限公司 | Vortex-proof collapse-proof structure and propellant storage tank with same |
| EP3702290A4 (en) * | 2017-10-26 | 2021-08-04 | Japan Aerospace Exploration Agency | Liquid behavior suppression device |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5427334A (en) * | 1993-09-17 | 1995-06-27 | Martin Marieta Corporation | Method for making nonmetallic pressure vessel with integral propellant management vane, and pressure vessel made by the method |
| JP2009143250A (en) * | 2007-12-11 | 2009-07-02 | Ihi Aerospace Co Ltd | Propellant tank for artificial satellite |
| CN201553157U (en) * | 2009-09-28 | 2010-08-18 | 北京控制工程研究所 | Storage tank plate-type propellant management device |
| US8534489B2 (en) * | 2011-03-21 | 2013-09-17 | Hamilton Sundstrand Space Systems International, Inc. | Demisable fuel supply system |
| CN103950557A (en) * | 2014-04-29 | 2014-07-30 | 北京控制工程研究所 | Hydraulic accumulator for propellant tank in spacecraft |
-
2014
- 2014-12-21 CN CN201410805385.9A patent/CN104533662B/en active Active
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5427334A (en) * | 1993-09-17 | 1995-06-27 | Martin Marieta Corporation | Method for making nonmetallic pressure vessel with integral propellant management vane, and pressure vessel made by the method |
| JP2009143250A (en) * | 2007-12-11 | 2009-07-02 | Ihi Aerospace Co Ltd | Propellant tank for artificial satellite |
| CN201553157U (en) * | 2009-09-28 | 2010-08-18 | 北京控制工程研究所 | Storage tank plate-type propellant management device |
| US8534489B2 (en) * | 2011-03-21 | 2013-09-17 | Hamilton Sundstrand Space Systems International, Inc. | Demisable fuel supply system |
| CN103950557A (en) * | 2014-04-29 | 2014-07-30 | 北京控制工程研究所 | Hydraulic accumulator for propellant tank in spacecraft |
Non-Patent Citations (2)
| Title |
|---|
| 李永，赵春章，潘海林，魏延明: "蓄液器在板式贮箱中的应用及性能分析", 《宇航学报》 * |
| 穆小强，陈祖奎: "竖管-叶片式表面张力管理装置的设计与分析", 《火箭推进》 * |
Cited By (13)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107152606A (en) * | 2017-05-24 | 2017-09-12 | 北京零壹空间科技有限公司 | A kind of space cryogenic propellant tank |
| CN107676196A (en) * | 2017-09-12 | 2018-02-09 | 中国人民解放军战略支援部队航天工程大学 | What a kind of cover plate connected can blocking type rocket engine propellant biasing spray panel |
| CN107676194A (en) * | 2017-09-12 | 2018-02-09 | 中国人民解放军战略支援部队航天工程大学 | A kind of modularization rocket engine propellant biasing spray panel of threaded connection |
| CN107676195A (en) * | 2017-09-12 | 2018-02-09 | 中国人民解放军战略支援部队航天工程大学 | A kind of modularization rocket engine propellant biasing spray panel of cover plate connection |
| CN107676196B (en) * | 2017-09-12 | 2019-07-09 | 中国人民解放军战略支援部队航天工程大学 | A kind of connection of cover board can blocking type rocket engine propellant bias spray panel |
| CN107676194B (en) * | 2017-09-12 | 2019-07-09 | 中国人民解放军战略支援部队航天工程大学 | A kind of modularization rocket engine propellant biasing spray panel of threaded connection |
| EP3702290A4 (en) * | 2017-10-26 | 2021-08-04 | Japan Aerospace Exploration Agency | Liquid behavior suppression device |
| US11447274B2 (en) | 2017-10-26 | 2022-09-20 | Japan Aerospace Exploration Agency | Liquid behavior suppression device |
| CN110282156A (en) * | 2019-05-24 | 2019-09-27 | 深圳市魔方卫星科技有限公司 | A kind of integrated cold air propulsion system and its control method |
| CN110525695B (en) * | 2019-09-06 | 2021-07-16 | 北京空间技术研制试验中心 | Spacecraft propellant storage and management split system |
| CN110525695A (en) * | 2019-09-06 | 2019-12-03 | 北京空间技术研制试验中心 | A kind of spacecraft propulsion developing agent storage and manage split type system |
| CN111102099A (en) * | 2019-11-18 | 2020-05-05 | 北京宇航***工程研究所 | De-swirling anti-collapse filtering integrated device |
| CN112012849B (en) * | 2020-10-15 | 2021-03-16 | 北京星际荣耀空间科技股份有限公司 | Vortex-proof collapse-proof structure and propellant storage tank with same |
Also Published As
| Publication number | Publication date |
|---|---|
| CN104533662B (en) | 2016-06-01 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN104533662A (en) | Propellant managing device with blades uneven in thickness and provided with holes | |
| JP6192000B2 (en) | Use of phase change materials, heat pipes, and fuel cells for aircraft applications | |
| CN103590924A (en) | High-rigidity propellant management device for large surface tension storage box | |
| CN104326091B (en) | It is subjected to the draining bar of the aircraft cabin of negative pressure | |
| CN104417743A (en) | Bag body telescopic stratospheric airship | |
| CN108661555A (en) | Hot gas ice sheet core bit | |
| CA2836380A1 (en) | Hydrodynamic ram mitigating fuel cell structure | |
| ZA202201577B (en) | Device for energy transfer and for energy storage in a liquid reservoir | |
| CN105675243B (en) | A kind of environment temperature simulation device for landing gear drop test | |
| Du et al. | Dynamical analysis of high-pressure supercritical carbon dioxide jet in well drilling | |
| JP2015172368A (en) | Fuel tank, fuel pipe, and aircraft | |
| Woods et al. | Blocked natural ventilation: the effect of a source mass flux | |
| CN210180885U (en) | CO2 displacement device of tight oily rock core | |
| CN106409356A (en) | Nuclear power plant passive overflow exhaust device | |
| CN212845119U (en) | Neutron scattering device for simulating high-temperature and high-pressure sample environment | |
| US9845144B2 (en) | Aircraft and air exchange systems for ventilated cavities of aircraft | |
| CN202868928U (en) | Automatic water supply device | |
| CN206990157U (en) | A kind of experiment room of drenching with rain of classification of waterproof test | |
| WO2011084114A3 (en) | Vibration absorber at surface openings of fluid flows | |
| CN208554259U (en) | A kind of high pressure gas heating heating device | |
| CN202730467U (en) | Flat ironing heating plate | |
| CN202358282U (en) | Hard tank waterflooding apparatus for column-type platform straightening process | |
| US20060254654A1 (en) | Fuel tank overflow preventer | |
| CN206736313U (en) | A kind of quick steel pipe cooling device for absorbing vapor | |
| Koroteev et al. | Experimental elaboration of liquid droplet cooler-radiator models under microgravity and deep vacuum conditions |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant |