CN105858583A - Space fuel storage box fluid management system based on electric field effect - Google Patents
Space fuel storage box fluid management system based on electric field effect Download PDFInfo
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- CN105858583A CN105858583A CN201610207430.XA CN201610207430A CN105858583A CN 105858583 A CN105858583 A CN 105858583A CN 201610207430 A CN201610207430 A CN 201610207430A CN 105858583 A CN105858583 A CN 105858583A
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- container
- doffing
- disk
- anelectrode
- electric field
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B67—OPENING, CLOSING OR CLEANING BOTTLES, JARS OR SIMILAR CONTAINERS; LIQUID HANDLING
- B67D—DISPENSING, DELIVERING OR TRANSFERRING LIQUIDS, NOT OTHERWISE PROVIDED FOR
- B67D7/00—Apparatus or devices for transferring liquids from bulk storage containers or reservoirs into vehicles or into portable containers, e.g. for retail sale purposes
- B67D7/06—Details or accessories
- B67D7/76—Arrangements of devices for purifying liquids to be transferred, e.g. of filters, of air or water separators
- B67D7/766—Arrangements of devices for purifying liquids to be transferred, e.g. of filters, of air or water separators of water separators
Abstract
The invention discloses a space fuel storage box fluid management system based on the electric field effect. The space fuel storage box fluid management system comprises a storage box wall, an exhaust pipe, a fluid discharging/feeding port, a center barrel, an inner deflector, an outer deflector, an upper tray ring, a lower tray, a positive electrode rod and a container, wherein the center barrel is composed of an upper barrel body and a lower barrel body. The upper barrel body and the lower barrel body are fixedly connected in an up-down mode through the inner deflector which is connected in an inserting mode or in a welding mode. The positive electrode rod connected with a positive pole of a power source is installed inside the lower barrel body, and the axis of the positive electrode rod coincides with that of the lower barrel body connected with a negative pole of the power source. A capillary screen net is installed between the lower end of the lower barrel body and the fluid discharging/feeding port. The container is composed of two revolved bodies with the upper cross sections and the lower cross sections being isosceles trapezoids, and the revolved bodies are connected together through a waist flange. Two installation round holes are symmetrically formed in the waist flange and used for installing a negative electrode wafer connected with the negative pole of the power source. A positive electrode wafer which is connected with the positive pole of the power source and parallel to the negative electrode wafer is installed inside the container. The upper end of the container is provided with an exhaust port which is fixedly connected with the exhaust pipe. The lower end of the container is provided with an air inlet.
Description
Technical field
The present invention relates to a kind of novel fuel tank fluid management system, particularly relate to a kind of based on electric field
The fuel tank fluid management system being applied under space microgravity environment of effect.The present invention is at space fuel
Creative utilization electricity hydrodynamics EHD theory in tank, replaces gravitational field by the conservative force field formed by electric field,
It is distributed the liquid phase of the fluid working substance fuel in the fuel tank of space effectively to strengthen and transports and actively control
System, belongs to service fluid management domain in-orbit.
Background technology
Along with mankind's space development and the rapid expansion utilizing scale, spacecraft, for performing aerial mission, meets
Its function, performance requirement, the demand of convection cell working medium fuel is increasing, and its task cycle is direct
By can consume on spacecraft flowing material load quantitative limitation, such as Satellite Orbit Maneuver and long term orbit keep,
The moon and planetary surface construction of base, large-scale survey of deep space activity etc., be required to carry and consume substantial amounts of pushing away
Enter agent fuel；The special space devices such as space-based chemical laser need to carry a considerable amount of chemical fuels etc..Cause
This, all kinds of spacecrafts service technology in-orbit with spacecraft maintenance, repair etc. as main purpose obtained in recent years
Arrive extensive concern and research, and as important component part therein, spacecraft loading technique in-orbit can
Under spatial environments, supplement fuel for spacecraft, extend its life-span in-orbit, it is possible to significantly save space tasks
Cost, mankind's space operation is played very important effect.Wherein, in-orbit loading technique as
One of core key technology of rail service fluid management, it is desirable in micro-gravity conditions the single liquid without steam
Body is transported to need from tank with specific temperature and pressure the Tank of Spacecraft of filling liquid.Normal conditions
Under, the life-span of spacecraft is decided by the carrying amount of fuel, by spacecraft in-orbit is filled, and Ke Yiyou
Effect extends the service life of spacecraft, saves launch cost, and improves mobility and the reliability of spacecraft.
In the case of current spatial resource day is becoming tight, loading technique is it can be avoided that the product of more space junk in-orbit
Raw, more highlight its using value.
It is a complicated process that fluid under microgravity condition effectively manages, although spacefaring nation exists both at home and abroad
Spacecraft filling tank design and the aspect such as properly functioning period fluid management have accumulated rich experience, but by
Special environment in microgravity exists, and the filling process of propellant fuel and ground still exist very big difference.
Under space microgravity environment, in tank the liquid phase of liquid will not due to biphase density variation natural layering,
But under the effect of the secondary power such as surface tension, it is interior in being randomly distributed that gas-liquid is suspended in tank jointly, because of
This unpredictable its is specifically distributed.Along with the increase of adding amount, the state of gas-liquid distribution also can occur the biggest change
Changing, simultaneously because the change of pressure, filling speed also can produce corresponding change.For space of ensuring supply
Fuel tank is single-phase liquid, the most necessary fuel working medium in tank under microgravity condition is passed through fluid
Managing device effectively manages, and its Main Function is to realize liquid phase during fuel fluid manages to separate,
Strengthening transports and makes fuel working medium to keep steady statue, prevents under microgravity condition due to the uncontrollable fortune of fuel
Move and cause spacecraft unstability.
On current spacecraft, commonly used surface tension propellant tank is as fuel liquid managing device.Surface tension is store
Case is the key equipment that propellant fuel fills in-orbit, and it utilizes surface tension to carry out liquid conveying and gas-liquid is divided
From, the fuel of not gas enclosure is provided for spacecraft, the demand of spacecraft to be met supply fuel, also will be
Fuel is effectively managed by fuel adding and discharge process.And the development of service technology the most in-orbit,
Have higher requirement for spacecraft fuel tank.In fuel adding and discharge transport process, if storage
Case runs into external interference and rocks or time fluid-flow rate is bigger, and surface tension propellant tank still cannot thoroughly realize
Gas-liquid separation is also completely secured as needing the Tank of Spacecraft of filling liquid to provide the fuel of not gas enclosure, therefore anxious
Need to develop a kind of novel can space fuel storage that actively intensive control microgravity liquid fuel liquid phase separates
Case fluid management system.
Summary of the invention
The technology of the present invention solves problem: overcome the deficiencies in the prior art, it is provided that a kind of based on field effect
Space fuel tank fluid management system, be effectively improved microgravity environment therapeutic method to keep the adverse QI flowing downwards liquid phase separation and actively control
Ability and in-orbit service fluid management level.
The technical solution of the present invention is: a kind of space of based on field effect fuel tank fluid management system
System, including tank wall, exhaustor, discharge opeing/filler, the central tube being made up of top cylinder and doffing, Inner guide
Plate, outer deflector, pop-up disk ring, lower tray, anelectrode rod and container；
Top cylinder and doffing realize upper and lower fixing connection, top cylinder and doffing by the inner deflector of grafting or welding
Between equal spray epoxy coating on interface, doffing outer circumference face；Anelectrode rod is fixed on down
The axis of cylinder inside and anelectrode rod and the dead in line of doffing, on anelectrode rod, disc and lower disc all spray
Epoxy coating；Anelectrode rod is connected with the positive pole of power supply, and doffing circumference wall is connected with the negative pole of power supply；
Multiple mm magnitude aperture is opened in the circumference wall of top cylinder and doffing, inner deflector；The lower end of doffing and discharge opeing/
Exhaustor is installed in upper end relative with discharge opeing/filler in installing capillary screen cloth, tank between filler；With
The container upper end of electric field is provided with air vent, and this air vent is fixing with exhaustor to be connected, and container lower end is provided with air inlet
Mouthful；Tank wall, exhaustor, discharge opeing/filler, central tube, inner deflector, outer deflector, pop-up disk ring,
Lower tray forms board-like surface tension fuel tank；
Under microgravity environment, when needing to discharge the fuel in tank, power supply powers up, and fuel is by center
Aperture on cylinder circumference wall enters central tube, is formed in entering doffing between anelectrode rod and doffing barrel
Electric field region, by the bubble that is mixed in fuel under the effect of electric field force, breaks through at doffing circumference wall aperture
Surface tension and the constraint of fluid resistance, off center cylinder at doffing circumference wall aperture and enter fuel
Inside tank, by the electric field action in central tube, it is to avoid bubble is mixed into discharge opeing/filler, by container
Electric field action, it is to avoid drop is mixed into exhaustor.
Described exhaustor is screw type exhaustor.
Described exhaustor is straight tube.
Parallel installation negative electrode disk in two of the waist of described container installation circular holes, negative electrode disk with
The negative pole of power supply connects；Between installation circular hole on negative electrode disk and container waist, outside negative electrode disk
Disc spray epoxy coating；The internally installed anelectrode disk being parallel to negative electrode disk of container,
Anelectrode disk circumference wall spray epoxy coating, negative electrode disk and anelectrode disk all have
The aperture of mm magnitude.
Described container is spindle container, is made up of two revolving bodies that upper lower section is isosceles trapezoid, two
Installed by waist flange between individual revolving body and link together, waist flange is arranged with two circle is installed
Hole, is used for installing negative electrode disk.
Described anelectrode disk run through its upper end air vent of connection of self centrage and spindle container with
The axis of rotation of lower end air inlet overlaps, and anelectrode disk is parallel to negative electrode disk.
The disk area of described anelectrode disk is more than the area of negative electrode disk.
The principle of the present invention is:
The present invention innovates introducing electricity hydrodynamics EHD theory, applies an external electric field in a fluid, by utilizing
Coupling between electric field, flow field and boundary and reaching actively controls liquid phase and separates and strengthening transports
Purpose.Panofsy and Philips, according to electromagnetic theory, derives the electric field suffered by the fluid in electric field
Power FeIt is represented by:
In formula: E is electric field intensity (V/m)；ε is dielectric constant (F/m)；Q is contained free charge in fluid
Density (C/m2)；ρ is fluid density；T is the temperature of liquid.DIELECTRIC CONSTANT ε represents that electric field line penetrates dielectric
The easy degree of matter, in the fluid of high-k, electric field will weaken, and the dielectric constant of gas is always than liquid
Body is little；Electric field space charge density q represents the number of free ion in liquid.Section 1 qE on the right of equal sign in formula
Represent the power that electric field is applied on unit volume fluid free charge, referred to as Coulomb force or electrophoretic force；Second
?Represent under electric field action the putting on of producing due to the spatial variations of DIELECTRIC CONSTANT ε of medium
Power on fluid, referred to as dielectrophoresis force；Section 3Represent due to electric field intensity E and dielectric
The spatial variations of constant ε and the power putting on fluid that produces, be also called electrostrictive forces.
For different working medium and different heat transfer types, effect and the size of these three power are different.Empty
Between liquid working substance in fuel tank belong to dielectric liquid (such as anhydrous hydrazine, methyl hydrazine and dinitrogen tetroxide etc.),
Then free charge is 0, and Section 1 Coulomb force qE can ignore；Liquid working substance in the fuel tank of space belongs to
Incompressible fluid, then Section 3Electrostrictive forces can be ignored；The electric field effect to bubble
Mainly Section 2 dielectrophoresis forceThis dielectrophoresis force occurs mainly with between gas phase and liquid phase
At interface.In order to this active force is described, being located at a dielectric constant is ε1Working medium in have a dielectric normal
Number is ε2, radius is the spheroid of R.Phol in 1978 et al. derives the dielectrophoresis acting on spheroid
Power FdGeneral expression be:
Now spheroid is bubble, now ε2<ε1, then FdDirection point to electric field reduce direction, i.e. bubble to
The direction motion that electric field reduces.
As can be seen here, the conservative force field that electric field is formed can substitute for gravitational field, produces steam bubble displacement effect
A main path, be the important strengthening means of Microgravity Fluid gas-liquid two-phase phase distributed controll.By
Two phase flow applies electric field, acts on the dielectrophoresis force at the interface between gas phase and liquid phase, make low dielectric
The bubble of constant to the little local motion of electric field intensity, makes the liquid of high-k to the big ground of electric field intensity
Fang Yundong, such that it is able to stable, effectively to the liquid phase of fluid working substance fuel in the management of service fluid in-orbit
Distribution is controlled, it is ensured that in micro-gravity conditions fuel is transported to from tank with specific temperature and pressure
Need not have during the Tank of Spacecraft of filling liquid the phenomenon of gas-liquid doping, thus be effectively improved micro-heavy
Force environment therapeutic method to keep the adverse QI flowing downwards liquid phase separation active control ability and in-orbit service fluid management level.
The present invention compared with prior art has the beneficial effect that
(1) present invention is by introducing electricity hydrodynamics EHD theory, utilizes between electric field, flow field and boundary
Coupling, can stablize, effectively service fluid in-orbit is managed in the liquid phase of fluid working substance fuel
Distribution carries out actively control, it is ensured that in micro-gravity conditions that fuel is defeated from tank with specific temperature and pressure
Deliver to not have during the Tank of Spacecraft needing filling liquid fuel the phenomenon of gas-liquid doping, and ensure aerofluxus
Do not have the phenomenon having drop to discharge at Kou, solve a filling fluid management liquid phase separation difficult problem in-orbit,
Thus be effectively improved microgravity environment therapeutic method to keep the adverse QI flowing downwards liquid phase separation active control ability and in-orbit service fluid management water
Flat；And the research of liquid phase distribution control system and design for aerospace system Microgravity Fluid provides one
Completely new approach and technological means.
(2) a kind of based on field effect the space fuel tank fluid management system that the present invention proposes, not only
Can thoroughly realize microgravity environment therapeutic method to keep the adverse QI flowing downwards liquid phase separation (rock even running into external interference at tank or flow
When body flowing velocity is bigger), it is also possible to strengthening transports and actively controls the fuel in tank and makes fuel working medium by it
Keep steady statue, prevent from causing spacecraft unstability due to the uncontrollable motion of fuel under microgravity condition,
Thus it is effectively improved service fluid management level in-orbit.
(3) a kind of based on field effect the space fuel tank fluid management system that the present invention proposes, not only
The management requirement of fuel in filling and discharge process can be met, bunkering process can also be met simultaneously
Requirement, has feature reusable, that reliability is high；
(4) a kind of based on field effect the space fuel tank fluid management system that the present invention proposes, permissible
Effectively extend the service life of spacecraft, save launch cost, and improve mobility and the reliability of spacecraft；
(5) a kind of based on field effect the space fuel tank fluid management system that the present invention proposes, is working as
In the case of front space resource day is becoming tight, this in-orbit loading technique can be prevented effectively from more space junk
Generation, more highlighted its using value.
Accompanying drawing explanation
Fig. 1 is the outside schematic diagram of the present invention；
Fig. 2,3 it is the internal each block diagram of tank of the present invention；
Fig. 4 and Fig. 5 is central tube of the present invention and inner deflector partial schematic diagram；
Fig. 6 is spindle container interior section schematic diagram of the present invention.
Detailed description of the invention
It is space based on field effect fuel tank fluid management system schematic diagram as Figure 1-5, system
Including: tank wall 1, exhaustor 2, discharge opeing/filler 3, central tube 4 (top cylinder 401, doffing 402),
Inner deflector 5, outer deflector 6, pop-up disk ring 7, lower tray 8, anelectrode rod 9, spindle container 10,
Anelectrode big circular slice 11, negative electrode sequin 12 and 13.
Space board-like surface tension fuel tank central tube 4 is made up of top cylinder 401 and doffing 402, top cylinder 401
All have multiple mm magnitude aperture with doffing 402 circumference wall, top cylinder 401 and doffing 402 by grafting or
The inner deflector 5 of welding realizes upper and lower fixing connection.Interface between top cylinder 401 and doffing 402, under
Equal spray epoxy coating on cylinder outer circumference face, carry out when being used for applying electric field upper doffing effectively insulate every
From.Doffing 402 outer circumferential walls face spray epoxy coating, is used for applying during electric field making doffing 402 and week
Surrounding environment is effectively dielectrically separated from.The internal anelectrode rod 9 that inserts of central tube 4, anelectrode rod 9 and power supply
Positive pole connect, on anelectrode rod 9, disc and lower disc equal spray epoxy coating, be used for applying electric field
Time make disc and lower disc on anelectrode rod 9 effectively be dielectrically separated from surrounding enviroment respectively, anelectrode rod
9 are fixed on the installing hole on doffing 402 by the fixing pin rod of both sides, keep anelectrode rod 9
Axis and the dead in line (as shown in Figures 4 and 5) of doffing 402..Doffing 402 circumference wall and power supply
Negative pole connects.By the electric field arrangement in this central tube 4, so that near anelectrode rod 9
Electric field intensity is far longer than the electric field intensity of doffing 402 circumference wall, when in fuel tank, fuel liquid flows through
When this electric field region discharges tank, if being now mixed with bubble in fuel liquid, bubble will be at electric field force
To the direction motion that electric field intensity reduces under effect, i.e. move to doffing 402 circumference wall direction.Bubble is
The surface tension at doffing 402 circumference wall aperture and the bundle of fluid resistance is broken through eventually under the effect of electric field force
Tie up, off center cylinder 4 at doffing 402 circumference wall aperture and enter inside fuel tank.At central tube
Capillary screen cloth is installed between 4 lower ends and discharge opeing/filler 3, blocks bubble further, prevent bubble with liquid
Body discharges discharge opeing/filler 3.
Thus, it could be seen that the mode applying electric field in central tube 4 can realize in spatial surface tension force fuel tank
In heart cylinder 4, liquid phase separates, it is ensured that in micro-gravity conditions without steam at supply tank discharge opeing/filler 3
Single liquid be transported to need from tank with specific temperature and pressure the Tank of Spacecraft of filling liquid.
Inner deflector 5 is installed in board-like surface tension propellant tank and outer deflector 6 carries out fluid to fuel working medium
Management.Inner deflector 5 (having the aperture of mm magnitude on it) with grafting or welding manner (along center
Cylinder 4 outer wall buses) fix with central tube 4 and to be connected, and be uniformly arranged on the axis of central tube 4 for axle
On heart cylinder 4 outer wall.The root of outer deflector 6 (has mm with central tube 4 bottom and lower tray 8 on it
The aperture of magnitude) fixing connection, the ending of outer deflector 6 is fixing with pop-up disk ring 7 to be connected, and with center
The axis of cylinder 4 is that axle is uniformly installed on the inwall of tank wall 1.By installing inner deflector 5 and outer deflector
6, fluid passage can be formed between inner deflector 5, between outer deflector 6 and tank wall 1, liquid fires
Material is fixed in fluid passage under capillary effect, forms steady statue.Even if tank is by dry
Disturbing, inner deflector 5 and outer deflector 6 also are able to rapidly propellant be carried out reorientation.Filling process,
In discharge process, propellant can be managed by inner deflector 5 and outer deflector 6 equally effectively.
If additionally, during spatial surface tension force fuel tank filling liquid fuel, when the liquid fuel of filling surpasses
When crossing the 80% of container, the drop near gas outlet is the most easily mixed into escape pipe 3, so easily causes
Instability in fuel tank.In order to anti-situation here occurs, patent of the present invention is at the gas outlet of tank upper end
It is also added into spindle container 10.Spindle container 10 can use as shown in Figure 6 by upper lower section be
The shape of two revolving body compositions of isosceles trapezoid, it is also possible to the deformation according to circumstances adapted to.Spindle container
10 upper ends are provided with air vent, with exhaustor 2 by being spirally connected or welding manner is fixing is connected, spindle container 10
Lower end is provided with air inlet, and upper and lower two semicircular container is installed by waist flange and linked together；Spindle describes
Device 10 waist flange is provided with two and installs circular hole, connects the parallel to each other of power cathode for fixed installation two
Negative electrode sequin 12 and 13, negative electrode sequin 12 and 13 and waist flange are installed between circular hole all
Spray epoxy coating, be used for applying during electric field making negative electrode sequin 12 and 13 respectively with around connect
The waist flange touched effectively is dielectrically separated from, and all sprays ring outside negative electrode sequin 12 and 13 on disc
Epoxy resins coating, be used for applying during electric field making negative electrode sequin 12 and 13 respectively with spindle container 10
Parts in addition are effectively dielectrically separated from, and negative electrode sequin 12 and 13 all has a millimeter magnitude aperture.
An anelectrode big circular slice 11 being parallel to negative electrode sequin 12 and 13 is had inside spindle container 10,
Anelectrode big circular slice 11 circumference wall spray epoxy coating, is used for applying during electric field making anelectrode big circular slice
11 circumference walls are effectively dielectrically separated from surrounding enviroment, the anelectrode big circular slice 11 connection by both sides
Pin rod is arranged on the installing hole of waist flange, and makes anelectrode big circular slice 11 run through self centrage and spin
Its upper end air vent that connects of capitate container 10 overlaps with the axis of rotation of lower end air inlet.Anelectrode big circular slice
The aperture of mm magnitude is had on 11.Now anelectrode big circular slice 11 electric field intensity is more than negative electrode sequin
The electric field intensity of 12 and 13, when in surface tension propellant tank, the liquid of filling exceedes the 80% of container, even if
Run into and have drop to be mixed into spindle container 10, it is also possible to by this inhomogeneous field arrangement so that drop
In the effect of electric field force to the little direction of electric field intensity, i.e. negative electrode sequin 12 and 13 direction motion, and
Surface tension constraint and fluid resistance is overcome, from negative electrode at aperture on negative electrode sequin 12 and 13
Depart from spindle container 10 at aperture on sequin 12 and 13 and enter inside surface tension propellant tank；With this
Meanwhile, bubble, is i.e. drawn close near anelectrode big circular slice 11 to the big direction of electric field intensity in the effect of electric field force,
Make bubble coalescence in spindle container 10 central authorities, finally need to be discharged by exhaustor 2 during aerofluxus.Additionally,
Exhaustor 2 can be that straight tube can also be for screw type exhaustor, when there being drop to be mixed into exhaustor 2, and spiral
Type exhaustor can play and stop the effect discharged by the trace drop being mixed into exhaustor 2 further.Thus
Visible, spindle container 10 and the screw type exhaustor 2 arranged with electric field by this may insure that a nothing
The pure gas of liquid is discharged with specific temperature and pressure.
Designed by invention system, the master of microgravity environment therapeutic method to keep the adverse QI flowing downwards liquid phase separation can be effectively improved
Dynamic control ability and and service fluid management level in-orbit.
The above, only one of embodiments of the invention, but do not limit the scope of the invention.According to this
The equivalence that invention claim is made changes and amendment, still falls within the scope of the present invention, and former capital should be regarded as this
Bright further embodiment.
In sum, present system is managed by creative utilization electricity hydrodynamics EHD in the fuel tank of space
Reading, the conservative force field formed by electric field replaces gravitational field, the liquid phase of microgravity fuel fluid is distributed into
Row intensive control, to meet the demand supplementing fuel under space microgravity environment for spacecraft, and ensures
Air vent does not haves the phenomenon that drop is discharged, thus effectively extends the service life of spacecraft, saves and launches
Cost, and improve mobility and the reliability of spacecraft.In the case of current spatial resource day is becoming tight,
This novel loading technique in-orbit, it can be avoided that the generation of more space junk, has more highlighted its using value.
Can be that the offers such as long-term human space flight, large-scale survey of deep space and construction exterior planets base add beam in-orbit
Body management technique is supported.This system has actively controlling, stability, persistency and repeatable feature.
The content not being described in detail in description of the invention belongs to the known skill of professional and technical personnel in the field
Art.
Claims (7)
1. space based on a field effect fuel tank fluid management system, it is characterised in that: include storage
Tank wall (1), exhaustor (2), discharge opeing/filler (3), it is made up of top cylinder (401) and doffing (402)
Central tube (4), inner deflector (5), outer deflector (6), pop-up disk ring (7), lower tray (8),
Anelectrode rod (9) and container (10)；
Top cylinder (401) and doffing (402) realize upper and lower solid by the inner deflector (5) of grafting or welding
Fixed connection, between top cylinder (401) and doffing (402), interface, doffing outer circumference all spray ring on face
Epoxy resins coating；Anelectrode rod (9) is fixed on doffing (402) inside and the axle of anelectrode rod (9)
Line and the dead in line of doffing (402), the upper disc of anelectrode rod (9) and the lower equal spray epoxy of disc
Coating；Anelectrode rod (9) is connected with the positive pole of power supply, doffing (402) circumference wall and the negative pole of power supply
Connect；Multiple mm magnitude is opened little in top cylinder (401) and the circumference wall of doffing (402), inner deflector
Hole；Capillary screen cloth is installed, in tank and discharge opeing between lower end and the discharge opeing/filler (3) of doffing (402)
Exhaustor (2) is installed in the upper end that/filler (3) is relative；Container (10) upper end with electric field is provided with row
QI KOU, this air vent is fixing with exhaustor (3) to be connected, and container (10) lower end is provided with air inlet；Tank wall
(1), exhaustor (2), discharge opeing/filler (3), central tube (4), inner deflector (5), outer deflector
(6), pop-up disk ring (7), lower tray (8) form board-like surface tension fuel tank；
Under microgravity environment, when needing to discharge the fuel in tank, power supply powers up, and fuel is by center
Aperture on cylinder (4) circumference wall enters central tube (4), enters doffing (402) interior anelectrode rod (9)
And the electric field region formed between doffing barrel, by the bubble that is mixed in fuel under the effect of electric field force, prominent
Surface tension at broken doffing (402) circumference wall aperture and the constraint of fluid resistance, from doffing (402)
Off center cylinder (4) at circumference wall aperture and enter inside fuel tank, by central tube (4)
Electric field action, it is to avoid bubble is mixed into discharge opeing/filler (3), by the electric field action in container, it is to avoid drop
It is mixed into exhaustor (2).
A kind of space of based on field effect the most according to claim 1 fuel tank fluid management system
System, it is characterised in that: described exhaustor (2) is screw type exhaustor.
A kind of space of based on field effect the most according to claim 1 fuel tank fluid management system
System, it is characterised in that: described exhaustor (2) is straight tube.
4. according to a kind of based on field effect the space fuel tank fluid management described in Claims 2 or 3
System, it is characterised in that: parallel installation negative electricity in two installation circular holes of the waist of described container (10)
Polar circle sheet (12,13), negative electrode disk (12,13) is connected with the negative pole of power supply；Negative electrode disk (12,
13) between the installation circular hole and on container (10) waist, outside negative electrode disk (12,13), disc is equal
Spray epoxy coating；Internally installed one of container (10) is parallel to negative electrode disk (12,13)
Anelectrode disk (11), anelectrode disk (11) circumference wall spray epoxy coating, negative electrode disk
With the aperture all having mm magnitude on anelectrode disk.
A kind of space of based on field effect the most according to claim 4 fuel tank fluid management system
System, it is characterised in that: described container (10) is spindle container, upper lower section be isosceles trapezoid
Two revolving body compositions, are installed by waist flange between two revolving bodies and link together, on waist flange
It is arranged with two and circular hole is installed, be used for negative electrode disk (12,13) is installed.
A kind of space of based on field effect the most according to claim 4 fuel tank fluid management system
System, it is characterised in that: described anelectrode disk (11) runs through centrage and the spindle container (10) of self
Its upper end air vent that connects overlap with the axis of rotation of lower end air inlet, and anelectrode disk (11) is flat
Row is in negative electrode disk (12,13).
A kind of space of based on field effect the most according to claim 4 fuel tank fluid management system
System, it is characterised in that: the disk area of described anelectrode disk (11) is more than the area of negative electrode disk.
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110884693A (en) * | 2019-12-06 | 2020-03-17 | 中国人民解放军国防科技大学 | Passive feed type electrospray thruster system |
| CN114044169A (en) * | 2021-10-21 | 2022-02-15 | 上海空间推进研究所 | Refillable tension type propellant storage tank and preparation method thereof |
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| EP0042784A2 (en) * | 1980-06-20 | 1981-12-30 | SOCIETE EUROPEENNE DE PROPULSION (S.E.P.) Société Anonyme dite: | Surface tension storage device |
| US4472278A (en) * | 1981-11-18 | 1984-09-18 | Agency Of Industrial Science & Technology | Separating device for an insulating gas-liquid two phase fluid |
| US5279323A (en) * | 1991-12-19 | 1994-01-18 | Lockheed Missiles & Space Company, Inc. | Liquid management apparatus for spacecraft |
| CN102518940A (en) * | 2011-12-20 | 2012-06-27 | 北京控制工程研究所 | Plate-type propellant management apparatus |
| CN103133862A (en) * | 2013-02-05 | 2013-06-05 | 上海空间推进研究所 | Bearing surface tension storage box |
| CN104691786A (en) * | 2015-01-07 | 2015-06-10 | 北京控制工程研究所 | Novel propellant management device used in propellant storage box |
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| EP0042784A2 (en) * | 1980-06-20 | 1981-12-30 | SOCIETE EUROPEENNE DE PROPULSION (S.E.P.) Société Anonyme dite: | Surface tension storage device |
| US4472278A (en) * | 1981-11-18 | 1984-09-18 | Agency Of Industrial Science & Technology | Separating device for an insulating gas-liquid two phase fluid |
| US5279323A (en) * | 1991-12-19 | 1994-01-18 | Lockheed Missiles & Space Company, Inc. | Liquid management apparatus for spacecraft |
| CN102518940A (en) * | 2011-12-20 | 2012-06-27 | 北京控制工程研究所 | Plate-type propellant management apparatus |
| CN103133862A (en) * | 2013-02-05 | 2013-06-05 | 上海空间推进研究所 | Bearing surface tension storage box |
| CN104691786A (en) * | 2015-01-07 | 2015-06-10 | 北京控制工程研究所 | Novel propellant management device used in propellant storage box |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110884693A (en) * | 2019-12-06 | 2020-03-17 | 中国人民解放军国防科技大学 | Passive feed type electrospray thruster system |
| CN110884693B (en) * | 2019-12-06 | 2021-06-25 | 中国人民解放军国防科技大学 | Passive feed type electrospray thruster system |
| CN114044169A (en) * | 2021-10-21 | 2022-02-15 | 上海空间推进研究所 | Refillable tension type propellant storage tank and preparation method thereof |
Also Published As
| Publication number | Publication date |
|---|---|
| CN105858583B (en) | 2018-04-10 |
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