CN111389150A - Full-working-condition gas-liquid separation device of satellite storage tank - Google Patents
Full-working-condition gas-liquid separation device of satellite storage tank Download PDFInfo
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- CN111389150A CN111389150A CN202010203213.XA CN202010203213A CN111389150A CN 111389150 A CN111389150 A CN 111389150A CN 202010203213 A CN202010203213 A CN 202010203213A CN 111389150 A CN111389150 A CN 111389150A
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B01—PHYSICAL OR CHEMICAL PROCESSES OR APPARATUS IN GENERAL
- B01D—SEPARATION
- B01D50/00—Combinations of methods or devices for separating particles from gases or vapours
- B01D50/20—Combinations of devices covered by groups B01D45/00 and B01D46/00
Abstract
A full-working-condition gas-liquid separation device of a satellite storage tank comprises an upper cover plate (1) and the like; the centrifugal blades (2) are uniformly distributed along the circumferential direction and are arranged between the upper cover plate (1) and the lower cover plate (3); the cylindrical cavity (8) is arranged in the center of the upper cover plate (1), and the cylindrical cavity (8) is communicated with the cavity between the centrifugal blades (2); the lower baffle (4) is fixed at the lower end of the cylindrical cavity (8), and the guide plates (5) are uniformly fixed on the inner wall surface of the cylindrical cavity (8) along the circumferential direction; the perforated plate (7) is arranged on the upper partition plate (6), and the perforated plate (7) and the upper partition plate (6) are arranged at the upper end of the cylindrical cavity (8). The device realizes effective gas-liquid separation of the satellite propellant storage tank in the microgravity environment by utilizing the principle that centrifugal force and surface tension drive fluid, avoids liquid clamping in the exhaust process of the storage tank, has simple structure, no moving part, easy processing, light weight and high reliability, and can meet the use requirements of various space environments.
Description
Technical Field
The invention relates to a full-working-condition gas-liquid separation device for a satellite storage tank, belonging to the technical field of spaceflight.
Background
The satellite on-orbit filling technology can be divided into pressurization type, exhaust type, through type filling and the like, and the exhaust type filling needs to exhaust through an air port of the storage tank so as to ensure that the internal pressure of the storage tank cannot be continuously increased and reduce the pressure of repeated filling of the propellant. The gas port of the storage tank is provided with a gas-liquid separator which is a key device of an exhaust type on-orbit filling mode, and at present, no mature gas-liquid separator device exists in China. The gas-liquid separation on the ground can be realized by the techniques of gravity separation, centrifugal separation and the like. When the satellite runs in orbit, the gravity action disappears, the surface tension action is obvious, and the gas-liquid separation can not be realized through the gravity action in the storage box. The centrifugal gas-liquid separation technology used on the ground is basically realized by adopting a rotating part or designing a spiral flow passage, the satellite propellant storage tank is changed into an electromechanical product by the aid of the rotating part, and reliability and safety of the storage tank are reduced. The spiral flow passage type gas-liquid separation can only play a role in separation under the condition of large flow rate, and cannot play a role in separation under the condition of small flow rate or pressure difference. The existing gas-liquid separator is based on surface tension separation, is arranged on a gas outlet pipeline of a storage tank, needs a separate installation space, increases the cost of a satellite, and is a key for realizing repeated supplement of a satellite propellant by a gas-liquid separation device arranged in the storage tank and used for an exhaust type on-orbit filling technology.
Disclosure of Invention
The technical problem to be solved by the invention is as follows: the device is arranged at the air port end of the propellant storage tank and fixed inside the storage tank, and the exhaust type on-orbit filling of the propellant storage tank is realized.
The technical solution of the invention is as follows: a full-working-condition gas-liquid separation device of a satellite storage tank comprises an upper cover plate, centrifugal blades, a lower cover plate, a lower partition plate, a guide plate, an upper partition plate, a perforated plate and a cylindrical cavity; the centrifugal blades are uniformly distributed along the circumferential direction and are arranged between the upper cover plate and the lower cover plate; the cylindrical cavity is arranged in the center of the upper cover plate and is communicated with the cavity between the centrifugal blades; the lower baffle plate is fixed at the lower end of the cylindrical cavity, and the guide plates are uniformly fixed on the inner wall surface of the cylindrical cavity along the circumferential direction; the perforated plate is arranged on the upper partition plate, and the perforated plate and the upper partition plate are arranged at the upper end of the cylindrical cavity; the lower partition plate and the upper partition plate are both provided with frustum-shaped grooves, and the bottoms of the grooves are provided with openings; a plurality of through holes are uniformly distributed on the perforated plate.
The centrifugal blades are rectangular blades, the number of the centrifugal blades is 12-20, and the included angle between the tangent line at the intersection point of the centrifugal blade and the lower cover plate and the corresponding centrifugal blade ranges from 30 degrees to 60 degrees from the overlooking angle.
The diameter of the through hole on the perforated plate is 0.02-0.05 mm.
The cone angle of the frustum-shaped groove on the lower clapboard is 30-80 degrees.
The cone angle of the frustum-shaped groove on the upper clapboard is 30-80 degrees.
The total number of the guide plates is 6, the guide plates are uniformly fixed in the cylindrical cavity and are arranged in the area between the upper partition plate and the lower partition plate.
The upper cover plate and the lower cover plate are both of two parallel disc structures with the same outer diameter.
The distance between the upper cover plate and the lower cover plate is 10-30 mm.
The satellite storage tank all-working-condition gas-liquid separation device is made of titanium alloy.
The full-working-condition gas-liquid separation device of the satellite storage tank is arranged at a gas port at the top of the storage tank, a gas-liquid mixed medium enters a region between centrifugal blades from the outer sides of the centrifugal blades, a propellant is separated to a region with a large diameter after centrifugal acceleration, gas is collected to the center of the centrifugal blades to realize gas-liquid separation, the gas is sucked into the cylindrical cavity under the action of the lower partition plate, and the gas is continuously discharged after passing through the upper partition plate and the perforated plate; the liquid in the cylindrical cavity is collected on the wall surface of the cylindrical cavity along the guide plate.
Compared with the prior art, the invention has the following advantages:
(1) the all-condition gas-liquid separation device of the satellite storage tank realizes the gas-liquid separation function of the all-condition exhaust type filling process by utilizing the centrifugal force and the surface tension effect, the flow rate of the gas-liquid separation can reach 20L/min, and the gas exhaust without liquid inclusion can be realized.
(2) The centrifugal blades are straight blades which are suitable in number according to the outer diameter of the gas-liquid separator, so that the centrifugal blades are convenient to process and manufacture, the gas-liquid mixed medium can be induced to generate centrifugal force, the propellant with high density is separated to an area with large diameter under the action of the centrifugal force, and the gas is collected to the center of the centrifugal blades, so that gas-liquid separation is realized.
(3) The perforated plate is a second defense line for exhausting and blocking liquid under microgravity, and can effectively prevent liquid from being discharged.
(4) The lower baffle plate and the upper baffle plate of the invention adopt a conical cavity structure, and can effectively guide the gas passing through the centrifugal blade into the cylindrical cavity and the gas port of the storage tank.
(5) The raw materials of the gas-liquid separation device are titanium alloy materials, the gas-liquid separation device basically belongs to a pure plate type structure without movable parts, the gas-liquid separation device is simple in structure, high in structural strength and good in flexibility, can effectively release loads such as impact and vibration born by the gas-liquid separation device, and can bear a certain lateral acceleration. The gas-liquid separation device can be used for gas-liquid separation of various conventional propellants in a microgravity environment.
Drawings
FIG. 1 is a schematic view of a full-condition gas-liquid separation device of a satellite storage tank according to the present invention;
FIG. 2 is a view of the construction of the centrifugal vane of the present invention;
FIG. 3 is a structural view of the apertured plate of the present invention;
FIG. 4 is a view showing the construction of the lower partition plate of the present invention;
FIG. 5 is a view showing the construction of the upper partition plate of the present invention;
Detailed Description
The following is further described with reference to the accompanying drawings.
Examples
As shown in fig. 1, the full-condition gas-liquid separation device for the satellite storage tank comprises: the centrifugal fan comprises an upper cover plate 1, a centrifugal blade 2, a lower cover plate 3, a lower baffle 4, a guide plate 5, an upper baffle 6, a perforated plate 7 and a cylindrical cavity 8; a plurality of centrifugal blades 2 are uniformly distributed along the circumferential direction and are arranged between the upper cover plate 1 and the lower cover plate 3; the cylindrical cavity 8 is arranged in the center of the upper cover plate 1, and the cylindrical cavity 8 is communicated with the cavity between the centrifugal blades 2; the lower baffle 4 is fixed at the lower end of the cylindrical cavity 8, and the guide plates 5 are uniformly fixed on the inner wall surface of the cylindrical cavity 8 along the circumferential direction; the perforated plate 7 is arranged on the upper partition plate 6, and the perforated plate 7 and the upper partition plate 6 are arranged at the upper end of the cylindrical cavity 8; the lower partition plate 4 and the upper partition plate 6 are both provided with frustum-shaped grooves, and the bottoms of the grooves are open; a plurality of through holes are uniformly distributed on the perforated plate 7.
As shown in figure 2, the centrifugal blade 2 is a structural schematic diagram, the centrifugal blade 2 is formed by periodically arranging 12-20 rectangular blades and can meet the requirements of different flow rates and exhaust speeds, the rectangular blades are of flat plate structures, the thickness of the rectangular blades is 0.5-1.5 mm, the placement angle A of the rectangular blades is 30-60 degrees, small-gap flow is formed among the rectangular blades, gap jet flow can be formed, the centrifugal movement speed is improved, and the gas-liquid separation rate is improved.
As shown in fig. 3, which is a schematic structural diagram of the perforated plate 7 of the present invention, the perforated plate 7 is a second defense line for exhausting and blocking liquid under microgravity, the aperture of the small hole on the perforated plate is 0.02-0.05 mm, and the bubble breaking point of the perforated plate is greater than 1000Pa, so that the liquid can be effectively blocked from being discharged. The perforated plate has a bubble break point value, generally not less than 1500Pa, and can effectively prevent liquid from being discharged out of the storage tank through the perforated plate. This is a third barrier to liquid drainage.
As shown in fig. 4, which is a schematic structural diagram of the lower baffle 4 of the present invention, the lower baffle 4 adopts a tapered cavity structure, the taper angle C is 50 ° to 75 °, the top of the cone is removed, and the diameter of the removed part is 30mm, so that the gas passing through the centrifugal blade can be effectively introduced into the cylindrical cavity.
As shown in FIG. 5, which is a schematic view of the structure of the upper baffle 6 of the present invention, the upper baffle 6 of the present invention adopts a tapered cavity structure, the taper angle B is 50 degrees to 75 degrees, the top of the cone is removed, the diameter of the removed part is 20mm, and the gas passing through the centrifugal blade can be effectively guided into the cylindrical cavity and the gas port of the storage tank.
The total 6 guide plates 6 are uniformly fixed in the cylindrical cavity 8 and are arranged in the area between the upper partition plate 6 and the lower partition plate 4, and the thickness of each guide plate 6 is 1 mm.
The upper cover plate 1 and the lower cover plate 6 are of two parallel disc structures with the same outer diameter, and the distance between the two disc structures is 10-30 mm.
The material of the satellite storage tank full-working-condition gas-liquid separation device is titanium alloy.
The working principle of the invention is as follows:
after gas-liquid mixed media enter the area between the centrifugal blades 2 from the outer sides of the centrifugal blades 2 and are accelerated centrifugally, liquid propellant with high density is separated to the area with large diameter, gas is collected towards the center of the centrifugal blades 2, primary gas-liquid separation is realized, the gas is sucked into the cylindrical cavity 8 under the action of the lower partition plate 4, and the gas is discharged after continuously passing through the upper partition plate 6 and the perforated plate 7. When a large amount of liquid enters the cylindrical cavity 8, the liquid can continuously collect near the wall surface of the cylindrical cavity 8 along the guide plate 5, and the gas is uniformly positioned in the central area of the cylindrical cavity and is smoothly discharged. The perforated plate 7 is a second defense line for exhausting and blocking liquid under microgravity, and can effectively block liquid from being discharged.
The invention utilizes the principle of centrifugal gas-liquid separation to design the centrifugal blades 2 to form a gap flow channel, so that gas-liquid mixed media are separated under the centrifugal action, and simultaneously, the perforated plate 7 is designed to form a second channel defense line for blocking liquid based on the principle that the surface tension forms resistance to establish a bubble breaking point.
Those skilled in the art will appreciate that the invention may be practiced without these specific details.
Claims (10)
1. A full-working-condition gas-liquid separation device of a satellite storage tank is characterized by comprising an upper cover plate (1), centrifugal blades (2), a lower cover plate (3), a lower partition plate (4), a guide plate (5), an upper partition plate (6), a perforated plate (7) and a cylindrical cavity (8);
the centrifugal blades (2) are uniformly distributed along the circumferential direction and are arranged between the upper cover plate (1) and the lower cover plate (3); the cylindrical cavity (8) is arranged in the center of the upper cover plate (1), and the cylindrical cavity (8) is communicated with the cavity between the centrifugal blades (2); the lower baffle (4) is fixed at the lower end of the cylindrical cavity (8), and the guide plates (5) are uniformly fixed on the inner wall surface of the cylindrical cavity (8) along the circumferential direction; the perforated plate (7) is arranged on the upper partition plate (6), and the perforated plate (7) and the upper partition plate (6) are arranged at the upper end of the cylindrical cavity (8); the lower partition plate (4) and the upper partition plate (6) are both provided with frustum-shaped grooves, and the bottoms of the grooves are open; a plurality of through holes are uniformly distributed on the perforated plate (7).
2. The full-working-condition gas-liquid separation device for the satellite storage tank according to claim 1, characterized in that: the centrifugal blades (2) are rectangular blades, the number of the centrifugal blades is 12-20, and the included angle between the tangent line at the intersection point of the centrifugal blade (2) and the lower cover plate (3) and the corresponding centrifugal blade (2) ranges from 30 degrees to 60 degrees from the overlooking angle.
3. The full-working-condition gas-liquid separation device for the satellite storage tank according to claim 1 or 2, characterized in that: the diameter of the through hole on the perforated plate (7) is 0.02-0.05 mm.
4. The full-condition gas-liquid separation device for the satellite storage tank according to claim 3, characterized in that: the cone angle of the frustum-shaped groove on the lower clapboard (4) is 30-80 degrees.
5. The full-working-condition gas-liquid separation device for the satellite storage tank according to claim 4, characterized in that: the cone angle of the frustum-shaped groove on the upper clapboard (6) is 30-80 degrees.
6. The full-working-condition gas-liquid separation device for the satellite storage tank according to claim 5, characterized in that: the number of the guide plates (6) is 6, the guide plates are uniformly fixed in the cylindrical cavity (8) and are arranged in the area between the upper partition plate (6) and the lower partition plate (4).
7. The full-condition gas-liquid separation device for the satellite storage tank according to claim 6, characterized in that: the upper cover plate (1) and the lower cover plate (6) are both of two parallel disc structures with the same outer diameter.
8. The full-condition gas-liquid separation device for the satellite storage tank according to claim 7, characterized in that: the distance between the upper cover plate (1) and the lower cover plate (6) is 10-30 mm.
9. The full-condition gas-liquid separation device for the satellite storage tank according to claim 8, characterized in that: the satellite storage tank all-working-condition gas-liquid separation device is made of titanium alloy.
10. The full-condition gas-liquid separation device for the satellite storage tank according to claim 9, characterized in that: the full-working-condition gas-liquid separation device of the satellite storage box is arranged at a gas port at the top of the storage box, a gas-liquid mixed medium enters an area between centrifugal blades (2) from the outer side of the centrifugal blades (2), a propellant is separated to an area with a large diameter after centrifugal acceleration, gas is collected towards the center of the centrifugal blades (2) to realize gas-liquid separation, the gas is sucked into a cylindrical cavity (8) under the action of a lower partition plate (4), and the gas is continuously discharged after passing through an upper partition plate (6) and a perforated plate (7); the liquid in the cylindrical cavity (8) is collected on the wall surface of the cylindrical cavity (8) along the guide plate (5).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010203213.XA CN111389150A (en) | 2020-03-20 | 2020-03-20 | Full-working-condition gas-liquid separation device of satellite storage tank |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010203213.XA CN111389150A (en) | 2020-03-20 | 2020-03-20 | Full-working-condition gas-liquid separation device of satellite storage tank |
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| CN111389150A true CN111389150A (en) | 2020-07-10 |
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| CN202010203213.XA Pending CN111389150A (en) | 2020-03-20 | 2020-03-20 | Full-working-condition gas-liquid separation device of satellite storage tank |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112412932A (en) * | 2020-09-30 | 2021-02-26 | 北京控制工程研究所 | Gas-liquid separation device for low-temperature storage tank of spacecraft |
| CN114259799A (en) * | 2021-11-30 | 2022-04-01 | 武汉格罗夫氢能汽车有限公司 | Steam-water separator for fuel cell |
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2020
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Patent Citations (6)
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| US5293895A (en) * | 1991-12-19 | 1994-03-15 | Lockheed Missiles & Space Company, Inc. | Liquid management apparatus for spacecraft |
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| CN104005985A (en) * | 2014-05-16 | 2014-08-27 | 江苏大学 | Multiple-blade blocking-free pump impeller and design method thereof |
| CN105346734A (en) * | 2015-11-20 | 2016-02-24 | 上海空间推进研究所 | Surface tension storage box capable of exhausting |
| CN108704392A (en) * | 2018-05-29 | 2018-10-26 | 中国人民解放军国防科技大学 | Centrifugal force inertia cascade gas-liquid separator |
| CN110052109A (en) * | 2019-05-15 | 2019-07-26 | 北京控制工程研究所 | A kind of gas-liquid separation device for satellite booster agent tank |
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| 宁继荣等: "多孔板泡破点试验研究", 《火箭推进》 * |
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Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112412932A (en) * | 2020-09-30 | 2021-02-26 | 北京控制工程研究所 | Gas-liquid separation device for low-temperature storage tank of spacecraft |
| CN112412932B (en) * | 2020-09-30 | 2023-02-03 | 北京控制工程研究所 | Gas-liquid separation device for low-temperature storage tank of spacecraft |
| CN114259799A (en) * | 2021-11-30 | 2022-04-01 | 武汉格罗夫氢能汽车有限公司 | Steam-water separator for fuel cell |
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Application publication date: 20200710 |
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