CN116085145A - Surface tension storage box of upper convex septum - Google Patents
Surface tension storage box of upper convex septum Download PDFInfo
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- CN116085145A CN116085145A CN202211633293.8A CN202211633293A CN116085145A CN 116085145 A CN116085145 A CN 116085145A CN 202211633293 A CN202211633293 A CN 202211633293A CN 116085145 A CN116085145 A CN 116085145A
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- 238000003860 storage Methods 0.000 title claims abstract description 59
- 238000005192 partition Methods 0.000 claims abstract description 61
- 239000007788 liquid Substances 0.000 claims abstract description 41
- 239000003380 propellant Substances 0.000 claims abstract description 28
- 238000004891 communication Methods 0.000 claims description 12
- 239000002184 metal Substances 0.000 claims description 10
- 238000000926 separation method Methods 0.000 claims description 7
- 238000003466 welding Methods 0.000 description 12
- 239000007789 gas Substances 0.000 description 10
- 238000010894 electron beam technology Methods 0.000 description 8
- 230000005486 microgravity Effects 0.000 description 6
- 239000004744 fabric Substances 0.000 description 5
- XKRFYHLGVUSROY-UHFFFAOYSA-N Argon Chemical compound [Ar] XKRFYHLGVUSROY-UHFFFAOYSA-N 0.000 description 4
- 229910052786 argon Inorganic materials 0.000 description 2
- 230000000694 effects Effects 0.000 description 2
- 239000012530 fluid Substances 0.000 description 2
- 230000005764 inhibitory process Effects 0.000 description 2
- 238000004519 manufacturing process Methods 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 239000000523 sample Substances 0.000 description 2
- 238000012546 transfer Methods 0.000 description 2
- 230000009471 action Effects 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000011161 development Methods 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 238000009826 distribution Methods 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 230000007613 environmental effect Effects 0.000 description 1
- 239000000446 fuel Substances 0.000 description 1
- 230000006872 improvement Effects 0.000 description 1
- 238000002955 isolation Methods 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 239000007800 oxidant agent Substances 0.000 description 1
- 230000001590 oxidative effect Effects 0.000 description 1
- 230000002265 prevention Effects 0.000 description 1
- 230000008569 process Effects 0.000 description 1
- 238000001179 sorption measurement Methods 0.000 description 1
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Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K9/00—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
- F02K9/42—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof using liquid or gaseous propellants
- F02K9/60—Constructional parts; Details not otherwise provided for
- F02K9/605—Reservoirs
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G1/00—Cosmonautic vehicles
- B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
- B64G1/40—Arrangements or adaptations of propulsion systems
- B64G1/402—Propellant tanks; Feeding propellants
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K9/00—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
- F02K9/42—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof using liquid or gaseous propellants
- F02K9/44—Feeding propellants
- F02K9/50—Feeding propellants using pressurised fluid to pressurise the propellants
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- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Remote Sensing (AREA)
- Aviation & Aerospace Engineering (AREA)
- Filling Or Discharging Of Gas Storage Vessels (AREA)
Abstract
The invention provides a surface tension storage tank with an upper convex septum, which comprises a storage tank pressure-bearing shell, wherein the storage tank pressure-bearing shell comprises an upper shell, a column section and a lower shell which are sequentially connected, the inside of the storage tank pressure-bearing shell is provided with the upper convex septum, the septum divides the storage tank into an upper cabin and a lower cabin, the top of the upper shell is provided with an air tap, the bottom of the lower shell is provided with a liquid tap, the top of the septum is provided with a deflation port screen, and the septum is provided with a septum screen; during the track-changing ignition period, pressurized gas enters the upper cabin through the air tap, propellant in the upper cabin enters the lower cabin through the middle partition screen, liquid films are arranged in the middle partition screen and the air discharge port screen, the pressurized gas can be prevented from entering the lower cabin before the propellant is exhausted, and the gas in the lower cabin is discharged to the upper cabin through the air discharge port screen. The invention has smaller size of the middle partition required for separating the lower cabin with the same volume, smaller structural mass and improved mechanical environment adaptability of the upper convex middle partition, and can be more suitable for vibration and impact of rocket launching stage.
Description
Technical Field
The invention relates to the technical field of spacecraft power systems, in particular to a surface tension storage tank of an upper convex septum, which is suitable for the surface tension storage tank of the upper convex septum for propellant management of a satellite or deep space probe propulsion system.
Background
With the development of aerospace technology, people have increasingly high requirements on spacecrafts. The existing space vehicle power systems such as satellites or deep space probes adopt a large number of surface tension storage tanks for storing and supplying non-air-entraining propellants to engines, and the surface tension storage tanks are key components for determining the performance and safety of the space vehicle, and the surface tension storage tanks which are light, reliable, high in emission efficiency and have liquid shaking inhibition capability have important significance for reducing the structural quality, improving the performance of the space vehicle, guaranteeing the emission safety, prolonging the service life and the like.
With the improvement of requirements of long service life, high performance, high reliability and the like of an aircraft, the volume of a used surface tension storage tank is continuously increased, the structural efficiency and the emission efficiency are also continuously improved, and the scheme of adopting a fully-managed propellant management device is not suitable for the requirements of tasks. The spacecraft power system uses a large-volume surface tension storage tank to gradually partition the cabin structure to improve the performance. At present, a large-volume surface tension storage tank commonly adopts a concave septum to divide the storage tank, so that the storage tank is more limited in the aspects of structural efficiency, lower tank volume and the like, and the concave septum has weak liquid management capability on an upper tank and cannot inhibit liquid shaking at the end of upper tank discharge.
The prior publication No. CN102991729B discloses a light net type surface tension storage tank, which adopts a concave middle bottom baffle plate to divide an upper cabin and a lower cabin, and an anti-shaking cone is added in the upper cabin for liquid shaking inhibition and a special exhaust port structure.
The utility model discloses a bearing type low temperature common-bottom storage box for spacecraft of the prior publication No. CN114922744A, adopts the protruding "common bottom" to carry out upper and lower cabin division, but "common bottom" is the casing that does not have the trompil or arrange metal screen cloth, and upper and lower cabin is totally independent after the division, is used for loading oxidant and fuel respectively, is totally different with this patent the septum function.
In the prior art, the partition structure of the middle partition is low in efficiency, the obtained lower partition has the same volume, needs larger structural size and mass, is not suitable for the requirements of the lower partition with high performance and large volume, has insufficient microgravity liquid storage capacity in the upper partition after the partition, is additionally provided with an anti-shaking device and an air outlet of a cantilever, leads to the complicated structure of a propellant management device, reduces the mechanical environment adaptability and reliability, leads the performance of a surface tension storage tank to be limited, and has the place to be improved.
Disclosure of Invention
In view of the shortcomings in the prior art, it is an object of the present invention to provide a surface tension reservoir for an upper convex septum.
The invention provides a surface tension storage tank with an upper convex septum, which comprises a storage tank pressure-bearing shell, wherein the storage tank pressure-bearing shell comprises an upper shell, a column section and a lower shell which are sequentially connected, the interior of the storage tank pressure-bearing shell is provided with the upper convex septum, the septum divides the storage tank into an upper cabin and a lower cabin, and the upper cabin is used for containing propellant;
the top of the upper shell is provided with an air tap, the bottom of the lower shell is provided with a liquid tap, the top of the middle partition is provided with a deflation port screen, the middle partition is provided with a middle partition screen, and the inner part of the lower cabin is provided with a net-carrying channel;
the surface tension storage tank of the upper convex septum is used for a space vehicle, when the space vehicle is in a track-changing ignition period, pressurized gas enters the upper cabin through the air tap, propellant in the upper cabin enters the lower cabin through the middle septum screen, liquid films are arranged in the middle septum screen and the air vent screen, the pressurized gas can be prevented from entering the lower cabin before the propellant is exhausted, the gas-liquid separation can be carried out through the net-carrying channel, and the gas in the lower cabin is discharged to the upper cabin through the air vent screen.
Preferably, the septum is disposed at the upper end of the lower housing and protrudes toward the column section to form a spherical or ellipsoidal thin-shell structure.
Preferably, a wedge-shaped cavity is formed between the middle partition and the column section of the spherical or ellipsoidal thin-shell structure, and during rail transfer ignition, the unspent propellant in the upper cabin is stored in the wedge-shaped cavity.
Preferably, the septum is made of metal.
Preferably, the lower cabin is internally provided with a pair of communicating seats and a plurality of strip net channels, and the pair of communicating seats are respectively arranged at the upper end and the lower end of the lower cabin;
the two ends of the net-carrying channels are respectively connected with the communication seats which are arranged in pairs, and the multi-band net-carrying channels are arranged along the circumferential direction of the lower cabin.
Preferably, the mesh-carrying channel is a semi-ring structure with a U-shaped section, and two ends of the semi-ring structure are respectively connected with the communication seats which are arranged in pairs;
and a metal screen is welded on the U-shaped opening with the net channel to form a liquid conveying channel.
Preferably, the metal screen, the middle-isolation screen and the air vent screen have bubble breaking points not lower than 3700Pa.
Preferably, the width of the U-shaped section is 35 mm-45 mm, and the depth is 6 mm-8 mm.
Preferably, the screened channels are disposed between adjacent septal screens.
Preferably, the septum screen is a plurality of, a plurality of septum screens set up in septum near the lower extreme along circumference evenly.
Compared with the prior art, the invention has the following beneficial effects:
1. the invention has simple structure and convenient operation, adopts the technical means of separating the storage tank with high efficiency by adopting the upward convex middle partition structure, has smaller middle partition size required by separating the lower cabin with the same volume, has smaller required structural mass, has the first-order frequency of the vibration of the spherical or ellipsoidal middle partition of about 75Hz and the first-order frequency of about 35Hz of the middle partition of the shallow conical plate and the butterfly middle partition, has improved mechanical environment adaptability, and is more suitable for the vibration and impact of rocket launching stage.
2. The invention adopts the technical means that the middle partition and the column section form the wedge-shaped cavity, is used for storing the propellant in the microgravity environment, has the functions of shaking prevention and cabin separation, ensures that liquid can be stored in the wedge-shaped cavity under the action of surface tension in the microgravity environment, has simple structure, inhibits the shaking of the liquid and has obvious storage effect, so that the middle partition screen at the bottom of the middle partition is always immersed in the propellant in the wedge-shaped cavity, and ensures the high-efficiency exhaustion of the propellant in the upper cabin more stably.
3. The invention adopts the technical means that the top of the upper convex septum is provided with the air vent screen, replaces the scheme of arranging the air vent of the additional cantilever of the lower concave septum in the upper cabin in the prior art, has better structural stability, lighter weight and smoother air vent path.
Drawings
Other features, objects and advantages of the present invention will become more apparent upon reading of the detailed description of non-limiting embodiments, given with reference to the accompanying drawings in which:
FIG. 1 is a schematic diagram of the structure of the present invention;
FIG. 2 is a schematic representation of the distribution of propellant discharged from the upper chamber in the microgravity environment in the present invention;
the figure shows:
Septum 7 of upper housing 2
The lower shell 4 is provided with a net passage 9
Detailed Description
The present invention will be described in detail with reference to specific examples. The following examples will assist those skilled in the art in further understanding the present invention, but are not intended to limit the invention in any way. It should be noted that variations and modifications could be made by those skilled in the art without departing from the inventive concept. These are all within the scope of the present invention.
The invention discloses a surface tension storage box of an upper convex septum, which has smaller size and smaller required structural mass for separating a lower cabin with the same volume from the upper convex septum, and the first-order frequency of vibration of the spherical or ellipsoidal septum is about 75Hz and is about 35Hz of that of the septum of a shallower conical septum and the septum of a butterfly, so that the mechanical environmental adaptability is improved, and the storage box is more suitable for vibration and impact of rocket launching stages.
The surface tension storage tank with the upper convex septum provided by the invention, as shown in figures 1-2, comprises a storage tank pressure-bearing shell, wherein the storage tank pressure-bearing shell comprises an upper shell 2, a column section 3 and a lower shell 4 which are sequentially connected, the storage tank pressure-bearing shell is internally provided with the upper convex septum 7, the septum 7 divides the storage tank into an upper cabin and a lower cabin, and the upper cabin is used for containing propellant; the middle partition 7 is arranged at the upper end of the lower shell 4 and protrudes towards the column section 3 to form a spherical or ellipsoidal thin shell structure, the middle partition 7 and the lower shell 4 form a lower cabin of the spherical structure, and preferably, the middle partition 7 is made of metal. The upper shell 2 top is provided with air cock 1, the bottom of lower casing 4 is provided with liquid mouth 5, the top of septum 7 is provided with bleed port screen cloth 6, be provided with septum screen cloth 8 on the septum 7, guarantee the intercommunication of fluid medium, the cabin is inside to be provided with down and takes net passageway 9, septum screen cloth 8 is a plurality of, a plurality of septum screen cloth 8 evenly set up in septum 7 near lower extreme department along circumference. Preferably, the middle partition 7 is provided with at least 4 holes on the upper side of the largest diameter, a middle partition screen 8 is welded at the hole, the middle partition screen 8 is placed at the wedge-shaped top angle of the wedge-shaped liquid storage cavity formed by the middle partition 7 and the column section 3 as far as possible, the top of the middle partition 7 is provided with a hole with the diameter not more than 30mm, the hole is welded with a vent screen 6, the liquid or gas of the upper cabin and the lower cabin is communicated through the screen, the gas-liquid fluid of the two cabins can still flow through the holes of the screen, the effect of separation is formed, and the pressurized gas can not enter the lower cabin before the liquid of the upper cabin is exhausted during rail discharge. The escape mouth screen 6 ensures that propellant in the lower cabin can be fully filled when the ground is filled, no suffocating phenomenon exists, and when the rail is discharged, the liquid film on the escape mouth screen 6 can effectively block pressurized gas in the upper cabin from entering the lower cabin, and the escape mouth screen has the advantages of simple structure, good production and manufacturing manufacturability, strong mechanical environment adaptability and the like compared with a concave middle partition.
The lower cabin is internally provided with a pair of communication seats 10 and a plurality of strip net channels 9, and the pair of communication seats 10 are respectively arranged at the upper end and the lower end of the lower cabin; the two ends of the net-carrying channels 9 are respectively connected with the communication seats 10 which are arranged in pairs, and the multi-band net-carrying channels 9 are arranged along the circumferential direction of the lower cabin. The mesh-carrying channel 9 is a semi-ring structure with a U-shaped section, and two ends of the semi-ring structure are respectively connected with the communication seats 10 which are arranged in pairs; a metal screen is welded on the U-shaped opening of the net-shaped channel 9 to form a liquid conveying channel. The screened channel 9, septum 7, septum screen 8 and vent screen 6 form a propellant management device. The net-carrying channel 9 can perform gas-liquid separation, and ensures that the storage tank discharges non-air-entrained propellant. Preferably, at least 4 net channels 9 are uniformly welded on the upper and lower communication seats 10 in a circumferential direction, and the two communication seats 10 are respectively welded on the middle partition 7 and the lower shell 4 to form a gas-liquid separation device in the lower cabin, so that pressurized gas is prevented from being discharged out of the storage tank before the liquid in the lower cabin is exhausted. The circumferential positioning of the meshed channels 9 ensures that the spacecraft is always immersed in the propellant during attitude and orbit control phases, thereby ensuring the supply of non-aerated propellant. Preferably, the metal screen, the middle partition screen 8 and the vent screen 6 have bubble breaking points of not less than 3700Pa.
A wedge-shaped cavity is formed between the middle partition 7 of the spherical or ellipsoidal thin shell structure and the column section 3, and during rail transfer ignition, the unused propellant in the upper cabin is stored in the wedge-shaped cavity. The middle partition 7 is of an upward convex structure and forms a wedge angle with the storage tank column section 3, a liquid storage wedge-shaped cavity is formed in the circumferential direction of the wedge angle, the liquid storage cavity is of a cone angle structure, and the liquid storage cavity has the function of exhausting and absorbing liquid in a microgravity environment. Under space microgravity environment, the wedge-shaped cavity formed by the upper convex middle partition 7 and the column section 3 has stronger liquid adsorption capacity relative to the column section 3 and the upper shell 2, so that the liquid in the upper cabin can cover the middle partition screen 8 welded on the convex middle partition 7, and the preferential exhaustion of the liquid propellant in the upper cabin is ensured.
The surface tension storage tank of the upper convex septum is used for a space vehicle, when the space vehicle is in a track-changing ignition period, pressurized gas enters the upper cabin through the air tap 1, propellant in the upper cabin enters the lower cabin through the middle septum screen 8, liquid films are arranged in the middle septum screen 8 and the air vent screen 6, the pressurized gas can be prevented from entering the lower cabin before the propellant is exhausted, the gas-liquid separation can be carried out through the net-carried channel 9, and the gas in the lower cabin is discharged to the upper cabin through the air vent screen 6.
The assembly process of the invention is as follows: in the work, the staff firstly welds the components through argon arc welding through the multi-strip net channel 9 and the communicating seat 10; the air vent screen 6, the middle partition 7 and the middle partition screen 8 are welded into a middle partition component through vacuum electron beam in parallel, and then the two components are assembled together with the lower shell 4 and the liquid nozzle 5 and welded through vacuum electron beam to form a lower cabin of the storage tank. The air tap 1, the upper shell 2 and the column section 3 are welded into a component through vacuum electron beam welding in parallel, and then are folded and welded with the lower shell 4 on the lower cabin of the storage tank to form the whole storage tank.
Example 1
The embodiment discloses a surface tension storage tank of an upper convex septum, which comprises an air tap 1, an upper shell 2, a column section 3, a lower shell 4, a liquid tap 5, a vent screen 6, a septum 7, a septum screen 8, a net channel 9 and a communication seat 10, wherein a plurality of net channels 9 and the communication seat 10 are welded into a component through argon arc welding; the air vent screen 6, the middle partition 7 and the middle partition screen 8 are welded into a middle partition component through vacuum electron beam, then the two components are assembled together with the lower shell 4 and the liquid nozzle 5 and are welded through vacuum electron beam to form a lower cabin, and the air nozzle 1, the upper shell 2 and the column section 3 are welded into a component through vacuum electron beam and then are folded and welded with the lower shell 4 to form an integral storage tank.
The wall thickness of the middle partition of the storage tank is not more than 0.85mm, and the minimum distance between the middle partition screen and the welding line of the shell is not more than 35mm. The tank lower volume can be adjusted by adjusting the diameter of the middle partition 7 and the welding position of the middle partition and the tank shell. The upper convex septum 7 can be welded on the lower shell 4 or the column section 3 by high-energy beam welding with concentrated energy such as vacuum electron beam or laser welding. The number of the middle partition edges welded on the middle partition 7 of the storage tank is 8. The open area of the single middle partition is not smaller than 950mm < 2 >. The number of the net-carrying channels 9 is 4, the width of the U-shaped section is 35 mm-45 mm, and the depth is 6 mm-8 mm, and the net-carrying channels 9 are arranged at the middle positions of the adjacent middle partition screens 8 so as to ensure that the flow rate is relatively uniform everywhere when the liquid flows from the middle partition screens 8 to the net-carrying channels 9.
The position of the welding seam between the middle partition 7 and the lower shell 4 is influenced by the volume of the lower cabin and the size of the middle partition 7, and if the welding seam between the middle partition 7 and the lower shell 4 is close to the welding seam between the column section 3 and the lower shell 4, vacuum electron beam welding is adopted, so that the distance between the two welding seams is at least required to be ensured to be 10mm.
In the description of the present application, it should be understood that the terms "upper," "lower," "front," "rear," "left," "right," "vertical," "horizontal," "top," "bottom," "inner," "outer," and the like indicate orientations or positional relationships based on the orientations or positional relationships illustrated in the drawings, merely to facilitate description of the present application and simplify the description, and do not indicate or imply that the devices or elements being referred to must have a specific orientation, be configured and operated in a specific orientation, and are not to be construed as limiting the present application.
The foregoing describes specific embodiments of the present invention. It is to be understood that the invention is not limited to the particular embodiments described above, and that various changes or modifications may be made by those skilled in the art within the scope of the appended claims without affecting the spirit of the invention. The embodiments of the present application and features in the embodiments may be combined with each other arbitrarily without conflict.
Claims (10)
1. The surface tension storage tank with the upper convex septum is characterized by comprising a storage tank pressure-bearing shell, wherein the storage tank pressure-bearing shell comprises an upper shell (2), a column section (3) and a lower shell (4) which are sequentially connected, the storage tank pressure-bearing shell is internally provided with the upper convex septum (7), the storage tank is divided into an upper cabin and a lower cabin by the septum (7), and the upper cabin is used for containing propellant;
the top of the upper shell (2) is provided with an air tap (1), the bottom of the lower shell (4) is provided with a liquid tap (5), the top of the middle partition (7) is provided with a vent screen (6), the middle partition (7) is provided with a middle partition screen (8), and the inner part of the lower cabin is provided with a net-carrying channel (9);
the surface tension storage tank of the upper convex septum is used for a space vehicle, when the space vehicle is in a track-changing ignition period, pressurized gas enters the upper cabin through the air tap (1), propellant in the upper cabin enters the lower cabin through the middle septum screen (8), liquid films are arranged in the middle septum screen (8) and the air vent screen (6) and can prevent the pressurized gas from entering the lower cabin before the propellant is exhausted, the net-carrying channel (9) can carry out gas-liquid separation, and gas in the lower cabin is discharged to the upper cabin through the air vent screen (6).
2. A surface tension tank for an upper convex septum according to claim 1, characterized in that the septum (7) is arranged at the upper end of the lower housing (4) and protrudes towards the column section (3) forming a spherical or ellipsoidal thin shell structure.
3. A surface tension tank for an upper convex septum according to claim 2, characterized in that a wedge-shaped cavity is formed between the septum (7) and the column section (3) of the spherical or ellipsoidal thin-shell structure, in which wedge-shaped cavity the unused propellant in the upper compartment is stored during rail-change ignition.
4. A surface tension tank for an upper convex septum according to claim 1, characterized in that the septum (7) is made of metal.
5. The surface tension storage tank of the upper convex septum according to claim 1, wherein a pair of communicating seats (10) and a plurality of strip network channels (9) are arranged in the lower cabin, and the pair of communicating seats (10) are respectively arranged at the upper end and the lower end of the lower cabin;
the two ends of the net-carrying channels (9) are respectively connected with the communication seats (10) which are arranged in pairs, and the multi-band net-carrying channels (9) are arranged along the circumferential direction of the lower cabin.
6. The surface tension storage tank of an upper convex septum according to claim 5, wherein the net-carrying channel (9) is a semi-ring structure with a U-shaped section, and two ends of the semi-ring structure are respectively connected with a pair of communication seats (10);
a metal screen is welded on the U-shaped opening of the net-carrying channel (9) to form a liquid conveying channel.
7. The upper septal surface tension tank of claim 6 wherein the metal screen, septal screen (8) and relief port screen (6) have bubble breaking points of no less than 3700Pa.
8. The surface tension tank for an upper septum of claim 6 wherein the U-shaped cross section has a width of 35mm to 45mm and a depth of 6mm to 8mm.
9. A surface tension tank for an upper septum according to claim 5, characterized in that the screened channels (9) are arranged between adjacent septum screens (8).
10. The surface tension tank for an upper convex septum according to claim 1, wherein the septum screen (8) is plural, and the septum screen (8) is uniformly disposed in the circumferential direction near the lower end of the septum (7).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202211633293.8A CN116085145A (en) | 2022-12-19 | 2022-12-19 | Surface tension storage box of upper convex septum |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202211633293.8A CN116085145A (en) | 2022-12-19 | 2022-12-19 | Surface tension storage box of upper convex septum |
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| Publication Number | Publication Date |
|---|---|
| CN116085145A true CN116085145A (en) | 2023-05-09 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202211633293.8A Pending CN116085145A (en) | 2022-12-19 | 2022-12-19 | Surface tension storage box of upper convex septum |
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| Country | Link |
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| CN (1) | CN116085145A (en) |
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- 2022-12-19 CN CN202211633293.8A patent/CN116085145A/en active Pending
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