CN211618103U - Anti-shaking oil tank structure - Google Patents
Anti-shaking oil tank structure Download PDFInfo
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- CN211618103U CN211618103U CN201922496203.5U CN201922496203U CN211618103U CN 211618103 U CN211618103 U CN 211618103U CN 201922496203 U CN201922496203 U CN 201922496203U CN 211618103 U CN211618103 U CN 211618103U
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Abstract
The utility model discloses an anti-shaking oil tank structure, relating to the technical field of aircraft oil tanks; the box body is provided with an inner cavity, and a plurality of cavity clapboards are fixedly arranged in the inner cavity of the box body side by side to divide the inner cavity of the box body into a plurality of containing cavities with the same volume; the box body is provided with an oil filling port, and after oil is injected into the inner cavity through the oil filling port, an oil part and an air part positioned above the oil part are formed in each cavity; the top end of each cavity partition plate is provided with a first through hole used for communicating the air part in each cavity, and the bottom end of each cavity partition plate is provided with a second through hole used for communicating the oil part in each cavity; the utility model has the advantages that: this prevent shaking oil tank structure can prevent that the fuel can rock at the inside oil tank fast, can not influence the flight stability and the ability of controlling of aircraft because of the focus of aircraft is undulant, has increased aircraft fail safe nature.
Description
Technical Field
The utility model relates to an aircraft oil tank technical field, more specifically the utility model relates to a prevent shaking oil tank structure.
Background
With the rapid development of manned aircrafts and unmanned aircrafts, particularly unmanned aircrafts with large maneuverability and long endurance are restricted by the current battery technology, fuel engines are adopted as power sources, and the fuel engines need to adopt related fuel tanks to store fuel.
SUMMERY OF THE UTILITY MODEL
In order to overcome the not enough of prior art, the utility model provides a prevent shaking oil tank structure should prevent shaking oil tank structure and can prevent that the fuel can rock inside the oil tank fast, can not influence the flight stability of aircraft and control the ability because of the focus of aircraft is undulant, has increased aircraft fail safe nature.
The utility model provides a technical scheme that its technical problem adopted is: an anti-shaking oil tank structure is improved in that: the box body is provided with an inner cavity, and a plurality of cavity clapboards are fixedly arranged in the inner cavity of the box body side by side to divide the inner cavity of the box body into a plurality of containing cavities with the same volume;
the box body is provided with an oil filling port, and after oil is injected into the inner cavity through the oil filling port, an oil part and an air part positioned above the oil part are formed in each cavity; the top end of each cavity partition plate is provided with a first through hole, the first through holes are used for communicating the air part in each accommodating cavity, the bottom end of each cavity partition plate is provided with a second through hole, and the second through holes are used for communicating the oil part in each accommodating cavity.
In the structure, the middle positions of the cavity partition plates are provided with a plurality of third through holes, and the third through holes are used for communicating the adjacent cavities.
In the structure, two third through holes which are arranged side by side up and down are arranged in the middle of each cavity partition plate.
In the structure, three cavity clapboards are arranged in the inner cavity of the box body side by side.
The utility model has the advantages that: the utility model relates to a prevent shaking oil tank structure can prevent that the fuel can rock inside the oil tank fast, can not fluctuate because of the focus of aircraft and influence the flight stability of aircraft and control the ability, has increased aircraft fail safe nature.
Drawings
Fig. 1 is a schematic view of a first state of an anti-sloshing oil tank structure of the present invention.
Fig. 2 is a schematic diagram of a second state of the anti-sloshing oil tank structure of the present invention.
Detailed Description
The present invention will be further explained with reference to the drawings and examples.
The conception, the specific structure, and the technical effects produced by the present invention will be clearly and completely described below in conjunction with the embodiments and the accompanying drawings to fully understand the objects, the features, and the effects of the present invention. Obviously, the described embodiments are only a part of the embodiments of the present invention, and not all embodiments, and other embodiments obtained by those skilled in the art without inventive labor based on the embodiments of the present invention all belong to the protection scope of the present invention. In addition, all the connection/connection relations referred to in the patent do not mean that the components are directly connected, but mean that a better connection structure can be formed by adding or reducing connection auxiliary components according to specific implementation conditions. The utility model discloses each technical feature in the creation can the interactive combination under the prerequisite that does not contradict conflict each other.
Referring to fig. 1 and 2, the present invention discloses an anti-sloshing oil tank structure, specifically, the anti-sloshing oil tank structure includes a tank body 10 and cavity partition plates 20, the tank body 10 has an inner cavity, and a plurality of cavity partition plates 20 are fixed in the inner cavity of the tank body 10 side by side to divide the inner cavity of the tank body 10 into a plurality of cavities with the same volume; the box body 10 is provided with an oil filling port 103, and after oil is injected into the inner cavity through the oil filling port 103, an oil part 101 and an air part 102 positioned above the oil part 101 are formed in each cavity; the top end of each cavity partition plate 20 is provided with a first through hole 201, the first through hole 201 is used for communicating the air part 102 in each cavity, the bottom end of each cavity partition plate 20 is provided with a second through hole 202, and the second through hole 202 is used for communicating the oil part 101 in each cavity. Further, a plurality of third through holes 203 are formed in the middle of the cavity partition plate 20, and the third through holes 203 are used for communicating adjacent cavities.
In a preferred embodiment, two third through holes 203 are arranged in parallel up and down in the middle of each cavity partition 20; three cavity clapboards 20 are arranged in the inner cavity of the box body 10 side by side.
Through foretell structure, the utility model discloses a this kind prevents shaking oil tank structure is used in the aircraft, when the aircraft appears the slope of short time when doing the maneuver, when the oil tank takes place to incline, causes the focus skew too big for preventing that the fuel from receiving one side flow of gravity factor toward low liquid level. The first through hole 201 is used for filling oil into the oil tank and communicating with other cavities, so that the situation that each cavity cannot be filled with oil due to oil and gas accumulation during oil filling is prevented; the second through hole 202 has the function that the liquid level is lower when the fuel is exhausted, so that the oil in the cavity of each cavity partition plate 20 is ensured to be communicated, and the purpose of exhausting the fuel as far as possible is achieved; the third through hole 203 is used for preventing too much oil or too little oil from passing through according to an oil hole opened by the actual flow of the oil consumption rate of the engine of the aircraft; when third through-hole 203 is too much or too big, the fuel flows fast and can cause whole oil tank focus skew when the slope appears in the oil tank, and through third through-hole 203 undersize or when being too little, the whole focus skew of oil tank can appear because of long-pending oil to the fuel of the little cavity of keeping away from the oil-out, consequently the utility model discloses a prevent shaking oil tank structure designs corresponding third through-hole 203's quantity and size according to actual engine oil consumption. Therefore, the utility model relates to a prevent shaking oil tank structure can prevent that the fuel can rock inside the oil tank fast, can not influence the flight stability of aircraft and control the ability because of the focus of aircraft is undulant, has increased aircraft fail safe nature.
While the preferred embodiments of the present invention have been described, the present invention is not limited to the above embodiments, and those skilled in the art can make various equivalent modifications or substitutions without departing from the spirit of the present invention, and such equivalent modifications or substitutions are intended to be included within the scope of the present invention as defined by the appended claims.
Claims (4)
1. The utility model provides an anti-shake oil tank structure which characterized in that: the box body is provided with an inner cavity, and a plurality of cavity clapboards are fixedly arranged in the inner cavity of the box body side by side to divide the inner cavity of the box body into a plurality of containing cavities with the same volume;
the box body is provided with an oil filling port, and after oil is injected into the inner cavity through the oil filling port, an oil part and an air part positioned above the oil part are formed in each cavity; the top end of each cavity partition plate is provided with a first through hole, the first through holes are used for communicating the air part in each accommodating cavity, the bottom end of each cavity partition plate is provided with a second through hole, and the second through holes are used for communicating the oil part in each accommodating cavity.
2. The slosh prevention tank structure according to claim 1, wherein: the middle position of the cavity partition plate is provided with a plurality of third through holes, and the third through holes are used for enabling adjacent cavities to be communicated.
3. The slosh prevention tank structure according to claim 2, wherein: and two third through holes which are arranged side by side up and down are arranged in the middle of each cavity partition plate.
4. The slosh prevention tank structure according to claim 1, wherein: three cavity clapboards are arranged in the inner cavity of the box body side by side.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201922496203.5U CN211618103U (en) | 2019-12-31 | 2019-12-31 | Anti-shaking oil tank structure |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201922496203.5U CN211618103U (en) | 2019-12-31 | 2019-12-31 | Anti-shaking oil tank structure |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN211618103U true CN211618103U (en) | 2020-10-02 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201922496203.5U Active CN211618103U (en) | 2019-12-31 | 2019-12-31 | Anti-shaking oil tank structure |
Country Status (1)
| Country | Link |
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| CN (1) | CN211618103U (en) |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112459925A (en) * | 2020-11-02 | 2021-03-09 | 中国运载火箭技术研究院 | Built-in baffle type storage box |
| CN112657087A (en) * | 2020-12-29 | 2021-04-16 | 中国航空工业集团公司西安飞机设计研究所 | Large-scale forest fire-fighting aircraft |
| CN112849419A (en) * | 2021-04-23 | 2021-05-28 | 西安羚控电子科技有限公司 | Complete oxygen isolation fuel tank for airplane |
| CN113148197A (en) * | 2021-04-25 | 2021-07-23 | 上海机电工程研究所 | Prevent rocking fuel storage tank and aircraft |
-
2019
- 2019-12-31 CN CN201922496203.5U patent/CN211618103U/en active Active
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112459925A (en) * | 2020-11-02 | 2021-03-09 | 中国运载火箭技术研究院 | Built-in baffle type storage box |
| CN112657087A (en) * | 2020-12-29 | 2021-04-16 | 中国航空工业集团公司西安飞机设计研究所 | Large-scale forest fire-fighting aircraft |
| CN112849419A (en) * | 2021-04-23 | 2021-05-28 | 西安羚控电子科技有限公司 | Complete oxygen isolation fuel tank for airplane |
| CN112849419B (en) * | 2021-04-23 | 2021-08-03 | 西安羚控电子科技有限公司 | Complete oxygen isolation fuel tank for airplane |
| CN113148197A (en) * | 2021-04-25 | 2021-07-23 | 上海机电工程研究所 | Prevent rocking fuel storage tank and aircraft |
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