CN221418628U - Aircraft oil tank capable of relieving water hammer effect - Google Patents
Aircraft oil tank capable of relieving water hammer effect Download PDFInfo
- Publication number
- CN221418628U CN221418628U CN202323481170.XU CN202323481170U CN221418628U CN 221418628 U CN221418628 U CN 221418628U CN 202323481170 U CN202323481170 U CN 202323481170U CN 221418628 U CN221418628 U CN 221418628U
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- plate
- bottom plate
- fuel tank
- aircraft fuel
- top plate
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- 230000000694 effects Effects 0.000 title claims abstract description 25
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 title claims abstract description 20
- 238000000576 coating method Methods 0.000 claims abstract description 29
- 229920002396 Polyurea Polymers 0.000 claims abstract description 28
- 239000011248 coating agent Substances 0.000 claims abstract description 27
- 230000002093 peripheral effect Effects 0.000 claims abstract description 18
- 239000002828 fuel tank Substances 0.000 claims description 22
- 238000010030 laminating Methods 0.000 claims description 2
- 230000000116 mitigating effect Effects 0.000 claims 3
- 230000001413 cellular effect Effects 0.000 claims 1
- 230000035515 penetration Effects 0.000 abstract description 11
- 230000035899 viability Effects 0.000 abstract description 6
- 238000000034 method Methods 0.000 abstract description 4
- 230000008569 process Effects 0.000 abstract description 4
- 239000000446 fuel Substances 0.000 description 7
- 238000005452 bending Methods 0.000 description 5
- 238000005192 partition Methods 0.000 description 4
- 239000007788 liquid Substances 0.000 description 3
- 239000000463 material Substances 0.000 description 2
- 230000035939 shock Effects 0.000 description 2
- 238000005299 abrasion Methods 0.000 description 1
- 239000000853 adhesive Substances 0.000 description 1
- 230000001070 adhesive effect Effects 0.000 description 1
- XAGFODPZIPBFFR-UHFFFAOYSA-N aluminium Chemical compound [Al] XAGFODPZIPBFFR-UHFFFAOYSA-N 0.000 description 1
- 229910052782 aluminium Inorganic materials 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000008859 change Effects 0.000 description 1
- 238000004891 communication Methods 0.000 description 1
- 238000004880 explosion Methods 0.000 description 1
- 239000012634 fragment Substances 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
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- Details Of Rigid Or Semi-Rigid Containers (AREA)
Abstract
The application discloses an aircraft oil tank capable of relieving water hammer effect, which comprises: top, bottom and peripheral side panels. The top plate is adjacent to the upper surface of the wing. The bottom plate with the roof interval sets up, the bottom plate is close to the lower surface of wing. The peripheral side plate is arranged between the top plate and the bottom plate and is connected with the top plate and the bottom plate, and the top plate, the bottom plate and the peripheral side plate enclose to form an oil cavity. Wherein at least the base plate is covered with a polyurea coating. When the aircraft flies, the bottom plate faces downwards, and is the part with the largest exposed area on the oil tank, and the aircraft is easily hit by a high-speed penetration body in the fight process. According to the embodiment of the application, the polyurea coating is covered on the bottom plate to protect the bottom plate, so that the water hammer effect can be relieved when the bottom plate is impacted by a high-speed penetration body, and the viability of the oil tank is improved.
Description
Technical Field
The application relates to the technical field of aircrafts, in particular to an aircraft oil tank capable of relieving a water hammer effect.
Background
The fuel tank of the aircraft stores a large amount of fuel, and the fuel is provided for the engine to generate power, so that the safety of the aircraft is ensured as a precondition for ensuring safe flight. As one of the components with the largest exposed area of the aircraft, the fuel tank is easily hit by a high-speed penetration body (such as a warhead fragment or a bullet) during the combat process, and the water hammer effect occurs: the penetration body carrying huge momentum can generate strong pressure and shock waves after entering liquid and acts on the wall plate of the oil tank, the structure of the oil tank is destroyed, oil leakage can even generate explosion reaction, and the safety of an airplane and a pilot is seriously threatened, so that the water hammer effect is an important problem to be considered in ensuring the safety of the oil tank of the airplane.
In view of this, the present utility model has been made.
Disclosure of utility model
The utility model provides an aircraft fuel tank capable of relieving a water hammer effect.
The utility model adopts the following technical scheme:
The embodiment of the application provides an aircraft oil tank capable of relieving a water hammer effect, which comprises the following components:
A top plate proximate an upper surface of the wing;
the bottom plate and the top plate are arranged at intervals, and the bottom plate is close to the lower surface of the wing;
The peripheral side plate is arranged between the top plate and the bottom plate and is connected with the top plate and the bottom plate, and the top plate, the bottom plate and the peripheral side plate are enclosed to form an oil cavity;
Wherein at least the base plate is covered with a polyurea coating.
Optionally, at least one of two wall surfaces of the two sides of the bottom plate along the thickness direction is covered with the polyurea coating.
Optionally, the top plate and/or the peripheral side plate are covered with the polyurea coating.
Optionally, the aircraft fuel tank capable of relieving the water hammer effect comprises a baffle assembly;
The baffle assembly is arranged in the oil cavity, the baffle assembly divides the oil cavity into a plurality of sub-oil cavities, and each sub-oil cavity is communicated.
Optionally, the baffle assembly includes a plurality of first direction plates and a plurality of second direction plates;
The first direction plates and the second direction plates are arranged in a staggered manner to divide the oil cavity into a plurality of rows and a plurality of columns of sub-oil cavities;
wherein the first and/or the second directional plate is covered with a polyurea coating.
Optionally, a plurality of second direction plates are disposed between the inner wall of the peripheral plate and two adjacent first direction plates.
Optionally, two ends of the second direction plate are respectively provided with a bent edge so as to be attached to the inner wall of the corresponding first direction plate or the peripheral side plate;
the bent edge attached to the first direction plate is fixedly connected with the first direction plate through a fastener;
the first direction board both ends are provided with the bent edge with the inner wall of week curb plate laminating mutually.
Optionally, the aircraft fuel tank capable of relieving the water hammer effect comprises a plurality of honeycomb units;
Each honeycomb unit is respectively arranged in the corresponding sub-oil cavity.
Optionally, the wall thickness of the baffle assembly is greater than the wall thickness of the honeycomb cells.
Optionally, the cells of the honeycomb unit extend in a direction perpendicular to the base plate.
By adopting the technical scheme, the utility model has the following beneficial effects:
When the aircraft flies, the bottom plate faces downwards, and is the part with the largest exposed area on the oil tank, and the aircraft is easily hit by a high-speed penetration body in the fight process. According to the embodiment of the application, the polyurea coating is covered on the bottom plate to protect the bottom plate, so that the water hammer effect can be relieved when the bottom plate is impacted by a high-speed penetration body, and the viability of the oil tank is improved.
The following describes the embodiments of the present utility model in further detail with reference to the accompanying drawings.
Drawings
The accompanying drawings, which are included to provide a further understanding of the utility model and are incorporated in and constitute a part of this specification, illustrate embodiments of the utility model and together with the description serve to explain the utility model. It is evident that the drawings in the following description are only examples, from which other drawings can be obtained by a person skilled in the art without the inventive effort. In the drawings:
Fig. 1 is a schematic structural view of an aircraft fuel tank provided in an embodiment of the present application in a separated state;
Fig. 2 is an exploded view of an aircraft fuel tank according to an embodiment of the present application after deleting a honeycomb unit.
In the figure, 1, a shell; 11. a top plate; 12. a bottom plate; 13. a peripheral plate; 131. a first side plate; 132. a second side plate; 2. a separator assembly; 21. a first direction plate; 22. a second direction plate; a. an oil-receiving cavity; b. bending the edge; 3. a honeycomb unit.
It should be noted that these drawings and the written description are not intended to limit the scope of the inventive concept in any way, but to illustrate the inventive concept to those skilled in the art by referring to the specific embodiments.
Detailed Description
For the purpose of making the objects, technical solutions and advantages of the embodiments of the present utility model more apparent, the technical solutions in the embodiments will be clearly and completely described with reference to the accompanying drawings in the embodiments of the present utility model, and the following embodiments are used to illustrate the present utility model, but are not intended to limit the scope of the present utility model.
In the description of the present utility model, it should be noted that the directions or positional relationships indicated by the terms "upper", "lower", "inner", "outer", etc. are based on the directions or positional relationships shown in the drawings, are merely for convenience of describing the present utility model and simplifying the description, and do not indicate or imply that the apparatus or component referred to must have a specific orientation, be constructed and operated in a specific orientation, and thus should not be construed as limiting the present utility model.
In the description of the present utility model, it should be noted that, unless explicitly specified and limited otherwise, the terms "mounted", "connected" and "connected" are to be construed broadly, and may be, for example, fixedly connected, detachably connected or integrally connected; can be mechanically or electrically connected; can be directly connected or indirectly connected through an intermediate medium. The specific meaning of the above terms in the present utility model will be understood in specific cases by those of ordinary skill in the art.
Referring to fig. 1 and 2, an embodiment of the present application provides an aircraft fuel tank capable of alleviating a water hammer effect, including: top plate 11, bottom plate 12 and peripheral side plate 13. The roof 11 is close to the upper surface of wing, bottom plate 12 with roof 11 interval sets up, bottom plate 12 is close to the lower surface of wing, week curb plate 13 set up in between roof 11 and the bottom plate 12 just week curb plate 13 connects roof 11 and bottom plate 12, roof 11, bottom plate 12 and week curb plate 13 enclose and close and form the oil pocket, wherein, at least bottom plate 12 is covered with the polyurea coating.
The polyurea coating generally adopts a one-time coating process, no chain joints exist in any large area, and the polyurea coating is a dust-free material, and has the characteristics of strong adhesive force, friction resistance, strong hardness and the like.
The floor 12 is directed downwardly during flight of the aircraft, and is the location of the fuel tank where the exposed area is greatest, and is susceptible to attack by high-speed penetration bodies during combat. According to the embodiment of the application, the polyurea coating is covered on the bottom plate 12 to protect the bottom plate 12, so that the water hammer effect can be relieved when the bottom plate is impacted by a high-speed penetration body, and the viability of the oil tank is improved.
In some possible embodiments, at least one of the two walls on both sides of the base plate 12 in the thickness direction is covered with the polyurea coating.
The polyurea coating is covered on at least one of the two wall surfaces of the bottom plate 12 along the thickness direction, and considering that the polyurea coating can increase the weight of the structure, in the embodiment of the application, the polyurea coating can be covered on only one surface of the bottom plate 12, such as the following surface, when the bottom plate is subjected to external impact, the polyurea coating can directly play a role of protection, and the external impact is relieved. The embodiment of the application can also cover polyurea coatings on the wall surfaces on both sides of the bottom plate 12, thereby obviously improving the structural strength of the bottom plate 12 and the viability of the aircraft fuel tank.
In some possible embodiments, the top plate 11 is provided with a polyurea coating, and the top plate 11 is provided with a polyurea coating on at least one of the wall surfaces on both sides in the thickness direction. Similarly, the peripheral plate 13 may be covered with a polyurea coating, and the outer wall and/or the inner wall of the peripheral plate 13 may be provided with a polyurea coating.
When the polyurea coating is arranged on the top plate 11, the bottom plate 12 and the peripheral side plates 13, the omnibearing coverage of the oil tank is realized, and the viability of the aircraft oil tank is obviously improved.
In some possible embodiments, the aircraft fuel tank capable of relieving the water hammer effect comprises a baffle assembly 2, wherein the baffle assembly 2 is arranged in the fuel cavity, the baffle assembly 2 divides the fuel cavity into a plurality of sub-fuel cavities a, and each sub-fuel cavity a is communicated.
The baffle assembly 2 is in a grid structure, can fill the gap of an oil cavity in the oil tank, can absorb the energy of liquid expansion through plate body deformation, reduces the expansion of the cavity, and reduces the damage of a high-speed penetration body to the shell 1. Specifically, the baffle assembly 2 absorbs kinetic energy of oil in the oil tank, and each plate body of the baffle assembly 2 reduces expansion and structural damage of a cavity formed by high-speed penetration body impact liquid, reduces shock wave pressure, and further relieves water hammer effect.
In some possible embodiments, the partition plate assembly 2 includes a plurality of first direction plates 21 and a plurality of second direction plates 22, and each of the first direction plates 21 and each of the second direction plates 22 are staggered to divide the oil chamber into a plurality of rows and a plurality of columns of sub-oil chambers a. Wherein the first direction plate 21 and/or the second direction plate 22 are covered with a polyurea coating. In this embodiment, a polyurea coating is further provided on the bulkhead assembly 2 such that both the aircraft tank inner and outer panel structure is enhanced.
An included angle is formed between the first direction plate 21 and the second direction plate 22, for example, an included angle of ninety degrees is formed between the first direction plate 21 and the second direction plate 22, and a plurality of square or cuboid sub-oil chambers a are formed between the first direction plate 21 and the second direction plate 22. The first direction plate 21 and the second direction plate 22 can be integrally connected and fixed into a whole, and the overall structure is not easy to deform.
In some possible embodiments, a plurality of said second direction plates 22 are provided between the inner wall of the peripheral plate 13 and adjacent two of each of said first direction plates 21.
For example, the peripheral side plate 13 may include two first side plates 131 and two second side plates 132, the two first side plates 131 are disposed at intervals, the two second side plates 132 are disposed between the two first side plates 131, and two sides of the second side plates 132 are respectively connected to the two first side plates 131. The first direction plates 21 and the first side plates 131 may be disposed substantially in parallel, and the second direction plates 22 and the second side plates 132 may be disposed substantially in parallel. Among the first side plates 131 and the first direction plates 21, a plurality of second direction plates 22 are provided between adjacent ones of them. The first direction plate 21 has a length greater than that of the second direction plate 22.
In some possible embodiments, the two ends of the second direction plate 22 are respectively provided with a bent edge b, so as to be attached to the corresponding first direction plate 21 or the inner wall of the housing 1, and the bent edge b attached to the first direction plate 21 and the first direction plate 21 are connected and fixed by a fastener.
The bent edges b are arranged at the two ends of the second direction plate 22, so that the bending edges can be attached to the inner wall of the first direction plate 21 or the outer shell 1 in a surface-to-surface mode, and the stability is good. Optionally, bent edges b are provided at both ends of the first direction plate 21 to be attached to the inner wall of the housing 1. The bending edge b on the first direction plate 21 and the second direction plate 22 are attached to the inner wall of the shell 1, but the bending edge b is not required to be connected and fixed, so that the assembly is convenient, the effect of the shell 1 is also protected, the bending edge b is attached to the inner wall of the shell 1, the contact between the surfaces is adopted, the contact between the surfaces is not the contact between the lines and the surfaces, the stability of the assembly is good, and serious abrasion and scratch cannot be generated. The bent edge b of the second direction plate 22 is attached to the first direction plate 21, and is conveniently connected and fixed by a fastener, for example, an anchor bolt.
In some possible embodiments, the aircraft fuel tank capable of relieving the water hammer effect comprises a plurality of honeycomb units 3, and each honeycomb unit 3 is respectively arranged in a corresponding sub-fuel cavity a.
In the embodiment of the application, the partition board assembly 2 and the honeycomb units 3 are arranged in the oil cavity in a combined way, the wall thickness of the honeycomb units 3 is small, the structure of the partition board assembly 2 is large, the structure strength is good, the honeycomb units 3 can be stably supported, a supporting boundary is provided for each honeycomb unit 3, and the deformation of the honeycomb units 3 in the process of absorbing energy is restrained, so that the impact resistance and the viability of wing oil are better than those of the wing oil with only one larger honeycomb structure in the oil cavity.
The extending direction of each honeycomb hole of the honeycomb unit 3 is perpendicular to the bottom plate 12. The honeycomb holes of the honeycomb unit 3 are parallel, and the influence of the change of penetration conditions on the damage effect is mainly analyzed through researching the damage of the hydraulic hammer effect on the oil tank, so that the hydraulic hammer effect is best relieved when the honeycomb holes of the honeycomb unit 3 extend along the direction vertical to the bottom plate 12.
In some possible embodiments, the wall thickness of the baffle assembly 2 is greater than the wall thickness of the honeycomb unit 3. The partition board assembly 2 and the honeycomb unit 3 are made of aluminum materials, and the structure is light. The thickness of the first direction plate 21 and the second direction plate 22 of the separator assembly 2 is larger than the wall thickness of the honeycomb unit 3, so that the boundary of the honeycomb unit 3 formed by the separator assembly 2 is high in reliability and is not easy to deform. The wall thickness of the honeycomb unit 3 is understood to mean that two adjacent honeycomb holes in the honeycomb unit 3 are separated by a thin wall, i.e. the wall thickness of the honeycomb unit 3.
In some possible embodiments, the part of the plate section of the baffle assembly 2 is in contact with the top plate 11 and the bottom plate 12 of the housing 1, and the part of the plate section of the baffle assembly 2 has a gap with the top plate 11 and the bottom plate 12, so that the baffle assembly 2 can be tightly matched with the inner wall of the housing 1, and meanwhile, the formed sub-oil cavities a can be communicated. For example, a part of the first direction plate 21 corresponding to the plate segment of each of the sub-oil chambers a is in contact with the top plate 11 and the bottom plate 12, and a part of the first direction plate is in clearance with the bottom plate 12 and the top plate 11, so that each of the sub-oil chambers a formed is not a closed chamber, and each of the sub-oil chambers a is in communication.
The foregoing description is only illustrative of the preferred embodiment of the present utility model, and is not to be construed as limiting the utility model, but is to be construed as limiting the utility model to any simple modification, equivalent variation and variation of the above embodiments according to the technical matter of the present utility model without departing from the scope of the utility model.
Claims (10)
1. An aircraft fuel tank capable of relieving the water hammer effect, comprising:
A top plate proximate an upper surface of the wing;
the bottom plate and the top plate are arranged at intervals, and the bottom plate is close to the lower surface of the wing;
The peripheral side plate is arranged between the top plate and the bottom plate and is connected with the top plate and the bottom plate, and the top plate, the bottom plate and the peripheral side plate are enclosed to form an oil cavity;
Wherein at least the base plate is covered with a polyurea coating.
2. The aircraft fuel tank capable of mitigating water hammer effect of claim 1, wherein at least one of two wall surfaces on both sides of the bottom plate in a thickness direction is covered with the polyurea coating.
3. The aircraft fuel tank of claim 1, wherein the top plate and/or the perimeter side plates are covered with the polyurea coating.
4. The aircraft fuel tank of claim 1, comprising a baffle assembly;
The baffle assembly is arranged in the oil cavity, the baffle assembly divides the oil cavity into a plurality of sub-oil cavities, and each sub-oil cavity is communicated.
5. The aircraft fuel tank of claim 4 wherein said baffle assembly comprises a plurality of first direction plates and a plurality of second direction plates;
The first direction plates and the second direction plates are arranged in a staggered manner to divide the oil cavity into a plurality of rows and a plurality of columns of sub-oil cavities;
wherein the first and/or the second directional plate is covered with a polyurea coating.
6. The hydraulic-hammer mitigation aircraft fuel tank of claim 5, wherein a plurality of said second direction plates are disposed between an inner wall of said perimeter plate and an adjacent one of each of said first direction plates.
7. The aircraft fuel tank capable of relieving the water hammer effect according to claim 6, wherein the two ends of the second direction plate are respectively provided with a bent edge so as to be attached to the inner wall of the corresponding first direction plate or the peripheral side plate;
the bent edge attached to the first direction plate is fixedly connected with the first direction plate through a fastener;
the first direction board both ends are provided with the bent edge with the inner wall of week curb plate laminating mutually.
8. An aircraft fuel tank capable of mitigating hydraulic hammer effects according to any one of claims 4-7, characterized by comprising a plurality of cellular units;
Each honeycomb unit is respectively arranged in the corresponding sub-oil cavity.
9. The aircraft fuel tank of claim 8 wherein said diaphragm assembly has a wall thickness greater than a wall thickness of said honeycomb cells.
10. The aircraft fuel tank of claim 8 wherein said honeycomb cells have cells extending in a direction perpendicular to said floor.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202323481170.XU CN221418628U (en) | 2023-12-20 | 2023-12-20 | Aircraft oil tank capable of relieving water hammer effect |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202323481170.XU CN221418628U (en) | 2023-12-20 | 2023-12-20 | Aircraft oil tank capable of relieving water hammer effect |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN221418628U true CN221418628U (en) | 2024-07-26 |
Family
ID=91974369
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202323481170.XU Active CN221418628U (en) | 2023-12-20 | 2023-12-20 | Aircraft oil tank capable of relieving water hammer effect |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN221418628U (en) |
-
2023
- 2023-12-20 CN CN202323481170.XU patent/CN221418628U/en active Active
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