Wing oil tank and aircraft

Abstract

An embodiment of the present application provides a wing fuel tank and an aircraft, wherein the wing fuel tank comprises: an outer shell and a honeycomb structure. The outer shell encloses an oil cavity. The honeycomb structure is disposed in the oil cavity, and the honeycomb structure has a plurality of honeycomb holes. A honeycomb structure is placed in the oil cavity of the wing fuel tank of the present application, and the honeycomb structure has a plurality of honeycomb holes, each of which can be filled with oil. During the process of the cavity formed by the oil impacted by the high-speed penetrator increasing in the container, the honeycomb structure undergoes plastic deformation, which can absorb a portion of the energy transferred to the fluid, reduce the expansion of the cavity, and further reduce the water hammer effect, thereby significantly improving the survivability of the wing fuel tank.

Description

Technical Field

[0001] The present invention relates to the technical field of aircraft, and in particular to a wing oil tank and an aircraft. Background Art

[0002] A large amount of fuel is stored in the wing tank, which generates power by providing fuel to the engine. Ensuring its safety is a prerequisite for safe flight. As one of the aircraft's largest exposed parts, the tank is vulnerable to high-speed penetrators (such as warhead fragments or bullets) during combat, and the water hammer effect will occur: the penetrator carrying huge momentum will enter the liquid and generate strong pressure and shock waves and act on the tank wall, destroying the tank structure, leaking oil, and even causing combustion and explosion reactions, seriously threatening the safety of the aircraft and the pilot. Therefore, the water hammer effect is an important issue that needs to be considered to ensure the safety of the wing tank.

[0003] In view of this, the present invention is proposed. Summary of the invention

[0004] The invention provides a wing oil tank and an aircraft.

[0005] The present invention adopts the following technical solutions:

[0006] The first object of the present application is to provide a wing fuel tank, comprising:

[0007] A housing, wherein the housing encloses an oil chamber;

[0008] A honeycomb structure is disposed in the oil chamber and has a plurality of honeycomb holes.

[0009] Optionally, the housing includes a top plate, a bottom plate and surrounding side plates;

[0010] The top plate is close to the upper surface of the wing, and the bottom plate is close to the lower surface of the wing;

[0011] The peripheral side plate is arranged between the top plate and the bottom plate and the peripheral side plate connects the top plate and the bottom plate;

[0012] The top plate, the bottom plate and the surrounding side plates enclose the oil chamber;

[0013] The extending direction of each honeycomb hole of the honeycomb structure is perpendicular to the bottom plate.

[0014] Optionally, the wing tank includes a bulkhead assembly;

[0015] The partition assembly is arranged in the oil chamber, and the partition assembly divides the oil chamber into a plurality of sub-oil chambers;

[0016] The honeycomb structure comprises a plurality of honeycomb units, and each of the honeycomb units is respectively arranged in a corresponding sub-oil chamber.

[0017] Optionally, the partition assembly includes a plurality of first direction plates and a plurality of second direction plates;

[0018] The first direction plates and the second direction plates are arranged alternately to divide the oil chamber into sub-oil chambers in multiple rows and columns.

[0019] Optionally, a plurality of second direction plates are arranged between the inner wall of the shell and two adjacent ones of the first direction plates.

[0020] Optionally, two ends of the second direction plate are respectively provided with bent edges to fit the corresponding first direction plate or the inner wall of the housing;

[0021] The bent edge attached to the first direction plate and the first direction plate are connected and fixed by fasteners.

[0022] Optionally, two ends of the first direction plate are provided with bent edges to fit with the inner wall of the shell.

[0023] Optionally, some plate segments of the partition assembly are in contact with the top plate and the bottom plate of the housing, and some plate segments of the partition assembly have gaps with the top plate and the bottom plate, so that the sub-oil chambers are connected.

[0024] Optionally, the wall thickness of the partition assembly is greater than the wall thickness of the honeycomb unit.

[0025] The second object of the present application is to provide an aircraft, comprising:

[0026] an aircraft body, the aircraft body having wings;

[0027] A wing oil tank is arranged on the wing.

[0028] By adopting the above technical solution, the present invention has the following beneficial effects:

[0029] A honeycomb structure is placed in the oil cavity of the wing fuel tank of the present application. The honeycomb structure has a plurality of honeycomb holes, each of which can be filled with oil. As the cavity formed by the oil impacted by the high-speed penetrator increases in the container, the honeycomb structure undergoes plastic deformation, which can absorb part of the energy transferred to the fluid, reduce the expansion of the cavity, and further reduce the water hammer effect, thereby significantly improving the survivability of the wing fuel tank.

[0030] The specific implementation modes of the present invention are further described in detail below in conjunction with the accompanying drawings. BRIEF DESCRIPTION OF THE DRAWINGS

[0031] The accompanying drawings are part of this application and are used to provide a further understanding of the present invention. The illustrative embodiments of the present invention and their descriptions are used to explain the present invention, but do not constitute an improper limitation of the present invention. Obviously, the drawings described below are only some embodiments. For ordinary technicians in this field, other drawings can be obtained based on these drawings without creative work. In the drawings:

[0032] Figure 1 A schematic structural diagram of the outer shell of a wing fuel tank provided in an embodiment of the present application in a separated state;

[0033] Figure 2 An exploded view of the wing fuel tank provided in an embodiment of the present application after the honeycomb unit is deleted.

[0034] In the figure, 1, outer shell; 11, top plate; 12, bottom plate; 13, peripheral side plate; 131, first side plate; 132, second side plate; 2, partition assembly; 21, first direction plate; 22, second direction plate; a, sub-oil chamber; b, bent edge; 3, honeycomb unit.

[0035] It should be noted that these drawings and textual descriptions are not intended to limit the conceptual scope of the present invention in any way, but are intended to illustrate the concept of the present invention for those skilled in the art by referring to specific embodiments. DETAILED DESCRIPTION

[0036] In order to make the purpose, technical solutions and advantages of the embodiments of the present invention clearer, the technical solutions in the embodiments will be clearly and completely described below in conjunction with the drawings in the embodiments of the present invention. The following embodiments are used to illustrate the present invention but are not used to limit the scope of the present invention.

[0037] In the description of the present invention, it should be noted that the terms "upper", "lower", "inside", "outside", etc. indicate directions or positional relationships based on the directions or positional relationships shown in the accompanying drawings, and are only for the convenience of describing the present invention and simplifying the description, rather than indicating or implying that the device or component referred to must have a specific direction, be constructed and operated in a specific direction, and therefore cannot be understood as a limitation on the present invention.

[0038] In the description of the present invention, it should be noted that, unless otherwise clearly specified and limited, the terms "installation" and "connection" should be understood in a broad sense, for example, it can be a fixed connection, a detachable connection, or an integral connection; it can be a mechanical connection or an electrical connection; it can be a direct connection or an indirect connection through an intermediate medium. For ordinary technicians in this field, the specific meanings of the above terms in the present invention can be understood according to specific circumstances.

[0039] A large amount of fuel is stored in the wing tank, which generates power by providing fuel to the engine. Ensuring its safety is a prerequisite for safe flight. As one of the aircraft's largest exposed parts, the tank is vulnerable to high-speed penetrators (such as warhead fragments or bullets) during combat, and the water hammer effect will occur. When the penetrator with huge momentum enters the liquid, it will generate strong pressure and shock waves and act on the tank wall, destroying the tank structure, leaking oil, and even causing combustion and explosion reactions, which seriously threaten the safety of the aircraft and the pilot. Therefore, the water hammer effect is an important issue that needs to be considered to ensure the safety of the wing tank.

[0040] In order to alleviate the water hammer effect and improve the survivability of the wing fuel tank, the embodiment of the present application provides a wing fuel tank, see Figure 1 and Figure 2 As shown, the wing oil tank comprises: an outer shell 1 and a honeycomb structure. The outer shell 1 encloses an oil cavity. The honeycomb structure is arranged in the oil cavity, and the honeycomb structure has a plurality of honeycomb holes.

[0041] A honeycomb structure is placed in the oil cavity of the wing fuel tank of the present application. The honeycomb structure has a plurality of honeycomb holes, each of which can be filled with oil. As the cavity formed by the oil impacted by the high-speed penetrator increases in the container, the honeycomb structure undergoes plastic deformation, which can absorb part of the energy transferred to the fluid, reduce the expansion of the cavity, and further reduce the water hammer effect, thereby significantly improving the survivability of the wing fuel tank.

[0042] In some possible embodiments, the outer shell 1 includes a top plate 11, a bottom plate 12 and a surrounding side plate 13, the top plate 11 is close to the upper surface of the wing, the bottom plate 12 is close to the lower surface of the wing, the surrounding side plate 13 is arranged between the top plate 11 and the bottom plate 12 and the surrounding side plate 13 connects the top plate 11 and the bottom plate 12, the top plate 11, the bottom plate 12 and the surrounding side plate 13 enclose the oil chamber, and the extension direction of each honeycomb hole of the honeycomb structure is perpendicular to the bottom plate 12.

[0043] The honeycomb holes of the honeycomb structure are parallel. After studying the damage caused by the water hammer effect to the oil tank, the influence of the change of penetration conditions on the damage effect was mainly analyzed. It was found that when the honeycomb holes of the honeycomb structure extend in the direction perpendicular to the bottom plate 12, the effect of alleviating the water hammer effect is best.

[0044] In some possible embodiments, the wing oil tank includes a partition assembly 2, which is arranged in the oil cavity. The partition assembly 2 divides the oil cavity into a plurality of sub-oil cavities a. The honeycomb structure includes a plurality of honeycomb units 3, and each of the honeycomb units 3 is respectively arranged in a corresponding sub-oil cavity a.

[0045] The wing fuel tank provided in the embodiment of the present application is also provided with a partition assembly 2, and there is no connection relationship between the partition assembly 2 and the inner wall of the shell 1, but only a contact and matching relationship, and the inner wall of the shell 1 limits the position of the partition assembly 2 to prevent the partition assembly 2 from moving inside the shell 1. The shell 1, the honeycomb structure and the partition assembly 2 can all be made of aluminum metal, which is light in weight and has good structural strength.

[0046] The partition assembly 2 has a grid structure and can fill the gaps in the oil cavity inside the oil tank. The partition assembly 2 can absorb the energy of liquid expansion through plate deformation, reduce the expansion of the cavity, and reduce the damage of the high-speed penetrating body to the shell 1. Specifically, the partition assembly 2 absorbs the kinetic energy of the oil in the oil tank, and each plate of the partition assembly 2 reduces the expansion of the cavity and structural damage, reduces the shock wave pressure, and thus alleviates the water hammer effect.

[0047] In the embodiment of the present application, a partition assembly 2 and a plurality of honeycomb units 3 are combined and arranged in the oil chamber, the honeycomb unit 3 has a small wall thickness and is easy to deform, while the partition assembly 2 has a large structural wall thickness and good structural strength, and can play a role in stably supporting the honeycomb unit 3, providing a support boundary for each honeycomb unit 3, and restraining the deformation of the honeycomb unit 3 in the process of absorbing energy, so that the impact resistance and survivability of the wing oil are better than that of only arranging a larger honeycomb structure in the oil chamber.

[0048] In some possible embodiments, the partition 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 is staggered to divide the oil chamber into a plurality of rows and columns of sub-oil chambers a. An angle is formed between the first direction plate 21 and the second direction plate 22, for example, a ninety-degree angle is formed between the first direction plate 21 and the second direction plate 22, and a plurality of cube or rectangular 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 to form a whole, and the overall structure is not easily deformed.

[0049] In some possible implementation schemes, a plurality of second direction plates 22 are disposed between the inner wall of the housing 1 and two adjacent ones of the first direction plates 21 .

[0050] 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 arranged at intervals, the two second side plates 132 are arranged between the two first side plates 131, and the two sides of the second side plate 132 are respectively connected to the two first side plates 131. Each first direction plate 21 and the first side plate 131 can be arranged substantially parallel, and each second direction plate 22 can be arranged substantially parallel to the second side plate 132. In each first side plate 131 and each first direction plate 21, a plurality of second direction plates 22 are arranged between adjacent two. The length of the first direction plate 21 is greater than the length of the second direction plate 22.

[0051] In some possible implementations, bent edges b are respectively provided at both ends of the second direction plate 22 to fit against the corresponding first direction plate 21 or the inner wall of the housing 1 , and the bent edges fitted against the first direction plate 21 are connected and fixed to the first direction plate 21 via fasteners.

[0052] By setting the bending edges b at both ends of the second direction plate 22, the first direction plate 21 or the inner wall of the outer shell 1 can be fitted with the bending edges b at both ends to achieve good stability. Optionally, the first direction plate 21 is provided with bending edges b at both ends to fit with the inner wall of the outer shell 1. The bending edges b on the first direction plate 21 and the second direction plate 22 fit with the inner wall of the outer shell 1, but do not need to be connected and fixed, which facilitates assembly. The bending edges b are used to fit with the inner wall of the outer shell 1, which is a surface-to-surface contact rather than a line-to-surface contact, and the matching stability is good, and no serious wear and scratches will be generated. The bending edges b on the second direction plate 22 fit with the first direction plate 21, which is convenient for connection and fixation by fasteners, for example, can be connected and fixed by anchor bolts.

[0053] In some possible implementations, part of the plate segments of the partition assembly 2 is in contact with the top plate 11 and the bottom plate 12 of the housing 1, and part of the plate segments of the partition assembly 2 has a gap with the top plate 11 and the bottom plate 12, so that the partition assembly 2 can be tightly matched with the inner wall of the housing 1, and at the same time, each sub-oil chamber a formed can be connected. For example, part of the plate segments of the first direction plate 21 corresponding to each sub-oil chamber a is in contact with the top plate 11 and the bottom plate 12, and part of the plate segments has a gap with the bottom plate 12 and the top plate 11, so that the formed sub-oil chamber a is not a closed cavity.

[0054] In some possible implementations, the wall thickness of the partition assembly 2 is greater than the wall thickness of the honeycomb unit 3. The partition assembly 2 and the honeycomb unit 3 can both be made of aluminum, and the structure is relatively light. The thickness of the first direction plate 21 and the second direction plate 22 of the partition assembly 2 is greater than the wall thickness of the honeycomb unit 3, so that the boundary reliability of the honeycomb unit 3 formed by the partition assembly 2 is high and not easy to deform. Among them, the wall thickness of the honeycomb unit 3 can be understood as: two adjacent honeycomb holes in the honeycomb unit 3 are separated by a thin wall, and the thin wall is the wall thickness of the honeycomb unit 3.

[0055] See also Figure 1 and Figure 2 As shown, the wing oil tank includes: a top plate 11, a bottom plate 12 and a peripheral side plate 13. The top plate 11 is close to the upper surface of the wing, the bottom plate 12 is spaced apart from the top plate 11, the bottom plate 12 is close to the lower surface of the wing, the peripheral side plate 13 is arranged between the top plate 11 and the bottom plate 12, and the peripheral side plate 13 connects the top plate 11 and the bottom plate 12, and the top plate 11, the bottom plate 12 and the peripheral side plate 13 enclose the oil cavity, wherein at least the bottom plate 12 is covered with the polyurea coating.

[0056] Polyurea coating usually adopts a one-time coating process. No matter how large the area is, there is no connection seam. It is also a dust-free material polyurea coating with the characteristics of strong adhesion, friction resistance, and high hardness.

[0057] When the aircraft is flying, the bottom plate 12 faces downward, which is the part with the largest exposed area on the fuel tank and is easily hit by high-speed penetrators during combat. The embodiment of the present application protects the bottom plate 12 by covering the bottom plate 12 with a polyurea coating, which can alleviate the water hammer effect when hit by a high-speed penetrator and improve the survivability of the fuel tank.

[0058] In some possible implementation schemes, at least one of the two wall surfaces on both sides of the bottom plate 12 along the thickness direction is covered with the polyurea coating.

[0059] At least one of the two wall surfaces on both sides of the bottom plate 12 along the thickness direction is covered with the polyurea coating. Considering that the polyurea coating will increase the weight of the structure, in the embodiment of the present application, the polyurea coating can be covered on only one surface of the bottom plate 12, such as the lower surface. When subjected to external impact, the polyurea coating can directly protect and alleviate the external impact. In the embodiment of the present application, the wall surfaces on both sides of the bottom plate 12 can also be covered with polyurea coatings, thereby significantly improving the structural strength of the bottom plate 12 and enhancing the survivability of the wing fuel tank.

[0060] In some possible embodiments, a polyurea coating is provided on the top plate 11, and a polyurea coating is provided on at least one of the wall surfaces on both sides of the top plate 11 in the thickness direction. Similarly, the peripheral side plate 13 may also be covered with a polyurea coating, and a polyurea coating is provided on the outer wall and / or inner wall of the peripheral side plate 13.

[0061] When the polyurea coating is provided on the top plate 11, the bottom plate 12 and the peripheral side plates 13, all-round coverage of the fuel tank is achieved, which significantly improves the survivability of the wing fuel tank.

[0062] In some possible implementations, a wing oil tank capable of alleviating water hammer effect includes a baffle assembly 2, which is arranged in the oil cavity, and the baffle assembly 2 divides the oil cavity into a plurality of sub-oil cavities a, each of which is connected. The baffle assembly 2 includes a plurality of first direction plates 21 and a plurality of second direction plates 22, each of which is staggered to divide the oil cavity into a plurality of rows and columns of sub-oil cavities a, wherein the first direction plates 21 and / or the second direction plates 22 are covered with a polyurea coating. In this implementation, a polyurea coating is further provided on the baffle assembly 2, so that the inner and outer wall structures of the wing oil tank are enhanced.

[0063] The present application also provides an aircraft, comprising: an aircraft body and the above-mentioned wing fuel tank. The aircraft body has wings. The wing fuel tank is arranged on the wings. The aircraft of the present application has the same beneficial effects as the above-mentioned wing fuel tank.

[0064] The above is only a preferred embodiment of the present invention, and does not limit the present invention in any form. Although the present invention has been disclosed as a preferred embodiment as above, it is not used to limit the present invention. Any technician familiar with this patent can make some changes or modify the technical contents suggested above into equivalent embodiments without departing from the scope of the technical solution of the present invention. However, any simple modification, equivalent change and modification made to the above embodiments according to the technical essence of the present invention without departing from the content of the technical solution of the present invention still fall within the scope of the solution of the present invention.

Claims

1. A wing fuel tank, characterized in that: include: A housing, the housing comprising a top plate, a bottom plate and a peripheral side plate, the top plate, the bottom plate and the peripheral side plate enclose an oil chamber, the top plate and the bottom plate are parallel, and the peripheral side plates are vertically connected to the top plate and the bottom plate respectively; A partition assembly, wherein the partition assembly is disposed in the oil chamber, and the partition assembly divides the oil chamber into multiple rows and columns of sub-oil chambers; A honeycomb structure, wherein the honeycomb structure comprises a plurality of honeycomb units, each of the honeycomb units is respectively arranged in a corresponding sub-oil cavity, and the wall thickness of the partition assembly is greater than the wall thickness of the honeycomb unit; Wherein, the partition assembly includes a plurality of first direction plates and a plurality of second direction plates, each of the first direction plates and each of the second direction plates are staggered to divide the oil chamber into a plurality of rows and columns of sub-oil chambers, a plurality of second direction plates are arranged between the inner wall of the shell and two adjacent ones of each of the first direction plates, and bent edges are respectively arranged at both ends of the second direction plates to fit with the corresponding first direction plates or the inner wall of the shell, the bent edges fitted with the first direction plates are connected and fixed to the first direction plates by fasteners, and bent edges are arranged at both ends of the first direction plates to fit with the inner wall of the shell; The bent edges on the first direction plate and the second direction plate are only fitted to the inner wall of the housing but are not connected or fixed; The bottom plate is covered with a polyurea coating; The first direction plate and / or the second direction plate is covered with a polyurea coating.

2. The wing fuel tank according to claim 1, characterized in that: The top plate is close to the upper surface of the wing, 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 the peripheral side plate connects the top plate and the bottom plate; The extending direction of each honeycomb hole of the honeycomb structure is perpendicular to the bottom plate.

3. The wing fuel tank according to claim 1 or 2, characterized in that: Part of the plate sections of the partition assembly are in contact with the top plate and the bottom plate of the housing, and there is a gap between the part of the plate sections of the partition assembly and the top plate and the bottom plate, so that the sub-oil chambers are connected.

4. An aircraft, characterized in that: include: an aircraft body, the aircraft body having wings; The wing oil tank according to any one of claims 1 to 3, wherein the wing oil tank is arranged on the wing.

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