A whole oil tank of a drone fuselage

Abstract

The application discloses a whole oil tank of a UAV fuselage and relates to the technical field of unmanned aerial vehicles. The whole oil tank comprises a storage oil tank and a consumption oil tank. The storage oil tank and the consumption oil tank are arranged in a top-bottom mode and are provided with an oil supply hole to communicate the storage oil tank with the consumption oil tank. The inside of the storage oil tank is divided into a front oil tank, a middle oil tank and a rear oil tank. The front oil tank and the rear oil tank are provided with an injection pump to supply oil into the middle oil tank. The consumption oil tank is below the middle oil tank, and a control valve is arranged in the oil supply hole to control the oil flow from the middle oil tank to the consumption oil tank. The application divides the oil tank into the storage oil tank and the consumption oil tank and divides them into layers in a top-bottom mode, so that the pressure of the oil on the bottom plate under a large overload coefficient can be reduced. Meanwhile, the storage oil tank is divided into independent storage units by the fuselage partition frame, so that the fuel shaking impact can be effectively reduced, and the oil supply reliability is improved.

Description

TECHNICAL FIELD

[0001] The present application relates to the technical field of unmanned aerial vehicles, and particularly relates to a whole oil tank of an unmanned aerial vehicle body. BACKGROUND

[0002] At present, in order to meet the long endurance technical index, a large unmanned aerial vehicle generally installs a wing oil tank on the basis of an oil tank of a body to increase the oil load. For some unmanned aerial vehicles with specific functions, the wing structure cannot be effectively utilized, and only the limited space in the body can be fully utilized to increase the oil load. The whole oil tank of the body can use the existing bearing structural members of the body as tank wall plates, and compared with a soft tank and a hard tank, the whole oil tank of the body reduces the support structure and effectively improves the space utilization.

[0003] The conventional metal structure whole oil tank wall plate is relatively thin, and only the self web stiffness can meet the use requirement. Generally, the wall plate is provided with a stiffening structure to improve the stiffness. The large unmanned aerial vehicle has the characteristics of wide size and high depth, and the oil tank wall plate has the characteristics of high oil pressure and large fuel impact force. The increase of the size and the load leads to the increase of the weight of the stiffening structure and the increase of the sealing assembly difficulty, and too many stiffening combinations are easy to increase the risk of oil leakage in the later period. In addition, the high depth characteristic of the large-capacity oil tank also leads to the deep installation position of the fuel equipment, and the maintenance operation is difficult. SUMMARY

[0004] To solve the technical problems in the background art, the present application provides a whole oil tank of an unmanned aerial vehicle body.

[0005] The whole oil tank of the unmanned aerial vehicle body comprises an oil storage tank and an oil consumption tank, the oil storage tank and the oil consumption tank are arranged in an upper-lower mode, and a fuel supply hole is arranged to communicate the oil storage tank and the oil consumption tank, and a control valve is arranged in the fuel supply hole to control the flow of oil from the oil storage tank to the oil consumption tank.

[0006] As a further optimization of the above scheme, the oil storage tank comprises a front frame assembly, a rear frame assembly, a left skin, a right skin, an upper cover plate and a lower bottom plate, the oil consumption tank comprises a lower bottom plate, a body front partition, a body rear partition, a left wall plate, a right wall plate and an oil consumption tank bottom plate, the internal space of the oil storage tank and the oil consumption tank is separated by the lower bottom plate, and the fuel supply hole is arranged on the lower bottom plate.

[0007] As a further optimization of the above scheme, the body front partition and the body rear partition vertically penetrate the lower bottom plate and extend to the oil storage tank to divide the internal space of the oil storage tank into three independent spaces, namely a front oil tank, a middle oil tank and a rear oil tank, and the body front partition and the body rear partition are both provided with a fuel mixing hole to communicate the middle oil tank with the front oil tank and the rear oil tank.

[0008] As a further optimization of the above scheme, the front and rear fuselage bulkheads are further provided with oil delivery holes, and the front and rear oil tanks are respectively provided with an ejector pump, and the ejector pump is connected with the oil delivery hole through an oil delivery pipe.

[0009] As a further optimization of the above scheme, the upper cover plate is detachably spliced by three cover plates, and is arranged on the top of the front, middle and rear oil tanks.

[0010] As a further optimization of the above scheme, the front and rear frame assemblies are adjacent to the front and rear oil tanks, and the front and rear frame assemblies are respectively provided with a maintenance opening at the lower part.

[0011] As a further optimization of the above scheme, the control valve is a one-way valve to allow oil to flow only from the middle oil tank to the consumption oil tank.

[0012] As a further optimization of the above scheme, the front and rear frame assemblies, left and right skins are all made of carbon fiber honeycomb sandwich structure.

[0013] The whole oil tank of the unmanned aerial vehicle fuselage divides the oil tank into a storage tank and a consumption tank, and is layered up and down, which can reduce the pressure of the oil on the bottom plate under large overload coefficient, and the independent oil supply of the consumption tank can ensure that the engine can be continuously supplied with oil at a specified pressure and flow rate under various flight states of the unmanned aerial vehicle, and the oil supply reliability is high.

[0014] The whole oil tank of the unmanned aerial vehicle fuselage divides the storage tank into a plurality of independent storage units by the fuselage bulkhead, which can effectively reduce the impact of fuel sloshing.

[0015] The whole oil tank of the unmanned aerial vehicle fuselage, the existence of the ejector pump and the oil transfer hole can ensure that the oil quantity of the middle oil tank is always maintained at a certain position, thereby ensuring the stable pressure of the consumption tank.

[0016] The whole oil tank of the unmanned aerial vehicle fuselage adopts a honeycomb sandwich structure to enhance the rigidity of the wall plate, compared with the traditional metal whole oil tank, avoids segmented connection and stiffened assembly, and reduces the sealing assembly difficulty.

[0017] The whole oil tank of the unmanned aerial vehicle fuselage, the design of the maintenance opening and the upper cover plate enables personnel to choose non-entry or entry maintenance, and solves the maintainability problem of high-depth oil tank. BRIEF DESCRIPTION OF DRAWINGS

[0018] Figure 1 The present application provides an external structure diagram of a whole oil tank of an unmanned aerial vehicle fuselage;

[0019] Figure 2A first angle view of the internal structure of the whole oil tank of the unmanned aerial vehicle body according to the present application is provided;

[0020] Figure 3 A second angle view of the internal structure of the whole oil tank of the unmanned aerial vehicle body according to the present application is provided;

[0021] Figure 4 A third angle view of the internal structure of the whole oil tank of the unmanned aerial vehicle body according to the present application is provided;

[0022] Figure 5 A fourth angle view of the internal structure of the whole oil tank of the unmanned aerial vehicle body according to the present application is provided. DETAILED DESCRIPTION

[0023] The whole oil tank of the unmanned aerial vehicle body according to the present application is provided with Figures 1 to 5 , which comprises an oil storage tank 1 and a consumption tank 2.

[0024] The oil storage tank 1 specifically comprises a front frame assembly 11, a rear frame assembly 12, a left skin 13, a right skin 14, an upper cover plate 15 and a lower bottom plate 16, and the consumption tank 2 specifically comprises the lower bottom plate 16, a front body partition 17, a rear body partition 18, a left wall plate 21, a right wall plate 22 and a consumption tank bottom plate 23, and it is worth noting that the oil storage tank 1 and the consumption tank 2 are based on the same lower bottom plate 16, thereby forming an upper and lower structure of the oil storage tank 1 and the consumption tank 2.

[0025] The lower bottom plate 16 is provided with an oil supply hole, and a control valve 201 is arranged in the oil supply hole to control the downward flow of oil from the oil storage tank 1 to the consumption tank 2. The number of oil supply holes is preferably two and the diameter is not less than 30mm.

[0026] The control valve 201 is a one-way valve to ensure that oil can only flow downward from the oil storage tank 1 to the consumption tank 2.

[0027] The front body partition 17 and the rear body partition 18 vertically penetrate the lower bottom plate 16 and extend to the oil storage tank 1 to divide the internal space of the oil storage tank 1 into three independent spaces, i.e., a front oil tank 3, a middle oil tank 4 and a rear oil tank 5. Figure 2 、 Figure 5 It can be seen that the consumption tank 2 is located below the middle oil tank 4 and is in communication with the middle oil tank 4 through the oil supply hole.

[0028] The front body partition 17 and the rear body partition 18 are provided with oil supply holes 102, and each of the front oil tank 3 and the rear oil tank 5 is provided with an injection pump 103, and an oil supply pipe 104 is connected between the injection pump 103 and the oil supply hole 102, so as to achieve the purpose of supplying oil from the front oil tank 3 and the rear oil tank 5 to the middle oil tank 4 through the injection pump 103 and the oil supply pipe 104. Preferably, the number of oil supply holes 102 is also two.

[0029] The front bulkhead 17 and the rear bulkhead 18 are provided with oil connection holes 101, preferably, the diameter of the oil connection holes 101 is not less than 30 mm, and the oil connection holes 101 are arranged at the position of 80% oil storage capacity of the middle oil tank 4, the oil connection holes 101 are used to ensure that the middle oil tank 4 keeps the oil level at 80% of the oil storage capacity, when the oil level of the middle oil tank 4 is lower than 80%, the front oil tank 3 and the rear oil tank 5 supply fuel to the middle oil tank 4 through the injection pump 103 and the fuel supply pipe 104, when the oil level of the middle oil tank 4 is higher than 80% of the oil storage capacity, the fuel is returned to the front oil tank 3 and the rear oil tank 5 through the oil connection holes 101, so that the fuel level of the middle oil tank 4 keeps at 80% of the oil storage capacity, and the pressure of the consumption oil tank 2 is stable.

[0030] The front frame assembly 11 and the rear frame assembly 12 are adjacent to the front oil tank 3 and the rear oil tank 5 respectively, and the front frame assembly 11 and the rear frame assembly 12 are provided with maintenance openings 111 at the lower parts thereof.

[0031] The oil storage tank 1 is divided into the front oil tank 3, the middle oil tank 4 and the rear oil tank 5, three cover plates are used to form the upper cover plate 15, and the three cover plates are arranged on the top of the front oil tank 3, the middle oil tank 4 and the rear oil tank 5 respectively.

[0032] Considering the design and weight requirements of the unmanned aerial vehicle, the front frame assembly 11, the rear frame assembly 12, the left skin 13 and the right skin 14 are made of carbon fiber honeycomb sandwich structure, and the thickness of the honeycomb is 5-15 mm.

[0033] When the oil tank of the unmanned aerial vehicle is used, the consumption oil tank 2 supplies fuel to the engine, the middle oil tank 4 supplies fuel to the consumption oil tank 2 through the lower control valve 201, the front oil tank 3 and the rear oil tank 5 supply fuel to the middle oil tank through the fuel supply holes 102, when the oil level of the middle oil tank 4 is lower than 80%, the front oil tank 3 and the rear oil tank 5 supply fuel to the middle oil tank 4 through the injection pump 103 and the fuel supply pipe 104, when the oil level of the middle oil tank 4 is higher than 80% of the oil storage capacity, the fuel is returned to the front oil tank 3 and the rear oil tank 5 through the oil connection holes 101, so that the fuel level of the middle oil tank 4 keeps at 80% of the oil storage capacity, and the pressure of the consumption oil tank 2 is stable, when the oil level of the front oil tank 3 and the rear oil tank 5 is 0, the injection pump 103 is closed, and the middle oil tank 4 supplies fuel to the consumption oil tank 2 independently.

[0034] The above is only the preferred embodiment of the present application, but the protection scope of the present application is not limited to this, any person skilled in the art can make equivalent replacement or change according to the technical scheme and the inventive concept of the present application within the technical range disclosed by the present application, which should be covered in the protection scope of the present application.

Claims

1. An integral fuel tank for a drone fuselage, characterized in that, It includes an oil storage tank (1) and a consumption tank (2). The oil storage tank (1) and the consumption tank (2) are arranged vertically and are provided with an oil supply hole to connect the oil storage tank (1) and the consumption tank (2). The oil supply hole is equipped with a control valve (201) to control the oil to flow from the oil storage tank (1) downward into the consumption tank (2). The oil storage tank (1) includes a front frame assembly (11), a rear frame assembly (12), a left skin (13), a right skin (14), an upper cover plate (15), and a lower bottom plate (16). The fuel tank (2) includes a lower bottom plate (16), a front fuselage bulkhead (17), a rear fuselage bulkhead (18), a left wall panel (21), a right wall panel (22), and a fuel tank bottom plate (23). The internal spaces of the oil storage tank (1) and the fuel tank (2) are separated by the lower bottom plate (16), and the oil supply hole is opened on the lower bottom plate (16). The front bulkhead (17) and rear bulkhead (18) of the fuselage vertically penetrate the bottom plate (16) and extend to the oil tank (1) to divide the internal space of the oil tank (1) into three independent spaces: the front oil tank (3), the middle oil tank (4) and the rear oil tank (5). The front bulkhead (17) and the rear bulkhead (18) of the fuselage are provided with oil passage holes (101) so that the middle oil tank (4) can be connected to the front oil tank (3) and the rear oil tank (5). Oil inlets (102) are provided on the front bulkhead (17) and rear bulkhead (18) of the fuselage, and each of the front oil tank (3) and the rear oil tank (5) is equipped with an ejector pump (103), and an oil pipe (104) is connected between the ejector pump (103) and the oil inlet (102). When the oil level in the middle tank (4) is below 80%, the front tank (3) and the rear tank (5) replenish fuel to the middle tank (4) through the ejector pump (103) and the oil supply pipe (104). When the oil level exceeds 80%, the fuel flows back to the front tank (3) and the rear tank (5) through the oil passage (101).

2. The integral fuel tank of the UAV fuselage according to claim 1, characterized in that, The upper cover plate (15) is composed of three detachable cover plates, which are arranged one by one on the top of the front oil tank (3), the middle oil tank (4) and the rear oil tank (5).

3. The integral fuel tank of the UAV fuselage according to claim 2, characterized in that, The front frame assembly (11) and the rear frame assembly (12) are adjacent to the front oil tank (3) and the rear oil tank (5) respectively, and both the front frame assembly (11) and the rear frame assembly (12) have maintenance ports (111) at their lower parts.

4. The integral fuel tank of the UAV fuselage according to claim 3, characterized in that, The control valve (201) is a one-way valve so that oil can only flow from the intermediate oil tank (4) into the consumption oil tank (2).

5. The integral fuel tank of the UAV fuselage according to claim 4, characterized in that, The front frame assembly (11), rear frame assembly (12), left skin (13), and right skin (14) all adopt a carbon fiber honeycomb sandwich structure.

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