Detachable structure oil tank for leading edge of wing of unmanned aerial vehicle

Abstract

The utility model relates to the technical field of unmanned aerial vehicles, in particular to an unmanned aerial vehicle wing leading edge detachable structure oil tank which comprises a wing shell, a supporting plate is fixed in the wing shell, and a protective lining is bonded on the inner surface of the wing shell. The utility model has the beneficial effects that the fuel tank can be detachably mounted in the wing shell, so that the fuel tank is convenient to replace and maintain; the protective lining is bonded on the inner surface of the wing shell to provide collision prevention protection for the surface of the fuel tank mounted in the wing shell, and the jacking plate and the protective pad are fixed on the inner side of the cover plate, so that after the wing shell is covered by the cover plate, the jacking plate jacks the outer side of the fuel tank through the protective pad, the fuel tank is kept stable and does not shake, and impact and extrusion of wind power are reduced; the safety of the oil tank is protected.

Description

Technical Field

[0001] The utility model relates to the technical field of unmanned aerial vehicles, in particular to a detachable structure fuel tank for the leading edge of an unmanned aerial vehicle wing. Background Technique

[0002] At present, in the prior art, the structural fuel tanks of most aircraft are arranged in the wing box area of the wing, which is the main load-bearing structure of the wing. It is impossible to realize the functional requirements of convenient disassembly and low-cost replacement and maintenance of the whole fuel tank. Moreover, the structure in the wing box area bears a large load, and the mechanical connection or bonding connection between the fuel tank area structure and each component deforms greatly after being loaded. Therefore, the risk of oil leakage from the fuel tank is relatively high.

[0003] Therefore, a detachable structure fuel tank needs to be arranged inside the wing shell to facilitate the disassembly, installation, replacement and maintenance of the fuel tank.

[0004] For example, the Chinese patent publication number "CN116280170A" in the prior art provides a detachable structure fuel tank for the leading edge of an unmanned aerial vehicle wing and a forming method. The fuel tank includes a connection assembly, a fuel tank body, and a fuel system assembly installed on the fuel tank body; the outer side surface of the fuel tank body is coplanar with the aerodynamic contour surface of the leading edge of the wing, forming the lift characteristic surface of the leading edge of the unmanned aerial vehicle wing. Its forming method specifically includes: laying and curing each component; drilling holes in each component; clamping and positioning the fuel tank skin; clamping and positioning the middle frame assembly in the fuel tank body; curing the fuel tank skin and the frame assembly at normal temperature with adhesive bonding and non-destructive testing; constructing the external sealing of the fuel tank body seams; installing the fuel system assembly and the sealing cover.

[0005] This device has good interchangeability and maintainability; the leading edge fuel tank bears a small load, has small deformation, and has a small risk of oil leakage; moreover, the gravity of the fuel can offset the aerodynamic load deformation of the leading edge skin, ensuring the aerodynamic lift effect of the unmanned aerial vehicle wing and improving the aerodynamic force.

[0006] For the existing detachable structure fuel tank for the leading edge of an unmanned aerial vehicle wing, the installation of the fuel tank inside the wing shell is relatively fixed, which is not convenient for disassembly, replacement and maintenance. The outside of the fuel tank lacks protection and is easily shaken and squeezed by wind impact, resulting in oil leakage from the fuel tank, and it is not convenient for disassembly and positioning installation. Content of the Utility Model

[0007] The purpose of the utility model is to solve the disadvantages that in the prior art, the installation of the fuel tank inside the wing shell is relatively fixed, which is not convenient for disassembly, replacement and maintenance, the outside of the fuel tank lacks protection, is easily shaken and squeezed by wind impact, and results in oil leakage from the fuel tank, and to propose a detachable structure fuel tank for the leading edge of an unmanned aerial vehicle wing.

[0008] To achieve the above purpose, the utility model provides the following technical solutions:

[0009] Design a detachable structure fuel tank for the leading edge of a drone wing, including a wing outer shell. A support plate is fixed inside the wing outer shell. A protective lining is bonded to the inner surface of the wing outer shell. A fuel tank is installed in the cavity separated by the support plate inside the wing outer shell. A guide oil pipe is connected between the bottom ends of the sides of the two fuel tanks. A connecting plate is fixed to the side of the fuel tank. A first connection hole is opened on the surface of the connecting plate. An oil pipe installation groove is opened at the outer bottom end of the support plate. A clamping groove is opened at the outer side of the support plate and above the oil pipe installation groove. A connecting rod is fixed inside the clamping groove. The connecting plate is clamped and inserted into the inside of the clamping groove, and the connecting rod passes through the first connection hole. A nut is connected to the surface of the connecting rod and outside the first connection hole.

[0010] Furthermore, a second connection hole is opened on the side of the wing outer shell. A cover plate is installed on the side of the wing outer shell. A third connection hole is opened at the side edge of the cover plate. A bolt is inserted into the inside of the third connection hole and the second connection hole. A pressing plate is fixed to the inner side of the cover plate. A protective pad is bonded to the outer side of the pressing plate. The protective pad abuts against the outer side of the fuel tank.

[0011] Furthermore, a connecting column is fixed to the connection end of the wing outer shell. The support plate is a rectangular plate structure and is vertically arranged. The wing outer shell is vertically arranged and its top end is inclined.

[0012] Furthermore, the guide oil pipe is a circular pipe structure and is horizontally arranged, and is slidably inserted into the oil pipe installation groove. The oil pipe installation groove is a U-shaped structure.

[0013] Furthermore, the connecting plate is a rectangular plate structure and its length is less than half of the length of the clamping groove. The clamping groove is a U-shaped structure and is located between the two fuel tanks.

[0014] Furthermore, the connecting rod is a threaded rod structure and is horizontally arranged, and its outer end does not protrude from the outer end of the clamping groove.

[0015] Furthermore, the second connection hole is a threaded hole structure and is aligned with the third connection hole.

[0016] Furthermore, the pressing plate is a rectangular plate structure and is vertically arranged. Both the pressing plate and the protective pad are rectangular structures.

[0017] The beneficial effects of a detachable structure fuel tank for the leading edge of a drone wing proposed by the present utility model are as follows:

[0018] 1. In the present utility model, a support plate is fixed inside the wing housing, and multiple cavities are formed inside the wing housing. Therefore, in the multiple cavities formed inside the wing housing, a fuel tank is detachably installed, and the oil pipe structure between the fuel tanks is snap-fitted into the oil pipe installation groove on the outer side of the support plate. Moreover, the fuel tank is snap-fitted and installed in the snap-fitting groove on the outer side of the support plate through the connecting plate on the side, and is detachably and firmly installed and connected through the connecting rod and the nut. In this way, the fuel tank can be detachably installed inside the wing housing, which is convenient for replacing and maintaining the fuel tank.

[0019] 2. In the present utility model, a protective lining is bonded to the inner surface of the wing housing to provide anti-collision protection for the installation on the surface of the fuel tank inside the wing housing, and a pressing plate and a protective pad are fixed to the inner side of the cover plate. Therefore, after the cover plate covers the wing housing, the pressing plate presses against the outer side of the fuel tank through the protective pad, keeping the fuel tank stable without shaking, reducing the impact and extrusion of the wind force, and protecting the safety of the fuel tank. Description of the Drawings

[0020] Figure 1 is a schematic diagram of the overall structure of the present utility model;

[0021] Figure 2 is the present utility model Figure 1 magnified view of part A;

[0022] Figure 3 is the present utility model Figure 1 schematic diagram of the partial structure of the wing housing of the present utility model;

[0023] Figure 4 is the present utility model Figure 3 magnified view of part B;

[0024] Figure 5 is the present utility model Figure 1 schematic diagram of the structure of the fuel tank installed inside the wing housing of the present utility model;

[0025] Figure 6 is the present utility model Figure 5 magnified view of part C;

[0026] Figure 7 is the present utility model Figure 1 schematic diagram of the partial structure of the cover plate of the present utility model.

[0027] In the figure: 1, wing housing; 2, connecting column; 3, fuel tank; 4, support plate; 5, nut; 6, cover plate; 7, bolt; 8, third connection hole; 9, pressing plate; 10, second connection hole; 11, protective lining; 12, snap-fitting groove; 13, oil pipe installation groove; 14, oil pipe; 15, connecting plate; 16, connecting rod; 17, first connection hole; 18, protective pad. Detailed Embodiment

[0028] Next, the technical solutions in the embodiments of the present utility model will be clearly and completely described in conjunction with the accompanying drawings in the embodiments of the present utility model. Obviously, the described embodiments are only a part of the embodiments of the present utility model, rather than all the embodiments. Embodiment

[0029] Please refer to Figure 1 、 Figure 2 、 Figure 3 、 Figure 4 、 Figure 5 、 Figure 6 and Figure 7 As shown in

[0030]

[0031]

[0032]

[0033] a detachable structure fuel tank at the leading edge of a drone wing in the drawings, including a wing outer shell 1. A support plate 4 is fixed inside the wing outer shell 1. A protective lining 11 is bonded to the inner surface of the wing outer shell 1. A fuel tank 3 is installed in the cavity separated by the support plate 4 inside the wing outer shell 1. A guide oil pipe 14 is connected between the bottom ends of the sides of the two fuel tanks 3. A connecting plate 15 is fixed to the side of the fuel tank 3. A first connection hole 17 is formed on the surface of the connecting plate 15. An oil pipe installation groove 13 is formed at the outer bottom end of the support plate 4. A clamping groove 12 is formed at the outer side of the support plate 4 and above the oil pipe installation groove 13. A connecting rod 16 is fixed inside the clamping groove 12. The connecting plate 15 is clamped and inserted into the inside of the clamping groove 12, and the connecting rod 16 passes through the first connection hole 17. A nut 5 is connected to the surface of the connecting rod 16 and outside the first connection hole 17. A support plate 4 is fixed inside the wing outer shell 1, and multiple cavities are formed inside the wing outer shell 1. Therefore, the fuel tank 3 can be detachably installed in the multiple cavities formed inside the wing outer shell 1. The guide oil pipe 14 structure between the fuel tanks 3 is clamped in the oil pipe installation groove 13 on the outer side of the support plate 4. In addition, the fuel tank 3 is clamped and installed in the clamping groove 12 on the outer side of the support plate 4 through the connecting plate 15 on the side, and is detachably and firmly installed and connected through the connecting rod 16 and the nut 5. In this way, the fuel tank 3 can be detachably installed inside the wing outer shell 1, facilitating the replacement and maintenance of the fuel tank 3. A connecting column 2 is fixed to the connection end of the wing outer shell 1. The support plate 4 is a rectangular plate structure and is vertically arranged. The wing outer shell 1 is vertically arranged, and the top end is inclined. The guide oil pipe 14 is a circular pipe structure and is horizontally arranged, and is slidably inserted into the oil pipe installation groove 13. The oil pipe installation groove 13 is a U-shaped structure.The connecting plate 15 is a rectangular plate structure and its length is less than half of the length of the clamping groove 12. The clamping groove 12 is a U-shaped structure and is located between the two fuel tanks 3. The connecting rod 16 is a threaded rod structure and is horizontally arranged, and its outer end does not protrude from the outer end of the clamping groove 12. Embodiment

[0034] Please refer to Figure 1 , Figure 2 , Figure 3 , Figure 4 , Figure 5 , Figure 6 and Figure 7 , a detachable structure fuel tank at the leading edge of a drone wing in one of the illustrations, includes a wing housing 1. A support plate 4 is fixed inside the wing housing 1. A protective lining 11 is bonded to the inner surface of the wing housing 1. Fuel tanks 3 are installed in the cavities separated by the support plate 4 inside the wing housing 1. A fuel pipe 14 is connected between the bottom ends of the sides of the two fuel tanks 3. A connecting plate 15 is fixed to the side of the fuel tank 3. A first connection hole 17 is formed on the surface of the connecting plate 15. A fuel pipe installation groove 13 is formed at the outer bottom end of the support plate 4. A clamping groove 12 is formed at the outer position of the support plate 4 and above the fuel pipe installation groove 13. A connecting rod 16 is fixed inside the clamping groove 12. The connecting plate 15 is clamped and inserted into the inside of the clamping groove 12, and the connecting rod 16 passes through the first connection hole 17. A nut 5 is connected to the surface of the connecting rod 16 at a position outside the first connection hole 17.

[0035] The support plate 4 is fixed inside the wing housing 1, and multiple cavities are formed inside the wing housing 1. Therefore, the fuel tank 3 can be detachably installed in the multiple cavities formed inside the wing housing 1. The fuel pipe 14 structure between the fuel tanks 3 is clamped in the fuel pipe installation groove 13 on the outside of the support plate 4. In addition, the fuel tank 3 is clamped and installed in the clamping groove 12 on the outside of the support plate 4 through the connecting plate 15 on the side, and is detachably and firmly installed and connected through the connecting rod 16 and the nut 5. In this way, the fuel tank 3 can be detachably installed inside the wing housing 1, which is convenient for replacing and maintaining the fuel tank 3.

[0036] A second connection hole 10 is formed on the side of the wing housing 1. A cover plate 6 is installed on the side of the wing housing 1. A third connection hole 8 is formed on the side edge of the cover plate 6. A bolt 7 is inserted into the inside of the third connection hole 8 and the second connection hole 10. A pressing plate 9 is fixed to the inside of the cover plate 6. A protective pad 18 is bonded to the outside of the pressing plate 9. The protective pad 18 abuts against the outside of the fuel tank 3.

[0037] A protective lining 11 is bonded to the inner surface of the wing casing 1 to provide anti-collision protection for the surface of the fuel tank 3 installed inside the wing casing 1. A pressing plate 9 and a protective pad 18 are fixed to the inner side of the cover plate 6. Therefore, after the cover plate 6 covers the wing casing 1, the pressing plate 9 presses against the outer side of the fuel tank 3 through the protective pad 18, keeping the fuel tank 3 stable without shaking, reducing the impact and extrusion of wind force, and protecting the safety of the fuel tank 3.

[0038] The second connecting hole 10 is of a threaded hole structure and is aligned with the third connecting hole 8; the pressing plate 9 is of a rectangular plate structure and is vertically arranged, and both the pressing plate 9 and the protective pad 18 are of rectangular structures.

[0039] Working method: A support plate 4 is fixed inside the wing casing 1, and a plurality of cavities are formed inside the wing casing 1. Therefore, in the plurality of cavities formed inside the wing casing 1, the fuel tank 3 is detachably installed. The oil pipe 14 structure between the fuel tanks 3 is clamped in the oil pipe installation groove 13 on the outer side of the support plate 4. In addition, the fuel tank 3 is clamped and installed in the clamping groove 12 on the outer side of the support plate 4 through the connecting plate 15 on the side, and is detachably and firmly installed and connected through the connecting rod 16 and the nut 5. In this way, the fuel tank 3 can be detachably installed inside the wing casing 1, facilitating the replacement and maintenance of the fuel tank 3.

[0040] A protective lining 11 is bonded to the inner surface of the wing casing 1 to provide anti-collision protection for the surface of the fuel tank 3 installed inside the wing casing 1. A pressing plate 9 and a protective pad 18 are fixed to the inner side of the cover plate 6. Therefore, after the cover plate 6 covers the wing casing 1, the pressing plate 9 presses against the outer side of the fuel tank 3 through the protective pad 18, keeping the fuel tank 3 stable without shaking, reducing the impact and extrusion of wind force, and protecting the safety of the fuel tank 3.

[0041] The above is only a preferred specific embodiment of the present invention, but the protection scope of the present invention is not limited thereto. Any person skilled in the art within the technical scope disclosed by the present invention, according to the technical solution and inventive concept of the present invention, makes equivalent substitutions or changes, and all should be covered within the protection scope of the present invention.

Claims

1. A detachable structural fuel tank at the leading edge of an unmanned aerial vehicle wing, comprising a wing outer shell (1), characterized in that: A support plate (4) is fixedly installed inside the wing housing (1). A protective lining (11) is bonded to the inner surface of the wing housing (1). A fuel tank (3) is installed in the cavity separated by the support plate (4) inside the wing housing (1). A fuel pipe (14) is connected between the bottom ends of the sides of the two fuel tanks (3). A connecting plate (15) is fixed to the side of the fuel tank (3). A first connection hole (17) is formed on the surface of the connecting plate (15). An oil pipe installation groove (13) is formed at the outer bottom end of the support plate (4). A clamping groove (12) is formed at the outer side of the support plate (4) above the oil pipe installation groove (13). A connecting rod (16) is fixedly installed inside the clamping groove (12). The connecting plate (15) is clamped and inserted into the clamping groove (12), and the connecting rod (16) passes through the first connection hole (17). A nut (5) is connected to the surface of the connecting rod (16) outside the first connection hole (17).

2. The detachable structure fuel tank at the leading edge of the wing of an unmanned aerial vehicle according to claim 1, wherein: A second connection hole (10) is formed on the side of the wing housing (1). A cover plate (6) is installed on the side of the wing housing (1). A third connection hole (8) is formed at the side edge of the cover plate (6). A bolt (7) is inserted into the third connection hole (8) and the second connection hole (10). A pressing plate (9) is fixedly installed inside the cover plate (6). A protective pad (18) is bonded to the outer side of the pressing plate (9). The protective pad (18) abuts against the outer side of the fuel tank (3).

3. The detachable structure fuel tank at the leading edge of the wing of an unmanned aerial vehicle according to claim 1, characterized in that: A connecting column (2) is fixed to the connection end of the wing housing (1). The support plate (4) is a rectangular plate structure and is vertically arranged. The wing housing (1) is vertically arranged and its top end is inclined.

4. The detachable structure fuel tank at the leading edge of the wing of the unmanned aerial vehicle according to claim 1, wherein: The fuel pipe (14) is a circular pipe structure and is horizontally arranged and slidably inserted into the oil pipe installation groove (13). The oil pipe installation groove (13) is a U-shaped structure.

5. The detachable structure fuel tank at the leading edge of the wing of an unmanned aerial vehicle according to claim 1, characterized in that: The connecting plate (15) is a rectangular plate structure and its length is less than half of the length of the clamping groove (12). The clamping groove (12) is a U-shaped structure and is located between the two fuel tanks (3).

6. The detachable structure fuel tank at the leading edge of the wing of a drone according to claim 1, wherein: The connecting rod (16) is a threaded rod structure and is horizontally arranged, and its outer end does not protrude from the outer end of the clamping groove (12).

7. The detachable structural fuel tank at the leading edge of the wing of an unmanned aerial vehicle according to claim 2, wherein: The second connection hole (10) is a threaded hole structure and is aligned with the third connection hole (8).

8. A detachable structure fuel tank for the leading edge of a drone wing according to claim 2, characterized in that: The pressing plate (9) is a rectangular plate structure and is vertically arranged. Both the pressing plate (9) and the protective pad (18) are rectangular structures.

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