Simple hard fuel tank of unmanned aerial vehicle

Abstract

The utility model relates to the technical field of unmanned aerial vehicle oil tanks, and discloses an unmanned aerial vehicle simple hard oil tank which comprises a tank body, a pipeline, a gravity oil filler cap, an oil collecting cabin and a flow limiting plate, the oil collecting cabin is arranged at the bottom of the tank body, the gravity oil filler cap is arranged at the top of the tank body, and the pipeline is arranged at the bottom of the tank body. One end of the pipeline is connected into the oil collecting cabin, the other end of the pipeline extends to one side of the box body, and the flow limiting plate is arranged at the bottom in the box body; the tank body is of a composite material structure, the structure is simple, the production cost is low, the thickness of each part of the tank body is proper according to the load transfer requirement, the designability is strong, the integral forming is adopted, the glue joint gaps are few, the sealing performance is good, the oil tank and the unmanned aerial vehicle body are made of the same material, the service life is equivalent, and the market application value is good.

Description

TECHNICAL FIELD

[0001] The utility model relates to unmanned aerial vehicle oil tank field, specifically, especially, it relates to a simple hard oil tank of unmanned aerial vehicle. BACKGROUND

[0002] The unmanned aerial vehicle is the no -load plane of using radio remote control equipment and self -provided program control device manipulation, or by vehicle -mounted computer completely or intermittently autonomously operation.

[0003] The aircraft fuel tank is usually divided into soft fuel tank, hard fuel tank and structural integral fuel tank three categories, soft fuel tank adopts soft material, cannot transfer load, production cost is high, traditional hard fuel tank is made by antirust aluminum alloy, and the weight is bigger, and structural integral fuel tank is not easy to seal, and the oil leakage event is easy to occur, and the maintenance cost is high.

[0004] The prior art has defects and needs to be improved. UTILITY MODEL CONTENT

[0005] In order to solve the defects existing in the prior art, the utility model provides a simple hard oil tank of unmanned aerial vehicle.

[0006] The utility model discloses a simple hard oil tank of unmanned aerial vehicle, including the box, pipeline, gravity oil filler cap, oil collecting cabin and flow limiting plate, the oil collecting cabin is located at the bottom of the box, the gravity oil filler cap is located at the top of the box, the pipeline is located at the bottom of the box, and one end of the pipeline is connected with the oil collecting cabin, and the other end of the pipeline extends to one side of the box, and the flow limiting plate is arranged in the bottom of the box.

[0007] Preferably, the box includes a lower shell, an upper shell and a wave protection plate, the lower shell and the upper shell are connected in a lap joint manner, a receiving cavity is formed between the lower shell and the upper shell, and the wave protection plate is arranged in the receiving cavity.

[0008] Preferably, the wave protection plate includes a left rib plate, a right rib plate, a rear rib plate, a front rib plate and a reinforcing corner piece, the left rib plate and the right rib plate are arranged in parallel and spaced apart in the receiving cavity, the rear rib plate and the front rib plate are arranged oppositely and are perpendicularly connected to the left rib plate and the right rib plate, the left rib plate, the right rib plate, the rear rib plate and the front rib plate are arranged in a character shape in the receiving cavity, and the left rib plate and the right rib plate are respectively provided with the reinforcing corner piece at the positions of being connected to the rear rib plate and the front rib plate.

[0009] Preferably, a gas passing hole is formed in the top of the left rib plate, an oil passing hole is formed in the bottom of the left rib plate, a lightening hole is formed in the middle of the left rib plate, and a slot is further arranged on the left rib plate.

[0010] Preferably, a plurality of circular holes with a diameter of 10 mm are formed in the flow limiting plate.

[0011] Preferably, the reinforcing corner piece is made of L-shaped glass fiber material.

[0012] Preferably, the box body is connected with the machine body by means of gluing, and the inside of the box body is connected by sealing glue.

[0013] Preferably, the box body is made of glass fiber prepreg.

[0014] Compared with the prior art, the box body of the unmanned aerial vehicle oil tank is made of composite material, has simple structure, light weight, low production cost, can transfer load, has strong designability, is integrally formed, has few glue joints, has good sealing performance, has the same service life as the unmanned aerial vehicle machine body, and has good market application value. BRIEF DESCRIPTION OF DRAWINGS

[0015] Figure 1 It is a schematic diagram of the overall structure of the utility model;

[0016] Figure 2 It is a schematic diagram of the internal structure of the box body of the utility model;

[0017] Figure 3 It is a schematic diagram of the left rib plate structure of the utility model;

[0018] Figure 4 It is a schematic diagram of the connection structure of the box body and the oil collecting tank of the utility model.

[0019] Mark: box body 1, pipeline 2, gravity oil filling cap 3, oil collecting tank 4, flow limiting plate 5, lower shell 11, left rib plate 12, right rib plate 13, rear rib plate 14, front rib plate 15, reinforcing corner piece 16, air vent hole 121, oil vent hole 122, lightening hole 123, slotted hole 124. DETAILED DESCRIPTION

[0020] It should be noted that the above technical features continue to be combined to form various embodiments not listed above, which are all considered to be within the scope of the description of the utility model; and for those skilled in the art, the above description can be improved or changed, and all these improvements and changes should belong to the protection scope of the claims of the utility model.

[0021] In order to facilitate understanding of the utility model, the utility model will be described in more detail below in combination with the drawings and specific embodiments. The preferred embodiments of the utility model are shown in the drawings. However, the utility model can be realized in many different forms, and is not limited to the embodiments described in the specification. On the contrary, the purpose of providing these embodiments is to make the disclosure of the utility model more thorough and comprehensive.

[0022] It should be noted that when an element is referred to as being "fixed to" another element, it may be directly attached to the other element or there may be an intermediate element. When an element is referred to as being "connected to" another element, it may be directly connected to the other element or there may be an intermediate element. The terms "vertical," "horizontal," "left," "right," and similar expressions used in this specification are for illustrative purposes only.

[0023] Unless otherwise defined, all technical and scientific terms used in this specification have the same meanings as those commonly understood by those skilled in the art in the art of the present invention. The terms used in this specification are only for the purpose of describing specific embodiments and are not intended to limit the present invention.

[0024] The utility model is described in detail below with reference to the accompanying drawings.

[0025] like Figures 1-4 As shown: A simple hard fuel tank for an unmanned aerial vehicle, comprising a tank body 1, a pipeline 2, a gravity refueling port cover 3, an oil collecting tank 4 and a flow limiting plate 5. The oil collecting tank 4 is arranged at the bottom of the tank body 1, the gravity refueling port cover 3 is arranged at the top of the tank body 1, the pipeline 2 is arranged at the bottom of the tank body 1, and one end of the pipeline 2 is connected to the oil collecting tank 4, and the other end of the pipeline 2 extends to one side of the tank body 1, and the flow limiting plate 5 is arranged at the bottom of the tank body 1.

[0026] It should be noted that four wave-breaking plates are arranged inside the fuel tank cavity in a "well" layout, namely the front rib, rear rib, left rib, and right rib. The wave-breaking plates divide the cavity into 9 parts. After strength calculation, the wave-breaking plates at different positions have different thicknesses. The longitudinal and transverse wave-breaking plates are plug-in and glued. The depth of the groove 124 is 1 / 2 of the height of the rib at the plug-in point, and the plug-in point is reinforced with an L-shaped glass fiber angle piece. An air hole 121 is opened on the top of the rib to connect the gas phase space between the fuel tank compartments. A small oil hole 122 is opened at the bottom of the rib, and a large oil hole 122 is opened in the middle of the rib. The entire fuel tank can be quickly filled during gravity refueling. The wave-breaking plates are bonded to the lower shell 11 of the fuel tank with an oil-resistant resin, and the upper shell and lower shell 11 of the fuel tank are connected in an overlapping manner. A suitable overlap width is selected and bonded with an oil-resistant resin.

[0027] The fuel tank's bottom features a fuel collecting chamber 4, with a flow restrictor 5 positioned between the chamber and the tank cavity. Two 10mm-diameter holes are provided in the flow restrictor 5, ensuring continuous fuel supply for a 5s negative overload of the fuel volume within the chamber 4. Pipeline 2 connects the front and rear fuel tanks to the chamber 4, ensuring the unusable fuel level in the tank is less than 3%. A check valve connects to the pipe 2 to prevent fuel from flowing back into the tank during changes in pitch attitude.

[0028] All fuel tank structures are bonded. The tank's exterior is bonded to the aircraft structure. Sealant is applied to the interior of the tank to isolate the fuel from the composite structure and prevent oil leakage.

[0029] When refueling on the ground, the fuel enters the tank through the gravity refueling cap 3, and the excess gas is discharged from the exhaust pipe;

[0030] Furthermore, the fuel tank supplies fuel to the engine through pipeline 2 and is also connected to the atmosphere through pipeline 2.

[0031] Preferably, the box body 1 includes a lower shell 11, an upper shell and a wave-breaking plate. The lower shell 11 is connected to the upper shell in an overlapping manner. A accommodating cavity is set between the lower shell 11 and the upper shell, and the wave-breaking plate is set in the accommodating cavity.

[0032] It should be noted that the accommodating cavity formed by the combination of the lower shell 11 and the upper shell can not only be used to install the wave-breaking plate, but also can contain liquid.

[0033] Preferably, the wave-breaking plate includes a left rib plate 12, a right rib plate 13, a rear rib plate 14, a front rib plate 15 and a reinforcing angle piece 16. The left rib plate 12 and the right rib plate 13 are arranged in parallel and spaced apart in the accommodating cavity. The rear rib plate 14 and the front rib plate 15 are arranged opposite to each other and are vertically plugged into and connected with the left rib plate 12 and the right rib plate 13. The left rib plate 12, the right rib plate 13, the rear rib plate 14 and the front rib plate 15 are arranged in a well shape in the accommodating cavity. The left rib plate 12 and the right rib plate 13 are respectively provided with a reinforcing angle piece 16 at the plug-in position with the rear rib plate 14 and the front rib plate 15.

[0034] It should be noted that the wave-breaking plates divide the accommodating cavity 1 in the box body 1 into 9 parts. The left rib plate 12, the right rib plate 13, the rear rib plate 14 and the front rib plate 15 wave-breaking plates are plug-in and glued. The upper shell and the lower shell 11 are overlapped. The appropriate overlap width is selected and bonded with oil-resistant resin. The wave-breaking plates and the lower shell 11 are bonded with oil-resistant resin. The box body 1 is a composite structure. According to the stress conditions of different parts, a suitable number of layers of glass fiber prepreg are selected to ensure the load-bearing while reducing the weight of the oil tank body 1 as much as possible.

[0035] Preferably, an air hole 121 is provided at the top of the left rib plate 12, an oil hole 122 is provided at the bottom of the left rib plate 12, a lightening hole 123 is provided in the middle of the left rib plate 12, and a slot 124 is further provided on the left rib plate 12, and the slot 124 is provided on one side of the lightening hole 123.

[0036] It should be noted that the left rib plate 12 top is provided with a string hole 121, so that the oil tank compartments are communicated with each other, the left rib plate 1212 bottom is provided with a string oil hole 122, the left rib plate 1212 middle is provided with a lightening hole 123, the slot 124 depth is 1 / 2 of the left rib plate 12 height, the surrounding of the slot 124 is paved with a reinforcing angle piece 16, and the reinforcing angle piece 16 is made of L-shaped glass fiber.

[0037] Preferably, the flow limiting plate 5 is provided with a plurality of circular holes with a diameter of 10 mm.

[0038] It should be noted that the plurality of circular holes with a diameter of 10 mm is at least two or more;

[0039] Further, the flow limiting plate 5 separates the tank 1 from the oil collecting tank 4, the flow limiting plate 5 is adhered to the tank 1 bottom by oil-resistant resin, two circular holes with a diameter of 10 mm are formed on the flow limiting plate 5, so that the fuel volume 5s in the oil collecting tank 4 can be continuously supplied under negative overload; the front and rear of the tank 1 are communicated with the oil collecting tank 4 through the pipeline 2, so that the unusable oil in the tank 1 is less than 3%; the pipeline 2 is connected with a one-way valve, so that the fuel in the oil collecting tank 4 cannot flow back to the tank 1 when the pitch angle changes;

[0040] Further, the fuel enters the oil tank through the gravity filler cap 3, the string oil hole 122 is used to fill the fuel in the whole oil tank, and the excess gas in the tank 1 is discharged through the pipeline 2; when refueling, the oil surface in the tank 1 should not exceed a specific height, so that 3% of the expansion space is left in the tank 1, and the fuel is prevented from overflowing due to temperature difference change.

[0041] Preferably, the reinforcing angle piece 16 is made of L-shaped glass fiber material.

[0042] Preferably, the tank 1 is connected with the engine body by gluing, and the tank 1 is sealed and connected by sealing glue.

[0043] It should be noted that all structures of the oil tank are glued, so that the fuel and the composite structure are isolated, and the oil leakage problem of the oil tank is avoided.

[0044] Preferably, the tank 1 is made of glass fiber prepreg.

[0045] It needs to be explained that a simple hard fuel tank of unmanned aerial vehicle, tank body 1, pipeline 2, gravity oil filler cap 3, oil collecting cabin 4, flow limiting plate 5. The oil collecting cabin 4 is located at the bottom of the oil tank, and the oil tank supplies oil to the engine through the pipeline 2, the tank body 1 is communicated with the oil collecting cabin 4, which avoids too much dead oil in the oil tank, the tank body 1 and the oil collecting cabin 4 are provided with the flow limiting plate 5, which realizes the continuous fuel supply of the fuel volume 5s in the oil collecting cabin 4 under negative overload; the tank body 1 is a composite structure, which is simple in structure, low in production cost, strong in designability, less in adhesive gap, good in sealing performance, and has the same service life as the unmanned aerial vehicle body.

[0046] It needs to be explained that each of the above technical features continues to be combined, forming various embodiments not listed above, which are considered to be within the scope of the description of the utility model; and for those skilled in the art, the above description can be improved or changed, and all these improvements and changes should belong to the protection scope of the appended claims of the utility model.

Claims

1. A simple hard fuel tank for a UAV, characterized by: It includes a box body, a pipeline, a gravity refueling port cover, an oil collecting tank and a flow limiting plate. The oil collecting tank is arranged at the bottom of the box body, the gravity refueling port cover is arranged at the top of the box body, the pipeline is arranged at the bottom of the box body, and one end of the pipeline is connected to the oil collecting tank, and the other end of the pipeline extends to one side of the box body, and the flow limiting plate is arranged at the bottom of the box body.

2. The simple hard fuel tank for UAV according to claim 1, characterized in that: The box body includes a lower shell, an upper shell and a wave-breaking plate. The lower shell is connected to the upper shell in an overlapping manner. A accommodating cavity is set between the lower shell and the upper shell, and the wave-breaking plate is set in the accommodating cavity.

3. The simple hard fuel tank for UAV according to claim 2, characterized in that: The wave-breaking plate includes a left rib plate, a right rib plate, a rear rib plate, a front rib plate and a reinforcing angle piece. The left rib plate and the right rib plate are arranged in parallel and spaced apart in the accommodating cavity. The rear rib plate and the front rib plate are arranged opposite to each other and are vertically plugged into the left rib plate and the right rib plate. The left rib plate, the right rib plate, the rear rib plate and the front rib plate are arranged in a well shape in the accommodating cavity. The left rib plate and the right rib plate are respectively provided with reinforcing angle pieces at the plug-in positions with the rear rib plate and the front rib plate.

4. The simple hard fuel tank for a UAV according to claim 3, characterized in that: An air hole is provided on the top of the left rib plate, an oil hole is provided on the bottom of the left rib plate, a lightening hole is provided in the middle of the left rib plate, and a slot is further provided on the left rib plate, and the slot is provided on one side of the lightening hole.

5. The simple hard fuel tank for UAV according to claim 4, characterized in that: The flow limiting plate is provided with a plurality of circular holes with a diameter of 10 mm.

6. The simple hard fuel tank for UAV according to claim 5, characterized in that: The reinforcing corner piece is made of L-shaped glass fiber.

7. The simple hard fuel tank for UAV according to claim 1, characterized in that: The outside of the box is connected to the machine body by gluing, and the inside of the box is sealed by sealant.

8. The simple hard fuel tank for UAV according to claim 1, characterized in that: The box body is made of glass fiber prepreg.

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