Aircraft fuel tanks and fuel aircraft

Abstract

The embodiments of the present application disclose an aircraft fuel tank and a fuel aircraft. A specific embodiment of the aircraft fuel tank includes: a first body, a second body, and a third body; the first body has a U-shaped structure, with both ends of the U connected; the second body and the third body have straight structures, with one end of the second body and the third body connected to the two ends of the first body respectively; the bottom of the first body is lower than the bottom of the second body and the bottom of the third body relative to the ground, wherein the bottom is the side facing the ground; the aircraft fuel tank is provided with an oil inlet, and the bottom of the first body is provided with an oil outlet. This embodiment can ensure that the fuel required for the aircraft's endurance is provided while also reducing the impact on the aircraft's cargo capacity.

Description

Technical Field

[0001] The embodiments of the present application relate to the field of aircraft technology, and in particular to aircraft fuel tanks and fuel aircraft. Background Art

[0002] Unmanned aerial vehicles (UAVs) are typically unmanned aerial vehicles controlled by radio remote control and self-contained programmable controls. They can also be operated fully or intermittently autonomously by an onboard computer.

[0003] With the development of science and technology, UAVs have been widely used in both military and civilian fields. Existing UAVs mainly use batteries or fuel as power sources to ensure the flight operation of UAVs. Summary of the Invention

[0004] The embodiments of the present application provide an aircraft fuel tank and a fuel aircraft.

[0005] In a first aspect, an embodiment of the present application proposes an aircraft fuel tank, comprising: a first main body, a second main body and a third main body; the structure of the first main body is U-shaped, and the two ends of the U are connected; the structures of the second main body and the third main body are both straight, and one end of the second main body and the third main body are respectively connected to the two ends of the first main body; the bottom of the first main body is lower than the bottom of the second main body and the bottom of the third main body relative to the ground, wherein the bottom is the side facing the ground; the aircraft fuel tank is provided with an oil inlet, and the bottom of the first main body is provided with an oil outlet.

[0006] In some embodiments, the other end of the second body and the other end of the third body are both closed, and the second body and / or the third body are provided with an exhaust hole at the top of the other end, wherein the top is the side opposite to the bottom.

[0007] In some embodiments, the oil inlet is disposed on the top of the second body or the top of the third body, and a fuel tank cap is installed at the oil inlet.

[0008] In some embodiments, the aircraft fuel tank is further provided with a fuel quantity detection component for detecting the fuel content in the tank.

[0009] In some embodiments, the oil level detection component includes a fuel float, and the fuel float is disposed on the top of one end of the first body.

[0010] In some embodiments, an oil outlet valve is further provided at the oil outlet, one end of the oil outlet valve is connected to the oil outlet, and the other end of the oil outlet valve is connected to an oil pipe that supplies oil to the aircraft.

[0011] In some embodiments, the aircraft fuel tank is further provided with a connecting component for fixedly connecting the fuel tank to the fuselage of the aircraft, including at least one of the following: a connecting plate, a connecting buckle, a connecting hole, and a hook.

[0012] In some embodiments, the connecting component is provided at at least one of the following locations: a bottom portion of the first body, top portions of both ends of the first body, the other end of the second body, and the other end of the third body.

[0013] In a second aspect, an embodiment of the present application provides a fuel aircraft, comprising: an aircraft fuselage and an aircraft fuel tank as described in any embodiment of the first aspect.

[0014] In some embodiments, the aircraft fuel tank is disposed inside the aircraft fuselage and fixedly connected to the aircraft fuselage via connecting components; a cargo carrying component is provided in the accommodation space formed between the main bodies of the aircraft fuel tank for loading cargo.

[0015] The aircraft fuel tank and fuel aircraft proposed in the embodiments of the present application may include a first body, a second body, and a third body. The structure of the first body may be U-shaped, and the two ends of the U are connected. That is, the first body is a U-shaped, hollow structure. The structures of the second body and the third body may both be straight. One end of the second body and the third body are respectively connected to the two ends of the first body. That is, the second body and the third body are connected through the first body. In addition, the bottom of the first body is lower than the bottom of the second body and the bottom of the third body relative to the ground. The bottom may be a side facing the ground. In this way, an oil outlet may be provided at the bottom of the first body, and an oil inlet may be provided for the aircraft fuel tank. A fuel tank of this structure can ensure that the fuel required for the aircraft's endurance is provided while reducing the space required for the fuel tank, thereby reducing the impact on the aircraft's cargo capacity. BRIEF DESCRIPTION OF THE DRAWINGS

[0016] Other features, objects and advantages of the present application will become more apparent upon reading the detailed description of non-limiting embodiments made with reference to the following drawings:

[0017] Figure 1 This is a schematic structural diagram of an embodiment of an aircraft fuel tank provided by the present application;

[0018] Figure 2 yes Figure 1 A front view of the structure of the aircraft fuel tank is shown;

[0019] Figure 3 yes Figure 1 The structure of the aircraft fuel tank is shown in right view;

[0020] Figure 4 yes Figure 1A top view of the structure of the aircraft fuel tank is shown;

[0021] Figure 5 It is a structural schematic diagram of an embodiment of the fuel aircraft provided by this application. DETAILED DESCRIPTION

[0022] The principles and features of the present application are further described in detail below with reference to the accompanying drawings and examples. It should be understood that the specific embodiments described herein are merely for the purpose of explaining the relevant invention and are not intended to limit the invention. It should also be noted that, for ease of description, only portions relevant to the invention are shown in the accompanying drawings.

[0023] It should be noted that, in the absence of conflict, the embodiments and features of the embodiments in this application can be combined with each other. The present application will be described in detail below with reference to the accompanying drawings and in combination with the embodiments.

[0024] See Figure 1 As shown, it shows a structural schematic diagram of an embodiment of the aircraft fuel tank provided by the present application. The aircraft may include (but is not limited to) a drone. Figure 1 As shown, the aircraft fuel tank in this embodiment may include a first body 11 , a second body 12 and a third body 13 .

[0025] In this embodiment, the first body 11 can have a U-shaped structure, with both ends of the U-shaped structure connected. That is, the first body 11 can have a U-shaped exterior with a hollow interior. The second body 12 and the third body 13 can both be straight. One end of the second body 12 and one end of the third body 13 are connected to the ends of the first body 11, respectively. In other words, the second body 12 and the third body 13 are connected through the first body 11.

[0026] In this embodiment, in order to increase the volume of the aircraft fuel tank, as shown in FIG. Figure 1 As shown, the first body 11 can be a U-shaped structure in the direction perpendicular to the ground. That is, the orthographic projection to the plane perpendicular to the ground is U-shaped, which can be seen from Figure 2 As shown, it shows Figure 1 A front view of the structure of an aircraft fuel tank.

[0027] In this case, the bottom of the first body 11 can be lower than the bottoms of the second body 12 and the third body 13 relative to the ground. That is, the distance between the bottom of the first body 11 and the ground is smaller than the distance between the bottom of the second body 12 and the ground, and also smaller than the distance between the bottom of the third body 13 and the ground. The bottom can be the side facing the ground, i.e., the side of each body located at the bottom when the aircraft fuel tank is properly positioned (installed on the aircraft).

[0028] It is understandable that, since the bottom of the first body 11 is the lowest point of the aircraft fuel tank, that is, the position closest to the ground, an oil outlet can be provided at the bottom of the first body 11. Figure 3 As shown, an oil outlet 14 may be provided at the lowest point of the bottom of the first body 11. In this way, the fuel in the aircraft fuel tank can flow to the oil outlet 14 under the effect of its own gravity, thereby making full use of the fuel in the fuel tank.

[0029] In addition, in order to facilitate the flow of fuel in the second body 12 and the third body 13 into the first body 11, the bottom of the second body 12 and the bottom of the third body 13 can be tilted at a certain angle in the direction perpendicular to the ground. That is, after the second body 12 and the third body 13 are respectively connected to the first body 11, as shown in FIG. Figure 3 As shown, the distance between the end of the bottom of the third body 13 connected to the first body 11 and the ground can be smaller than the distance between the other end not connected to the first body 11 and the ground. The inclination angle here can be set according to actual conditions (such as the fluidity of the fuel, etc.).

[0030] In this embodiment, if Figure 1 As shown, the aircraft fuel tank should also be provided with a fuel inlet 15. Fuel can be added to the aircraft fuel tank through the fuel inlet 15. It should be noted that the fuel in the aircraft fuel tank is not limited in this application and can be, for example, a flammable liquid such as diesel or gasoline. For environmental protection, higher-purity gasoline can be used.

[0031] from Figure 1 As can be seen, a storage space is formed between the first body 11, the second body 12, and the third body 13. This storage space allows cargo to be loaded. In other words, the aircraft fuel tank provided in this embodiment can ensure the fuel required for aircraft endurance while also reserving space for cargo, reducing the space required by the fuel tank and thus minimizing the impact on the aircraft's loading capacity.

[0032] In some optional implementations of this embodiment, in order to maximize the volume of the aircraft fuel tank so as to be able to carry more fuel, the fuel inlet can usually be set at a high position in the fuel tank. For example, it can be set at the top of the second body or the top of the third body. Figure 1 As shown, the fuel inlet 15 can be located at the top of the second body 12, near the other end (the end not connected to the first body 11). A fuel tank cap can be installed at the fuel inlet 15 to prevent fuel from overflowing during flight and to prevent foreign matter from entering the tank. The top here can be the side opposite the bottom, i.e., the top side of each body when the aircraft fuel tank is properly positioned (installed on the aircraft).

[0033] Alternatively, as Figure 1 As shown, the other end of the second body (i.e., the end not connected to the first body) and the other end of the third body (i.e., the end not connected to the first body) can both be closed structures. In this case, in order to promote the flow of fuel in the fuel tank, an exhaust hole can be opened on the fuel tank. For example, an exhaust hole can be set on the top of the other end of the second body and / or the third body. Figure 4 As shown, it shows Figure 1 A top view of the aircraft fuel tank structure is shown. A vent hole 16 is provided on the top of the second body 12 near the other end. Another vent hole 16 is provided on the top of the third body 13 near the other end. Vent holes 16 can be connected to an exhaust pipe to discharge gas from the fuel tank, reducing or preventing problems with air pressure that could cause poor fuel flow.

[0034] Furthermore, the aircraft fuel tank in this application may also be equipped with a fuel level detection component. This fuel level detection component can be used to detect the fuel content in the tank, and its specific structure is not limited in this application. As an example, this fuel level detection component can be a fuel float (i.e., a fuel buoy). This can detect the fuel level, allowing timely refueling of the tank to avoid affecting the aircraft's operating efficiency.

[0035] It should be noted that, since the oil outlet is provided at the bottom of the first body, in order to improve the accuracy of the detection result of the fuel float, the fuel float can be provided at the top of either end of the first body. Figure 3 As shown, the fuel float 17 can be arranged on the top of one end of the first body 11 connected to the third body 13. In this way, even after there is no fuel in the second body and the third body, the fuel content in the first body can still be detected.

[0036] In addition, if Figure 3 As shown, an oil outlet valve 18 may be provided at the oil outlet 14. One end of the oil outlet valve 18 may be connected to the oil outlet 14, and the other end of the oil outlet valve 18 may be connected to an oil pipe. In this way, oil can be supplied to the aircraft through the oil pipe to ensure the power required for the aircraft to fly.

[0037] In some applications, a filter component may be installed at the fuel outlet to filter impurities from the fuel, thereby helping to extend the aircraft's service life. Furthermore, to improve the sealing performance of the aircraft's fuel tank, sealing components may be installed at the fuel inlet, outlet, and / or exhaust vent. Filter components and sealing components may also be installed based on actual needs. For example, sealing components may include (but are not limited to) at least one of the following: a sealing ring, a sealing strip, a sealant, a gasket, etc.

[0038] At the same time, in order to facilitate the installation of aircraft fuel tanks, such as Figure 1 As shown, the aircraft fuel tank in the embodiment of the present application may also be provided with a connecting component 19. The connecting component 19 can be used to securely connect the aircraft fuel tank to the fuselage of the aircraft. Here, the connecting component 19 may include (but is not limited to) at least one of the following: a connecting plate, a connecting buckle, a connecting hole, a hook, etc. The location of the connecting component 19 may also be adjusted according to actual conditions. Figures 1 to 3 As shown, the connecting member 19 can be provided at at least one of the following locations: the bottom of the first body 11, the tops of both ends of the first body 11, the other end of the second body 12, and the other end of the third body 13. It should be noted that the structural shape and position of the connecting member 19 in the figure are merely schematic.

[0039] It is understood that the aircraft fuel tank in this application can be made of oil-resistant and corrosion-resistant materials. Furthermore, in order to reduce the overall weight of the aircraft, the material of the aircraft fuel tank can also have the characteristics of light weight. In addition, in order to further increase the volume of the aircraft fuel tank, such as Figure 1 and Figure 4 As shown, the side of the second body 12 away from the third body 13 can be a curved surface, and the side of the third body 13 away from the second body 12 can also be a curved surface. This can also adapt to the shape of the aircraft and will not affect the space formed between the main bodies of the aircraft tank.

[0040] Optionally, to increase the capacity of the aircraft fuel tank, the aircraft fuel tank may further include a fourth body. The fourth body has two ends connected to the other end of the second body and the other end of the third body, respectively. In this case, the other end of the second body and the other end of the third body may not be closed, and the two ends of the fourth body may be connected. In other words, the other end of the second body and the other end of the third body are connected via the fourth body.

[0041] The present application also provides a fuel aircraft, which may include an aircraft fuselage and the aircraft fuel tank described in the above embodiments. As an example, the structure of the fuel aircraft may be as follows: Figure 5 As shown, it shows a structural schematic diagram of an embodiment of the fuel aircraft provided by the present application.

[0042] like Figure 5 As shown, the fuel aircraft may include an aircraft fuel tank 1 and an aircraft fuselage 2. The aircraft fuel tank 1 may be disposed inside the aircraft fuselage 2 and may be fixedly connected to the aircraft fuselage 2 via a connecting component. Figure 5 The structure of the aircraft fuselage 2 is merely schematic.

[0043] As can be seen from the figure, the aircraft fuselage 2 wraps around the aircraft fuel tank 1, thus providing protection. Furthermore, the structure of the aircraft fuel tank 1 creates a storage space in the middle of the fuselage 2, defined as the space between the various components of the aircraft fuel tank 1. A cargo-carrying component (such as a cargo box) can be placed within this storage space to carry cargo. The specific structure and dimensions of the cargo-carrying component can be determined based on the storage space and the desired cargo.

[0044] The fuel-powered aircraft provided in this embodiment, by providing the above-mentioned aircraft fuel tank, can not only ensure the fuel required for endurance flight, but also reserve space for cargo. This effectively solves the problem of reduced loading capacity due to increased fuel tank volume, and can greatly expand the application range of fuel-powered aircraft.

[0045] The above description is merely a preferred embodiment of the present application and an illustration of the technical principles employed. Those skilled in the art should understand that the scope of the invention herein is not limited to the technical solutions formed by the specific combination of the above-mentioned technical features, but also encompasses other technical solutions formed by any combination of the above-mentioned technical features or their equivalents without departing from the inventive concept. For example, a technical solution formed by replacing the above-mentioned features with (but not limited to) technical features having similar functions disclosed in this application.

Claims

1. A fuel-powered aircraft, comprising: An aircraft fuselage (2) and an aircraft fuel tank (1), wherein the aircraft fuel tank (1) comprises: a first body (11), a second body (12), a third body (13), and a fourth body, wherein two ends of the fourth body are respectively connected to the other end of the second body and the other end of the third body; The structure of the first body (11) in a direction perpendicular to the ground is U-shaped, with both ends of the U-shaped structure being connected; The second body (12) and the third body (13) are both straight in structure, and one end of the second body (12) and the third body (13) are respectively connected to two ends of the first body (11); The bottom of the first body (11) is lower than the bottom of the second body (12) and the bottom of the third body (13) relative to the ground, wherein the bottom is the side facing the ground, and the other end of the second body (12) not connected to the first body (11) and the other end of the third body (13) not connected to the first body (11) are both facing obliquely upward on the same side of the first body (11); The aircraft fuel tank is provided with an oil inlet (15), and the bottom of the first body (11) is provided with an oil outlet (14); The aircraft fuselage (2) wraps around the aircraft fuel tank (1), forming a storage space inside the aircraft fuselage (2). The storage space is formed between the main bodies of the aircraft fuel tank and is used for loading cargo, wherein the aircraft fuselage (2), the second main body (12), and the third main body (13) are all located on the same side of the first main body (11).

2. The fuel-powered aircraft according to claim 1, wherein: The other end of the second body (12) and the other end of the third body (13) are both closed, and the second body (12) and / or the third body (13) are provided with an exhaust hole (16) at the top of the other end, wherein the top is the side opposite to the bottom.

3. The fuel-powered aircraft according to claim 1, wherein: The oil inlet (15) is arranged at the top of the second main body (12) or the top of the third main body (13), and a fuel tank cap is installed at the oil inlet (15).

4. The fuel-powered aircraft according to claim 1, wherein: The aircraft fuel tank is also provided with a fuel quantity detection component (17) for detecting the content of fuel in the fuel tank.

5. The fuel-powered aircraft according to claim 4, wherein: The oil quantity detection component (17) comprises a fuel float, and the fuel float is arranged on the top of one end of the first body (11).

6. The fuel-powered aircraft according to claim 1, wherein: An oil outlet valve (18) is also provided at the oil outlet (14), one end of the oil outlet valve (18) is connected to the oil outlet (14), and the other end of the oil outlet valve (18) is connected to an oil pipe for supplying oil to the aircraft.

7. The fuel-powered aircraft according to any one of claims 1 to 6, wherein: The aircraft fuel tank is also provided with a connecting component (19) for fixedly connecting the fuel tank to the fuselage of the aircraft, comprising at least one of the following: a connecting plate, a connecting buckle, a connecting hole, and a hook.

8. The fuel-powered aircraft according to claim 7, wherein: The connecting component (19) is provided at at least one of the following locations: the bottom of the first body (11), the tops of both ends of the first body (11), the other end of the second body (12), and the other end of the third body (13).

9. The fuel-powered aircraft according to claim 1, wherein: The aircraft fuel tank (1) is arranged inside the aircraft fuselage (2) and is fixedly connected to the aircraft fuselage (2) via a connecting component; A cargo carrying component is provided in the accommodation space formed between the main bodies of the aircraft fuel tank (1) for loading cargo.

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