A pressurized pod-mounted fuel tank

Abstract

The present application relates to a kind of pressurized missile-borne fuel tank, belong to the technical field of missile fuel system, the pressurized missile-borne fuel tank includes fuel tank body, oil suction subassembly and flexible pipe, fuel tank body is equipped with oil inlet, oil outlet, inflation port and exhaust port, oil suction subassembly and flexible pipe are arranged in fuel tank body, oil suction subassembly includes oil suction nozzle and universal connecting mechanism, universal connecting mechanism is used to connect oil suction nozzle movably in fuel tank body, to make the oil inlet end of oil suction nozzle always towards the direction of fuel gathering and keep in fuel, the one end of flexible pipe is communicated with the oil outlet end of oil suction nozzle, and the other end is communicated with oil outlet, using the structure, by universal connecting mechanism, oil suction nozzle is installed in fuel tank body, so that oil suction nozzle can move with inertia and fuel together, ensure that when missile is flying, oil suction nozzle's mouth portion can always towards the direction of fuel gathering, not deviate from fuel, so as to keep the continuity and reliability of fuel supply, there is no suction empty phenomenon.

Description

Technical Field

[0001] This invention belongs to the field of missile fuel system technology, and specifically relates to a pressurized missile fuel tank. Background Technology

[0002] The missile's onboard fuel tank is a critical component of missiles and other aircraft, used to store and supply fuel to the engine. In existing technology, many missile-borne fuel tanks use fixed fuel intake nozzles, whose intake port remains in a fixed position within the tank. When the missile is in pitch, dive, or under overload conditions, the fuel will violently slosh under inertial forces, potentially causing the fuel level to temporarily detach from the fixed intake port. In this situation, the fuel intake system will draw in gas instead of fuel, interrupting the engine's fuel supply. This phenomenon is commonly known as cavitation, and cavitation seriously threatens the continuity and reliability of fuel supply, posing a potential risk to the aircraft's safety.

[0003] Therefore, there is an urgent need for a pressurized missile fuel tank with a fuel suction nozzle that can move with the fuel due to inertia, will not suck in air, and will ensure flight safety. Summary of the Invention

[0004] This invention provides a pressurized missile fuel tank to solve the technical problem that missile fuel tanks in the prior art are prone to air suction during pitch, dive, or overload flight.

[0005] This invention is achieved through the following technical solution: a pressurized missile fuel tank, comprising a fuel tank body, a fuel suction assembly, and a flexible tube. The fuel tank body is provided with a fuel inlet, a fuel outlet, an air inlet, and a vent outlet. The fuel suction assembly and the flexible tube are disposed within the fuel tank body. The fuel suction assembly includes a fuel suction nozzle and a universal joint mechanism. The universal joint mechanism is used to movably connect the fuel suction nozzle to the fuel tank body so that the fuel inlet end of the fuel suction nozzle always faces the direction of fuel accumulation and remains in the fuel. One end of the flexible tube is connected to the fuel outlet end of the fuel suction nozzle, and the other end is connected to the fuel outlet.

[0006] To better realize the present invention, further optimizations are made to the above structure. The universal connection mechanism includes a support frame and a bearing seat. The support frame is fixed to the middle of the inner wall of the oil tank body, and the bearing seat is fixed on the support frame. A sliding bearing is provided in the bearing seat, and the oil suction nozzle is rotatably connected to the bearing seat through the sliding bearing.

[0007] To better realize the present invention, further optimizations are made to the above structure. The number of support frames and bearing seats are both two. The two support frames are symmetrically fixed in the middle of the inner wall of the oil tank body. There is a gap space between the two support frames for the oil suction nozzle to rotate circumferentially. The two bearing seats are opposite to each other and fixed at intervals on the two support frames. The oil suction nozzle is a rocker arm type oil suction nozzle. A connecting shaft is provided in the middle of the oil suction nozzle. The two ends of the connecting shaft are respectively rotatably connected to the sliding bearings of the two bearing seats.

[0008] To better realize the present invention, the above structure is further optimized by including a damping mesh plate, which is fixed in the fuel tank body to slow down the flow rate of fuel in the fuel tank body.

[0009] To better realize the present invention, the above structure is further optimized. The damping mesh plate has a central hole at its center, and the flexible tube passes through the central hole through the damping mesh plate and communicates with the oil suction nozzle.

[0010] To better realize the present invention, the above structure is further optimized by having two damping mesh plates, which are respectively disposed on both sides of the universal connection mechanism.

[0011] To better realize the present invention, further optimizations are made to the above structure. The oil tank body is provided with a front end cover and a rear end cover. The oil inlet and the vent are respectively located at the lower and upper parts of the front end cover. The oil outlet and the air inlet are respectively located at the lower and upper parts of the rear end cover. The oil inlet is provided with an oil inlet connector. The oil inlet end of the oil inlet connector extends into the oil tank body and is positioned downwards. The vent is provided with an air outlet connector with an air valve. The air inlet end of the air outlet connector extends into the oil tank body and is positioned upwards. The oil outlet is provided with an oil outlet connector. The oil inlet end of the oil outlet connector is connected to the flexible tube and the oil outlet end is provided with a plug. The air inlet is provided with an air inlet connector with an air valve. The air outlet end of the air inlet connector extends into the oil tank body and is positioned upwards.

[0012] To better realize the present invention, the above structure is further optimized by providing a pressure relief hole on the upper part of the rear end cover, and a safety valve is provided on the pressure relief hole.

[0013] To better realize the present invention, the above structure is further optimized by including a liquid level sensor, which is fixed on the fuel tank body and the sensing end of the liquid level sensor extends into the fuel.

[0014] Compared with the prior art, the present invention has the following advantages:

[0015] The pressurized missile-borne fuel tank provided by this invention includes a fuel tank body, a fuel suction assembly, and a flexible tube. The fuel tank body is provided with a fuel inlet, a fuel outlet, a venting port, and a venting port. The fuel suction assembly and the flexible tube are disposed within the fuel tank body. The fuel suction assembly includes a fuel suction nozzle and a universal joint mechanism. The universal joint mechanism is used to movably connect the fuel suction nozzle to the fuel tank body so that the fuel inlet end of the fuel suction nozzle always faces the direction of fuel accumulation and remains in the fuel. One end of the flexible tube is connected to the fuel outlet end of the fuel suction nozzle, and the other end is connected to the fuel outlet. With this structure, the fuel suction nozzle is installed in the fuel tank body through the universal joint mechanism, so that the fuel suction nozzle can move with the fuel due to inertia. This ensures that during missile pitch, yaw, or overload flight, the mouth of the fuel suction nozzle can always face the direction of fuel accumulation and will not deviate from the fuel, thereby maintaining the continuity and reliability of fuel supply and preventing cavitation. Attached Figure Description

[0016] To more clearly illustrate the technical solutions in the embodiments of the present invention or the prior art, the drawings used in the description of the embodiments or the prior art will be briefly introduced below. Obviously, the drawings described below are only some embodiments of the present invention. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort.

[0017] Figure 1 This is a schematic diagram of the internal structure of the pressurized missile fuel tank in this invention;

[0018] Figure 2 This is a schematic diagram of the internal structure of the pressurized missile fuel tank in this invention from another perspective;

[0019] Figure 3 This is a schematic diagram of the oil-absorbing component;

[0020] Figure 4 This is a schematic diagram of the damping mesh plate structure;

[0021] Figure 5 This is a 3D view of a pressurized missile fuel tank.

[0022] In the picture:

[0023] 1-Oil tank body; 2-Flexible tube; 3-Oil suction nozzle; 4-Support frame; 5-Bearing seat; 6-Gap space; 7-Connecting shaft; 8-Damping mesh plate; 9-Center hole; 10-Front end cover; 11-Rear end cover; 12-Oil filling connector; 13-Exhaust connector; 14-Oil outlet connector; 15-Air filling connector; 16-Safety valve; 17-Level sensor. Detailed Implementation

[0024] To make the objectives, technical solutions, and advantages of this invention clearer, the technical solutions of this invention will be described in detail below. Obviously, the described embodiments are merely some embodiments of this invention, and not all embodiments. Based on the embodiments of this invention, all other implementation methods obtained by those skilled in the art without creative effort are within the scope of protection of this invention.

[0025] In the description of this invention, it should be noted that, unless otherwise stated, "a plurality of" means two or more; the terms "upper," "lower," "left," "right," "inner," "outer," "front end," "rear end," "head," "tail," etc., indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings, and are only for the convenience of describing the invention and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation, and therefore should not be construed as a limitation of the invention. Furthermore, the terms "first," "second," "third," etc., are used for descriptive purposes only and should not be construed as indicating or implying relative importance.

[0026] In the description of this invention, it should also be noted that, unless otherwise explicitly specified and limited, the terms "installation," "connection," and "joining" should be interpreted broadly. For example, they can refer to a fixed connection, a detachable connection, or an integral connection; they can refer to a mechanical connection or an electrical connection; they can refer to a direct connection or an indirect connection through an intermediate medium. Those skilled in the art can understand the specific meaning of the above terms in this invention according to the specific circumstances.

[0027] Example 1:

[0028] In this embodiment, a pressurized missile fuel tank, such as Figures 1 to 5 As shown, the system includes a fuel tank body 1, a fuel suction assembly, and a flexible tube 2. Specifically, the fuel tank body 1 is provided with a fuel inlet, a fuel outlet, a gas filling port, and a venting port. The fuel inlet is used to fill the fuel tank body 1 with fuel. The fuel outlet is used to supply fuel to the missile engine. The gas filling port is used to introduce high-pressure gas to initially pressurize the fuel inside the fuel tank body 1. The venting port is used to exhaust gas during fuel filling. The fuel suction assembly and the flexible tube 2 are disposed inside the fuel tank body 1. The fuel suction assembly is used to draw fuel and direct it to the missile engine through the flexible tube 2 and the fuel outlet. The fuel suction assembly includes a fuel suction nozzle 3 and a universal joint mechanism. One end of the flexible tube 2 is connected to the fuel outlet end of the fuel suction nozzle 3, and the other end is connected to the fuel outlet. The universal joint mechanism is used to movably connect the fuel suction nozzle 3 inside the fuel tank body 1. The fuel suction nozzle 3 can achieve different orientations in the vertical plane through the universal joint mechanism, so that the fuel inlet end of the fuel suction nozzle 3 always faces the direction of fuel accumulation and remains in the fuel.

[0029] With this structure, the fuel suction nozzle 3 is installed inside the fuel tank body 1 through the universal connection mechanism, so that the fuel suction nozzle 3 can move with the fuel due to inertia. This ensures that when the missile is in pitch, tilt or overloaded, the mouth of the fuel suction nozzle 3 can always face the direction of fuel convergence and will not deviate from the fuel, thereby maintaining the continuity and reliability of fuel supply and preventing cavitation.

[0030] In this embodiment, as Figures 1 to 3 As shown, the universal joint mechanism includes a support frame 4 and a bearing seat 5. The support frame 4 is fixed to the middle of the inner wall of the fuel tank body 1 by welding, so that the fuel suction nozzle 3 is approximately located at the center of the fuel tank body 1. The bearing seat 5 is fixed to the support frame 4 by bolts and fasteners. A sliding bearing is provided in the bearing seat 5. The fuel suction nozzle 3 is rotatably connected to the bearing seat 5 through the sliding bearing. During the entire flight of the missile, the fuel volume is always greater than half the volume of the fuel tank body 1. When the missile is in pitch, tilt, or overload flight attitude, the fuel suction nozzle 3 located at the center is always immersed in fuel. At the same time, since the fuel suction nozzle 3, which is rotatable through the sliding bearing, can always move synchronously with the fuel due to inertia, the mouth of the fuel suction nozzle 3 always faces the direction of fuel accumulation, thereby ensuring that the fuel can be continuously and uninterruptedly sucked by the fuel suction nozzle 3, effectively avoiding the occurrence of cavitation.

[0031] As an optimization, such as Figure 1 and Figure 2 As shown, there are two support frames 4 and two bearing seats 5. The two support frames 4 are symmetrically fixed in the middle of the inner wall of the fuel tank body 1. There is a space 6 between the two support frames 4 for the fuel suction nozzle 3 to rotate circumferentially. The two bearing seats 5 are fixed to the two support frames 4 at opposite and intervals. The fuel suction nozzle 3 is a rocker arm type fuel suction nozzle 3. The middle of the fuel suction nozzle 3 is provided with a connecting shaft 7. The two ends of the connecting shaft 7 are respectively rotatably connected to the sliding bearings of the two bearing seats 5, so that the entire fuel suction nozzle 3 can pivot around the axis of the connecting shaft 7 and swing freely under the influence of gravity or inertial force generated by flight overload under the constraint and limiting action of the two bearing seats 5 and the sliding bearings provided inside, ensuring that the fuel inlet end of the fuel suction nozzle 3 always faces the direction of fuel accumulation.

[0032] In this embodiment, as Figure 3As shown, the aforementioned rocker arm type fuel suction nozzle 3 is a tubular structure bent at 90°, with one end being the fuel suction end and the other end being the fuel outlet end. The fuel suction end is flared, increasing the effective cross-sectional area of ​​the fuel suction end and reducing the flow resistance when fuel is sucked in. The aforementioned connecting shaft 7 is integrally set on both sides of the bend of the rocker arm type fuel suction nozzle 3. In the static state, the fuel suction end hangs down naturally due to gravity and points towards the bottom of the fuel tank body 1. During missile flight, the inertial force vector acting on the rocker arm type fuel suction nozzle 3 will always point towards the direction in which the fuel accumulates due to inertia, thereby driving the rocker arm type fuel suction nozzle 3 to swing, so that its fuel suction end always faces and is immersed in the deepest position of the fuel surface.

[0033] In this embodiment, as Figure 1 , Figure 2 and Figure 4 As shown, it also includes a damping mesh plate 8, which is fixed inside the fuel tank body 1 to slow down the flow rate of fuel within the fuel tank body 1. Multiple lugs are provided circumferentially on the inner wall of the fuel tank body 1 to abut the edges of the damping mesh plate 8. Screws or bolts are then used to fix the damping mesh plate 8 to the lugs. Multiple mesh holes are evenly distributed on the damping mesh plate 8. During missile pitch, tilt, or overload flight attitudes, the mesh holes do not affect the flow of fuel within the fuel tank body 1, while the damping mesh plate 8 provides some obstruction to the fuel, preventing excessively fast fuel flow. As an optimization, two damping mesh plates 8 are used, positioned on either side of the universal joint mechanism, resulting in a better effect in slowing down the fuel flow.

[0034] Furthermore, such as Figure 4 As shown, the damping mesh plate 8 has a central hole 9 at its center. The flexible tube 2 passes through the central hole 9 and then communicates with the oil suction nozzle 3. The outer diameter of the flexible tube 2 is smaller than the diameter of the central hole 9. When the oil suction nozzle 3 rotates due to inertia, the flexible tube 2 can also move without jamming in the central hole 9, without affecting the operation of the oil suction nozzle 3.

[0035] In this embodiment, the flexible tube 2 is a high-pressure hose with good flexibility and resistance to fuel corrosion. One end of the flexible tube 2 is reliably connected to the oil outlet of the suction nozzle 3 by means of clamps or quick-connect couplings, and the other end is connected and fixed at the oil outlet. It should be noted that the length and flexibility of the flexible tube 2 are selected for adaptability to ensure that the flexible tube 2 will not be overstretched or twisted or collapsed and blocked within the entire swing range of the suction nozzle 3, thus maintaining smooth oil delivery at all times.

[0036] As one specific implementation method of this embodiment, such as Figure 1 , Figure 2 and Figure 5As shown, the fuel tank body 1 is provided with a front cover 10 and a rear cover 11. The front cover 10 and the rear cover 11 are sealed to the front and rear ends of the fuel tank body 1 through a flange structure and a sealing ring, thereby forming a stable pressure-bearing sealed space inside the fuel tank body 1. The fuel inlet and vent are respectively located at the lower and upper parts of the front cover 10, and the fuel outlet and air inlet are respectively located at the lower and upper parts of the rear cover 11. Specifically, the fuel inlet is provided with a fuel inlet connector 12, which is sealed and installed on the fuel inlet by a flange, a gasket, and bolts. The fuel inlet end of the fuel inlet connector 12 extends into the fuel tank body 1 with its opening facing downwards, so that the injected fuel directly flows into the fuel inside the fuel tank body 1 and does not directly contact the air. The vent is provided with a vent connector 13 with an air valve, which is sealed and installed on the vent by a flange, a gasket, and bolts. The air inlet end of the vent connector 13 extends into the fuel tank body 1. The exhaust port is positioned with its opening facing upwards to ensure that only air can be discharged through the exhaust connector 13 during fuel injection, while fuel will not. The fuel outlet is equipped with an exhaust connector 14, which is sealed and installed on the fuel outlet via a flange, gasket, and bolts. The inlet end of the exhaust connector 14 is sealed and connected to the flexible tube 2 via a flange, and the outlet end is equipped with a plug. During fuel injection, the plug blocks the exhaust connector 14. During fuel extraction, the plug is removed, allowing the outlet end of the exhaust connector 14 to connect to the missile engine to supply fuel. The air inlet is equipped with an air inlet connector 15 with an air valve, which is sealed and installed on the air inlet via a flange, gasket, and bolts. The outlet end of the air inlet connector 15 extends into the fuel tank body 1 with its opening facing upwards to ensure that after the high-pressure gas enters the fuel tank body 1 through the air inlet connector 15, it will not directly impact the fuel and cause violent fuel fluctuations, or impact the fuel suction assembly and cause the fuel suction nozzle 3 to swing.

[0037] In this embodiment, high-pressure gas is introduced into the fuel tank body 1 through the gas filling connector 15. When filling with fuel, the high-pressure gas causes the internal air pressure of the fuel tank body 1 to increase, thereby actively pushing the fuel out through the fuel suction nozzle 3, which can meet the high-pressure, high-flow fuel supply requirements of high-performance missile engines.

[0038] As an optimization, such as Figure 1 and Figure 2 As shown, the upper part of the rear cover 11 is also provided with a pressure relief hole, and a safety valve 16 is provided on the pressure relief hole. The safety valve 16 plays the role of overpressure protection. When the pressure in the oil tank body 1 abnormally exceeds the preset safety value, the safety valve 16 can automatically open to relieve pressure, so as to prevent the oil tank body 1 from being structurally damaged due to overpressure and ensure system safety.

[0039] In this embodiment, as Figure 1 and Figure 2 As shown, it also includes a liquid level sensor 17, which is fixed on the fuel tank body 1. The sensing end of the liquid level sensor 17 extends into the fuel, so that the operator can understand the fuel level in the fuel tank body 1 when filling the tank.

[0040] When filling the pressurized missile fuel tank, the outlet connector 14 is first sealed with a plug, and the vent connector 13 is opened. Fuel is pumped into the tank body 1 through the filling connector 12. As the fuel level rises, the air in the tank is gradually discharged through the vent connector 13. The fuel level is then observed through the level sensor 17. Filling is stopped when the fuel level approaches the air inlet of the vent connector 13. The filling connector 12 and the vent connector 13 are then closed, and the fuel filling is completed and the tank is ready for use.

[0041] During the fuel extraction process of the aforementioned pressurized missile fuel tank, i.e., during missile flight, the high-pressure gas source built into the missile connects to the gas filling connector 15 to inject high-pressure gas into the fuel tank body 1, maintaining the internal pressure within a suitable range. The specific value depends on the fuel supply requirements of the missile engine. The high-pressure gas acts on the fuel surface, pushing the fuel actively into the fuel suction nozzle 3. Since the fuel suction nozzle 3 can swing or rotate circumferentially through the universal joint mechanism, the mouth of the fuel suction nozzle 3 can always follow the direction of fuel movement under inertia when the missile is in pitch, tilt, or overloaded flight attitude, ensuring that the fuel can be continuously and uninterruptedly drawn in by the fuel suction nozzle 3, effectively avoiding the occurrence of cavitation. The fuel is finally supplied to the missile engine through the fuel suction nozzle 3, flexible pipe 2, and fuel outlet connector 14. Throughout the entire fuel consumption process, no matter how the missile is in pitch, tilt, or overloaded, the fuel suction nozzle 3 can always reliably point to the fuel accumulation area, ensuring an uninterrupted fuel supply.

[0042] When the aforementioned pressurized missile fuel tank requires maintenance or partial fuel release on the ground, the aforementioned inflation connector 15 is connected to an external high-pressure gas source to pressurize the interior of the fuel tank body 1 with high-pressure gas. At the same time, the plug of the aforementioned fuel outlet connector 14 is removed. The high-pressure gas pushes the fuel through the aforementioned fuel suction nozzle 3, flexible pipe 2 and fuel outlet connector 14 to be discharged. Then, the aforementioned fuel outlet connector 14 is closed and the aforementioned exhaust connector 13 is opened to balance the pressure inside the tank with the external atmospheric pressure, thereby ensuring the safety of ground maintenance.

[0043] The above description is merely a specific embodiment of the present invention, but the scope of protection of the present invention is not limited thereto. Any variations or substitutions that can be easily conceived by those skilled in the art within the technical scope disclosed in the present invention should be included within the scope of protection of the present invention. Therefore, the scope of protection of the present invention should be determined by the scope of the claims.

Claims

1. A pressurized projectile-mounted fuel tank, characterized by: The oil tank body (1) is provided with an oil inlet, an oil outlet, an air inlet and an air outlet, the oil suction assembly and the flexible pipe (2) are arranged in the oil tank body (1), the oil suction assembly comprises an oil suction nozzle (3) and a universal connecting mechanism, the universal connecting mechanism is used for movably connecting the oil suction nozzle (3) in the oil tank body (1), so that the oil inlet end of the oil suction nozzle (3) always faces the fuel gathering direction and is kept in the fuel, one end of the flexible pipe (2) is communicated with the oil outlet end of the oil suction nozzle (3), and the other end is communicated with the oil outlet; The universal connecting mechanism comprises a support frame (4) and a bearing seat (5), the support frame (4) is fixed to the middle part of the inner wall of the oil tank body (1), the bearing seat (5) is fixed to the support frame (4), and the bearing seat (5) is provided with a sliding bearing; the oil suction nozzle (3) is rotatably connected to the bearing seat (5) through the sliding bearing; The number of the support frame (4) and the bearing seat (5) is two, the two support frames (4) are symmetrically fixed to the middle part of the inner wall of the oil tank body (1), and a spacing space (6) for the circumferential rotation of the oil suction nozzle (3) is arranged between the two support frames (4), the two bearing seats (5) are oppositely and spacedly fixed to the two support frames (4), the oil suction nozzle (3) is a rocker arm type oil suction nozzle (3), the middle part of the oil suction nozzle (3) is provided with a connecting shaft (7), and the two ends of the connecting shaft (7) are rotatably connected to the sliding bearings of the two bearing seats (5).

2. The pressurized munition-mounted fuel tank of claim 1, wherein: A damping mesh plate (8) is further arranged in the oil tank body (1) and used for delaying the flow speed of the fuel in the oil tank body (1).

3. The pressurized munition-mounted fuel tank of claim 2, wherein: The center of the damping mesh plate (8) is provided with a center hole (9), and the flexible pipe (2) is communicated with the oil suction nozzle (3) after penetrating through the damping mesh plate (8) through the center hole (9).

4. The pressurized munition-mounted fuel tank of claim 2, wherein: The number of the damping mesh plate (8) is two, and the two damping mesh plates (8) are arranged on the two sides of the universal connecting mechanism.

5. The pressurized munition-mounted fuel tank of claim 1, wherein: The oil tank body (1) is provided with a front end cover (10) and a rear end cover (11), the oil inlet and the air outlet are arranged in the lower part and the upper part of the front end cover (10), the oil outlet and the air inlet are arranged in the lower part and the upper part of the rear end cover (11), the oil inlet is provided with an oil inlet joint (12), the oil inlet end of the oil inlet joint (12) extends into the oil tank body (1) and the mouth part is arranged downward, the air outlet is provided with an air outlet joint (13) with an air valve, the air inlet end of the air outlet joint (13) extends into the oil tank body (1) and the mouth part is arranged upward, the oil outlet is provided with an oil outlet joint (14), the oil inlet end of the oil outlet joint (14) is communicated with the flexible pipe (2) and the oil outlet end is provided with a plug, and the air inlet is provided with an air inlet joint (15) with an air valve, the air outlet end of the air inlet joint (15) extends into the oil tank body (1) and the mouth part is arranged upward.

6. The pressurized projectile-mounted fuel tank of claim 5, wherein: The upper portion of the rear end cover (11) is further provided with a pressure relief hole, and a safety valve (16) is arranged on the pressure relief hole.

7. The pressurized projectile-mounted fuel tank of claim 1, wherein: The oil tank further comprises a liquid level sensor (17) fixed on the oil tank body (1), and a sensing end of the liquid level sensor (17) extends into the fuel.

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