A fuel tank device and method for pressurized inverted flight of an aircraft

Abstract

The invention discloses a fuel tank device and method for pressurized inverted flight of an aircraft. The device comprises a main fuel tank, an inverted flight fuel tank, a transition fuel tank, an air pipeline and an oil pipeline; a transition fuel tank is arranged in the main fuel tank, and a gravity valve is arranged in the transition fuel tank; one end of a first pipeline is connected to the gravity valve, and the other end is located at the inner top of the inverted flight fuel tank; one end of a second pipeline is connected to the gravity valve, and the other end is located at the inner bottom of the main fuel tank; one end of a third pipeline is connected to the gravity valve, and the other end is located at the inner top of the main fuel tank; along the air intake direction, a pressure reducing valve and an air circuit three-way valve are arranged on the air pipeline in sequence; along the oil supply direction, an oil circuit three-way valve and a fuel pump are arranged on the oil pipeline in sequence; an oil delivery hose is located inside the inverted flight fuel tank, and a heavy hammer is fixed at one end, so that the engine can continuously obtain fuel from the inverted flight fuel tank in both the forward flight and inverted flight states of the aircraft. The invention designs the main fuel tank, the inverted flight fuel tank and the transition fuel tank as one body, and the manufacture and assembly are relatively simple.

Description

Technical Field

[0001] The present invention relates to the field of aviation, and in particular to a fuel tank device and a method for pressurized inverted flight of an aircraft. Background Art

[0002] When an aircraft is flying at high altitude, its engine fuel supply system needs to be pressurized. There are mainly two types of pressurization schemes: soft fuel tank and hard fuel tank. For the use of soft fuel tank for pressurization, a closed container needs to be provided externally. This method has the following disadvantages: 1) Due to the requirements for the installation, fixation, use and maintenance of the soft fuel tank, the soft fuel tank installation bulkhead needs an opening cover or hole, which makes it difficult to ensure the cabin seal; 2) Because the cover needs to be frequently removed when refueling, exhausting and maintaining the soft fuel tank, additional related operations are required to ensure the cabin seal, which increases costs and is inconvenient to use and maintain; 3) It will cause problems such as complex structure and reduced fuel volume.

[0003] In addition, for aircraft with large maneuverability, when there is a negative overload or inverted flight, the air in the fuel tank may enter the fuel supply line, causing discontinuous fuel supply to the engine and causing a special situation of mid-air parking. Summary of the invention

[0004] The purpose of the present invention is to solve the problems and shortcomings of traditional aircraft fuel supply tanks, and to propose a fuel tank device and method for aircraft pressurized inverted flight based on a hard fuel tank. The present invention has the advantages of light weight, good sealing, large fuel tank capacity, constant pressurization, etc., and has the ability to continuously supply fuel under negative overload and inverted flight conditions.

[0005] In order to achieve the above object, the technical solution adopted by the present invention is as follows:

[0006] The first object of the present invention is to provide a fuel tank device for pressurized inverted flight of an aircraft, which comprises a main fuel tank, an inverted flight fuel tank, a transition fuel tank, an air pipeline and an oil pipeline;

[0007] A transition tank is provided in the main tank, and a gravity valve is provided in the transition tank; the transition tank is connected to the inverted flight tank through a first pipeline; one end of the first pipeline is connected to the gravity valve, and the other end is located at the inner top of the inverted flight tank; the transition tank is connected to the main tank through a second pipeline and a third pipeline respectively; one end of the second pipeline is connected to the gravity valve, and the other end is located at the inner bottom of the main tank; one end of the third pipeline is connected to the gravity valve, and the other end is located at the inner top of the main tank; when the aircraft is in a positive overload state, the first pipeline is connected to the second pipeline; when the aircraft is in a negative overload state, the first pipeline is connected to the third pipeline;

[0008] Along the air inlet direction, a pressure reducing valve and a gas circuit three-way valve are sequentially arranged on the gas transmission pipeline; the gas circuit three-way valve has two different conduction states through valve switching, and can connect the main oil tank with the external atmosphere in the first state, and can connect the main oil tank with the external compressed gas pipeline through the gas transmission pipeline in the second state;

[0009] Along the oil supply direction, an oil circuit three-way valve and a fuel pump are arranged on the oil pipeline in sequence; the oil circuit three-way valve has two different conduction states through valve switching, and when in the first state, the inverted flight fuel tank can be connected with the external oil delivery or oil pumping device, and when in the second state, the inverted flight fuel tank can be connected with the external engine through the interconnected oil hose and oil pipeline; the oil hose is located inside the inverted flight fuel tank, one end of which is connected with the oil pipeline, and a weight is fixed on the other end; the weight can drive the end of the oil hose to move freely in the inverted flight fuel tank as the overload changes, so that the engine can continue to obtain fuel from the inverted flight fuel tank whether the aircraft is in the forward or inverted flight state.

[0010] Preferably, a plurality of anti-surge baffles are provided in the main oil tank.

[0011] Preferably, an air line pressure sensor is provided on the air delivery pipeline between the pressure reducing valve and the main fuel tank; and an oil line pressure sensor is provided on the oil delivery pipeline between the fuel pump and the engine.

[0012] Preferably, the engine includes but is not limited to a turbofan engine, a turbojet engine, a turboprop engine or a piston engine.

[0013] Preferably, the compressed gas introduced into the compressed gas pipeline is engine bleed air or compressed gas carried by the aircraft.

[0014] Preferably, an anti-bubble oil filtering device is provided at one end of the second pipeline where a weight is provided.

[0015] Preferably, the main fuel tank, inverted flight fuel tank and transition fuel tank are all made of materials that are both hard and lightweight.

[0016] Preferably, a gas filter is provided at the air inlet end of the gas pipeline, and an oil filter is provided at the connecting end of the oil pipeline and the engine.

[0017] Preferably, a cover for maintaining the oil tank and pipelines is provided at the bottom of the transition oil tank.

[0018] The second object of the present invention is to provide a method for supplying fuel to an aircraft according to any of the above-mentioned fuel tank devices, which is specifically as follows:

[0019] When refueling the fuel tank device, the fuel tank device is in a horizontal state, and the weight is located at the lower part of the inverted flight fuel tank; the gas circuit three-way valve and the oil circuit three-way valve are both in the first state, the main fuel tank is connected to the external atmosphere, and the inverted flight fuel tank is connected to the external refueling device; the fuel is gradually injected into the inverted flight fuel tank from the refueling device through the oil pipeline, and then the fuel is gradually injected into the transition tank through the first pipeline, and finally the fuel is gradually injected into the main fuel tank through the second pipeline; when the fuel enters the gas pipeline and the fuel is visible in the pipeline connected to the external atmosphere by the gas circuit three-way valve, the main fuel tank, the inverted flight fuel tank and the transition tank are all in a full state, and the refueling process is completed;

[0020] When oil is pumped out from the oil tank device, the oil tank device is in a horizontal state, and the weight is located at the lower part of the inverted flight oil tank; the three-way valve of the air circuit and the three-way valve of the oil circuit are both in the first state, the main oil tank is connected to the external atmosphere, and the inverted flight oil tank is connected to the external oil pumping device; the remaining fuel in the inverted flight oil tank is pumped out, and the liquid level in the inverted flight oil tank drops. Under the action of negative pressure, the fuel in the main oil tank enters the transition oil tank through the second pipeline, and then enters the inverted flight oil tank through the first pipeline; under the action of the oil pumping device, the fuel in the inverted flight oil tank is continuously pumped out until the fuel in the main oil tank, the inverted flight oil tank and the transition oil tank are all emptied, and the oil pumping process is completed;

[0021] When the aircraft is in upright flight, the fuel tank device is in a horizontal state, the weight is located at the lower part of the inverted flight fuel tank, and the three-way valve of the gas circuit and the three-way valve of the oil circuit are both in the second state; the main fuel tank is connected with the external compressed gas pipeline through the gas pipeline, and the compressed gas enters the main fuel tank at a constant pressure after passing through the pressure reducing valve to maintain the pressure in the main fuel tank stable; the first pipeline and the second pipeline are connected; under the action of pressure, the fuel in the main fuel tank enters the transition tank through the second pipeline, and then enters the inverted flight fuel tank through the first pipeline; the inverted flight fuel tank is connected with the external engine through the interconnected oil delivery hose and oil delivery pipeline to continuously supply fuel to the engine;

[0022] When the aircraft is in an inverted flight state, the fuel tank device is in an inverted state, the weight is located at the upper part of the inverted flight fuel tank, and the three-way valve of the air circuit and the three-way valve of the oil circuit are both in the second state; the main fuel tank is connected with the external compressed gas pipeline through the air pipeline, and the compressed gas enters the main fuel tank at a constant pressure after passing through the pressure reducing valve to maintain the pressure in the main fuel tank stable; the first pipeline and the third pipeline are connected; under the action of pressure, the fuel in the main fuel tank enters the transition tank through the third pipeline, and then enters the inverted flight fuel tank through the first pipeline; the inverted flight fuel tank is connected to the external engine through the interconnected oil hose and oil pipeline to continuously supply fuel to the engine.

[0023] Compared with the prior art, the present invention has the following beneficial effects:

[0024] 1) The present invention designs the main fuel tank, the inverted flight fuel tank and the transition fuel tank as an integrated whole, and the manufacture and assembly are relatively simple.

[0025] 2) The present invention adopts an integrated oil pumping / suction design, that is, an external oil delivery or oil pumping device is connected to the oil pipeline through the setting of a three-way valve, which can simultaneously realize the setting of adding oil to or sucking oil from the oil tank; and there is only one air vent on the air pipeline that is connected to the external atmosphere through the setting of a three-way valve; the present invention is conducive to solving the sealing problem of the oil tank and reducing the sealing cost by only providing one air vent and one oil delivery port.

[0026] 3) The bottom of the transition oil tank of the present invention is provided with a cover, which provides great convenience for the installation of pipelines and gravity valves, and the sealing detection and maintenance of the main oil tank and the inverted flight oil tank.

[0027] 4) The anti-surge baffle provided in the main fuel tank of the present invention can reduce the sloshing of the fuel tank liquid level caused by the change of the aircraft's attitude, and also reduce the influence of the fuel on the center of gravity of the entire aircraft.

[0028] 5) A heavy hammer is provided at the end of the oil delivery hose in the inverted flight oil tank of the present invention, which can meet the oil extraction requirements of the aircraft engine under various postures and various overloads. BRIEF DESCRIPTION OF THE DRAWINGS

[0029] Figure 1 It is a structural schematic diagram of the device of the present invention;

[0030] The reference numerals in the figure are: 1 main fuel tank, 2 inverted flight fuel tank, 3 transition fuel tank, 4 pressure reducing valve, 5 gas pipeline, 6 gas circuit pressure sensor, 7 gas circuit three-way valve, 8 oil circuit three-way valve, 9 gravity valve, 10 weight, 11 first pipeline, 12 second pipeline, 13 third pipeline, 14 anti-surge baffle, 15 oil filter, 16 fuel pump, 17 oil circuit pressure sensor, 18 oil pipeline, 19 gas filter. DETAILED DESCRIPTION

[0031] The present invention is further described and illustrated below in conjunction with the accompanying drawings and specific embodiments. The technical features of each embodiment of the present invention can be combined accordingly without conflicting with each other.

[0032] like Figure 1 As shown, the present invention provides a fuel tank device for pressurized inverted flight of an aircraft, the fuel tank device comprising a main fuel tank 1, an inverted flight fuel tank 2 for fuel supply, a transition fuel tank 3 for connecting the main fuel tank 1 and the inverted flight fuel tank 2, an air pipeline 5 and an oil pipeline 18.

[0033] The main fuel tank 1 is used to contain fuel, and a transition fuel tank 3 is provided inside the main fuel tank 1, and a gravity valve 9 is provided inside the transition fuel tank 3. The transition fuel tank 3 is connected to the inverted flight fuel tank 2 through a first pipeline 11, one end of the first pipeline 11 is connected to the gravity valve 9, and the other end of the first pipeline 11 is located at the inner top of the inverted flight fuel tank 2. The transition fuel tank 3 is connected to the main fuel tank 1 through a second pipeline 12, one end of the second pipeline 12 is connected to the gravity valve 9, and the other end of the second pipeline 12 is located at the inner bottom of the main fuel tank 1. The transition fuel tank 3 can also be connected to the main fuel tank 1 through a third pipeline 13, one end of the third pipeline 13 is connected to the gravity valve 9, and the other end of the third pipeline 13 is located at the inner top of the main fuel tank 1.

[0034] When the aircraft is in a positive overload state (i.e., overload downward), the main fuel tank 1 is connected to the inverted flight fuel tank 2 through the connection between the first pipeline 11 and the second pipeline 12. When the aircraft is in a negative overload state (i.e., overload upward), the main fuel tank 1 is connected to the inverted flight fuel tank 2 through the connection between the first pipeline 11 and the third pipeline 13, thereby ensuring that the aircraft can effectively take fuel in both the forward and inverted flight states.

[0035] In this embodiment, a plurality of anti-surge baffles 14 are also provided in the main fuel tank 1, which can effectively reduce the sloshing of the liquid level in the main fuel tank 1 caused by the change of the attitude of the aircraft, and also reduce the influence of the change of the center of gravity of the fuel in the main fuel tank 1 on the center of gravity of the entire aircraft. The main fuel tank 1, the inverted flight fuel tank 2 and the transition fuel tank 3 can all be made of materials with both hard and light properties, and can be set as a hard shell structure. The selected material can be a light metal or a composite material, and the material also needs to have a certain strength so as to effectively resist the pressure increase inside the fuel tank.

[0036] Along the air inlet direction, the air delivery pipeline 5 is provided with a pressure reducing valve 4 and an air circuit three-way valve 7 in sequence. The air circuit three-way valve 7 has two different conduction states through valve switching. When in the first state, the main fuel tank 1 can be connected to the external atmosphere. When in the second state, the main fuel tank 1 can be connected to the external compressed gas pipeline through the air delivery pipeline 5. The compressed gas introduced into the compressed gas pipeline can be the engine bleed air or the compressed gas carried by the aircraft.

[0037] In this embodiment, a gas line pressure sensor 6 is also provided on the gas pipeline 5 between the pressure reducing valve 4 and the main fuel tank 1, so as to monitor the gas pressure after the pressure reducing valve 4 is applied in real time, and ensure the stability and safety of the internal pressure of the fuel tank. The pressure reducing valve 4 has the ability to supply constant pressure and stable pressure, and can automatically keep the pressure of the gas entering the main fuel tank 1 stable. A gas filter 19 is provided at the air inlet end of the gas pipeline 5 to ensure that the gas introduced from the compressed gas pipeline does not contain foreign particles, thereby ensuring the stable operation of the aerospace vehicle.

[0038] Along the oil supply direction, the oil pipeline 18 is provided with an oil circuit three-way valve 8 and a fuel pump 16 in sequence. The oil circuit three-way valve 8 has two different conduction states through valve switching. When in the first state, the inverted flight oil tank 2 can be connected to the outside world. When in the second state, the inverted flight oil tank 2 can be connected to the external engine through the oil hose and the oil pipeline 18 that are interconnected. Among them, the oil hose is located inside the inverted flight oil tank 2, one end of the oil hose is connected to the oil pipeline 18, and the end of the other end is fixed with a weight 10. The weight 10 is a component with a large gravity, which can drive the end of the oil hose to move freely in the inverted flight oil tank 2 with the change of overload, so that one end of the oil pipeline 18 equipped with the weight 10 can be immersed below the fuel liquid level in the inverted flight oil tank 2, ensuring that the engine can continue to obtain fuel from the inverted flight oil tank 2 when the aircraft is in the forward or inverted flight state. Since the weight 10 will swing back and forth under the action of gravity, stirring the fuel in the inverted flight tank 2 to form tiny bubbles, in order to prevent the tiny bubbles from entering the oil pipeline 18 through the oil hose, an anti-bubble oil filter device can also be provided on one end of the second pipeline 12 where the weight 10 is provided.

[0039] In this embodiment, an oil line pressure sensor 17 is provided on the oil line 18 between the fuel pump 16 and the engine to monitor the oil line pressure after the fuel pump 16 in real time to prevent damage to the engine. An oil filter 15 is also provided at the connection end between the oil line 18 and the engine to ensure that the fuel entering the engine from the oil line does not contain foreign particles, thereby ensuring the stable operation of the spacecraft. The engine can be set as needed, such as a turbofan engine, a turbojet engine, a turboprop engine or a piston engine, etc.

[0040] In order to facilitate the installation of the various pipelines (the first pipeline 11, the second pipeline 12 and the third pipeline 13) and the gravity valve 9 in the inverted flight oil tank 2, as well as the sealing detection and maintenance of the main oil tank 1, the inverted flight oil tank 2 and the transition oil tank 3, a cover can be opened at the bottom of the transition oil tank 3. The cover can be opened as needed, but can maintain the sealing of the transition oil tank 3 when closed.

[0041] The method for supplying fuel to an aircraft using the above fuel tank device is as follows:

[0042] When refueling is needed in the oil tank device, the oil tank device is in a horizontal state, and the weight 10 is located at the lower part of the inverted flight oil tank 2. The gas circuit three-way valve 7 and the oil circuit three-way valve 8 are both in the first state, that is, the main oil tank 1 is connected to the external atmosphere, and the inverted flight oil tank 2 is connected to the external refueling device. The refueling device can be an oil tank or an oil barrel.

[0043] The fuel is gradually injected from the refueling device into the inverted flight tank 2 through the oil delivery pipeline 18, and then the fuel in the inverted flight tank 2 is gradually injected into the transition tank 3 through the first pipeline 11, and finally the fuel in the transition tank 3 is gradually injected into the main tank 1 through the second pipeline 12. When the fuel enters the gas delivery pipeline 5, and the fuel can be seen in the pipeline connected to the external atmosphere by the gas circuit three-way valve 7, it means that the main tank 1, the inverted flight tank 2 and the transition tank 3 are all filled with fuel, and the refueling process is completed.

[0044] When it is necessary to pump oil from the oil tank device, the oil tank device is in a horizontal state at this time, and the weight 10 is located at the lower part of the inverted flight oil tank 2. The gas circuit three-way valve 7 and the oil circuit three-way valve 8 are both in the first state, that is, the main oil tank 1 is connected to the external atmosphere, and the inverted flight oil tank 2 is connected to the external pumping device. The remaining fuel in the inverted flight oil tank 2 is pumped out, and the liquid level in the inverted flight oil tank 2 drops. At the same time, under the negative pressure of the pumping device, the fuel in the main oil tank 1 enters the transition oil tank 3 through the second pipeline 12, and then the fuel in the transition oil tank 3 enters the inverted flight oil tank 2 through the first pipeline 11. Under the action of the pumping device, the fuel in the inverted flight oil tank 2 is continuously pumped out until the fuel in the main oil tank 1, the inverted flight oil tank 2 and the transition oil tank 3 is emptied, indicating that the pumping process is over.

[0045] When the aircraft is in the upright flight state, the fuel tank device is also in a horizontal state, the weight 10 is located at the lower part of the inverted flight fuel tank 2, and the gas circuit three-way valve 7 and the oil circuit three-way valve 8 are both in the second state, that is, the main fuel tank 1 is connected to the external compressed gas pipeline through the gas pipeline 5, and the inverted flight fuel tank 2 is connected to the external engine through the interconnected oil delivery hose and the oil delivery pipeline 18. The main fuel tank 1 is connected to the external compressed gas pipeline through the gas delivery pipeline 5, and the compressed gas enters the main fuel tank 1 at a constant pressure after the pressure reducing valve 4 acts to maintain the pressure in the main fuel tank 1 stable. The first pipeline 11 and the second pipeline 12 are connected. Under the pressure of the compressed gas, the fuel in the main fuel tank 1 enters the transition tank 3 through the second pipeline 12, and then enters the inverted flight fuel tank 2 through the first pipeline 11. The inverted flight fuel tank 2 is connected to the external engine through the interconnected oil delivery hose and the oil delivery pipeline 18, so as to realize continuous fuel supply to the engine.

[0046] When the aircraft is in an inverted flight state, the fuel tank device is in an inverted state, the weight 10 is located at the upper part of the inverted flight fuel tank 2, and the gas circuit three-way valve 7 and the oil circuit three-way valve 8 are both in the second state, that is, the main fuel tank 1 is connected to the external compressed gas pipeline through the gas pipeline 5, and the inverted flight fuel tank 2 is connected to the external engine through the interconnected oil delivery hose and the oil delivery pipeline 18. The main fuel tank 1 is connected to the external compressed gas pipeline through the gas delivery pipeline 5, and the compressed gas enters the main fuel tank 1 at a constant pressure after the pressure reducing valve 4 acts to maintain the pressure in the main fuel tank 1 stable. The first pipeline 11 and the third pipeline 13 are connected. Under the pressure of the compressed gas, the fuel in the main fuel tank 1 enters the transition tank 3 through the third pipeline 13, and then enters the inverted flight fuel tank 2 through the first pipeline 11. The inverted flight fuel tank 2 is connected to the external engine through the interconnected oil delivery hose and the oil delivery pipeline 18, so as to realize continuous fuel supply to the engine.

[0047] The above-described embodiment is only a preferred solution of the present invention, but it is not intended to limit the present invention. A person skilled in the relevant technical field may make various changes and modifications without departing from the spirit and scope of the present invention. Therefore, any technical solution obtained by equivalent replacement or equivalent transformation falls within the protection scope of the present invention.

Claims

1. A fuel tank device for pressurized inverted flight of an aircraft, characterized in that: It comprises a main fuel tank (1), an inverted flight fuel tank (2), a transition fuel tank (3), an air transmission pipeline (5) and an oil transmission pipeline (18); A transition tank (3) is provided in the main tank (1), and a gravity valve (9) is provided in the transition tank (3); the transition tank (3) is connected to the inverted flight tank (2) via a first pipeline (11); one end of the first pipeline (11) is connected to the gravity valve (9), and the other end is located at the inner top of the inverted flight tank (2); the transition tank (3) is connected to the main tank (1) via a second pipeline (12) and a third pipeline (13); one end of the second pipeline (12) is connected to the gravity valve (9), and the other end is located at the inner bottom of the main tank (1); one end of the third pipeline (13) is connected to the gravity valve (9), and the other end is located at the inner top of the main tank (1); when the aircraft is in a positive overload state, the first pipeline (11) and the second pipeline (12) are connected; when the aircraft is in a negative overload state, the first pipeline (11) and the third pipeline (13) are connected; Along the air inlet direction, a pressure reducing valve (4) and a gas circuit three-way valve (7) are sequentially provided on the gas transmission pipeline (5); the gas circuit three-way valve (7) has two different conduction states through valve switching, and when in the first state, the main oil tank (1) can be connected to the external atmosphere, and when in the second state, the main oil tank (1) can be connected to an external compressed gas pipeline through the gas transmission pipeline (5); Along the oil supply direction, an oil circuit three-way valve (8) and a fuel pump (16) are sequentially arranged on the oil delivery pipeline (18); the oil circuit three-way valve (8) has two different conduction states through valve switching, and when in the first state, the inverted flight oil tank (2) can be connected to an external oil delivery or oil pumping device, and when in the second state, the inverted flight oil tank (2) can be connected to an external engine through an oil delivery hose and an oil delivery pipeline (18) that are interconnected; the oil delivery hose is located inside the inverted flight oil tank (2), one end of which is connected to the oil delivery pipeline (18), and a weight (10) is fixed to the other end; the weight (10) can drive the end of the oil delivery hose to move freely in the inverted flight oil tank (2) as the overload changes, so that the engine can continuously obtain fuel from the inverted flight oil tank (2) when the aircraft is in the forward or inverted flight state.

2. The fuel tank device according to claim 1, characterized in that: A plurality of surge protection baffles (14) are provided in the main oil tank (1).

3. The fuel tank device according to claim 1, characterized in that: An air line pressure sensor (6) is provided on the air delivery pipeline (5) between the pressure reducing valve (4) and the main fuel tank (1); and an oil line pressure sensor (17) is provided on the oil delivery pipeline (18) between the fuel pump (16) and the engine.

4. The fuel tank device according to claim 1, characterized in that: The engine includes a turbofan engine, a turbojet engine, a turboprop engine or a piston engine.

5. The fuel tank device according to claim 1, characterized in that: The compressed gas introduced into the compressed gas pipeline is engine bleed air or compressed gas carried by the aircraft.

6. The fuel tank device according to claim 1, characterized in that: An anti-bubble oil filtering device is also provided at one end of the second pipeline (12) where the weight (10) is provided.

7. The fuel tank device according to claim 1, characterized in that: The main fuel tank (1), the inverted flight fuel tank (2) and the transition fuel tank (3) are all made of a material that is both hard and light.

8. The fuel tank device according to claim 1, characterized in that: The air inlet end of the air delivery pipeline (5) is provided with a gas filter (19), and the connection end of the oil delivery pipeline (18) and the engine is provided with an oil filter (15).

9. The fuel tank device according to claim 1, characterized in that: The bottom of the transition oil tank (3) is provided with a cover for maintaining the oil tank and pipelines.

10. A method for supplying fuel to an aircraft according to any one of claims 1 to 9, characterized in that: The details are as follows: When refueling the fuel tank device, the fuel tank device is in a horizontal state, and the weight (10) is located at the lower part of the inverted flight fuel tank (2); the gas circuit three-way valve (7) and the oil circuit three-way valve (8) are both in a first state, the main fuel tank (1) is connected to the external atmosphere, and the inverted flight fuel tank (2) is connected to the external refueling device; the fuel is gradually injected from the refueling device into the inverted flight fuel tank (2) through the oil delivery pipeline (18), and then the fuel is gradually injected into the transition fuel tank (3) through the first pipeline (11), and finally the fuel is gradually injected into the main fuel tank (1) through the second pipeline (12); when the fuel enters the gas delivery pipeline (5) and the fuel is visible in the pipeline connected to the external atmosphere by the gas circuit three-way valve (7), the main fuel tank (1), the inverted flight fuel tank (2) and the transition fuel tank (3) are all in a full state, and the refueling process is completed; When pumping oil from the oil tank device, the oil tank device is in a horizontal state, and the weight (10) is located at the lower part of the inverted flight oil tank (2); the gas circuit three-way valve (7) and the oil circuit three-way valve (8) are both in a first state, the main oil tank (1) is connected to the external atmosphere, and the inverted flight oil tank (2) is connected to the external oil pumping device; the remaining fuel in the inverted flight oil tank (2) is pumped out, and the liquid level in the inverted flight oil tank (2) drops. Under the action of negative pressure, the fuel in the main oil tank (1) enters the transition oil tank (3) through the second pipeline (12), and then enters the inverted flight oil tank (2) through the first pipeline (11); under the action of the oil pumping device, the fuel in the inverted flight oil tank (2) is continuously pumped out until the fuel in the main oil tank (1), the inverted flight oil tank (2) and the transition oil tank (3) is emptied, and the oil pumping process is completed; When the aircraft is in the upright flight state, the fuel tank device is in a horizontal state, the weight (10) is located at the lower part of the inverted flight fuel tank (2), and the gas circuit three-way valve (7) and the oil circuit three-way valve (8) are both in the second state; the main fuel tank (1) is connected to an external compressed gas pipeline through an air pipeline (5), and the compressed gas enters the main fuel tank (1) at a constant pressure after passing through a pressure reducing valve (4) to maintain the pressure in the main fuel tank (1) stable; the first pipeline (11) and the second pipeline (12) are connected; under the action of pressure, the fuel in the main fuel tank (1) enters the transition fuel tank (3) through the second pipeline (12), and then enters the inverted flight fuel tank (2) through the first pipeline (11); the inverted flight fuel tank (2) is connected to an external engine through an oil delivery hose and an oil delivery pipeline (18) that are interconnected, so as to continuously supply fuel to the engine; When the aircraft is in an inverted flight state, the fuel tank device is in an inverted state, the weight (10) is located at the upper part of the inverted flight fuel tank (2), and the gas circuit three-way valve (7) and the oil circuit three-way valve (8) are both in a second state; the main fuel tank (1) is connected to an external compressed gas pipeline through an air delivery pipeline (5), and the compressed gas enters the main fuel tank (1) at a constant pressure after passing through a pressure reducing valve (4) to maintain the pressure in the main fuel tank (1) stable; the first pipeline (11) and the third pipeline (13) are connected; under the action of pressure, the fuel in the main fuel tank (1) enters the transition fuel tank (3) through the third pipeline (13), and then enters the inverted flight fuel tank (2) through the first pipeline (11); the inverted flight fuel tank (2) is connected to an external engine through an oil delivery hose and an oil delivery pipeline (18) that are interconnected, so as to continuously supply fuel to the engine.

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