An anti-tear flexible fuel tank for aircraft

Abstract

The present invention discloses a tear-resistant flexible fuel tank for an aircraft, which relates to the technical field of aircraft fuel tanks. The tear-resistant flexible fuel tank for an aircraft includes a fuel tank body. A fuel filling port is fixedly connected to the top of the fuel tank body. A fuel supply pump is fixedly connected to the bottom inside the fuel tank body. A fuel delivery pipe is fixedly connected to the bottom of the fuel supply pump. A lifting mechanism is fixedly connected inside the fuel tank body. A fuel supply guarantee mechanism is movably connected inside the fuel tank body. A fixing structure is fixedly connected to the bottom of the fuel tank body. In the tear-resistant flexible fuel tank for an aircraft, when the aircraft is inverted during flight, the fuel is located at the top of the movable diaphragm and part of the air is located at the bottom of the movable diaphragm. At this time, the fuel will have a downward movement force under the action of gravity. The air inside the fuel tank body is compressed through the movable diaphragm, and the internal air cannot be discharged from the fuel filling port. The movable diaphragm is supported by air pressure to prevent the fuel from being inverted, thus avoiding the situation where the fuel supply pump cannot pump fuel.

Description

Technical Field

[0001] The present invention relates to the technical field of aircraft fuel tanks, and specifically to a tear-resistant flexible fuel tank for aircraft. Background Art

[0002] The application of flexible fuel tanks in the aviation field is mainly reflected in their flexibility and adaptability. Flexible fuel tanks are usually made of high-strength rubber or composite materials, and can be adjusted according to the shape of the internal space of the aircraft, so as to maximize the use of space. At the same time, the weight of the flexible fuel tank is relatively light, which helps to improve the fuel efficiency and flight performance of the aircraft;

[0003] The patent with the application number CN202022053044.4 discloses a flexible fuel tank for aircraft, which is used to supply fuel to the engine. It includes a flexible fuel tank with upper and lower hollow parts made of elastomeric rubber material. The engine is nested in the hollow cavity of the flexible fuel tank. An oil outlet communicating with the engine fuel inlet is opened on the fuel tank body. At least one U-shaped groove is respectively arranged on the two inner side surfaces of the flexible fuel tank in contact with the engine. Convex platforms are arranged on the opposite sides of the upper surface of the flexible fuel tank, and the convex platforms are communicated with the flexible fuel tank;

[0004] When the aircraft is inverted, the fuel naturally flows to the bottom of the fuel tank due to the action of gravity. At this time, the fuel supply system pumps fuel from the top and transports it to the engine, and cannot effectively pump fuel, resulting in a weakening of the aircraft's power. Summary of the Invention

[0005] Aiming at the deficiencies of the prior art, the present invention provides a tear-resistant flexible fuel tank for aircraft to solve the problems raised in the above background art.

[0006] To achieve the above objectives, the present invention is realized through the following technical solutions: A tear-resistant flexible fuel tank for aircraft, including a fuel tank body, a fuel filling port is fixedly connected to the top of the fuel tank body, a fuel supply pump is fixedly connected to the bottom inside the fuel tank body, a fuel delivery pipe is fixedly connected to the bottom of the fuel supply pump, a lifting mechanism is fixedly connected inside the fuel tank body, a fuel supply guarantee mechanism is movably connected inside the fuel tank body, and a fixing structure is fixedly connected to the bottom of the fuel tank body;

[0007] The lifting mechanism includes:

[0008] An elastic diaphragm, which is fixedly connected inside the fuel tank body;

[0009] A communication pipe, which is fixedly connected to the outer wall of the fuel tank body;

[0010] An air box, which is fixedly connected to the end of the communication pipe far away from the fuel tank body.

[0011] Preferably, two elastic diaphragms are provided, and the two elastic diaphragms are respectively located on the left and right sides of the fuel supply pump. Two connecting pipes are provided, and the connecting pipes are respectively located outside the corresponding elastic diaphragms, and air boxes are fixedly connected to the outer sides of the connecting pipes.

[0012] Preferably, a movable plate is movably connected inside the air box. A first spring is fixedly connected to the outer wall of the movable plate. A support plate is fixedly connected to the outer side of the first spring. The support plate is fixedly connected to the outer side of the air box. A reinforcing plate is fixedly connected to the outer wall of the connecting pipe, and the reinforcing plate is fixedly connected to the outer wall of the fuel tank body.

[0013] Preferably, the fuel supply guarantee mechanism includes a first magnet ring, the first magnet ring is movably connected to the outer wall of the fuel tank body, a second magnet ring is movably connected inside the fuel tank body, the second magnet ring is arranged at a position corresponding to the first magnet ring, and a movable diaphragm is arranged inside the fuel tank body, and the outer wall of the movable diaphragm is fixedly connected to the second magnet ring.

[0014] Preferably, a flow port is fixedly connected inside the movable diaphragm, and a backflow prevention plate is movably connected inside the flow port.

[0015] Preferably, a floating air chamber is fixedly connected to the bottom of the movable diaphragm, and several anti-disturbance plates are fixedly connected to the bottom of the movable diaphragm. The outer walls of the anti-disturbance plates are provided with openings.

[0016] Preferably, a barrier piece is movably connected inside the fuel filling port. A second spring is fixedly connected to the top of the barrier piece. A fixing plate is fixedly connected to the top of the second spring, and the fixing plate is fixedly connected to the inner wall of the fuel filling port.

[0017] Preferably, the fixing structure includes a fixed bottom frame, the fixed bottom frame is arranged at the bottom of the fuel tank body, a support fixing frame is fixedly connected to the top of the fixed bottom frame, and the support fixing frame is fixedly connected to the bottom of the fuel tank body.

[0018] Preferably, first outer plates are fixedly connected to the front and back of the fuel tank body at the top of the fixed bottom frame, and the first outer plates are located outside the outer wall of the first magnet ring. Second outer plates are fixedly connected to the outside of the first magnet ring at the top of the air box.

[0019] Preferably, side limiting plates are fixedly connected to the outside of the two air boxes at the top of the fixed bottom frame, and the side limiting plates are fixedly connected to the outer wall of the support plate.

[0020] The present invention provides a tear-resistant flexible fuel tank for an aircraft. It has the following beneficial effects:

[0021] 1. The anti - tear flexible fuel tank for aircraft. When the aircraft is inverted during flight, the fuel is located at the top of the movable diaphragm, and the air part is located at the bottom of the movable diaphragm. At this time, the fuel has a downward movement force under the action of gravity. Through the movable diaphragm, the air inside the fuel tank body is compressed, and the internal air cannot be discharged from the fuel filling port. The movable diaphragm is supported by air pressure to prevent the fuel from being inverted, avoiding the situation where the fuel supply pump cannot pump fuel, which would lead to a weakening of the aircraft's power.

[0022] 2. The anti - tear flexible fuel tank for aircraft. When the fuel inside the fuel tank body gradually decreases, the pressure on the elastic diaphragm gradually decreases. At this time, the first spring will gradually push the movable plate inward, causing the internal elastic diaphragm to bulge upward. As a result, the fuel will converge at the fuel supply pump, facilitating the fuel supply pump to pump the fuel into the aircraft engine through the fuel delivery pipe. At the same time, placing the fuel supply pump inside the fuel can facilitate the heat dissipation of the fuel supply pump during operation, thereby avoiding a slowdown in the fuel pumping speed that would lead to a weakening of the aircraft's power.

[0023] 3. The anti - tear flexible fuel tank for aircraft. When the aircraft is inverted and accelerates or decelerates, the fuel will slosh back and forth. This will cause the sloshing fuel to push the corresponding elastic diaphragm to contract, thereby reducing the force of fuel sloshing and promoting the stability of the fuel inside the fuel tank body, avoiding interference with the operation of the fuel supply pump by fuel sloshing and interference with the aircraft's power.

[0024] 4. The anti - tear flexible fuel tank for aircraft. When the fuel inside the fuel tank body decreases, the movable diaphragm moves as the fuel volume decreases, ensuring that the fuel always remains in the space formed by the movable diaphragm and the inner bottom of the fuel tank body. This can reduce the space for fuel sloshing. At the same time, the first outer plate and the second outer plate will limit the movement space of the first magnet ring, preventing excessive fuel sloshing that would cause the fuel supply pump to pump in air and affect the aircraft's power.

[0025] 5. The anti - tear flexible fuel tank for aircraft. When the aircraft is inverted, the fuel inside the fuel tank body is located at the top of the movable diaphragm. The fuel will no longer exert pressure on the elastic diaphragm, causing the elastic diaphragm to bulge under the push of the movable plate. When the fuel squeezes the air downward, the elastic diaphragm will cause the fuel to bulge towards the middle part, making it easier for the fuel to come into contact with the fuel supply pump, facilitating the fuel supply pump to supply fuel to the aircraft engine through the fuel delivery pipe. BRIEF DESCRIPTION OF THE DRAWINGS

[0026] Figure 1 is the front - view three - dimensional structure schematic diagram of the present invention;

[0027] Figure 2 is the back - side three - dimensional structure schematic diagram of the present invention;

[0028] Figure 3 is Figure 1 the cross - sectional structure schematic diagram;

[0029] Figure 4 is Figure 3 Schematic diagram of the enlarged structure of part A in

[0030] Figure 5 Schematic diagram of the support and fixing frame structure of the present invention;

[0031] Figure 6 is Figure 5 Schematic diagram of the enlarged structure of part D in

[0032] Figure 7 Top view three - dimensional structure schematic diagram of the present invention;

[0033] Figure 8 is Figure 3 Schematic diagram of the enlarged structure of part B in

[0034] Figure 9 is Figure 3 Schematic diagram of the enlarged structure of part C in

[0035] Figure 10 is Figure 7 Schematic diagram of the enlarged structure of part E in

[0036] Figure 11 Schematic diagram of the movable diaphragm structure of the present invention;

[0037] Figure 12 is Figure 11 Schematic diagram of the sectional structure;

[0038] Figure 13 is Figure 12 Schematic diagram of the enlarged structure of part F in

[0039] Figure 14 Schematic diagram of the sectional structure of the fuel filling port.

[0040] In the figure: 1, fuel tank body; 2, fuel filling port; 3, fuel supply pump; 4, delivery pipe; 5, lifting mechanism; 501, elastic diaphragm; 502, connecting pipe; 503, air box; 504, movable plate; 505, first spring; 506, support plate; 507, reinforcing plate; 6, fuel supply guarantee mechanism; 601, first magnet ring; 602, second magnet ring; 603, movable diaphragm; 604, suspended air chamber; 605, flow port; 606, anti - backflow plate; 607, anti - disturbance plate; 608, barrier sheet; 609, second spring; 610, fixing plate; 7, fixing structure; 701, fixed bottom frame; 702, support and fixing frame; 703, first outer side plate; 704, second outer side plate; 705, side limiting plate. Detailed implementation manners

[0041] Next, the technical solutions in the embodiments of the present invention will be clearly and completely described in conjunction with the accompanying drawings in the embodiments of the present invention. Obviously, the described embodiments are only a part of the embodiments of the present invention, rather than all the embodiments.

[0042] Examples of the embodiments are shown in the accompanying drawings, where the same or similar reference numerals represent the same or similar elements or elements with the same or similar functions throughout. The embodiments described below by referring to the accompanying drawings are exemplary and are intended to explain the present invention, and should not be construed as a limitation to the present invention.

[0043] Example 1: Please refer to Figures 1-6 , the present invention provides a technical solution: a tear-resistant soft fuel tank for an aircraft, including a fuel tank body 1. The fuel tank body 1 adopts a three-layer composite structure process. The upper and lower layers are rubber layers, and the middle layer is made of high-strength fiber cloth, which is bonded by an adhesive to improve the compressive and anti-twisting capabilities of the fuel tank body 1. A fuel filling port 2 is fixedly connected to the top of the fuel tank body 1, a fuel supply pump 3 is fixedly connected to the inner bottom of the fuel tank body 1, a fuel delivery pipe 4 is fixedly connected to the bottom of the fuel supply pump 3, a lifting mechanism 5 is fixedly connected inside the fuel tank body 1, a fuel supply guarantee mechanism 6 is movably connected inside the fuel tank body 1, and a fixing structure 7 is fixedly connected to the bottom of the fuel tank body 1;

[0044] The lifting mechanism 5 includes:

[0045] An elastic diaphragm 501, which is fixedly connected inside the fuel tank body 1;

[0046] A connecting pipe 502, which is fixedly connected to the outer wall of the fuel tank body 1;

[0047] An air box 503, which is fixedly connected to the end of the connecting pipe 502 away from the fuel tank body 1.

[0048] There are two elastic diaphragms 501, and the two elastic diaphragms 501 are respectively located on the left and right sides of the fuel supply pump 3. There are two connecting pipes 502, and the connecting pipes 502 are respectively located outside the corresponding elastic diaphragms 501, and air boxes 503 are fixedly connected to the outside of the connecting pipes 502.

[0049] During use, the fuel tank body 1 is installed inside the aircraft, and the left and right sides of the fuel tank body 1 are located in the forward or backward direction of the aircraft. Fuel is added to the inside of the fuel tank body 1 through the fuel filling port 2. During the fuel filling process, the fuel inside the fuel tank body 1 gradually increases, causing the pressure on the two elastic diaphragms 501 to gradually increase. As a result, the two elastic diaphragms 501 are pressed against the inner wall of the fuel tank body 1, and at the same time, the gas at the bottom of the elastic diaphragms 501 is pressed into the corresponding air boxes 503 through the connecting pipes 502.

[0050] Inside the air box 503, there is a movable plate 504 movably connected. On the outer wall of the movable plate 504, a first spring 505 is fixedly connected. On the outside of the first spring 505, a support plate 506 is fixedly connected. The support plate 506 is fixedly connected to the outside of the air box 503. On the outer wall of the connecting pipe 502, a reinforcing plate 507 is fixedly connected. The reinforcing plate 507 is fixedly connected to the outer wall of the fuel tank body 1. The reinforcing plate 507 can increase the fixed area between the fuel tank body 1 and the connecting pipe 502 to maintain the stability of the fixed connecting pipe 502.

[0051] The gas entering the air box 503 through the connecting pipe 502 will push the movable plate 504 outward and compress the first spring 505 by the movable plate 504, allowing the gas to enter the inside of the air box 503. When the fuel in the fuel tank body 1 is gradually consumed, the pressure on the elastic diaphragm 501 gradually decreases. At this time, the first spring 505 will gradually push the movable plate 504 inward, causing the elastic diaphragm 501 inside to bulge upward. Furthermore, it will cause the fuel to converge at the fuel supply pump 3, facilitating the fuel supply pump 3 to pump the fuel into the aircraft engine through the fuel delivery pipe 4, and at the same time making the fuel supply pump 3 located inside the fuel for the fuel supply pump 3 to work and dissipate heat.

[0052] Embodiment Two: Please refer to Figures 1-14 , on the basis of Embodiment One, the present invention provides a technical solution:

[0053] The fuel supply guarantee mechanism 6 includes a first magnet ring 601 movably connected to the outer wall of the fuel tank body 1. Inside the fuel tank body 1, a second magnet ring 602 is movably connected. The second magnet ring 602 is arranged at a position corresponding to the first magnet ring 601. Inside the fuel tank body 1, a movable diaphragm 603 is arranged, and the outer wall of the movable diaphragm 603 is fixedly connected to the second magnet ring 602.

[0054] The second magnet ring 602 and the first magnet ring 601 attract each other by magnetic force, causing the second magnet ring 602 to closely adhere to the inner wall of the fuel tank body 1, dividing the inside of the fuel tank body 1 into upper and lower parts.

[0055] Inside the movable diaphragm 603, a flow port 605 is fixedly connected. Inside the flow port 605, a backflow prevention plate 606 is movably connected.

[0056] When refueling through the fuel filling port 2, the fuel will fall onto the top of the movable diaphragm 603. The fuel at the top of the flow port 605 will enter the bottom of the movable diaphragm 603 through the flow port 605. When the fuel tank body 1 is inverted, it will cause the backflow prevention plate 606 to fit against the edge of the flow port 605 under the push of the fuel at the top, resulting in the fuel passing through the flow port 605.

[0057] At the bottom of the movable diaphragm 603, a floating air chamber 604 is fixedly connected. At the bottom of the movable diaphragm 603, several anti-disturbance plates 607 are fixedly connected. Openings are provided on the outer walls of the anti-disturbance plates 607.

[0058] When refueling through the fuel filling port 2, the fuel flows through the circulation port 605 and enters the bottom of the movable diaphragm 603, causing the floating air chamber 604 to generate buoyancy. The buoyancy will push the second magnet ring 602 upward through the movable diaphragm 603, and the second magnet ring 602 will drive the outer first magnet ring 601 to move upward through suction. Since the first magnet ring 601 is restricted by the second magnet ring 602 and the outer wall of the fuel tank body 1, the gap between the first magnet ring 601 and the second magnet ring 602 cannot cause the fuel tank body 1 to bend. Instead, only the first magnet ring 601 can move up and down, thereby restricting the movement mode of the second magnet ring 602 inside the fuel tank body 1. Therefore, when the aircraft accelerates or decelerates, the movement of the top liquid level during the sloshing of the fuel inside the fuel tank body 1 will be blocked by the anti-disturbance plate 607, dispersing the sloshing thrust.

[0059] An isolation piece 608 is movably connected inside the fuel filling port 2. The top of the isolation piece 608 is fixedly connected to a second spring 609, and the top of the second spring 609 is fixedly connected to a fixing plate 610, and the fixing plate 610 is fixedly connected to the inner wall of the fuel filling port 2.

[0060] When refueling the fuel tank body 1 through the fuel filling port 2, during refueling, the external fuel is used to push the isolation piece 608, stretching the second spring 609 by the isolation piece 608 to allow the fuel to enter the fuel tank body 1. When the fuel is consumed, the air pressure at the top of the fuel inside the fuel tank body 1 decreases, and the external air pressure presses open the isolation piece 608 to enter the fuel tank body 1. When the aircraft is inverted during flight, the fuel will be located at the top of the movable diaphragm 603, and part of the air will be located at the bottom of the movable diaphragm 603. At this time, the fuel will have a downward movement force under the action of gravity, and the air inside the fuel tank body 1 will be compressed through the movable diaphragm 603. The movable diaphragm 603 is supported by air pressure to prevent the fuel from being inverted, making it impossible for the fuel supply pump 3 to extract fuel.

[0061] At the same time, when the aircraft is inverted, the fuel inside the fuel tank body 1 is located at the top of the movable diaphragm 603, and the fuel will no longer exert pressure on the elastic diaphragm 501. Instead, the elastic diaphragm 501 will bulge under the push of the movable plate 504. Therefore, while the fuel squeezes the air downward, the elastic diaphragm 501 will cause the fuel to bulge towards the middle part, making it easier for the fuel to contact the fuel supply pump 3, facilitating the fuel supply pump 3 to supply fuel to the aircraft engine through the fuel delivery pipe 4.

[0062] When the aircraft is inverted and accelerating or decelerating, the fuel will slosh back and forth, and the sloshing fuel will push the corresponding elastic diaphragm 501 to contract, thereby reducing the force of fuel sloshing and promoting the stability of the fuel inside the fuel tank body 1.

[0063] Embodiment Three: Please refer to Figures 1-14, on the basis of the first and second embodiments, the present invention provides a technical solution:

[0064] The fixing structure 7 includes a fixing chassis 701, the fixing chassis 701 is arranged at the bottom of the fuel tank body 1, a supporting and fixing frame 702 is fixedly connected to the top of the fixing chassis 701, and the supporting and fixing frame 702 is fixedly connected to the bottom of the fuel tank body 1.

[0065] By fixing the fixing chassis 701 inside the aircraft, the fixing chassis 701 makes the fuel tank body 1 fixed inside the aircraft through the supporting and fixing frame 702.

[0066] On the top of the fixing chassis 701, first outer plates 703 are fixedly connected to both the front and the back of the fuel tank body 1, and the first outer plates 703 are located on the outer wall of the first magnet ring 601. On the top of the air box 503 and on the outside of the first magnet ring 601, second outer plates 704 are fixedly connected.

[0067] On the top of the fixing chassis 701 and on the outside of the two air boxes 503, side limiting plates 705 are fixedly connected, and the side limiting plates 705 are fixedly connected to the outer wall of the support plate 506.

[0068] When the fuel inside the fuel tank body 1 decreases, the movable diaphragm 603 will move along with the decrease of the fuel volume, and the first magnet ring 601 on the outside will move along with the movement of the movable diaphragm 603 under the attraction of the second magnet ring 602, so that the fuel is always located in the space formed by the movable diaphragm 603 and the inner bottom of the fuel tank body 1. Furthermore, the space for fuel sloshing can be reduced. When the fuel inside the fuel tank body 1 is sloshed, the first outer plate 703 and the second outer plate 704 will be pushed by the first magnet ring 601. Since the first outer plate 703 and the second outer plate 704 will limit the moving space of the first magnet ring 601, it can prevent the fuel from sloshing excessively and causing air to be pumped into the fuel pump 3.

[0069] The above is only the preferred specific embodiment of the present invention, but the protection scope of the present invention is not limited thereto. Any person skilled in the art within the technical scope disclosed by the present invention, according to the technical solution of the present invention and its inventive concept, makes equivalent substitutions or changes, and all should be covered within the protection scope of the present invention.

Claims

1. A tear-resistant soft fuel tank for an aircraft, comprising a fuel tank body (1), characterized in that: The top of the oil tank body (1) is fixedly connected to a refueling port (2); the bottom of the oil tank body (1) is fixedly connected to a fuel supply pump (3); the bottom of the oil supply pump (3) is fixedly connected to a fuel delivery pipe (4); the inside of the oil tank body (1) is fixedly connected to a lifting mechanism (5); the inside of the oil tank body (1) is movably connected to a fuel supply guarantee mechanism (6); and the bottom of the oil tank body (1) is fixedly connected to a fixed structure (7); The lifting mechanism (5) comprises: An elastic diaphragm (501), wherein the elastic diaphragm (501) is fixedly connected inside the oil tank body (1); A connecting pipe (502), wherein the connecting pipe (502) is fixedly connected to the outer wall of the oil tank body (1); An air box (503), wherein the air box (503) is fixedly connected to an end of the connecting pipe (502) away from the oil tank body (1); The air box (503) is movably connected to a movable plate (504) inside, the outer wall of the movable plate (504) is fixedly connected to a first spring (505), and the outer side of the first spring (505) is fixedly connected to a support plate (506); A movable diaphragm (603) is arranged inside the oil tank body (1); Two elastic diaphragms (501) are provided, and the two elastic diaphragms (501) are respectively located on the left and right sides of the oil supply pump (3); two connecting pipes (502) are provided, and the connecting pipes (502) are respectively located on the outside of the corresponding elastic diaphragms (501), and the outsides of the connecting pipes (502) are fixedly connected to the air boxes (503); The support plate (506) is fixedly connected to the outside of the air box (503); the outer wall of the connecting pipe (502) is fixedly connected to a reinforcing plate (507); and the reinforcing plate (507) is fixedly connected to the outer wall of the oil tank body (1); The oil supply guarantee mechanism (6) comprises a first magnet ring (601), the first magnet ring (601) being movably connected to the outer wall of the oil tank body (1), a second magnet ring (602) being movably connected inside the oil tank body (1), the second magnet ring (602) being arranged at a position corresponding to the first magnet ring (601), and an outer wall of a movable diaphragm (603) being fixedly connected to the second magnet ring (602).

2. The tear-resistant soft fuel tank for aircraft according to claim 1, characterized in that: The movable diaphragm (603) is fixedly connected to a flow port (605) inside, and the flow port (605) is movably connected to an anti-backflow plate (606) inside.

3. The tear-resistant soft fuel tank for aircraft according to claim 1, characterized in that: The bottom of the movable diaphragm (603) is fixedly connected to a suspension gas chamber (604), and the bottom of the movable diaphragm (603) is fixedly connected to a plurality of anti-disturbance plates (607), and the outer walls of the anti-disturbance plates (607) are provided with openings.

4. The tear-resistant soft fuel tank for aircraft according to claim 1, characterized in that: A barrier sheet (608) is movably connected inside the refueling port (2), a second spring (609) is fixedly connected to the top of the barrier sheet (608), a fixing plate (610) is fixedly connected to the top of the second spring (609), and the fixing plate (610) is fixedly connected to the inner wall of the refueling port (2).

5. The tear-resistant soft fuel tank for aircraft according to claim 1, characterized in that: The fixed structure (7) comprises a fixed base frame (701), the fixed base frame (701) being arranged at the bottom of the oil tank body (1), the top of the fixed base frame (701) being fixedly connected to a supporting fixed frame (702), and the supporting fixed frame (702) being fixedly connected to the bottom of the oil tank body (1).

6. The tear-resistant soft fuel tank for aircraft according to claim 5, characterized in that: The top of the fixed base frame (701) is located on the front and back sides of the oil tank body (1) and is fixedly connected to a first outer plate (703), and the first outer plate (703) is located on the outer wall of the first magnet ring (601), and the top of the air box (503) is located on the outside of the first magnet ring (601) and is fixedly connected to a second outer plate (704).

7. The tear-resistant soft fuel tank for aircraft according to claim 5, characterized in that: The top of the fixed base frame (701) is located outside the two air boxes (503) and is fixedly connected to a side limiting plate (705), and the side limiting plate (705) is fixedly connected to the outer wall of the support plate (506).

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