Tear-resistant soft oil tank for airplane

Abstract

The invention discloses a tear-resistant soft oil tank for an airplane, and relates to the technical field of airplane oil tanks. The tear-resistant soft oil tank for the airplane comprises an oil tank body, an oil filling port is fixedly connected to the top of the oil tank body, an oil supply pump is fixedly connected to the bottom in the oil tank body, an oil supply pipe is fixedly connected to the bottom of the oil supply pump, a lifting mechanism is fixedly connected to the interior of the oil tank body, and an oil supply guarantee mechanism is movably connected to the interior of the oil tank body. The bottom of the oil tank body is fixedly connected with a fixing structure. According to the tear-resistant soft oil tank for the airplane, the airplane is inverted in the flying process, fuel oil is located at the top of the movable diaphragm, an air part is located at the bottom of the movable diaphragm, at the moment, the fuel oil has downward movement force under the action of gravity, air in the oil tank body is compressed through the movable diaphragm, and the internal air cannot be discharged from the oil filling port; the movable diaphragm is supported through air pressure to prevent fuel from being inverted, and the situation that the fuel supply pump cannot extract the fuel is avoided.

Description

Technical Field

[0001] The invention relates to the technical field of aircraft fuel tanks, in particular to a tear-resistant soft fuel tank for aircraft. Background Art

[0002] The application of soft fuel tanks in the aviation field is mainly reflected in their flexibility and adaptability. Soft fuel tanks are usually made of high-strength rubber or composite materials and can be adjusted according to the shape of the aircraft's internal space to maximize the use of space. At the same time, soft fuel tanks are relatively light in weight, which helps to improve the aircraft's fuel efficiency and flight performance. Patent application number CN202022053044.4 discloses a soft fuel tank for aircraft, which is used to supply fuel to an engine, and includes a soft fuel tank made of an elastomeric rubber material and hollowed out at the top and bottom. The engine is nested in the hollow cavity of the soft fuel tank, and an oil outlet connected to the oil inlet of the engine is provided on the tank body. The soft fuel tank is provided with at least one U-shaped groove on two opposite inner sides in contact with the engine, and bosses are provided on opposite sides of the upper surface of the soft fuel tank, and the bosses are connected to the soft fuel tank; When the aircraft is inverted, the fuel naturally flows to the bottom of the fuel tank due to gravity. At this time, the fuel supply system draws fuel from the top and delivers it to the engine. The fuel cannot be extracted effectively, causing the aircraft's power to weaken. Summary of the invention

[0003] In view of the deficiencies of the prior art, the present invention provides a tear-resistant soft fuel tank for an aircraft to solve the problems raised in the above background technology.

[0004] To achieve the above objectives, the present invention is implemented through the following technical solutions: an anti-tear soft fuel tank for an aircraft, comprising a fuel tank body, a fuel filling port fixedly connected to the top of the fuel tank body, a fuel supply pump fixedly connected to the bottom of the fuel tank body, a fuel delivery pipe fixedly connected to the bottom of the fuel supply pump, a lifting mechanism fixedly connected to the inside of the fuel tank body, a fuel supply guarantee mechanism movably connected to the inside of the fuel tank body, and a fixed structure fixedly connected to the bottom of the fuel tank body; The institutions that promote positions include: An elastic diaphragm, wherein the elastic diaphragm is fixedly connected to the inside of the oil tank body; A connecting pipe, the connecting pipe is fixedly connected to the outer wall of the oil tank body; The air box is fixedly connected to one end of the connecting pipe away from the oil tank body.

[0005] Preferably, two elastic diaphragms are provided, and the two elastic diaphragms are respectively located on the left and right sides of the oil supply pump, and two connecting pipes are provided, and the connecting pipes are respectively located on the outsides of the corresponding elastic diaphragms, and the outsides of the connecting pipes are fixedly connected with air boxes.

[0006] Preferably, the air box is movably connected to a movable plate inside, the outer wall of the movable plate is fixedly connected to a first spring, the outer side of the first spring is fixedly connected to a support plate, the support plate is fixedly connected to the outside of the air box, the outer wall of the connecting pipe is fixedly connected to a reinforcing plate, and the reinforcing plate is fixedly connected to the outer wall of the oil tank body.

[0007] Preferably, the oil supply guarantee mechanism includes a first magnet ring, which is movably connected to the outer wall of the oil tank body, and a second magnet ring is movably connected inside the oil tank body, and the second magnet ring is arranged at a position corresponding to the first magnet ring. A movable diaphragm is arranged inside the oil tank body, and the outer wall of the movable diaphragm is fixedly connected to the second magnet ring.

[0008] Preferably, a flow port is fixedly connected inside the movable diaphragm, and an anti-backflow plate is movably connected inside the flow port.

[0009] Preferably, a suspension gas chamber is fixedly connected to the bottom of the movable diaphragm, and a plurality of anti-disturbance plates are fixedly connected to the bottom of the movable diaphragm, and the outer walls of the anti-disturbance plates are provided with openings.

[0010] Preferably, a barrier plate is movably connected inside the fuel filler port, a second spring is fixedly connected to the top of the barrier plate, 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 filler port.

[0011] Preferably, the fixing structure comprises a fixed base frame, the fixed base frame is arranged at the bottom of the oil tank body, the top of the fixed base frame is fixedly connected to a supporting fixing frame, and the supporting fixing frame is fixedly connected to the bottom of the oil tank body.

[0012] Preferably, the top of the fixed base frame is located on the front and back sides of the oil tank body and is fixedly connected to a first outer plate, and the first outer plate is located on the outer wall of the first magnet ring, and the top of the air box is located on the outside of the first magnet ring and is fixedly connected to a second outer plate.

[0013] Preferably, the top of the fixed base frame is fixedly connected to the outsides of the two air boxes with side limiting plates, and the side limiting plates are fixedly connected to the outer walls of the support plates.

[0014] The present invention provides a tear-resistant soft fuel tank for aircraft, which has the following beneficial effects: 1. The aircraft uses a tear-resistant soft fuel tank. The aircraft is inverted during flight, so that the fuel is located on the top of the movable diaphragm and the air part is located at the bottom of the movable diaphragm. At this time, the fuel will have a downward force under the action of gravity, and the air inside the fuel tank body is compressed through the movable diaphragm. The internal air cannot be discharged from the refueling port. The movable diaphragm is supported by air pressure to prevent the fuel from being inverted and the fuel supply pump from being unable to extract fuel, which will cause the aircraft power to be weakened.

[0015] 2. The aircraft uses a tear-resistant soft fuel tank. When the fuel inside the fuel tank is gradually consumed, 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, which will then allow the fuel to gather at the fuel supply pump, making it easier for the fuel supply pump to pump the fuel into the aircraft engine through the fuel delivery pipe. At the same time, the fuel supply pump is located inside the fuel to facilitate heat dissipation during operation of the fuel supply pump, thereby avoiding a reduction in aircraft power due to a slowdown in the oil pumping speed.

[0016] 3. The aircraft uses a tear-resistant soft fuel tank. When the aircraft is inverted and accelerates or decelerates, the fuel will shake back and forth, and the shaking fuel will push the corresponding elastic diaphragm to contract, thereby reducing the force of the fuel shaking, promoting the stability of the fuel in the tank, and preventing the fuel shaking from interfering with the work of the fuel supply pump and interfering with the power of the aircraft.

[0017] 4. The aircraft uses a tear-resistant soft fuel tank. When the fuel inside the fuel tank decreases, the movable diaphragm moves as the fuel amount decreases, so that the fuel is always located in the space formed by the movable diaphragm and the bottom of the fuel tank, thereby reducing the space for fuel shaking. At the same time, the first outer plate and the second outer plate will limit the movement space of the first magnet ring, which can prevent the fuel from shaking excessively and causing the fuel pump to pump in air, affecting the power of the aircraft.

[0018] 5. The aircraft uses a tear-resistant soft fuel tank. When the aircraft is inverted, the fuel inside the fuel tank is located on the top of the movable diaphragm. The fuel will no longer exert pressure on the elastic diaphragm, causing the elastic diaphragm to bulge out under the push of the movable plate. Then, while the fuel squeezes the air downward, the elastic diaphragm will cause the fuel to bulge toward the middle part, allowing the fuel to more easily contact the fuel supply pump, thereby facilitating the fuel supply pump to supply fuel to the aircraft engine through the fuel delivery pipe. BRIEF DESCRIPTION OF THE DRAWINGS

[0019] Figure 1 It is a schematic diagram of the main stereoscopic structure of the present invention; Figure 2 It is a schematic diagram of the back three-dimensional structure of the present invention; Figure 3 for Figure 1 Schematic diagram of the cross-section structure; Figure 4 for Figure 3 A schematic diagram of the enlarged structure of the middle part A; Figure 5 This is a schematic diagram of the structure of the support and fixing frame of the present invention; Figure 6 for Figure 5 The enlarged structural diagram of the middle D part; Figure 7 It is a top view of the three-dimensional structure of the present invention; Figure 8 for Figure 3 The enlarged structural diagram of the middle B part; Fig. 9 for Figure 3 The enlarged structural diagram of the middle C part; Fig.10 for Figure 7 The enlarged structural diagram of the middle E part; Fig.11 It is a schematic diagram of the structure of the movable diaphragm of the present invention; Fig.12 for Fig.11 Schematic diagram of the cross-section structure; Fig.13 for Fig.12 The enlarged structural diagram of the middle F part; Fig.14 This is a schematic diagram of the cross-sectional structure of the fuel filler port.

[0020] In the figure: 1. oil tank body; 2. oil filling port; 3. oil supply pump; 4. oil delivery pipe; 5. lifting mechanism; 501. elastic diaphragm; 502. connecting pipe; 503. air box; 504. movable plate; 505. first spring; 506. support plate; 507. reinforcement plate; 6. oil supply guarantee mechanism; 601. first magnet ring; 602. second magnet ring; 603. movable diaphragm; 604. suspension air chamber; 605. flow port; 606. anti-backflow plate; 607. anti-disturbance plate; 608. barrier plate; 609. second spring; 610. fixed plate; 7. fixed structure; 701. fixed base frame; 702. support and fixing frame; 703. first outer plate; 704. second outer plate; 705. side limiting plate. DETAILED DESCRIPTION

[0021] The technical solutions in the embodiments of the present invention will be described clearly and completely below in conjunction with the drawings in the embodiments of the present invention. Obviously, the described embodiments are only part of the embodiments of the present invention, rather than all the embodiments.

[0022] Examples of the embodiments are shown in the accompanying drawings, wherein the same or similar reference numerals throughout represent the same or similar elements or elements having the same or similar functions. The embodiments described below with reference to the accompanying drawings are exemplary and are intended to be used to explain the present invention, and should not be construed as limiting the present invention.

[0023] Example 1: Please refer to Figure 1-6The present invention provides a technical solution: a tear-resistant soft fuel tank for an aircraft, comprising a fuel tank body 1, wherein the fuel tank body 1 adopts a three-layer laminated structure process, wherein 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 compression and distortion resistance of the fuel tank body 1, wherein a refueling port 2 is fixedly connected to the top of the fuel tank body 1, a fuel supply pump 3 is fixedly connected to the bottom of the fuel tank body 1, a fuel supply pipe 4 is fixedly connected to the bottom of the fuel supply pump 3, a lifting mechanism 5 is fixedly connected to the inside of the fuel tank body 1, a fuel supply guarantee mechanism 6 is movably connected to the inside of the fuel tank body 1, and a fixed structure 7 is fixedly connected to the bottom of the fuel tank body 1; The lifting mechanism 5 comprises: An elastic diaphragm 501, the elastic diaphragm 501 is fixedly connected to the inside of the oil tank body 1; A connecting pipe 502, the connecting pipe 502 is fixedly connected to the outer wall of the oil tank body 1; The air box 503 is fixedly connected to one end of the connecting pipe 502 away from the oil tank body 1.

[0024] There are two elastic diaphragms 501 , which are respectively located on the left and right sides of the oil supply pump 3 . There are two connecting pipes 502 , which are respectively located on the outsides of the corresponding elastic diaphragms 501 . Air boxes 503 are fixedly connected to the outsides of the connecting pipes 502 .

[0025] When in use, the fuel tank body 1 is placed 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. Refueling is added to the fuel tank body 1 through the refueling port 2. During the refueling process, the fuel inside the fuel tank body 1 gradually increases, which will gradually increase the pressure on the two elastic diaphragms 501, and then the two elastic diaphragms 501 will be pressed to fit the inner wall of the fuel tank body 1. At the same time, the gas at the bottom of the elastic diaphragm 501 will be pressed into the corresponding air box 503 through the connecting pipe 502.

[0026] A movable plate 504 is movably connected inside the air box 503, a first spring 505 is fixedly connected to the outer wall of the movable plate 504, a support plate 506 is fixedly connected to the outer side of the first spring 505, the support plate 506 is fixedly connected to the outer side of the air box 503, a reinforcing plate 507 is fixedly connected to the outer wall of the connecting pipe 502, the reinforcing plate 507 is fixedly connected to the outer wall of the oil tank body 1, the reinforcing plate 507 can increase the fixed area between the oil tank body 1 and the connecting pipe 502 to maintain the stability of the fixing of the connecting pipe 502.

[0027] The gas entering the air box 503 through the connecting pipe 502 will push the movable plate 504 outward, and let the movable plate 504 compress the first spring 505, allowing the gas to enter the air box 503. When the fuel inside 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, allowing the internal elastic diaphragm 501 to bulge upward, and then let the fuel gather at the fuel supply pump 3, so that the fuel supply pump 3 can pump the fuel into the aircraft engine through the fuel delivery pipe 4. At the same time, the fuel supply pump 3 is located inside the fuel to facilitate the heat dissipation of the fuel supply pump 3 during operation.

[0028] Example 2: Please refer to Figure 1-14 Based on the first embodiment, the present invention provides a technical solution: The oil supply guarantee mechanism 6 includes a first magnet ring 601, which is movably connected to the outer wall of the oil tank body 1. A second magnet ring 602 is movably connected inside the oil tank body 1. The second magnet ring 602 is arranged at a position corresponding to the first magnet ring 601. A movable diaphragm 603 is arranged inside the oil tank body 1, and the outer wall of the movable diaphragm 603 is fixedly connected to the second magnet ring 602.

[0029] The second magnet ring 602 and the first magnet ring 601 attract each other through magnetic force, so that the second magnet ring 602 is closely attached to the inner wall of the oil tank body 1, and the inside of the oil tank body 1 is divided into two upper and lower parts.

[0030] A flow port 605 is fixedly connected inside the movable diaphragm 603 , and an anti-backflow plate 606 is movably connected inside the flow port 605 .

[0031] When refueling through the refueling port 2, the fuel will fall to the top of the movable diaphragm 603, and 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, the anti-backflow plate 606 will fit with the edge of the flow port 605 under the push of the top fuel, causing the fuel to pass through the flow port 605.

[0032] A suspension gas chamber 604 is fixedly connected to the bottom of the movable diaphragm 603 , and a plurality of anti-disturbance plates 607 are fixedly connected to the bottom of the movable diaphragm 603 . The outer wall of the anti-disturbance plate 607 is provided with openings.

[0033] When refueling through the refueling port 2, the fuel flows through the flow port 605 into the bottom of the movable diaphragm 603, and the suspension gas chamber 604 generates buoyancy, which pushes the second magnet ring 602 upward through the movable diaphragm 603, and allows the second magnet ring 602 to drive the outer first magnet ring 601 to move upward through suction, and because 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 allow the fuel tank body 1 to bend, and thus only the first magnet ring 601 can move up and down, thereby limiting the movement of the second magnet ring 602 inside the fuel tank body 1, and then when the aircraft accelerates or decelerates, when the fuel shakes inside the fuel tank body 1, the movement of the top liquid surface will be blocked by the anti-disturbance plate 607, thereby dispersing the thrust of the shaking.

[0034] A barrier sheet 608 is movably connected inside the fuel filler 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 fuel filler port 2 .

[0035] Refuel the fuel tank 1 through the fuel filling port 2. When refueling, the external fuel pushes the barrier sheet 608, and the second spring 609 is stretched by the barrier sheet 608 to allow the fuel to enter the fuel tank 1. When the fuel is consumed, the air pressure at the top of the fuel in the fuel tank 1 decreases, and the external air pressure presses open the barrier sheet 608 and enters the fuel tank 1. When the aircraft is inverted during flight, the fuel will be located on the top of the movable diaphragm 603, and the air part will be located at the bottom of the movable diaphragm 603. At this time, the fuel will have a downward force under the action of gravity, and the air inside the fuel tank 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, so that the fuel supply pump 3 cannot extract fuel.

[0036] At the same time, when the aircraft is inverted, the fuel inside the fuel tank body 1 is located on the top of the movable diaphragm 603, and the fuel will no longer exert pressure on the elastic diaphragm 501, causing the elastic diaphragm 501 to bulge out under the push of the movable plate 504, and then cooperate with the fuel to squeeze the air downward, while the elastic diaphragm 501 will cause the fuel to bulge toward the middle part, allowing the fuel to more easily contact the fuel supply pump 3, so as to facilitate the fuel supply pump 3 to supply fuel to the aircraft engine through the oil delivery pipe 4.

[0037] When the aircraft is inverted and accelerates or decelerates, the fuel will shake back and forth, and the shaking fuel will push the corresponding elastic diaphragm 501 to contract, thereby reducing the force of the fuel shaking and promoting the stability of the fuel in the fuel tank body 1.

[0038] Example 3: Please refer to Figure 1-14 Based on the first and second embodiments, the present invention provides a technical solution: The fixed structure 7 includes a fixed base frame 701 , which is arranged at the bottom of the oil tank body 1 , and a support frame 702 is fixedly connected to the top of the fixed base frame 701 , and the support frame 702 is fixedly connected to the bottom of the oil tank body 1 .

[0039] By fixing the fixing base frame 701 inside the aircraft, the fixing base frame 701 fixes the oil tank body 1 inside the aircraft by supporting the fixing frame 702 .

[0040] The top of the fixed base frame 701 is located at the front and back of the oil tank body 1 and is fixedly connected to the first outer plate 703, and the first outer plate 703 is located on the outer wall of the first magnet ring 601. The top of the air box 503 is located outside the first magnet ring 601 and is fixedly connected to the second outer plate 704.

[0041] The top of the fixed base frame 701 is located outside the two air boxes 503 and is fixedly connected with side limiting plates 705 , and the side limiting plates 705 are fixedly connected to the outer wall of the support plate 506 .

[0042] When the fuel inside the fuel tank body 1 decreases, the movable diaphragm 603 will move with the decrease in the amount of fuel, and the first outer magnet ring 601 will be moved by the attraction of the second magnet ring 602 with the movement of the movable diaphragm 603, so that the fuel is always located in the space formed by the movable diaphragm 603 and the bottom of the fuel tank body 1, thereby reducing the space for fuel shaking. When the fuel in the fuel tank body 1 is shaken, 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 will prevent the fuel from shaking excessively and cause the fuel supply pump 3 to pump air into it.

[0043] The above description is only a preferred specific implementation manner of the present invention, but the protection scope of the present invention is not limited thereto. Any technician familiar with the technical field can make equivalent replacements or changes according to the technical scheme and inventive concept of the present invention within the technical scope disclosed by the present invention, which should be covered by 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).

2. The tear-resistant soft fuel tank for aircraft according to claim 1, characterized in that: 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 air boxes (503).

3. The tear-resistant soft fuel tank for aircraft according to claim 1, characterized in that: 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).

4. The tear-resistant soft fuel tank for aircraft according to claim 3, characterized in that: 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).

5. The tear-resistant soft fuel tank for aircraft according to claim 4, 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.

6. The tear-resistant soft fuel tank for aircraft according to claim 4, 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.

7. 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).

8. The tear-resistant soft fuel tank for aircraft according to claim 4, 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).

9. The tear-resistant soft fuel tank for aircraft according to claim 8, 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).

10. The tear-resistant soft fuel tank for aircraft according to claim 8, 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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