Inflation valve for aircraft landing gear

Abstract

The inflation valve comprises a valve body, a valve element, a first connecting piece and an inner core assembly, the inner core assembly is arranged in a cylinder of the valve element, and a first through hole is formed in the side wall of the cylinder of the valve element; one end of the valve body is clamped with the first connecting piece; the end, provided with an opening, of the valve element sequentially penetrates through the valve body and the first connecting piece, the valve element is connected with the first connecting piece through threads, the outer end of the valve body and the side wall of the valve element are sealed or separated, and the first through hole is formed between the outer end of the valve body and the first connecting piece. The inner core assembly comprises a core rod, a second sealing gasket, an elastic unit and a shaft sleeve unit, a second protruding part is arranged on the core rod, and the end of the elastic unit abuts against the inner wall of the cylinder of the valve element. The outer wall of the shaft sleeve unit is in sealing connection with the inner wall of the valve element, and a first circulation channel is arranged between the shaft sleeve unit and the core rod. According to the inflation valve, the technical problem that in the prior art, an inflation valve is low in reliability is solved.

Description

TECHNICAL FIELD

[0001] The present application belongs to the technical field of aircraft landing gear, and particularly relates to an inflatable valve for aircraft landing gear. BACKGROUND

[0002] The inflatable valve is a functional part often used in various gas pressure devices, and is a gas filling valve of the device. The existing inflatable valves of various types usually bear small gas pressure, have no mechanical locking function, low reliability, no looseness alarm function and other shortcomings. The inflatable valve for aircraft landing gear has particularly harsh environment, and has higher requirements for bearing hydraulic pressure / gas pressure capacity, reliability and safety. SUMMARY

[0003] In view of the existing technical problems, the present application aims to provide an inflatable valve for aircraft landing gear, which can solve the technical problem of low reliability of the inflatable valve in the prior art.

[0004] In order to achieve the above-mentioned purpose, the technical scheme adopted by the present application is as follows:

[0005] An inflatable valve for aircraft landing gear has the following structural characteristics: comprising a valve body, a valve core, a first connecting piece and an inner core assembly, the valve core is a cylinder structure with one end being open, the inner core assembly is arranged in the cylinder of the valve core, and a first through hole is arranged on the side wall of the cylinder of the valve core; one end of the valve body is clamped with the first connecting piece, and the valve body and the first connecting piece can move relative to each other along the height direction of the valve body, and the other end of the valve body is used for being connected with the aircraft landing gear; the valve core is arranged with an open end, which penetrates the valve body and the first connecting piece in sequence, the side wall of the valve core is connected with the first connecting piece through threads, the outer end of the valve body is sealed with the side wall of the valve core or separated from the side wall of the valve core, and the first through hole is arranged between the outer end of the valve body and the first connecting piece; the inner core assembly comprises a core rod, a second sealing gasket fixedly connected with the core rod, an elastic unit and a shaft sleeve unit arranged on the core rod, a second protruding part is arranged on the core rod, the elastic unit and the shaft sleeve unit are arranged on the two sides of the second protruding part respectively, the second sealing gasket is arranged between the second protruding part and the shaft sleeve unit, the end of the elastic unit is abutted with the inner wall of the cylinder of the valve core, and a spacing is arranged between the abutted position and the bottom of the cylinder of the valve core; the outer wall of the shaft sleeve unit is sealed and connected with the inner wall of the valve core, a first flow-through channel is arranged between the shaft sleeve unit and the core rod, one end of the first flow-through channel is connected with the open end of the cylinder of the valve core, and the other end of the first flow-through channel is sealed by the second sealing gasket or connected with the inner cavity of the cylinder of the valve core; when the outer end of the valve body is sealed with the side wall of the valve core, the second sealing gasket is abutted with the shaft sleeve unit under the elastic force of the elastic unit, so that the end of the first flow-through channel is sealed; when the shaft sleeve unit is separated from the second sealing gasket under the action of the gas source, the first flow-through channel is connected with the first through hole, and the side wall of the valve core is separated from the outer end of the valve body.

[0006] The valve body and the first connecting piece can be assembled by cold shrinkage method, and a gap is arranged at the assembly position, so that the valve body and the first connecting piece can be relatively moved along the height direction of the valve body, and the gap forms the opening / closing stroke of the inflation valve. When the inflation valve for aircraft landing gear is used, the end of the valve body is connected with the aircraft landing gear. When the inflation valve for aircraft landing gear is in the locked state, the outer end of the valve body is sealed with the side wall of the valve core, the end of the first flow channel is sealed by the second sealing pad, the first connecting piece is rotated clockwise to move downward to the stop position, and the top of the valve body is abutted with the first connecting piece. When it is needed to open the inflation valve for aircraft landing gear, the first connecting piece is rotated counterclockwise to move upward to the stop position. When the inflation valve for aircraft landing gear is inflated, the gas source interface is connected with the open end of the valve core, the core rod is pressed downward by the gas source, the core rod and the second sealing ring move to the bottom of the valve core under the action of the gas source, at this time, the shaft sleeve unit is separated from the second sealing pad, the elastic unit is compressed, the valve core moves downward under the action of the core rod, the side wall of the valve core is separated from the outer end of the valve body, that is, the sealing surface of the valve core and the valve body is opened. At this time, the first connecting piece moves downward to the stop position. The gas enters the landing gear through the open end of the valve core, the first flow channel, the inner cavity of the valve core, the first through hole and the gap between the side wall of the valve core and the outer end of the valve body in sequence. After the inflation is completed, the gas source interface is removed, the core rod and the second sealing pad move upward under the action of the elastic unit, the second sealing pad is in contact with the shaft sleeve unit to seal, and the first flow channel is sealed by the second sealing pad. The first connecting piece is rotated clockwise to the stop position, so that the valve core moves upward as a whole, the side wall of the valve core is in contact with the outer end of the valve body to form double sealing, at this time, the inflation valve is in the locked state. When the inflation valve is in the locked state, even if the gas source interface is connected with the inflation valve, the core rod is pressed downward by the gas source, the elastic unit is compressed, the core rod and the second sealing pad move downward to separate the second sealing pad from the shaft sleeve unit, and the two are in contact to open the sealing. Since the first connecting piece cannot move downward, the valve core as a whole cannot move downward, the sealing between the valve core and the valve body cannot be opened, and the inflation valve cannot leak or be inflated. When the inflation valve is in the opened state, the first flow channel is sealed by the second sealing pad, the valve core and the valve body are in contact to seal, and the inflation channel cannot be opened. Only when the inflation valve is inflated, the inflation channel can be opened. The inflation valve for aircraft landing gear has the advantages of high reliability, high safety and strong gas pressure bearing capacity.

[0007] Specifically, the valve body comprises a valve body, a first connecting part and a second connecting part arranged at both ends of the valve body respectively, and the second connecting part is used for being connected with the aircraft landing gear; one end of the first connecting piece is provided with a third connecting part, the third connecting part is clamped with the first connecting part, and the third connecting part and the first connecting part can be relatively moved along the height direction of the valve body.

[0008] Preferably, the outer wall of the second connecting part is provided with an external thread, and the external thread has a first groove along the height direction. A first sealing ring is provided on the end face of the valve body near the second connecting part. When the second connecting part is connected to the aircraft landing gear by the thread, the aircraft landing gear abuts against the first sealing ring. When the inflation valve becomes loose from the landing gear, the high-pressure gas inside the landing gear escapes from the first groove on the outer wall of the second connecting part of the valve body, emitting a whistle alarm. This can alert ground maintenance personnel and prevent the loose inflation valve from being fired like a bullet and injuring people, thereby improving the safety of the inflation valve.

[0009] Preferably, the outer wall of the valve core is provided with a first protrusion, which is located near the bottom of the valve core cylinder; the end of the first protrusion near the valve body is a conical surface, and the first protrusion can form a conical seal with the outer end of the valve body.

[0010] Preferably, the outer wall of the valve core and the inner wall of the valve body are sealed by a second sealing ring, and the first through hole is disposed between the second sealing ring and the first protrusion. The second sealing ring ensures a seal between the outer wall of the valve core and the valve body.

[0011] Preferably, the inner wall of the valve core is provided with a first step and a second step along the height direction in the circumferential direction, and the first step is provided near the bottom wall of the valve core cylinder; one end of the elastic unit abuts against the first step, and the other end of the elastic unit is provided outside the second step.

[0012] Preferably, the width of the second step is greater than the width of the second protrusion, and the width of the second protrusion is greater than the width of the first step.

[0013] Preferably, the elastic unit includes an elastic element and a mounting base, both of which are sleeved on the mandrel; one end of the elastic element is connected to the second protrusion, the other end of the elastic element is connected to the mounting base, and the outer end of the mounting base abuts against the inner wall of the valve core cylinder.

[0014] Preferably, the bushing unit includes a first bushing and a second bushing, the side wall of the second bushing being threadedly connected to the inner wall of the valve core cylinder; both the first and second bushings are fitted onto the mandrel, and a gap is provided between the first and second bushings and the mandrel; one end of the first bushing is adjacent to the second sealing gasket, and the other end of the first bushing is rotatably connected to the second bushing; a third sealing ring is provided on the side wall of the first bushing, which seals against the inner wall of the valve core cylinder. The gap between the first and second bushings and the mandrel forms a first flow channel, and the third sealing ring ensures a seal between the inner wall of the valve core and the first bushing.

[0015] Preferably, the valve core has a valve cover at its open end, which is threadedly connected to the valve core, and the inner bottom wall of the valve cover is sealed to the top of the valve core by a first sealing gasket; the inner wall of the valve body has at least one boss, and the outer wall of the valve core has a groove that matches the boss at a corresponding position, with the boss on the valve body engaging with the groove on the valve core. By providing a valve cover to protect the open end of the valve core, and by providing a boss and a groove to engage with the valve body and valve core, relative rotation between the valve body and valve core is restricted.

[0016] Compared with the prior art, the beneficial effects of the present invention are as follows:

[0017] 1. The inflatable valve for aircraft landing gear of the present invention has the advantages of high reliability, high safety and strong air pressure resistance.

[0018] 2. The inflatable valve for aircraft landing gear of the present invention can emit a whistle alarm to remind ground maintenance personnel and prevent a loose inflatable valve from being fired out like a bullet and injuring people, thereby improving the safety of the inflatable valve. Attached Figure Description

[0019] Figure 1 This is a schematic diagram of the inflatable valve structure for aircraft landing gear according to the present invention;

[0020] Figure 2 yes Figure 1 A schematic diagram of the cross-sectional structure;

[0021] Figure 3 yes Figure 2 Schematic diagram of the inner core component structure;

[0022] Figure 4 yes Figure 1 Schematic diagram of the structure with the centrally inflated valve in the closed state;

[0023] Figure 5 yes Figure 1 Schematic diagram of the structure with the centrally inflated valve in the open position;

[0024] Figure 6 yes Figure 1 A schematic diagram of the structure of the inflatable valve in the inflatable state.

[0025] In the diagram:

[0026] 1-Valve body; 101-Valve body body; 102-First connecting part; 103-Second connecting part; 104-First groove; 2-Valve core; 201-First through hole; 202-First protrusion; 203-First step; 204-Second step; 3-First connecting piece; 301-Third connecting part; 4-Valve cover; 5-First sealing gasket; 6-First sealing ring; 7-Second sealing ring; 8-Inner core assembly; 801-Core rod; 802-Second sealing gasket; 803-Elastic unit; 803-1-Elastic element; 803-2-Mounting base; 804-Sleeve unit; 804-1-First sleeve; 804-2-Second sleeve; 804-3-Third sealing ring; 805-First flow channel; 806-Second protrusion. Detailed Implementation

[0027] The present invention will now be described in detail with reference to the accompanying drawings and embodiments. It should be noted that, unless otherwise specified, the embodiments and features described herein can be combined with each other. For ease of description, the terms "upper," "lower," "left," and "right" used below only indicate that they correspond to the upper, lower, left, and right directions in the accompanying drawings and do not limit the structure.

[0028] like Figure 1 and Figure 2As shown, this embodiment provides an inflatable valve for aircraft landing gear, comprising a valve body 1, a valve core 2, a first connecting member 3, a valve cover 4, and an inner core assembly 8. The valve core 2 is a cylindrical structure with one open end, and the inner core assembly 8 is disposed within the cylinder of the valve core 2. A first through hole 201 is provided on the side wall of the cylinder of the valve core 2. The valve body 1 is a hollow cylinder, comprising a valve body 101, a first connecting portion 102 and a second connecting portion 103 respectively disposed at both ends of the valve body 101. The second connecting portion 103 is used to connect with the aircraft landing gear. An external thread is provided on the outer wall of the second connecting portion 103, and a first groove 104 is formed along the height direction of the external thread. The first groove 104 is rectangular, and a first sealing ring 6 is provided on the end face of the valve body 101 near the second connecting portion 103. When the second connecting portion 103 is connected to the aircraft landing gear by the thread, the aircraft landing gear abuts against the first sealing ring 6 to form a seal. The first connecting member 3 is a hollow cylinder with an internal thread at one axial end and a third connecting part 301 at the other axial end. The third connecting part 301 is an annular groove and conical in shape. The third connecting part 301 engages with the first connecting part 102, and the third connecting part 301 and the first connecting part 102 can move a small distance relative to each other along the height direction of the valve body 101. The third connecting part 301 and the first connecting part 102 are assembled and connected by a cold shrinking method, and the assembly gap between the two forms the inflation valve opening and closing stroke. The valve core 2 has an opening at one end that passes through the valve body 1 and the first connecting member 3 in sequence. The inner wall of the valve body 1 has at least one boss, and the outer wall of the valve core 2 has a groove at a corresponding position that matches the boss. The boss on the valve body 1 engages with the groove on the valve core 2, and the boss on the inner wall of the valve body 1 and the groove on the outer wall of the valve core 2 cooperate to restrict their relative rotation. A first protrusion 202 is provided on the outer wall of the valve core 2. The first protrusion 202 is located near the bottom of the valve core 2's cylinder and is located inside the aircraft landing gear. The end of the first protrusion 202 near the second connecting part 103 is a conical surface, which can form a conical seal with the inner wall of the outer end of the second connecting part 103. The outer wall of the valve core 2 is sealed with the inner wall of the valve body 1 by a second sealing ring 7, and a first through hole 201 is provided between the second sealing ring 7 and the first protrusion 202. The outer wall of the valve core 2's cylinder opening end to the middle part is provided with external threads, and the valve core 2 is connected to the first connecting member 3 by threads. A valve cover 4 is provided on the opening end of the valve core 2. The valve cover 4 is hollow cylindrical and closed at one end. The valve cover 4 is connected to the valve core 2 by threads, and the inner bottom wall of the valve cover 4 is sealed with the top of the valve core 2 by a first sealing gasket 5. The inner wall of the valve core 2 is provided with a first step 203 and a second step 204 along the height direction in the circumferential direction. The first step 203 is located near the bottom wall of the valve core 2.

[0029] like Figure 2 and Figure 3As shown, the inner core assembly 8 includes a core rod 801, a second sealing gasket 802 fixedly connected to the core rod 801, an elastic unit 803 sleeved on the core rod 801, and a bushing unit 804. The core rod 801 has a second protrusion 806, and the second sealing gasket 802 is fixedly connected to the second protrusion 806. The second protrusion 806 is located above the second step 204. The width of the second step 204 is greater than the width of the second protrusion 806, and the width of the second protrusion 806 is greater than the width of the first step 203. The elastic unit 803 and the bushing unit 804 are respectively disposed on both sides of the second protrusion 806, and the second sealing gasket 802 is disposed between the second protrusion 806 and the bushing unit 804. The elastic unit 803 includes an elastic element 803-1 and a mounting base 803-2. The elastic element 803-1 is a spring, and both the elastic element 803-1 and the mounting base 803-2 are sleeved on the core rod 801. One end of the elastic element 803-1 is connected to the second protrusion 806, and the connection is located above the second step 204. The other end of the elastic element 803-1 is connected to the mounting base 803-2, and the outer end of the mounting base 803-2 abuts against the first step 203. The bushing unit 804 includes a first bushing 804-1 and a second bushing 804-2. The side wall of the second bushing 804-2 is threadedly connected to the inner wall of the valve core 2. Both the first bushing 804-1 and the second bushing 804-2 are sleeved on the core rod 801, and a gap is provided between the first bushing 804-1 and the second bushing 804-2 and the core rod 801 to form a first flow channel 805. One end of the first bushing 804-1 is closely adjacent to the second sealing gasket 802, and the other end of the first bushing 804-1 is rotatably connected to the second bushing 804-2. The two are assembled and fitted by a cold shrinkage method. A third sealing ring 804-3 is provided on the side wall of the first bushing 804-1, which seals against the inner wall of the valve core 2. One end of the first flow channel 805 is connected to the open end of the valve core 2, and the other end of the first flow channel 805 is sealed by the second sealing gasket 802 or connected to the inner cavity of the valve core 2.

[0030] When the air-filled valve for the aircraft landing gear is in use, the second connecting part 103 of the valve body 1 is threadedly connected to the aircraft landing gear and sealed by the first sealing ring 6. When the air-filled valve becomes loose from the aircraft landing gear, the internal gas passes through the first groove 104, emitting an audible alarm. Figure 4 As shown, when the aircraft landing gear inflation valve is in the locked state, the outer end of the second connecting part 103 forms a conical seal with the side wall of the first protrusion 202 on the valve core 2. Under the elastic force of the elastic element 803-1, the second sealing gasket 802 abuts against the first bushing 804-1, sealing the end of the first flow channel 805. Rotating the first connecting member 3 clockwise moves the first connecting member 3 downward to the stop position, and the top of the first connecting part 102 of the valve body 1 abuts against the first connecting member 3.Figure 5 As shown, when the aircraft landing gear inflation valve needs to be opened, the first connecting member 3 is rotated counterclockwise, causing it to move upward to the stop position. At this time, the third connecting part 301 of the first connecting member 3 engages with the first connecting part 102. Figure 6 As shown, when the aircraft landing gear inflation valve is inflated, the valve cover 4 is unscrewed, and the air source interface is connected to the open end of the valve core 2 for inflation. The air source presses down on the mandrel 801, and the mandrel 801 and the second sealing ring 802 move towards the bottom of the valve core 2 cylinder under the action of the air source. At this time, the first bushing 804-1 separates from the second sealing gasket 802, the elastic element 803-1 is compressed, and the valve core 2 moves downward under the action of the mandrel 801, so that the side wall of the valve core 2 separates from the outer end of the second connecting part 103, that is, the sealing surface between the valve core 2 and the second connecting part 103 opens. At this time, the first connecting piece 3 moves downward with the valve core 2 to the stop position. The gas enters the landing gear through the open end of the valve core 2, sequentially through the first flow channel 805, the inner cavity of the valve core 2, the first through hole 201, and the gap between the valve core 2 and the second connecting part 103. After inflation is complete, the air source interface is removed. The core rod 801 and the second sealing gasket 802 move upward under the elastic force of the elastic element 803-1. The second sealing gasket 802 contacts and seals with the first bushing 804, and the first flow channel 805 is sealed by the second sealing gasket 802. Rotate the first connecting piece 3 clockwise to the stop position, causing the valve core 2 to move upward as a whole. The side wall of the first protrusion 202 on the valve core 2 contacts and seals with the outer end of the second connecting part 103 of the valve body 1, forming a double seal. At this time, the inflation valve is in the closed state. When the inflation valve is closed, even if the air source interface is connected to the inflation valve, the air source presses down on the mandrel 801, compressing the elastic element 803-1. The mandrel 801 and the second sealing gasket 802 move downwards, causing the second sealing gasket 802 to separate from the first bushing 804. The seal between them opens, but because the first connecting piece 3 cannot move downwards, the valve core 2 as a whole will not move downwards, and the seal between the valve core 2 and the valve body 1 will not open. Therefore, the inflation valve will not leak air and cannot be inflated. When the inflation valve is open, the first flow channel 805 is sealed by the second sealing gasket 802, and the valve core 2 and the valve body 1 are sealed, preventing the inflation channel from opening. The inflation channel can only open when the inflation valve is inflated.

[0031] The above embodiments should be understood as being used only to illustrate the present invention more clearly, and not to limit the scope of the present invention. After reading the present invention, any modifications of the present embodiments by those skilled in the art will fall within the scope defined by the appended claims.

Claims

1. An inflatable shutter for an aircraft landing gear, characterised in that: The valve body (1), the valve core (2), the first connecting piece (3) and the inner core assembly (8) are included, the valve core (2) is a cylinder structure with one end opening, the inner core assembly (8) is arranged in the cylinder of the valve core (2), and the first through hole (201) is arranged on the side wall of the cylinder of the valve core (2); One end of the valve body (1) is clamped with the first connecting piece (3), and the valve body (1) and the first connecting piece (3) can be relatively moved along the height direction of the valve body (1), and the other end of the valve body (1) is used for being connected with the aircraft landing gear; The one end of the valve core (2) provided with the opening penetrates the valve body (1) and the first connecting piece (3) in sequence, the side wall of the valve core (2) is connected with the first connecting piece (3) through threads, the outer end of the valve body (1) is sealed with the side wall of the valve core (2) or is separated from the side wall, and the first through hole (201) is arranged between the outer end of the valve body (1) and the first connecting piece (3); The inner core assembly (8) includes a core rod (801), a second sealing gasket (802) fixedly connected with the core rod (801), an elastic unit (803) sleeved on the core rod (801) and a shaft sleeve unit (804), the core rod (801) is provided with a second protruding portion (806), the elastic unit (803) and the shaft sleeve unit (804) are arranged on the two sides of the second protruding portion (806) respectively, the second sealing gasket (802) is arranged between the second protruding portion (806) and the shaft sleeve unit (804), the end of the elastic unit (803) abuts against the inner wall of the cylinder of the valve core (2), and a spacing is formed between the abutting position and the bottom of the cylinder of the valve core (2); The outer wall of the shaft sleeve unit (804) is sealed and connected with the inner wall of the valve core (2), a first flow channel (805) is formed between the shaft sleeve unit (804) and the core rod (801), one end of the first flow channel (805) is connected with the opening end of the cylinder of the valve core (2), and the other end of the first flow channel (805) is sealed by the second sealing gasket (802) or is connected with the inner cavity of the cylinder of the valve core (2); When the outer end of the valve body (1) is sealed with the side wall of the valve core (2), the second sealing gasket (802) abuts against the shaft sleeve unit (804) under the elastic force of the elastic unit (803), so that the end of the first flow channel (805) is sealed; when the shaft sleeve unit (804) is separated from the second sealing gasket (802) under the action of the gas source, the first flow channel (805) is connected with the first through hole (201), and the side wall of the valve core (2) is separated from the outer end of the valve body (1).

2. An aircraft landing gear inflatable shutter according to claim 1, characterised in that: The valve body (1) includes a valve body (101), a first connecting part (102) and a second connecting part (103) arranged at the two ends of the valve body (101) respectively, and the second connecting part (103) is used for being connected with the aircraft landing gear; one end of the first connecting piece (3) is provided with a third connecting part (301), the third connecting part (301) is clamped with the first connecting part (102), and the third connecting part (301) and the first connecting part (101) can be relatively moved along the height direction of the valve body (101).

3. An aircraft landing gear inflatable shutter according to claim 2, characterised in that: The outer wall of the second connecting part (103) is provided with external threads, the external threads are provided with a first groove (104) in the height direction, and the end face of the valve body (101) close to the second connecting part (103) is provided with a first sealing ring (6); when the second connecting part (103) is connected with the aircraft landing gear through threads, the aircraft landing gear abuts against the first sealing ring (6).

4. An aircraft landing gear inflatable shutter according to claim 1, characterised in that: The outer wall of the valve core (2) is provided with a first protruding part (202), and the first protruding part (202) is arranged close to the bottom of the cylinder of the valve core (2); one end of the first protruding part (202) close to the valve body (1) is a conical surface, and the first protruding part (202) can form a conical surface seal with the outer end part of the valve body (1).

5. An aircraft landing gear inflatable shutter according to claim 4, characterised in that: The outer wall of the valve core (2) and the inner wall of the valve body (1) are sealed by a second sealing ring (7), and the first through hole (201) is arranged between the second sealing ring (7) and the first protruding part (202).

6. An aircraft landing gear inflatable shutter according to claim 1, characterised in that: The inner wall of the valve core (2) is provided with a first step (203) and a second step (204) in the height direction in the circumferential direction, and the first step (203) is arranged close to the bottom wall of the cylinder of the valve core (2); one end of the elastic unit (803) abuts against the first step (203), and the other end of the elastic unit (803) is arranged outside the second step (204).

7. An aircraft landing gear inflatable shutter according to claim 6, characterised in that: The width of the second step (204) is greater than the width of the second protruding part (806), and the width of the second protruding part (806) is greater than the width of the first step (203).

8. An aircraft landing gear inflatable shutter according to claim 1, characterised in that: The elastic unit (803) comprises an elastic element (803-1) and a mounting seat (803-2), and the elastic element (803-1) and the mounting seat (803-2) are both sleeved on the core rod (801); one end of the elastic element (803-1) is connected with the second protruding part (806), the other end of the elastic element (803-1) is connected with the mounting seat (803-2), and the outer end part of the mounting seat (803-2) abuts against the inner wall of the cylinder of the valve core (2).

9. An aircraft landing gear inflatable shutter according to claim 1, characterised in that: The shaft sleeve unit (804) comprises a first shaft sleeve (804-1) and a second shaft sleeve (804-2), and the side wall of the second shaft sleeve (804-2) is connected with the inner wall of the cylinder of the valve core (2) through threads; the first shaft sleeve (804-1) and the second shaft sleeve (804-2) are both sleeved on the core rod (801), and gaps are arranged between the first shaft sleeve (804-1), the second shaft sleeve (804-2) and the core rod (801); one end of the first shaft sleeve (804-1) is arranged close to the second sealing gasket (802), and the other end of the first shaft sleeve (804-1) is rotationally connected with the second shaft sleeve (804-2); the side wall of the first shaft sleeve (804-1) is provided with a third sealing ring (804-3), and the third sealing ring (804-3) is sealed with the inner wall of the cylinder of the valve core (2).

10. An aircraft landing gear inflatable shutter according to claim 1, characterised in that: The opening end of the valve core (2) is provided with a valve cover (4), the valve cover (4) is connected with the valve core (2) through threads, and the inner bottom wall of the valve cover (4) is sealed with the top of the valve core (2) through a first sealing gasket (5); the inner wall of the valve body (1) is provided with at least one boss, the outer side wall of the valve core (2) is provided with a groove matched with the boss at the corresponding position, and the boss on the valve body (1) is clamped with the groove on the valve core (2).

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