Small volume integrated anti-sway front landing gear

Abstract

The application discloses a small-size front landing gear with integrated swing reduction function and relates to the technical field of landing gears.The landing gear comprises a buffer strut structure, a landing gear mounting joint is arranged at the upper end of the buffer strut structure, the lower end of the buffer strut structure is connected with the upper end of a piston rod, and the outer periphery of the buffer strut structure is provided with an outer cylinder; a swing reduction structure is arranged at the outer periphery of the connecting position of the piston rod, and the upper end of the swing reduction structure is connected with the outer cylinder; a wheel fork assembly is connected with the lower end of the piston rod at the upper end, and the lower end of the wheel fork assembly is connected with a machine wheel; and a torsion arm assembly is connected with the swing reduction structure and the wheel fork assembly at the two ends. The landing gear integrates a swing reducer and a transmission mechanism to the buffer strut, effectively reduces the overall size of the landing gear, reduces the weight of the landing gear, and has good buffer performance and swing reduction performance.

Description

Technical Field

[0001] This invention belongs to the field of landing gear technology, and more specifically, relates to a small-volume nose landing gear with integrated anti-sway function. Background Technology

[0002] During aircraft landing gear roll, shimmy often occurs. Shimmy dampers installed on the landing gear effectively reduce and suppress the effects of shimmy, preventing damage to the landing gear and the aircraft. Based on the transmission method, shimmy dampers can be broadly classified into rod-type and cylindrical-type. Rod-type dampers convert landing gear shimmy into linear reciprocating motion of the damper; cylindrical-type dampers convert it into rotational reciprocating motion, and then dissipate the energy generated by the shimmy through damping. However, regardless of the type of damper, a mounting bracket needs to be provided on the outer cylinder of the landing gear for the damper to be installed, and additional space is required to design the transmission mechanism to transmit the oscillating motion of the wheels to the damper. This places special space and weight requirements on the design of the landing gear dampers. Simultaneously, the landing gear needs sufficient space to avoid interference with other components during retraction and extension. Therefore, reducing the size of the landing gear's shock absorber strut, thus occupying less space and weight, while still providing both shock absorption and shimmy reduction performance, will become a key technology in the landing gear design process.

[0003] The main problems with existing landing gear with dampers are: 1. The damper requires the landing gear to install a mounting bracket and transmission mechanism, and both the damper and the transmission mechanism require a certain amount of space, which increases the overall size of the landing gear; 2. The external damper and transmission mechanism also occupy a certain amount of weight of the landing gear, which limits the lightweight indicators in the landing gear design. Summary of the Invention

[0004] The purpose of this invention is to address the shortcomings of existing technologies by providing a small-volume nose landing gear with integrated anti-sway function. This landing gear integrates the anti-sway device and its transmission mechanism into the buffer strut, effectively reducing the overall volume and weight of the landing gear, while also exhibiting good cushioning and anti-sway performance.

[0005] To achieve the above objectives, the present invention provides a compact front landing gear with integrated anti-sway function, comprising:

[0006] The buffer strut structure has a landing gear mounting joint at the upper end, the lower end of the buffer strut structure is connected to the upper end of the piston rod, and an outer cylinder is sleeved around the outer periphery of the buffer strut structure.

[0007] A damping structure is disposed on the outer periphery of the connection point of the piston rod, and the outer periphery of the damping structure is connected to the outer cylinder;

[0008] The upper end of the wheel fork assembly is connected to the lower end of the piston rod, and the lower end of the wheel fork is connected to the wheel.

[0009] The torque arm assembly is connected at both ends to the anti-sway structure and the wheel fork assembly, respectively.

[0010] Optionally, the buffer support structure includes a plunger rod, a piston, and a damping valve. The plunger rod is inserted into one end of the piston, the damping valve is disposed inside the piston, and the other end of the piston is connected to the piston rod via an upper cam and a lower cam.

[0011] Optionally, the top end of the outer cylinder is connected to the landing gear mounting joint, and the bottom end of the outer cylinder is connected to the anti-sway structure.

[0012] Optionally, the anti-sway structure includes:

[0013] The lower bushing assembly has its inner circumference sealed to the piston rod, and its outer side is screwed to the outer cylinder.

[0014] An outer bushing assembly is sleeved on the outer periphery of the piston rod. The lower end of the outer bushing assembly is sealed to the piston rod. An outer ring assembly is provided between the upper end of the outer bushing assembly and the piston rod. The outer ring assembly is threaded to the outer bushing assembly. The outer periphery of the outer ring assembly is provided with a mounting hole that is hinged to the torque arm assembly.

[0015] An inner ring assembly is disposed between the outer cylinder and the lower bushing assembly. The outer cylinder and the lower bushing assembly clamp and fix the inner ring assembly, and the inner ring assembly and the outer ring assembly are rotatably engaged relative to each other.

[0016] Multiple arc-shaped springs are disposed between the inner ring assembly and the outer ring assembly, and the arc-shaped springs reduce the relative rotational speed of the inner ring assembly and the outer ring assembly.

[0017] Optionally, the outer ring assembly includes an outer ring body, the outer periphery of which is fitted to the outer bushing assembly through a first sealing gasket and a first wear-resistant gasket, and at least two first blades are uniformly arranged on the inner periphery of the outer ring body, with a first blade sealing gasket and a first blade wear-resistant gasket provided on the first blade.

[0018] Optionally, the inner ring assembly includes an inner ring body, which is limited and fixed to the lower bushing assembly by the outer cylinder. The inner circumference of the inner ring body is in contact with the outer cylinder by a second sealing gasket and a second wear-resistant gasket. At least two second blades should be provided on the outer circumference of the inner ring body, and a second blade sealing gasket and a second blade wear-resistant gasket are provided on the second blades.

[0019] Optionally, the number of the second blades is the same as the number of the first blades, and the arc-shaped springs are respectively disposed between the first blades and the second blades.

[0020] Optionally, the second blade has a damping hole, and the space between the outer ring and the inner ring is filled with damping fluid.

[0021] Optionally, the lower bushing assembly includes a lower bushing, the outer bushing assembly includes an outer bushing, protective rings are provided between the lower bushing and the piston rod and between the outer bushing and the piston rod, and a dustproof ring is provided between the lower bushing and the outer cylinder.

[0022] This invention provides a small-volume nose landing gear with integrated anti-sway function. Its advantages are: the nose landing gear integrates the anti-sway structure and its transmission mechanism into the buffer strut structure, which effectively saves the space inside the landing gear bay, reduces the weight of the landing gear, and at the same time has good buffer performance and anti-sway performance.

[0023] Other features and advantages of the present invention will be described in detail in the following detailed description section. Attached Figure Description

[0024] The above and other objects, features and advantages of the present invention will become more apparent from the more detailed description of exemplary embodiments of the invention in conjunction with the accompanying drawings, wherein the same reference numerals generally represent the same components in the exemplary embodiments of the invention.

[0025] Figure 1 A schematic diagram of a small-volume integrated anti-sway front landing gear according to an embodiment of the present invention is shown.

[0026] Figure 2 A schematic diagram of a buffer support structure according to an embodiment of the present invention is shown.

[0027] Figure 3 A schematic diagram of the internal structure of a buffer support structure according to an embodiment of the present invention is shown.

[0028] Figure 4 A schematic diagram of the internal structure of a sway-reducing structure according to an embodiment of the present invention is shown.

[0029] Figure 5 A schematic diagram showing the connection between the inner ring assembly and the outer ring assembly according to an embodiment of the present invention is shown.

[0030] Figure 6 A schematic diagram of the structure of an inner ring assembly according to an embodiment of the present invention is shown.

[0031] Figure 7A schematic diagram of the structure of an outer ring assembly according to an embodiment of the present invention is shown.

[0032] Figure 8 A schematic diagram of a wheel fork assembly according to an embodiment of the present invention is shown.

[0033] Figure 9 A schematic diagram of a torsion arm assembly according to an embodiment of the present invention is shown.

[0034] Explanation of reference numerals in the attached figures:

[0035] 1. Landing gear mounting joint; 2. Buffer strut structure; 3. Anti-sway structure; 4. Piston rod; 5. Wheel fork assembly; 6. Wheel; 7. Torque arm assembly; 8. Plunger rod; 9. Piston; 10. Damping valve; 11. Upper cam; 12. Lower cam; 13. Damping orifice; 14. Outer cylinder; 15. Outer ring assembly; 16. Inner ring assembly; 17. Lower bushing assembly; 18. Outer bushing assembly; 19. Arc spring; 20. First blade; 21. Second blade. Detailed Implementation

[0036] Preferred embodiments of the invention will now be described in more detail. While preferred embodiments of the invention are described below, it should be understood that the invention can be implemented in various forms and should not be limited to the embodiments set forth herein. Rather, these embodiments are provided so that the invention will be thorough and complete, and will fully convey the scope of the invention to those skilled in the art.

[0037] This invention provides a compact front landing gear with integrated anti-sway function, comprising:

[0038] The buffer strut structure has a landing gear mounting joint at the upper end, the lower end of the buffer strut structure is connected to the upper end of the piston rod, and an outer cylinder is fitted around the outer periphery of the buffer strut structure.

[0039] The anti-slip structure is located on the outer periphery of the piston rod connection, and the outer periphery of the anti-slip structure is connected to the outer cylinder.

[0040] The upper end of the wheel fork assembly is connected to the lower end of the piston rod, and the lower end of the wheel fork is connected to the wheel.

[0041] The torsion arm assembly is connected at both ends to the anti-sway structure and the wheel fork assembly, respectively.

[0042] Specifically, the nose landing gear, from top to bottom, includes a landing gear mounting joint, a shock absorber structure, a sway damping structure, a piston rod, a wheel fork assembly, and a wheel. A torque arm assembly is installed between the sway damping structure and the wheel fork assembly. This reduces the impact of vertical vibrations caused by the wheel landing on the shock absorber structure. Furthermore, the sway damping structure, positioned between the shock absorber structure and the piston rod, mitigates the problem of excessive rotation angle between the outer shock absorber cylinder and the wheel fork assembly. This gives the nose landing gear excellent cushioning and sway damping performance. All structures within the nose landing gear, except for the torque arm assembly, are arranged in the same axial direction, effectively reducing the overall volume of the landing gear. The torque arm assembly is also positioned as close as possible to the side of the wheel fork assembly, which not only improves the effect of reducing vertical vibrations but also effectively controls the space occupied.

[0043] In one embodiment, the torsion arm assembly can adopt a folding structure, so that when the wheels are subjected to vertical vibrations during landing, the vibrations are transmitted upwards sequentially to the piston rod, the damping structure, and the buffer strut structure. The folding structure can buffer the vertical vibrations and avoid damage to the nose landing gear.

[0044] Optionally, the buffer support structure includes a plunger rod, a piston, and a damping valve. The plunger rod is inserted into one end of the piston, the damping valve is disposed inside the piston, and the other end of the piston is connected to the piston rod via an upper cam and a lower cam.

[0045] Optionally, the top of the outer tube is connected to the landing gear mounting joint, and the bottom of the outer tube is connected to the anti-sway structure.

[0046] Specifically, the buffer strut is connected to the fuselage via the landing gear mounting joint. The outer cylinder completely encloses the buffer strut structure and its part connected to the landing gear mounting joint, connecting the buffer strut structure and the landing gear mounting joint to the fuselage as a whole. The three are relatively stable in the circumferential direction. The buffer strut structure adopts a relatively mature structural design, which only reduces vertical vibration of the nose landing gear. The anti-sway structure set at the lower end of the buffer strut structure is to solve the problem of excessive circumferential sway of the piston rod driven by the wheel.

[0047] Optionally, the anti-sway structure includes:

[0048] The lower bushing assembly has an inner circumference that is sealed to the piston rod, and an outer side of the lower bushing assembly that is screwed to the outer cylinder.

[0049] An outer bushing assembly is fitted around the outer periphery of the piston rod. The lower end of the outer bushing assembly is sealed to the piston rod. An outer ring assembly is provided between the upper end of the outer bushing assembly and the piston rod. The outer ring assembly is threaded to the outer bushing assembly. The outer periphery of the outer ring assembly is provided with mounting holes that are hinged to the torque arm assembly.

[0050] The inner ring assembly is disposed between the outer cylinder and the lower bushing assembly. The outer cylinder and the lower bushing assembly clamp and fix the inner ring assembly, and the inner ring assembly and the outer ring assembly rotate relative to each other.

[0051] Multiple arc-shaped springs are positioned between the inner ring assembly and the outer ring assembly to slow down the relative rotational speed between them.

[0052] Specifically, the outer circumference of the anti-sway structure is the outer cylinder, and the inner circumference of the anti-sway structure is the piston rod. Since the lower bushing assembly is screwed to the outer cylinder, and the inner ring body can be clamped and fixed through the outer cylinder and the lower bushing assembly, when the wheel drives the wheel fork assembly to swing, the torque arm assembly is hinged to the outer ring body assembly, while the inner ring body assembly and the outer cylinder remain stable. This forms a relative rotation between the outer ring body assembly and the inner ring body assembly. During the rotation, the arc spring provides buffering, which has good buffering performance and anti-sway performance.

[0053] Optionally, the outer ring assembly includes an outer ring body, the outer periphery of which is fitted to the outer bushing assembly through a first sealing gasket and a first wear-resistant gasket, and at least two first blades are uniformly arranged on the inner periphery of the outer ring body, with a first blade sealing gasket and a first blade wear-resistant gasket provided on the first blade.

[0054] Specifically, the outer ring body is positioned between the outer cylinder and the outer bushing assembly. The lower end of the outer ring body is connected to the outer bushing assembly by a threaded connection. The inner circumference of the upper end of the outer ring body is sealed to the outer circumference of the outer cylinder through a first sealing gasket and a first wear-resistant gasket. Multiple first blades can be provided on the inner circumference of the outer ring body. A first blade sealing gasket and a first blade wear-resistant strip are installed at the outer end of the first blade, which can seal the space between the inner ring body assembly and the outer ring body assembly.

[0055] Optionally, the inner ring assembly includes an inner ring body, which is limited and fixed by the outer cylinder and the lower bushing assembly. The inner circumference of the inner ring body is in contact with the outer cylinder by a second sealing gasket and a second wear-resistant gasket. The outer circumference of the inner ring body should be provided with at least two second blades, and the second blades are provided with a second blade sealing gasket and a second blade wear-resistant gasket.

[0056] Specifically, the inner ring is positioned between the outer cylinder and the lower bushing assembly. The inner ring is fixed by adjusting the screw connection between the outer cylinder and the lower bushing assembly. The inner circumference of the inner ring fits against the outer circumference of both the outer cylinder and the lower bushing assembly, and is sealed by a second sealing gasket and a second wear-resistant gasket. Multiple second blades are provided on the outer circumference of the inner ring, and second blade sealing gaskets and second blade wear-resistant gaskets are provided at the outer ends of the second blades. This also improves the sealing performance of the space between the inner ring assembly and the outer ring assembly, and reduces the wear on the surface of the parts caused by rotation.

[0057] Optionally, the number of second blades is the same as that of first blades, and the arc-shaped springs are respectively disposed between the first blades and the second blades.

[0058] Specifically, a cavity is formed between the inner ring and the outer ring. An arc spring is installed between adjacent first and second blades. When the wheel swings and transmits the force to the outer ring through the torsion arm assembly, the first blade will start to rotate. Since the inner ring and the outer cylinder always maintain a relatively fixed position, the first and second blades will start to squeeze the arc spring. The arc spring reduces the rotation of the outer ring assembly through its own elasticity. When the external force disappears, the arc spring can also maintain its own elasticity, so that the wheel and tire will automatically remain neutral.

[0059] Optionally, the second blade has a damping hole, and the space between the outer ring and the inner ring is filled with damping fluid.

[0060] Specifically, aviation hydraulic oil is injected into the space between the inner ring body, the outer ring body, and the adjacent first and second blades. When the outer ring body rotates, the inner blades of the green grape squeeze the oil, which is then passed through the damping holes on the inner ring body to form an oil damping force that hinders the rotation of the outer ring body and dissipates the oscillation energy.

[0061] Optionally, the lower bushing assembly includes a lower bushing, the outer bushing assembly includes an outer bushing, protective rings are provided between the lower bushing and the piston rod and between the outer bushing and the piston rod, and a dustproof ring is provided between the lower bushing and the outer cylinder.

[0062] Specifically, the lower bushing and the outer cylinder are threaded together, and their positions are relatively fixed. A dustproof ring prevents foreign objects from entering the anti-sway structure. The inner circumference of the lower bushing and the piston rod are sealed together. A protective ring is used to improve the sealing between the lower bushing and the piston rod and to ensure that the piston rod can move normally within the lower bushing. The outer bushing includes an upper barrel-shaped part and a lower barrel-shaped part. The diameter of the upper barrel-shaped part is larger than that of the lower barrel-shaped part. The lower barrel-shaped part and the piston rod are sealed together by a protective ring to ensure the normal extension and retraction of the piston rod. The upper barrel-shaped part is used to accommodate the inner ring assembly, the outer ring assembly, the lower end of the outer cylinder, and the lower bushing assembly.

[0063] Example

[0064] like Figures 1 to 9 As shown, the present invention provides a small-volume nose landing gear with integrated anti-sway function, comprising:

[0065] The buffer strut structure 2 has a landing gear mounting joint 1 at its upper end, and the lower end of the buffer strut structure 2 is connected to the upper end of the piston rod 4. The outer periphery of the buffer strut structure 2 is fitted with an outer cylinder 14.

[0066] The anti-sway structure 3 is set on the outer periphery of the connection of the piston rod 4, and the upper end of the anti-sway structure 3 is connected to the outer cylinder 14;

[0067] The upper end of the wheel fork assembly 5 is connected to the lower end of the piston rod 4, and the lower end of the wheel fork assembly 5 is connected to the wheel 6.

[0068] The torsion arm assembly 7 is connected at both ends to the anti-sway structure 3 and the wheel fork assembly 5, respectively.

[0069] In this embodiment, the buffer support structure 2 includes a plunger rod 8, a piston 9, and a damping valve 10. The plunger rod 8 is inserted into one end of the piston 9, the damping valve 10 is disposed inside the piston 9, and the other end of the piston 9 is connected to the piston rod 4 through an upper cam 11 and a lower cam 12.

[0070] In this embodiment, the top end of the outer cylinder 14 is connected to the landing gear mounting joint 1, and the lower end of the outer cylinder 14 is connected to the anti-sway structure 3.

[0071] In this embodiment, the anti-sway structure 3 includes:

[0072] The lower bushing assembly 17 is sealed to the piston rod 4 on its inner circumference, and the outer side of the lower bushing assembly 17 is screwed to the outer cylinder 14.

[0073] The outer bushing assembly 18 is sleeved on the outer periphery of the piston rod 4. The lower end of the outer bushing assembly 18 is sealed to the piston rod 4. An outer ring assembly 15 is provided between the upper end of the outer bushing assembly 18 and the piston rod 4. The outer ring assembly 15 is threaded to the outer bushing assembly 18. The outer periphery of the outer ring assembly 15 is provided with a mounting hole that is hinged to the torque arm assembly 7.

[0074] The inner ring assembly 16 is disposed between the outer cylinder 14 and the lower bushing assembly 17. The outer cylinder 14 and the lower bushing assembly 17 clamp and fix the inner ring assembly 16, and the inner ring assembly 16 and the outer ring assembly 15 rotate relative to each other.

[0075] Multiple arc-shaped springs 19 are disposed between the inner ring assembly 16 and the outer ring assembly 15. The arc-shaped springs 19 reduce the relative rotational speed between the inner ring assembly 16 and the outer ring assembly 15.

[0076] In this embodiment, the outer ring assembly 15 includes an outer ring body. The outer periphery of the outer ring body is attached to the outer bushing assembly 18 through a first sealing gasket and a first wear-resistant gasket. At least two first blades 20 are uniformly arranged on the inner periphery of the outer ring body. A first blade sealing gasket and a first blade wear-resistant gasket are provided on the first blade 20.

[0077] In this embodiment, the inner ring assembly 16 includes an inner ring body, which is limited and fixed to the lower bushing assembly 17 by the outer cylinder 14. The inner circumference of the inner ring body is attached to the outer cylinder 14 by the second sealing gasket and the second wear-resistant gasket. At least two second blades 21 should be provided on the outer circumference of the inner ring body. The second blades 21 are provided with a second blade sealing gasket and a second blade wear-resistant gasket.

[0078] In this embodiment, the number of second blades 21 is the same as that of first blades 20, and arc springs 19 are respectively disposed between the first blades 20 and the second blades 21.

[0079] In this embodiment, the second blade 21 has a damping hole 13, and the space between the outer ring and the inner ring is filled with damping fluid.

[0080] In this embodiment, the lower bushing assembly 17 includes a lower bushing, the outer bushing assembly 18 includes an outer bushing, protective rings are provided between the lower bushing and the piston rod 4 and between the outer bushing and the piston rod 4, and a dustproof ring is provided between the lower bushing and the outer cylinder 14.

[0081] In summary, aircraft using this nose landing gear experience frequent shimmy during takeoff. The wheel 6 and tire transmit the shimmy energy to the anti-shimmy structure 3 via the wheel fork assembly 5 and the torsion arm assembly 7. The outer ring assembly 15 has mounting holes for connection with the torsion arm assembly 7, and the outer ring is fixedly connected to the torsion arm assembly 7. When the anti-shimmy structure 3 is working, the outer ring converts the shimmy energy into its own rotation around its axis. The inner ring assembly 16, connected to the outer cylinder 14, is fixed relative to the landing gear strut. Four cavities are formed between the inner and outer rings, filled with aviation hydraulic oil. When the outer ring rotates, the first blade 20 pushes the oil within the cavity, creating a damping force through the damping orifice 13 on the second blade 21, which hinders the rotation of the outer ring and dissipates the shimmy energy. The first blade 20 and the second blade 21 are respectively equipped with sealing gaskets and wear-resistant pads to form a sealed cavity and reduce wear on the surface of the parts caused by rotation. Meanwhile, the cavity contains four arc-shaped springs 19, which maintain a certain relative position between the outer and inner rings. Therefore, when the external force disappears, the wheel 6 and the tire will automatically maintain their neutral position under the action of the spring force. This nose landing gear effectively saves space in the landing gear bay, reduces the weight of the landing gear, and has good cushioning and anti-sway performance.

[0082] The various embodiments of the present invention have been described above. These descriptions are exemplary and not exhaustive, nor are they limited to the disclosed embodiments. Many modifications and variations will be apparent to those skilled in the art without departing from the scope and spirit of the described embodiments.

Claims

1. A compact front landing gear with integrated anti-sway function, characterized in that, include: The buffer strut structure has a landing gear mounting joint at the upper end, the lower end of the buffer strut structure is connected to the upper end of the piston rod, and an outer cylinder is sleeved around the outer periphery of the buffer strut structure. A sway-reducing structure is disposed on the outer periphery of the connection point of the piston rod, and the upper end of the sway-reducing structure is connected to the outer cylinder; The upper end of the wheel fork assembly is connected to the lower end of the piston rod, and the lower end of the wheel fork assembly is connected to the wheel. The torsion arm assembly is connected at both ends to the anti-sway structure and the wheel fork assembly, respectively. The buffer support structure includes a plunger rod, a piston, and a damping valve. The plunger rod is inserted into one end of the piston, the damping valve is disposed inside the piston, and the other end of the piston is connected to the piston rod via an upper cam and a lower cam. The top end of the outer cylinder is connected to the landing gear mounting joint, and the bottom end of the outer cylinder is connected to the anti-sway structure. The damping structure includes: The lower bushing assembly has its inner circumference sealed to the piston rod, and its outer side is screwed to the outer cylinder. An outer bushing assembly is sleeved on the outer periphery of the piston rod. The lower end of the outer bushing assembly is sealed to the piston rod. An outer ring assembly is provided between the upper end of the outer bushing assembly and the piston rod. The outer ring assembly is threaded to the outer bushing assembly. The outer periphery of the outer ring assembly is provided with a mounting hole that is hinged to the torque arm assembly. An inner ring assembly is disposed between the outer cylinder and the lower bushing assembly. The outer cylinder and the lower bushing assembly clamp and fix the inner ring assembly, and the inner ring assembly and the outer ring assembly are rotatably engaged relative to each other. Multiple arc-shaped springs are disposed between the inner ring assembly and the outer ring assembly, and the arc-shaped springs reduce the relative rotational speed of the inner ring assembly and the outer ring assembly.

2. The nose landing gear with integrated anti-sway function in a small volume as described in claim 1, characterized in that, The outer ring assembly includes an outer ring body. The outer periphery of the outer ring body is fitted to the outer bushing assembly through a first sealing gasket and a first wear-resistant gasket. At least two first blades are uniformly arranged on the inner periphery of the outer ring body. A first blade sealing gasket and a first blade wear-resistant gasket are provided on the first blade.

3. The nose landing gear with integrated anti-sway function in a small volume as described in claim 2, characterized in that, The inner ring assembly includes an inner ring body, which is fixed to the lower bushing assembly by the outer cylinder. The inner circumference of the inner ring body is in contact with the outer cylinder by a second sealing gasket and a second wear-resistant gasket. At least two second blades should be provided on the outer circumference of the inner ring body, and a second blade sealing gasket and a second blade wear-resistant gasket are provided on the second blades.

4. The nose landing gear with integrated anti-sway function in a small volume as described in claim 3, characterized in that, The number of the second blade is the same as that of the first blade, and the arc-shaped springs are respectively disposed between the first blade and the second blade.

5. The nose landing gear with integrated anti-sway function in a small volume as described in claim 3, characterized in that, The second blade has a damping hole, and the space between the outer ring and the inner ring is filled with damping fluid.

6. The nose landing gear with integrated anti-sway function in a small volume as described in claim 1, characterized in that, The lower bushing assembly includes a lower bushing, the outer bushing assembly includes an outer bushing, protective rings are provided between the lower bushing and the piston rod and between the outer bushing and the piston rod, and a dustproof ring is provided between the lower bushing and the outer cylinder.

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