Airplane and shimmy damper thereof

Abstract

The invention relates to the technical field of mechanical vibration control, and discloses an aircraft and a shimmy damper thereof. An adjusting part is arranged on the periphery of an adjusting rod of the shimmy damper, and a first damping adjusting hole is formed in the adjusting part. The piston piece is provided with a second damping adjusting hole, and the first damping adjusting hole and the second damping adjusting hole are oppositely arranged in the axial direction. Through relative rotation between the adjusting rod and the piston piece, the overlapping area of the first damping adjusting hole and the second damping adjusting hole is adjusted, the flow of damping fluid capable of passing through the first damping adjusting hole and the second damping adjusting hole is changed, and damping adjustment is achieved. Damping adjustment of the shimmy damper can be achieved through a simple system, a complex sensor and a complex control system do not need to be additionally installed, the shimmy damper can be simplified, the system complexity of the shimmy damper is greatly reduced, the weight and the size of the shimmy damper are reduced, and the use cost of the shimmy damper is also reduced. The shimmy damper is particularly suitable for application scenes such as small airplanes.

Description

Technical Field

[0001] The present application relates to the technical field of mechanical vibration control, and in particular to an aircraft and a shimmy damper thereof. Background Art

[0002] During taxiing, the nose wheel can swing sideways due to external disturbances, causing nose gear shimmy. This can cause the nose gear structure and fuselage to vibrate, severely impacting the aircraft's stability during taxiing. Gear shimmy is a constant threat to aircraft safety, and addressing it is an essential area of ​​aviation research.

[0003] One of the main causes of shimmy is insufficient torsional stiffness and damping in the nose landing gear struts. The current solution to this problem is to use a shimmy damper to dampen the torsional direction to suppress the divergence of oscillations. In practice, a shimmy damper must balance shimmy reduction with aircraft stability in the taxiing direction. Too little damping will make shimmy reduction difficult, while too much damping will lead to unstable response speed during turning maneuvers. Therefore, it is necessary to adjust the damping of the shimmy damper according to actual conditions. However, the damping adjustment systems in current shimmy dampers often require the addition of complex sensors and control systems, resulting in excessive system complexity. Summary of the Invention

[0004] The present application provides an aircraft and a shimmy damper thereof, which are conducive to simplifying the shimmy damper and are particularly suitable for application scenarios such as small aircraft.

[0005] The present application provides an aircraft. The aircraft includes a landing gear, a steering mechanism, and a shimmy damper, wherein the shimmy damper is connected to the landing gear and the steering mechanism, respectively. The shimmy damper has an axial direction and a reference plane perpendicular to each other. The shimmy damper includes a housing, wherein a first chamber for storing a damping fluid is provided inside the housing. The shimmy damper also includes an adjusting rod, which is axially movably disposed in the first chamber, an adjusting portion is provided on the outer periphery of the adjusting rod, the adjusting portion is located in the first chamber, and the adjusting portion is provided with a first damping adjustment hole. The shimmy damper also includes a piston member, which is disposed in the first chamber, the piston member is disposed on the outer periphery of the adjusting rod, and the piston member can move axially synchronously with the adjusting rod; the piston member is provided with a second damping adjustment hole, and the first damping adjustment hole and the second damping adjustment hole are axially arranged relative to each other; as the landing gear shimmies, the adjusting rod can move axially relative to the first chamber, so that the damping fluid passes through the first damping adjustment hole and the second damping adjustment hole. The adjusting rod and the piston are configured to be relatively rotatable so as to adjust an overlapping area between an orthographic projection of the first damping adjusting hole on the reference plane and an orthographic projection of the second damping adjusting hole on the reference plane.

[0006] In one embodiment of the present application, at least one of the first damping adjustment hole and the second damping adjustment hole is a target damping adjustment hole, and the target damping adjustment hole extends along the circumference of the adjusting rod, and the two ends of the target damping adjustment hole in the circumferential direction of the adjusting rod are respectively the first end and the second end; along the circumference of the adjusting rod and in the direction from the first end to the second end, the width of the target damping adjustment hole gradually increases.

[0007] In one embodiment of the present application, the piston member includes: a first piston portion, located on one side of the adjusting portion in the axial direction, and the first piston portion is provided with a second damping adjustment hole; and a second piston portion, located on the other side of the adjusting portion in the axial direction, and the second piston portion is provided with an avoidance hole passing through the axial direction, and the avoidance hole is arranged opposite to the first damping adjustment hole in the axial direction.

[0008] In one embodiment of the present application, the orthographic projection of the first damping adjustment hole on the reference plane is within the orthographic projection of the avoidance hole on the reference plane.

[0009] In one embodiment of the present application, the adjusting portion is further provided with a first limiting portion, and the first piston portion and / or the second piston portion is provided with a second limiting portion. The first limiting portion and the second limiting portion cooperate to limit the maximum rotation angle between the adjusting rod and the piston member, so that the orthographic projection of the first damping adjustment hole on the reference plane is in the orthographic projection of the avoidance hole on the reference plane.

[0010] In one embodiment of the present application, the shell includes: an outer cylinder having a first chamber therein; and a first end cover, which is arranged on the axial end of the first chamber, and the first end cover and the second piston part are located on the same side of the adjusting part; wherein, one of the first end cover and the second piston part is provided with a stop protrusion, and the other is provided with a stop groove, the stop protrusion is embedded in the stop groove, and the stop protrusion and the stop groove cooperate to limit the relative rotation between the first end cover and the second piston part.

[0011] In one embodiment of the present application, the second piston part includes: a first sub-part, which is provided with a avoidance hole; and a second sub-part, which is connected to the side of the first sub-part facing away from the adjusting part; wherein, a avoidance groove is provided on the side of the first end cover close to the adjusting part, and one of the groove walls of the second sub-part and the avoidance groove is provided with a rotation-stop protrusion, and the other is provided with a rotation-stop groove.

[0012] In one embodiment of the present application, the first damping adjustment hole and the second damping adjustment hole are both through-hole structures extending axially, and the first damping adjustment hole and the second damping adjustment hole are both configured to allow the damping fluid to pass through the first damping adjustment hole and the second damping adjustment hole from either side in the axial direction.

[0013] In one embodiment of the present application, the interior of the shell further has a second chamber axially separated from the first chamber, and the adjusting rod is also axially movably arranged in the second chamber; the damper also includes: an elastic member, which is arranged in the second chamber, and the elastic member is respectively connected to the shell and the adjusting rod, and the elastic member is used to drive the adjusting rod to reset.

[0014] In one embodiment of the present application, a retaining ring located in the second chamber is further provided on the outer periphery of the adjusting rod; the elastic member includes: a first elastic member, located on one side of the retaining ring in the axial direction; and a second elastic member, located on the other side of the retaining ring in the axial direction, and the first elastic member and the second elastic member cooperate to drive the adjusting rod to reset.

[0015] In one embodiment of the present application, the shimmy damper further includes: a sealing assembly, which is axially located between the first chamber and the second chamber, and the sealing assembly is respectively sealingly connected to the adjusting rod and the inner wall of the housing to seal the first chamber.

[0016] In one embodiment of the present application, a first connecting member is provided on the outer wall of the shell, and a second connecting member is provided at the end of the adjusting rod. One of the first connecting member and the second connecting member is connected to the landing gear, and the other is connected to the steering mechanism.

[0017] In one embodiment of the present application, a locking member is provided at the end of the adjusting rod, and the locking member can be switched between a locked state and a released state; when the locking member is switched to the locked state, the adjusting rod is restricted from rotating relative to the second connecting member; when the locking member is switched to the released state, the adjusting rod is allowed to rotate relative to the second connecting member while the second connecting member remains connected to the landing gear.

[0018] Correspondingly, the present application also provides a shimmy damper, which has mutually perpendicular axial directions and reference planes, and comprises: a housing having a first chamber for storing a damping fluid; an adjusting rod movably arranged in the first chamber along the axial direction, an adjusting portion being arranged on the outer periphery of the adjusting rod, the adjusting portion being located in the first chamber, and the adjusting portion being provided with a first damping adjusting hole; one of the housing and the adjusting rod being used to connect to the landing gear of the aircraft, and the other being used to connect to the steering mechanism of the aircraft; and a piston member being arranged in the first chamber, the piston member being arranged on the outer periphery of the adjusting rod, and the piston member can move axially synchronously with the adjusting rod; the piston member is provided with a second damping adjustment hole, and the first damping adjustment hole and the second damping adjustment hole are arranged axially opposite to each other; as the landing gear yaws, the adjusting rod can move axially relative to the first chamber, so that the damping fluid passes through the first damping adjustment hole and the second damping adjustment hole; wherein, the adjusting rod and the piston member are configured to be able to rotate relative to each other to adjust the overlapping area of ​​the orthographic projection of the first damping adjustment hole on the reference plane and the orthographic projection of the second damping adjustment hole on the reference plane.

[0019] In one embodiment of the present application, at least one of the first damping adjustment hole and the second damping adjustment hole is a target damping adjustment hole, and the target damping adjustment hole extends along the circumference of the adjusting rod, and the two ends of the target damping adjustment hole in the circumferential direction of the adjusting rod are respectively the first end and the second end; along the circumference of the adjusting rod and in the direction from the first end to the second end, the width of the target damping adjustment hole gradually increases.

[0020] In one embodiment of the present application, the first damping adjustment hole and the second damping adjustment hole are both through-hole structures extending axially, and the first damping adjustment hole and the second damping adjustment hole are both configured to allow the damping fluid to pass through the first damping adjustment hole and the second damping adjustment hole from either side in the axial direction.

[0021] The present application provides an aircraft and a shimmy damper therefor, unlike the prior art. The shimmy damper comprises an adjustment portion disposed on the outer periphery of an adjustment rod, the adjustment portion being provided with a first damping adjustment hole. A piston member is provided with a second damping adjustment hole, the first damping adjustment hole and the second damping adjustment hole being axially opposed to each other. As the landing gear shimmies, the adjustment rod is capable of axially moving relative to a first chamber within the housing, allowing damping fluid to flow through the first and second damping adjustment holes, thereby converting mechanical energy generated by the landing gear shimmy into heat energy for dissipation, thereby achieving shimmy reduction.

[0022] Furthermore, the adjusting rod and the piston member of the present application are configured to be able to rotate relative to each other so as to adjust the overlapping area of ​​the orthographic projection of the first damping adjustment hole on the reference plane and the orthographic projection of the second damping adjustment hole on the reference plane. The present application adjusts the overlapping area of ​​the first damping adjustment hole and the second damping adjustment hole by the relative rotation between the adjusting rod and the piston member, changes the flow rate of the damping fluid that can pass through the first damping adjustment hole and the second damping adjustment hole, and realizes damping adjustment. The present application can realize the damping adjustment of the shimmy damper through a relatively simple system, without the need to install complex sensors and control systems, which is conducive to simplifying the shimmy damper, greatly reducing the system complexity of the shimmy damper, reducing the weight and volume of the shimmy damper, and also reducing the cost of using the shimmy damper. The shimmy damper of the present application is particularly suitable for application scenarios such as small aircraft. BRIEF DESCRIPTION OF THE DRAWINGS

[0023] In order to more clearly illustrate the technical solutions in the embodiments of the present application, the following briefly introduces the drawings required for use in the description of the embodiments. Obviously, the drawings described below are only some embodiments of the present application. For those skilled in the art, other drawings can be obtained based on these drawings without creative work.

[0024] Figure 1 This is a structural schematic diagram of an embodiment of a landing gear for an aircraft of the present application;

[0025] Figure 2This is a structural diagram of an embodiment of the shimmy damper of the present application;

[0026] Figure 3 yes Figure 2 Schematic diagram of the cross-sectional structure of the shimmy damper shown;

[0027] Figure 4 This is a structural diagram of an embodiment of an adjusting rod of the present application;

[0028] Figure 5 This is a structural diagram of an embodiment of the first piston portion of the present application;

[0029] Figure 6 This is a structural schematic diagram of an embodiment of the overlapping state of the first damping adjustment hole and the second damping adjustment hole of the present application;

[0030] Figure 7 1 is a structural schematic diagram of another embodiment of the overlapping state of the first damping adjustment hole and the second damping adjustment hole of the present application;

[0031] Figure 8 This is a structural diagram of an embodiment of the regulating rod and piston member of the present application;

[0032] Figure 9 This is a structural diagram of an embodiment of the overlapping state of the avoidance hole and the first damping adjustment hole of the present application;

[0033] Figure 10 yes Figure 4 A schematic structural diagram of the adjustment rod from another perspective;

[0034] Figure 11 It is a structural schematic diagram of an embodiment of the first end cover of the present application.

[0035] Description of reference numerals:

[0036] 10 Landing gear; 11 Turning clamp; 20 Steering mechanism; 30 Shimmy damper; 31 Housing; 311 First chamber; 312 Outer cylinder; 313 First end cap; 314 Anti-rotation protrusion; 315 Anti-rotation groove; 316 Avoidance groove; 317 Second chamber; 318 First connecting member; 319 Second end cap; 32 Adjusting rod; 321 Adjusting portion; 322 First limiting portion; 323 Retaining ring; 324 Second connecting member; 325 Locking member; 33 Piston member; 331 First piston portion; 332 Second piston portion; 3321 first subsection; 3322 second subsection; 333 avoidance hole; 334 second limiting section; 34 elastic member; 341 first elastic member; 342 second elastic member; 35 sealing assembly; 351 sealing support; 352 fourth sealing member; 353 fifth sealing member; 361 first sealing member; 362 second sealing member; 363 third sealing member; 37 filling valve; 40 target damping adjustment hole; 40a first end; 40b second end; 41 first damping adjustment hole; 42 second damping adjustment hole. DETAILED DESCRIPTION

[0037] The technical solutions in the embodiments of the present application will be clearly and completely described below in conjunction with the drawings in the embodiments of the present application. Obviously, the described embodiments are only a part of the embodiments of the present application, rather than all the embodiments. Based on the embodiments in the present application, all other embodiments obtained by those skilled in the art without making creative work are within the scope of protection of the present application. In addition, it should be understood that the specific implementation methods described herein are only used to illustrate and explain the present application, and are not used to limit the present application. In the present application, unless otherwise specified, the directional words used, such as "up", "down", "left", and "right", generally refer to the up, down, left, and right of the device in actual use or working state, specifically the drawing direction in the accompanying drawings.

[0038] In this application, unless otherwise specified or limited, terms such as "connected," "connected," and "stacked" should be understood broadly. For example, they may refer to fixed connections, detachable connections, or integration; they may refer to direct connections or indirect connections through an intermediate medium; they may refer to internal communication between two components or interaction between two components. Those skilled in the art will understand the specific meanings of these terms in this application based on the specific circumstances.

[0039] This application provides an aircraft and a shimmy damper therefor, which are described in detail below. It should be noted that the order in which the following embodiments are described does not limit the preferred order of the embodiments of this application. Furthermore, the descriptions of each embodiment below have their own specific focus. For details not detailed in one embodiment, please refer to the relevant descriptions of other embodiments.

[0040] To address the technical issues related to the relatively complex damping adjustment system of a shimmy damper in the prior art, one embodiment of the present application provides an aircraft. The aircraft includes a landing gear, a steering mechanism, and a shimmy damper, the shimmy damper being connected to the landing gear and the steering mechanism, respectively. The shimmy damper has a mutually perpendicular axial direction and a reference plane. The shimmy damper includes a housing, within which is a first chamber for storing a damping fluid. The shimmy damper also includes an adjustment rod axially movably disposed within the first chamber. An adjustment portion is disposed on the outer periphery of the adjustment rod, the adjustment portion being located within the first chamber and having a first damping adjustment hole. The shimmy damper also includes a piston disposed within the first chamber, the piston being disposed on the outer periphery of the adjustment rod and capable of axially moving synchronously with the adjustment rod. The piston is provided with a second damping adjustment hole, the first and second damping adjustment holes being axially opposed to each other. As the landing gear yaws, the adjustment rod is capable of axially moving relative to the first chamber, allowing the damping fluid to pass through the first and second damping adjustment holes. The adjusting rod and the piston are configured to rotate relative to each other to adjust the overlapping area of ​​the orthographic projection of the first damping adjustment hole on the reference plane and the orthographic projection of the second damping adjustment hole on the reference plane.

[0041] See also Figure 1 , Figure 1 It is a structural schematic diagram of an embodiment of the landing gear of the aircraft of the present application.

[0042] In one embodiment, an aircraft includes a landing gear 10, a steering mechanism 20, and a shimmy damper 30. The shimmy damper 30 is connected to the landing gear 10 and the steering mechanism 20, respectively. The steering mechanism 20 is used to control the steering of the aircraft's front wheels. The mechanical energy generated by the shimmy of the landing gear 10 is converted into heat energy and dissipated by the shimmy damper 30, thereby achieving the purpose of shimmy reduction. Specifically, the shimmy damper 30 is connected to a turning clamp 11 on the landing gear 10. The driving force provided by the steering mechanism 20 acts on the turning clamp 11 through the shimmy damper 30, thereby controlling the steering of the aircraft's front wheels.

[0043] For details, please refer to Figures 2 to 5 The shimmy damper 30 has an axial direction X. The shimmy damper 30 includes a housing 31, which has a first chamber 311 for storing damping fluid. The shimmy damper 30 also includes an adjusting rod 32, which is movably disposed in the first chamber 311 along the axial direction X. The adjusting rod 32 is provided with an adjusting portion 321 on its outer periphery, which is located in the first chamber 311 and has a first damping adjustment hole 41. The shimmy damper 30 also includes a piston 33, which is disposed in the first chamber 311. The piston 33 is disposed on the outer periphery of the adjusting rod 32 and can move synchronously with the adjusting rod 32 along the axial direction X. The piston 33 is provided with a second damping adjustment hole 42, and the first damping adjustment hole 41 and the second damping adjustment hole 42 are disposed opposite each other in the axial direction X.

[0044] When the landing gear 10 shims, the adjustment rod 32 moves relative to the first chamber 311 along the axial direction X as the landing gear 10 deflects, causing the damping fluid to flow through the first and second damping adjustment holes 41, 42. Driven by the reciprocating movement of the adjustment rod 32 along the axial direction X, the damping fluid reciprocates through the first and second damping adjustment holes 41, 42 along the axial direction X. During this process, the damping fluid generates a damping force to suppress shimmy, thereby converting the mechanical energy generated by the shimmy of the landing gear 10 into heat energy for dissipation, thereby achieving the purpose of reducing shimmy.

[0045] Also, please refer to Figures 6 and 7 In this embodiment, the damper 30 further has a reference plane α perpendicular to the axial direction X. The adjusting rod 32 and the piston member 33 are configured to be able to rotate relative to each other to adjust the overlapping area of ​​the orthographic projection of the first damping adjustment hole 41 on the reference plane α and the orthographic projection of the second damping adjustment hole 42 on the reference plane α. In this embodiment, the overlapping area of ​​the first damping adjustment hole 41 and the second damping adjustment hole 42 is adjusted by relative rotation between the adjusting rod 32 and the piston member 33, thereby changing the flow rate of the damping fluid that can pass through the first damping adjustment hole 41 and the second damping adjustment hole 42 to achieve damping adjustment. In this embodiment, the damping adjustment of the damper 30 can be achieved through a relatively simple system without the need to install complex sensors and control systems, which is conducive to simplifying the damper 30, greatly reducing the system complexity of the damper 30, reducing the weight and volume of the damper 30, and also reducing the cost of using the damper 30. The damper 30 of this embodiment is particularly suitable for application scenarios such as small aircraft.

[0046] Compared to shimmy dampers that require numerous sensors for real-time, precise control, the shimmy damper 30 of this embodiment does not require a complex sensor system or control system, significantly reducing its system complexity, weight, and size, making it particularly suitable for applications such as small aircraft. Compared to magnetorheological shimmy dampers, which require an electric current to alter the viscosity of the damping fluid to adjust the damping level, this embodiment changes the flow rate in the effective damping channel formed by the first and second damping adjustment holes 41, 42 through a simple rotational operation between the adjustment rod 32 and the piston 33. This makes it more convenient, practical, and easier to maintain, offering advantages such as high reliability, low manufacturing and maintenance costs, and simple operation. Compared to technical solutions that use springs instead of damping fluid and must consider the potential fatigue effects of the springs, the shimmy damper 30 of this embodiment relies primarily on the damping fluid to provide damping force, making it safer and more reliable.

[0047] In one embodiment, at least one of the first damping adjustment hole 41 and the second damping adjustment hole 42 is a target damping adjustment hole 40. The target damping adjustment hole 40 extends along the circumference of the adjustment rod 32. The target damping adjustment hole 40 has two circumferential ends, a first end 40a and a second end 40b, respectively. The width of the target damping adjustment hole 40 gradually increases along the circumference of the adjustment rod 32, in a direction from the first end 40a toward the second end 40b.

[0048] Figure 6 and Figure 7 The second damping adjustment hole 42 is exemplarily shown as the target damping adjustment hole 40. The width of the target damping adjustment hole 40 should be understood as the size of the target damping adjustment hole 40 at various positions in the radial direction of the adjustment rod 32 in the circumferential direction of the adjustment rod 32. The first damping adjustment hole 41 can be a circular hole, etc. When the adjustment rod 32 rotates relative to the piston member 33, the first damping adjustment hole 41 and the second damping adjustment hole 42 are relatively arranged at different positions in the circumferential direction of the adjustment rod 32, and the overlapping area of ​​the first damping adjustment hole 41 and the second damping adjustment hole 42 changes, so that the flow area of ​​the effective damping channel formed by the first damping adjustment hole 41 and the second damping adjustment hole 42 changes, thereby achieving damping adjustment.

[0049] For example, Figure 6 The first damping adjustment hole 41 is shown to be located at the first end 40a, at which point the overlapping area between the first damping adjustment hole 41 and the second damping adjustment hole 42 is minimal; Figure 7 It is shown that the first damping adjustment hole 41 is located at the second end 40 b , and at this time, the overlapping area of ​​the first damping adjustment hole 41 and the second damping adjustment hole 42 is the largest.

[0050] Of course, in other embodiments of the present application, the first damping adjustment hole 41 and the second damping adjustment hole 42 are not limited to being designed as the above-mentioned target damping adjustment hole 40. The first damping adjustment hole 41 and the second damping adjustment hole 42 can also be designed as round holes or waist-shaped holes, etc., and the overlapping area of ​​the first damping adjustment hole 41 and the second damping adjustment hole 42 can also be adjusted by rotating the adjusting rod 32 relative to the piston part 33, which is not limited here.

[0051] Please also refer to Figure 8 , Figure 8 It is a structural schematic diagram of an embodiment of the adjusting rod and the piston member of the present application.

[0052] In one embodiment, the piston member 33 includes a first piston portion 331 and a second piston portion 332. The first piston portion 331 is located on one side of the adjustment portion 321 in the axial direction X and is provided with a second damping adjustment hole 42. The second piston portion 332 is located on the other side of the adjustment portion 321 in the axial direction X. The second piston portion 332 is provided with a relief hole 333 extending along the axial direction X. The relief hole 333 is arranged opposite the first damping adjustment hole 41 in the axial direction X.

[0053] In the above manner, when the adjusting rod 32 moves along the axial direction X and toward the side where the first piston part 331 is located, the adjusting rod 32 can drive the entire piston part 33 to move synchronously through the first piston part 331, and when the adjusting rod 32 moves along the axial direction X and toward the side where the second piston part 332 is located, the adjusting rod 32 can drive the entire piston part 33 to move synchronously through the second piston part 332, so that the adjusting rod 32 drives the piston part 33 to move back and forth synchronously along the axial direction X, thereby causing the damping fluid to flow back and forth through the first damping adjustment hole 41 and the second damping adjustment hole 42.

[0054] Furthermore, when the landing gear 10 experiences shimmy, as the landing gear 10 deflects, the adjustment rod 32 can move relative to the first chamber 311 along the axial direction X, allowing the damping fluid to pass through the first damping adjustment hole 41, the second damping adjustment hole 42, and the avoidance hole 333. Driven by the reciprocating movement of the adjustment rod 32 along the axial direction X, the damping fluid reciprocates along the axial direction X through the first damping adjustment hole 41, the second damping adjustment hole 42, and the avoidance hole 333. During this process, the damping fluid generates a damping force to suppress shimmy, thereby converting the mechanical energy generated by the shimmy of the landing gear 10 into heat energy for dissipation, thereby achieving the purpose of shimmy reduction. In this embodiment, the avoidance hole 333 is provided to ensure that the damping fluid can reciprocate through the second piston portion 332, thereby ensuring that the damping fluid can reciprocate through the first damping adjustment hole 41 and the second damping adjustment hole 42.

[0055] For details, please refer to Figure 9 The orthographic projection of the first damping adjustment hole 41 on the reference plane α is in the orthographic projection of the avoidance hole 333 on the reference plane α, thereby ensuring that the damping fluid can flow back and forth through the first damping adjustment hole 41 and the second damping adjustment hole 42.

[0056] It should be noted that the first damping adjustment hole 41, the second damping adjustment hole 42, and the avoidance hole 333 are all through-hole structures extending along the axial direction X. They are configured to allow damping fluid to pass through them from either side in the axial direction X. The number of first damping adjustment holes 41, the number of second damping adjustment holes 42, and the avoidance hole 333 is arranged to be a plurality of holes spaced apart along the circumference of the adjustment rod 32. As a result, when the adjustment rod 32 moves toward one side in the axial direction X, the damping fluid can simultaneously flow through the plurality of first damping adjustment holes 41, the second damping adjustment holes 42, and the avoidance hole 333.

[0057] Please also refer to Figure 10 , Figure 10 yes Figure 4 A structural schematic diagram of the adjustment rod from another perspective is shown.

[0058] In one embodiment, the adjusting portion 321 is further provided with a first limiting portion 322, and the first piston portion 331 and / or the second piston portion 332 is provided with a second limiting portion 334. The first limiting portion 322 and the second limiting portion 334 cooperate to limit the maximum rotation angle between the adjusting rod 32 and the piston member 33, so that the orthographic projection of the first damping adjustment hole 41 on the reference plane α is in the orthographic projection of the avoidance hole 333 on the reference plane α.

[0059] Figure 4 and Figure 5 The exemplary embodiment shows that the first stopper 322 of the adjustment portion 321 is a long groove extending along the circumference of the adjustment rod 32. The first piston portion 331 is provided with a second stopper 334, which is a raised structure and is movably embedded in the first stopper 322. When the adjustment rod 32 rotates relative to the piston member 33, the second stopper 334 moves synchronously along the first stopper 322 until it reaches the end of the first stopper 322, thereby limiting the maximum rotation angle between the adjustment rod 32 and the piston member 33.

[0060] Please also refer to Figure 11 , Figure 11 It is a structural schematic diagram of an embodiment of the first end cover of the present application.

[0061] In one embodiment, the housing 31 includes an outer cylinder 312 and a first end cap 313. The outer cylinder 312 defines a first chamber 311. The first end cap 313 covers the end of the first chamber 311 in the axial direction X, and the first end cap 313 and the second piston portion 332 are located on the same side of the adjustment portion 321. One of the first end cap 313 and the second piston portion 332 is provided with a rotation-stopping protrusion 314, and the other is provided with a rotation-stopping groove 315. The rotation-stopping protrusion 314 is embedded in the rotation-stopping groove 315. The rotation-stopping protrusion 314 and the rotation-stopping groove 315 cooperate to limit relative rotation between the first end cap 313 and the second piston portion 332. The second piston portion 332 and the first piston portion 331 are locked together by screws, thereby limiting relative rotation of the first piston portion 331.

[0062] In the above manner, the first end cap 313 of this embodiment is fastened to the outer cylinder 312 via fasteners such as bolts. A rotation-stopping protrusion 314 and a rotation-stopping groove 315 are provided between the first end cap 313 and the second piston portion 332 to prevent rotation. The first piston portion 331 and the second piston portion 332 are locked together via screws, further preventing rotation of the piston member 33. This prevents the piston member 33 from rotating synchronously with the adjusting rod 32 when the adjusting rod 32 rotates relative to the piston member 33, thereby ensuring that the overlapping area of ​​the first damping adjustment hole 41 and the second damping adjustment hole 42 is changed, thereby ensuring that the damping adjustment function is achieved.

[0063] Furthermore, the second piston portion 332 includes a first sub-portion 3321 and a second sub-portion 3322. The first sub-portion 3321 is provided with a relief hole 333, and the second sub-portion 3322 is connected to the side of the first sub-portion 3321 facing away from the adjustment portion 321. A relief groove 316 is provided on the side of the first end cap 313 near the adjustment portion 321. One of the groove walls of the second sub-portion 3322 and the relief groove 316 is provided with a rotation-stopping protrusion 314, and the other is provided with a rotation-stopping groove 315.

[0064] Optionally, the damper 30 further includes a first seal 361 and a second seal 362. The first seal 361 is sleeved around the outer periphery of the first end cap 313, and a seal is established between the first end cap 313 and the outer cylinder 312 via the first seal 361. The adjustment rod 32 extends through the first end cap 313. The second seal 362 is sleeved around the outer periphery of the adjustment rod 32, and a seal is established between the adjustment rod 32 and the first end cap 313 via the second seal 362. The first seal 361 and the second seal 362 cooperate to seal the first chamber 311, minimizing leakage of the damping fluid in the first chamber 311.

[0065] The shimmy damper 30 also includes a third seal 363, which is sleeved around the outer circumference of the piston 33. The third seal 363 forms a seal between the piston 33 and the inner wall of the outer tube 312. The piston 33 is also movable relative to the outer tube 312 in the axial direction X. This ensures that the damping fluid flows as much as possible through the first damping adjustment hole 41 and the second damping adjustment hole 42, reciprocating through the adjustment portion 321 on the adjustment rod 32 and the piston 33, thereby ensuring that the damping fluid provides the set damping force.

[0066] In one embodiment, the shimmy damper 30 further includes a sealing assembly 35, which is located in the axial direction X on the side of the piston member 33 facing away from the first end cap 313. The sealing assembly 35 is sealingly connected to the adjustment rod 32 and the inner wall of the housing 31, respectively, to seal the first chamber 311. In other words, the sealing assembly 35, the first sealing member 361, and the second sealing member 362 of this embodiment cooperate to seal the first chamber 311, thereby minimizing leakage of the damping fluid in the first chamber 311.

[0067] Specifically, the sealing assembly 35 includes a sealing support 351, a fourth sealing member 352, and a fifth sealing member 353. The sealing support 351 is sleeved on the outer periphery of the adjusting rod 32. The fourth sealing member 352 is sleeved on the outer periphery of the adjusting rod 32, and the fourth sealing member 352 is located between the adjusting rod 32 and the sealing support 351, thereby achieving a seal between the adjusting rod 32 and the sealing support 351. The fifth sealing member 353 is sleeved on the outer periphery of the sealing support 351, and the inner wall of the housing 31 and the sealing support 351 are sealed by the fifth sealing member 353. In other words, in this embodiment, the fourth sealing member 352 and the fifth sealing member 353 cooperate to achieve a seal of the first chamber 311, thereby preventing leakage of the damping fluid in the first chamber 311 as much as possible.

[0068] In one embodiment, a hole structure is formed in the first end cover 313 of the housing 31, and the adjustment rod 32 extends from the hole structure in the first end cover 313. A damping scale is provided on the adjustment rod 32 and the edge of the hole in the housing 31 to indicate the current shimmy damping value.

[0069] In one embodiment, the shimmy damper 30 further includes a filling valve 37 . The filling valve 37 is disposed in the housing 31 , and the damping fluid is filled into the first chamber 311 through the filling valve 37 .

[0070] In one embodiment, the housing 31 further includes a second chamber 317 spaced apart from the first chamber 311 in the axial direction X. The adjustment rod 32 is further movably disposed in the second chamber 317 along the axial direction X. The shimmy damper 30 further includes an elastic member 34 disposed in the second chamber 317 and connected to the housing 31 and the adjustment rod 32, respectively. The elastic member 34 is used to reset the adjustment rod 32.

[0071] In the above manner, this embodiment provides an elastic member 34 to drive the adjustment rod 32 to reset, so that when the landing gear 10 shims, the adjustment rod 32 can move back and forth along the axial direction X under external excitation, so that the damping fluid flows back and forth along the axial direction X through the first damping adjustment hole 41 and the second damping adjustment hole 42. During this process, the damping fluid generates a damping force to suppress the shimmy, so that the mechanical energy generated by the shimmy of the landing gear 10 is converted into heat energy for dissipation, thereby achieving the purpose of reducing shimmy.

[0072] Specifically, the outer periphery of the adjustment rod 32 is further provided with a retaining ring 323 located in the second chamber 317. The elastic member 34 includes a first elastic member 341 and a second elastic member 342. The first elastic member 341 is located on one side of the retaining ring 323 in the axial direction X, and the second elastic member 342 is located on the other side of the retaining ring 323 in the axial direction X. The first elastic member 341 and the second elastic member 342 cooperate to drive the adjustment rod 32 to reset.

[0073] For example, the shimmy damper 30 further includes a second end cap 319. The second chamber 317 is located on the side of the first chamber 311 facing away from the first end cap 313. The second end cap 319 covers the end of the second chamber 317 facing away from the first chamber 311. The aforementioned seal assembly 35 is located between the first chamber 311 and the second chamber 317 in the axial direction X. The second end cap 319 can be fastened to the outer cylinder 312 using fasteners such as bolts. Similarly, the retaining ring 323 can also be fastened to the adjusting rod 32 using fasteners such as bolts.

[0074] In one embodiment, a first connector 318 is provided on the outer wall of the housing 31, specifically, the outer wall of the outer tube 312. A second connector 324 is provided at the end of the adjustment rod 32. One of the first connector 318 and the second connector 324 is connected to the landing gear 10, and the other is connected to the steering mechanism 20. For example, the first connector 318 is connected to the steering mechanism 20, and the second connector 324 is connected to the turning clamp 11 on the landing gear 10.

[0075] Furthermore, a locking member 325 is provided at the end of the adjustment rod 32, and the locking member 325 can be switched between a locked state and a released state. When the locking member 325 is switched to the locked state, the adjustment rod 32 is restricted from rotating relative to the second connecting member 324. When the locking member 325 is switched to the released state, the adjustment rod 32 is allowed to rotate relative to the second connecting member 324 while the second connecting member 324 remains connected to the turning clamp 11 on the landing gear 10. This allows the adjustment rod 32 and the piston member 33 to rotate relative to each other, thereby adjusting the overlapping area of ​​the first damping adjustment hole 41 and the second damping adjustment hole 42, changing the flow rate of the damping fluid that can pass through the first damping adjustment hole 41 and the second damping adjustment hole 42, and achieving damping adjustment.

[0076] It should be noted that the locking member 325 may be a locking nut, etc. The damping adjustment process of the shimmy damper 30 in this embodiment may be as follows: loosening the locking member 325, i.e., switching the locking member 325 to a loosened state, rotating the adjustment rod 32 to adjust the damping of the shimmy damper 30 to a target value; after the damping adjustment is completed, connecting the first connecting member 318 to the steering mechanism 20 and the second connecting member 324 to the turning clamp 11 on the landing gear 10, and then locking the locking member 325, i.e., switching the locking member 325 to a locked state, locking the current angle of the adjustment rod 32. The locking member 325 will not loosen during the operation of the shimmy damper 30 and affect the change in the damping magnitude.

[0077] In summary, the present application provides an aircraft and a shimmy damper therefor. The shimmy damper comprises an adjustment portion disposed on the outer periphery of an adjustment rod, which includes a first damping adjustment hole. A piston member is provided with a second damping adjustment hole, with the first and second damping adjustment holes being axially opposed to each other. As the landing gear shimmies, the adjustment rod is capable of axially moving relative to a first chamber within the housing, allowing damping fluid to flow through the first and second damping adjustment holes. This, in turn, converts the mechanical energy generated by the landing gear shimmy into heat energy for dissipation, thereby achieving shimmy reduction.

[0078] Furthermore, the adjusting rod and the piston member of the present application are configured to be able to rotate relative to each other so as to adjust the overlapping area of ​​the orthographic projection of the first damping adjustment hole on the reference plane and the orthographic projection of the second damping adjustment hole on the reference plane. The present application adjusts the overlapping area of ​​the first damping adjustment hole and the second damping adjustment hole by the relative rotation between the adjusting rod and the piston member, changes the flow rate of the damping fluid that can pass through the first damping adjustment hole and the second damping adjustment hole, and realizes damping adjustment. The present application can realize the damping adjustment of the shimmy damper through a relatively simple system, without the need to install complex sensors and control systems, which is conducive to simplifying the shimmy damper, greatly reducing the system complexity of the shimmy damper, reducing the weight and volume of the shimmy damper, and also reducing the cost of using the shimmy damper. The shimmy damper of the present application is particularly suitable for application scenarios such as small aircraft.

[0079] The above is a detailed introduction to the aircraft and its shimmy damper provided by the present application. Specific examples are used herein to illustrate the principles and implementation methods of the present application. The description of the above embodiments is only used to help understand the method and core ideas of the present application. At the same time, for those skilled in the art, based on the ideas of the present application, there may be changes in the specific implementation methods and application scope. In summary, the contents of this specification should not be understood as limiting the present application.

Claims

1. An aircraft, characterized in that: It includes a landing gear, a steering mechanism and a shimmy damper, wherein the shimmy damper is connected to the landing gear and the steering mechanism respectively; The shimmy damper has mutually perpendicular axial directions and a reference plane, and the shimmy damper comprises: a housing having a first chamber therein for storing a damping fluid; an adjusting rod movably provided in the first chamber along the axial direction, an adjusting portion provided on the outer periphery of the adjusting rod, the adjusting portion being located in the first chamber and provided with a first damping adjusting hole; and a piston member disposed in the first chamber, the piston member being disposed on an outer periphery of the adjusting rod and being capable of synchronously moving along the axial direction with the adjusting rod; the piston member being provided with a second damping adjustment hole, the first damping adjustment hole and the second damping adjustment hole being disposed opposite each other in the axial direction; and as the landing gear yaws, the adjusting rod is capable of moving along the axial direction relative to the first chamber, such that the damping fluid passes through the first damping adjustment hole and the second damping adjustment hole; The adjusting rod and the piston are configured to be relatively rotatable to adjust an overlapping area between an orthographic projection of the first damping adjusting hole on the reference plane and an orthographic projection of the second damping adjusting hole on the reference plane.

2. The aircraft according to claim 1, characterized in that At least one of the first damping adjustment hole and the second damping adjustment hole is a target damping adjustment hole, which extends along the circumference of the adjustment rod, and the two ends of the target damping adjustment hole in the circumferential direction of the adjustment rod are respectively a first end and a second end; along the circumference of the adjustment rod and in the direction from the first end to the second end, the width of the target damping adjustment hole gradually increases.

3. The aircraft according to claim 1, characterized in that The piston member comprises: a first piston portion, located on one side of the adjustment portion in the axial direction, the first piston portion being provided with the second damping adjustment hole; and The second piston part is located on the other side of the adjustment part in the axial direction. The second piston part is provided with a avoidance hole penetrating along the axial direction. The avoidance hole is arranged opposite to the first damping adjustment hole in the axial direction.

4. The aircraft according to claim 3, characterized in that The orthographic projection of the first damping adjustment hole on the reference plane is located in the orthographic projection of the avoidance hole on the reference plane.

5. The aircraft according to claim 4, characterized in that The adjusting portion is also provided with a first limiting portion, and the first piston portion and / or the second piston portion is provided with a second limiting portion. The first limiting portion and the second limiting portion cooperate to limit the maximum rotation angle between the adjusting rod and the piston member, so that the orthographic projection of the first damping adjustment hole on the reference plane is in the orthographic projection of the avoidance hole on the reference plane.

6. The aircraft according to claim 3, characterized in that The housing comprises: an outer cylinder having the first chamber therein; and a first end cover, which is provided at an end portion of the first chamber in the axial direction, and the first end cover and the second piston portion are located on the same side of the adjusting portion; Among them, one of the first end cover and the second piston part is provided with a rotation-stopping protrusion, and the other is provided with a rotation-stopping groove, the rotation-stopping protrusion is embedded in the rotation-stopping groove, and the rotation-stopping protrusion and the rotation-stopping groove cooperate to limit the relative rotation between the first end cover and the second piston part.

7. The aircraft according to claim 6, characterized in that The second piston portion includes: The first sub-section is provided with the avoidance hole; and a second sub-section connected to a side of the first sub-section facing away from the adjusting section; Wherein, a side of the first end cover close to the adjusting portion is provided with an avoidance groove, one of the second sub-portion and the groove wall of the avoidance groove is provided with the anti-rotation protrusion, and the other is provided with the anti-rotation groove.

8. The aircraft according to any one of claims 1 to 7, characterized in that The first damping adjustment hole and the second damping adjustment hole are both through-hole structures penetrating along the axial direction, and the first damping adjustment hole and the second damping adjustment hole are both configured to allow the damping fluid to pass through the first damping adjustment hole and the second damping adjustment hole from either side in the axial direction.

9. The aircraft according to any one of claims 1 to 7, characterized in that The housing further comprises a second chamber spaced apart from the first chamber in the axial direction, and the adjusting rod is movably disposed in the second chamber along the axial direction. The shimmy damper further comprises: An elastic member is disposed in the second chamber and is connected to the housing and the adjusting rod respectively. The elastic member is used to drive the adjusting rod to reset.

10. The aircraft according to claim 9, characterized in that The outer periphery of the adjusting rod is further provided with a retaining ring located in the second chamber; The elastic member comprises: a first elastic member, located on one side of the retaining ring in the axial direction; and The second elastic member is located on the other side of the retaining ring in the axial direction, and the first elastic member and the second elastic member cooperate to drive the adjusting rod to reset.

11. The aircraft according to claim 9, characterized in that The shimmy damper further comprises: A sealing assembly is located between the first chamber and the second chamber in the axial direction. The sealing assembly is sealingly connected to the adjusting rod and the inner wall of the housing to seal the first chamber.

12. The aircraft according to any one of claims 1 to 7, characterized in that A first connecting member is provided on the outer wall of the shell, a second connecting member is provided on the end of the adjusting rod, one of the first connecting member and the second connecting member is connected to the landing gear, and the other is connected to the steering mechanism.

13. The aircraft according to claim 12, characterized in that A locking piece is provided at the end of the adjusting rod, and the locking piece can be switched between a locked state and a released state; when the locking piece is switched to the locked state, the adjusting rod is restricted from rotating relative to the second connecting piece; when the locking piece is switched to the released state, the adjusting rod is allowed to rotate relative to the second connecting piece while the second connecting piece remains connected to the landing gear.

14. A shimmy damper, characterized in that: The shimmy damper has mutually perpendicular axial directions and a reference plane, and the shimmy damper comprises: a housing having a first chamber therein for storing a damping fluid; an adjusting rod movably disposed in the first chamber along the axial direction, an adjusting portion being disposed on an outer periphery of the adjusting rod, the adjusting portion being located in the first chamber, and having a first damping adjustment hole; one of the housing and the adjusting rod being connected to a landing gear of an aircraft, and the other being connected to a steering mechanism of the aircraft; and a piston member disposed in the first chamber, the piston member being disposed on an outer periphery of the adjusting rod and being capable of synchronously moving along the axial direction with the adjusting rod; the piston member being provided with a second damping adjustment hole, the first damping adjustment hole and the second damping adjustment hole being disposed opposite each other in the axial direction; and as the landing gear yaws, the adjusting rod is capable of moving along the axial direction relative to the first chamber, such that the damping fluid passes through the first damping adjustment hole and the second damping adjustment hole; The adjusting rod and the piston are configured to be relatively rotatable to adjust an overlapping area between an orthographic projection of the first damping adjusting hole on the reference plane and an orthographic projection of the second damping adjusting hole on the reference plane.

15. The shimmy damper according to claim 14, characterized in that At least one of the first damping adjustment hole and the second damping adjustment hole is a target damping adjustment hole, which extends along the circumference of the adjustment rod, and the two ends of the target damping adjustment hole in the circumferential direction of the adjustment rod are respectively a first end and a second end; along the circumference of the adjustment rod and in the direction from the first end to the second end, the width of the target damping adjustment hole gradually increases.

16. The shimmy damper according to claim 14 or 15, characterized in that: The first damping adjustment hole and the second damping adjustment hole are both through-hole structures penetrating along the axial direction, and the first damping adjustment hole and the second damping adjustment hole are both configured to allow the damping fluid to pass through the first damping adjustment hole and the second damping adjustment hole from either side in the axial direction.

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