Anti-shimmy device and landing gear

Abstract

A kind of anti-shimmy device and landing gear, including parallel axis steering mechanism, parallel axis steering mechanism includes steering wheel steering wheel (3) of steering gear, parallel arm (4) and front lift steering steering wheel (5), steering wheel steering wheel is connected with the rotating shaft (1a) of servo steering gear (1), front lift steering steering wheel is connected with the landing gear outer cylinder (7) of landing gear main body, parallel arm is connected between steering wheel steering wheel and front lift steering steering wheel, and steering wheel steering wheel, parallel arm and front lift steering steering wheel form parallelogram mechanism by steering wheel steering wheel.The driving force arm can be kept unchanged to ensure the transmission accuracy of steering gear and the feedback force is not amplified, and the shimmy phenomenon can be reduced during the landing gear sliding process.

Description

Technical Field

[0001] This invention relates to an anti-shielding device and landing gear. More particularly, it relates to an anti-shielding device and landing gear for unmanned aerial vehicles. Background Technology

[0002] The nose landing gear is an important device for unmanned aerial vehicles to turn during taxiing on the ground. A reliable and stable steering system can prevent the aircraft from running off the runway during high-speed taxiing, thus affecting flight safety.

[0003] Currently, the main methods for directional control of the nose landing gear in small drones include gear transmission, worm gear transmission, and crankshaft connecting rod transmission. These mechanical structures inevitably have clearances, which can lead to the possibility of shimmy.

[0004] Currently, the design of the nose landing gear for small UAVs mainly focuses on miniaturization and lightweighting. Therefore, the following problems may exist in the structural design: (1) there is a gap in the drive mechanism, especially at the front end of the servo output; (2) due to the inconsistent lever arms on the transmission path, the force output by the servo and the feedback force transmitted from the landing gear tires are inconsistent, which may amplify the torque demand of the servo and may exceed the actual capability of the servo. The above-mentioned gap problem and the problem of insufficient torque resistance of the servo may cause the nose landing gear to oscillate.

[0005] As a device to prevent landing gear shimmy, one known technology (CN114987744A) uses electromagnetic components in the landing gear to provide sufficient damping, thereby reducing shimmy. It utilizes the principle of electromagnetic induction, causing the rotor disk to cut magnetic field lines in a magnetic field and generate a current. This induced current then impedes the rotor disk's movement within the magnetic field, converting its kinetic energy into heat energy, thus reducing shimmy in the front wheel. However, adding electromagnetic components increases costs, complicates the structure, and adds weight to the drone, hindering its miniaturization and weight reduction.

[0006] In addition, a nose landing gear with integrated anti-sway function (CN117698995A) is also known. This landing gear integrates the anti-sway device and its transmission mechanism onto the buffer strut, and the anti-sway function is achieved through the springs, damping, and other structures of the buffer strut. However, this structure does not take into account the inconsistency between the force output by the servo motor and the feedback force transmitted from the landing gear tires, therefore, there is room for improvement.

[0007] Existing technical documents

[0008] Patent documents

[0009] Patent Document 1: CN114987744A

[0010] Patent Document 2: CN117698995A Summary of the Invention

[0011] This invention is made to solve the above-mentioned technical problems. Its purpose is to provide an anti-shielding device and landing gear, which can ensure the transmission accuracy of the servo motor and prevent the feedback force from being amplified by eliminating the movement gap and keeping the drive arm constant, thereby reducing shielding during the landing gear sliding process.

[0012] One aspect of the present invention relates to an anti-shielding device, comprising a parallel axis steering mechanism, the parallel axis steering mechanism including a servo steering disk, a parallel swing arm, and a front steering turntable, the servo steering disk being connected to the rotation shaft of a servo servo, the front steering turntable being connected to the outer cylinder of the landing gear body, the parallel swing arm being connected between the servo steering disk and the front steering turntable, the servo steering turntable, the parallel swing arm, and the front steering turntable forming a parallelogram mechanism.

[0013] Based on the anti-shielding device of this structure, the parallel-axis steering mechanism, consisting of a servo steering dial, a parallel arm, and a front steering dial, forms a parallelogram mechanism. This ensures that the power transmission arm remains constant, meaning that the force transmitted from the servo motor to the landing gear body and the force fed back from the landing gear body to the servo motor remain constant, thus avoiding amplifying the servo motor's torque resistance requirements. Furthermore, the design employing a servo motor and a parallel-axis steering mechanism achieves miniaturization and weight reduction of the structure.

[0014] Ideally, the anti-shield device also includes a landing gear damping mechanism, which includes an outer cylinder and an inner cylinder of the landing gear. The inner cylinder is sleeved inside the outer cylinder of the landing gear, and a piston is provided at the top of the inner cylinder. Oil is injected into the outer cylinder of the landing gear, and the inner cylinder passes through a spring and is sleeved inside the outer cylinder of the landing gear.

[0015] The landing gear damping mechanism is designed with an outer cylinder and an inner cylinder. The inner cylinder is fitted inside the outer cylinder. A piston is installed at the top of the inner cylinder, and oil is injected into the outer cylinder. The inner cylinder passes through a spring and is fitted inside the outer cylinder, thus achieving the damping function.

[0016] Furthermore, a through hole is formed in the center of the servo steering disk for the servo servo's rotating shaft to pass through. A plurality of first mounting holes are formed around the through hole for a pin to pass through, so as to directly connect with a fixing member provided on the rotating shaft of the servo servo. The front steering disk includes a base portion and a protrusion portion. The protrusion portion is arranged to protrude from the base portion toward the landing gear outer cylinder. A groove is provided in the center of the front steering disk. A boss structure is formed to protrude from the top of the landing gear outer cylinder. The front steering disk is connected to the landing gear outer cylinder by the engagement of the boss structure with the groove.

[0017] Based on this structure, the servo steering rudder and the front steering turntable can stably transmit torque between the servo servo and the landing gear body.

[0018] In addition, the parallel shaft steering mechanism includes a translational backlash elimination mechanism, which consists of a first top bolt hole, a second top bolt hole, a first nut pre-embedded position, and a second nut pre-embedded position. The first top bolt hole is formed on the first and second opposing surfaces of the groove, respectively. The second top bolt hole is formed on the boss structure at the position corresponding to the first top bolt hole. The first and second top bolt holes form a hole for bolt insertion. The lower part of the first top bolt hole on the first and second opposing surfaces of the groove is formed on the first nut pre-embedded position, respectively. The second nut pre-embedded position is formed on the boss structure at the position corresponding to the first nut pre-embedded position. The first and second nut pre-embedded positions form a space for nut pre-embedding.

[0019] The parallel axis steering mechanism of this structure ensures that there is no translational backlash during the transmission of motion from the servo motor to the landing gear body, thus eliminating one of the causes of landing gear shimmy.

[0020] Ideally, the parallel shaft steering mechanism includes a backlash elimination mechanism, which is composed of a first pair of locking bolt holes, a third pair of locking bolt holes, a second pair of locking bolt holes, and a fourth pair of locking bolt holes. The first pair of locking bolt holes and the second pair of locking bolt holes are respectively provided on both sides of the front steering turntable, and the third pair of locking bolt holes and the fourth pair of locking bolt holes are respectively provided at the positions corresponding to the first pair of locking bolt holes and the second pair of locking bolt holes on the boss structure.

[0021] The parallel axis steering mechanism of this structure ensures that there is no rotational backlash in the process of the servo motor transmitting motion to the landing gear body, thus eliminating one of the causes of landing gear shimmy.

[0022] In addition, at least one second mounting hole is provided at each end of the long side of the servo steering disk, and at least one third mounting hole is provided at each end of the long side of the front steering turntable. The distance between the third mounting holes of the front steering turntable is the same as the distance between the second mounting holes of the servo steering disk.

[0023] By setting the distance between the third mounting holes of the front steering turntable to be the same as the distance between the second mounting holes of the servo steering rudder, a parallelogram mechanism can be easily formed by a parallel swing arm.

[0024] In addition, the parallel swing arm is formed in the shape of a long strip plate, and at least one fixing hole is formed at each end of the long side of the parallel swing arm. The parallel swing arm and the servo steering disk are fixed by passing a pin through the fixing hole and the second mounting hole of the servo steering disk. The parallel swing arm and the front steering disk are fixed by passing a pin through the fixing hole and the third mounting hole of the front steering disk.

[0025] Based on this structure, a parallelogram mechanism can be easily formed.

[0026] In addition, an air hole is provided in the center of the boss structure, and an air nozzle is installed in the air hole.

[0027] By setting an air hole in the center of the boss structure and installing an air nozzle in the air hole, it can play a role in buffering and shock absorption.

[0028] Another aspect of the present invention relates to a landing gear, comprising: a servo motor; a servo motor bracket for fixing the servo motor; an anti-shield device; a fuselage bracket for fixing the servo motor bracket and the anti-shield device to the fuselage of an aircraft; and a landing gear body.

[0029] Based on the landing gear structure, a servo motor and parallel axis steering mechanism were adopted to achieve miniaturization and weight reduction. By keeping the drive arm unchanged in the parallel axis steering mechanism, the feedback force transmitted from the landing gear body to the servo motor was not amplified, thus avoiding the second cause of landing gear shimmy - insufficient support stiffness (servo motor resistance).

[0030] Ideally, the fuselage support includes a triangular frame and a cylinder arranged through the center of the triangular frame, and the landing gear outer cylinder is configured to rotate freely about the axial direction within the cylinder of the fuselage support.

[0031] The body support structure provides stable support and is simple in design. Attached Figure Description

[0032] Figure 1 This is a perspective view showing the structure of the landing gear to which the anti-shield device of the present invention is applied.

[0033] Figure 2 This is a diagram showing the structure of a servo motor and its support.

[0034] Figure 3 This is a diagram showing the structure of a parallel shaft steering mechanism.

[0035] Figure 4 It is a diagram showing the structure of the landing gear.

[0036] Figure 5 This is a schematic diagram showing the assembly of the steering wheel of the anti-shield device and the outer cylinder of the landing gear.

[0037] (Symbol Explanation)

[0038] 1 servo motor

[0039] 2 servo brackets

[0040] 3-Steering servo

[0041] 4 parallel swing arms

[0042] 5. Front steering wheel

[0043] 6. Body support

[0044] 7. Landing gear outer cylinder

[0045] 8. Landing gear upper support

[0046] 9. Landing gear torsion arm

[0047] 10 Landing gear inner and outer cylinder connection end caps

[0048] 11 Inner Tube

[0049] 12 landing gear underbody

[0050] 13 First top bolt hole

[0051] 14 First pair of lock bolt holes

[0052] 15-bore structure

[0053] 16 Third pair of lock bolt holes

[0054] 17 Second Nut Embedded Position

[0055] 18 grooves

[0056] 19 First Nut Embedded Position

[0057] 20 Second pair of lock bolt holes

[0058] 21 stomata

[0059] 22 Fourth pair of lock bolt holes

[0060] 23 Second top bolt hole

[0061] 31 Through Hole

[0062] 32 First mounting hole

[0063] 33 Second mounting hole

[0064] 1a Rotating shaft

[0065] 3a Triangle border

[0066] 5a Base section

[0067] 5b Protrusion

[0068] 51 Third mounting hole

[0069] 6b Cylinder

[0070] W landing gear wheels Detailed Implementation

[0071] Hereinafter, preferred embodiments of the present invention will be described in detail with reference to the accompanying drawings. In the figures, the same symbols are used to denote the same components, and repeated descriptions are sometimes omitted. Furthermore, in the figures, dimensions and shapes are sometimes exaggerated to facilitate understanding of the invention. In addition, in the following detailed description, directional terms such as "up," "down," "left," "right," "front," and "back" are used for illustrative purposes and not for limitation. In the present invention, the flight direction of the aircraft is defined as the forward / backward direction X, and the vertical direction of the aircraft is defined as the vertical direction Y. The left / right direction Z is perpendicular to both the forward / backward and vertical directions.

[0072] Figure 1 This is a perspective view showing the structure of a landing gear to which the anti-shield device according to an embodiment of the present invention is applied. (See image below.) Figure 1 As shown, the main structure of the landing gear includes a servo motor 1, a servo motor bracket 2, a fuselage bracket 6, a servo motor steering disk 3 as a parallel axis steering mechanism, a parallel swing arm 4 and a front steering disk 5, an outer landing gear cylinder 7, an upper landing gear support 8, a landing gear torque arm 9, a connecting end cap for the inner and outer landing gear cylinders 10, an inner cylinder 11, a lower landing gear support 12, and landing gear wheels W.

[0073] Servo servo 1 is fixed to the aircraft fuselage via servo bracket 2 to provide driving force and steer the landing gear wheels W. Servo bracket 2 and fuselage bracket 6 are fixed structures connected to the aircraft fuselage via pins (not shown). Servo bracket 2 is used to mount servo servo 1, and fuselage bracket 6 is used to mount the landing gear body. Here, as an example, servo bracket 2 is mounted to fuselage bracket 6 via pins, and then fixed to the aircraft fuselage via fuselage bracket 6. To form a stable support, servo bracket 2 is formed into a roughly triangular prism frame shape, and fuselage bracket 6 is also formed into a roughly triangular shape. The specific structure of servo bracket 2 and fuselage bracket 6 will be described in detail later.

[0074] Next, refer to Figure 2 , Figure 3 The parallel shaft steering mechanism is explained.

[0075] like Figure 3 As shown, the parallel axis steering mechanism includes a servo steering rudder 3, a parallel rotating arm 4, and a front steering turntable 5.

[0076] The servo steering disk 3 is formed in a generally rhomboid flat plate shape. A through hole 31 is formed in the center of the servo steering disk 3, which is used for the insertion of the rotation shaft 1a of the servo servo 1. In addition, a plurality of first mounting holes 32 are formed at approximately equal intervals around the through hole 31. The first mounting holes 32 are used for pins to pass through, so as to be directly connected to the fixing member 1b of the rotation shaft 1a of the servo servo 1 via the pins. In addition, at least one second mounting hole 33 is provided at each end of the long side of the servo steering disk 3, for fixing the parallel swing arm 4 via pins. The fixing member 1b of the rotation shaft 1a is fixed to the end accessory of the rotation shaft 1a near the servo steering disk 3. On the fixing member 1b, a plurality of through holes are formed at positions corresponding to the first mounting holes 32 of the servo steering disk 3, for pins to pass through, so as to be connected to the first mounting holes 32 of the servo steering disk 3 via the pins.

[0077] The parallel swing arm 4 is formed in the shape of a long strip plate. At least one fixing hole 41 (two are shown in this example) is formed at both ends of the long side of the parallel swing arm 4. The parallel swing arm 4 and the servo steering disk 3 are fixed by passing a pin through the fixing hole 41 and the second mounting hole 33 of the servo steering disk 3.

[0078] The front steering dial 5 includes a base portion 5a and a protrusion portion 5b. The base portion 5a is shaped to be approximately the same as the servo steering disc 3, and the protrusion portion 5b is provided to protrude downward from the lower surface of the base portion 5a. At least one third mounting hole 51 is provided at each end of the long side of the base portion 5a for fixing the parallel swing arm 4 by a pin. The distance between the two third mounting holes 51 of the front steering dial 5 is the same as the distance between the two second mounting holes 33 of the servo steering disc 3.

[0079] In this way, the servo steering rudder 3 and the front steering turntable 5 are connected by two parallel rotating arms 4, and the distance between the two second mounting holes 33 of the servo steering rudder 3 is equal to the distance between the two third mounting holes 51 of the front steering turntable 5. That is, the servo steering rudder 3, the parallel rotating arms 4, and the front steering turntable 5 form a parallelogram mechanism.

[0080] According to the parallel shaft steering mechanism of the above structure, the feedback force generated from the landing gear wheel W and the feedback force received by the servo motor 1 can be kept equal, and the driving force generated from the servo motor 1 and the driving force received by the landing gear wheel W can be equal, so as not to amplify the torque resistance requirement of the servo motor and generate potential shimmy hazards due to insufficient stiffness.

[0081] like Figure 5 As shown, the front steering wheel 5 has a central groove 18. As an example, a roughly hexagonal groove 18 is shown, but its shape is not limited to this; it can also be pentagonal, octagonal, or any other shape. This groove 18 is used to fit a boss structure 15 located at the top of the landing gear outer cylinder 7. The boss structure 15 is formed to protrude from the top of the landing gear outer cylinder 7 and is shaped to correspond to the groove 18. The engagement of the front steering wheel 5 with the landing gear body is achieved through the engagement of the boss structure 15 with the groove 18.

[0082] First top bolt holes 13 are formed on the two opposite surfaces of the groove 18, namely the first opposite surface and the second opposite surface. A second top bolt hole 23 is formed on the boss structure 15 at the position corresponding to the first top bolt hole 13. The first top bolt hole 13 and the second top bolt hole 23 form a complete hole for bolt insertion. Furthermore, a first nut embedment position 19 is formed at the lower part of the first top bolt hole 13 on the first and second opposite surfaces of the groove 18. A second nut embedment position 17 is formed on the boss structure 15 at the position corresponding to the first nut embedment position 19. The first nut embedment position 19 and the second nut embedment position 17 form a complete space for nut embedding. After the boss structure 15 of the front steering turntable 5 and the landing gear outer cylinder 7 is assembled in place, the locking nuts are used through the first top bolt hole 13 and the second top bolt hole 23 to limit the axial translational clearance of the landing gear body. The first top bolt hole 13, the second top bolt hole 23, the first nut pre-embedded position 19, and the second nut pre-embedded position 17 constitute the translational clearance elimination mechanism.

[0083] Furthermore, a first pair of locking bolt holes 14 and a second pair of locking bolt holes 20 are respectively provided on both sides of the short side of the front steering turntable 5. A third pair of locking bolt holes 16 and a fourth pair of locking bolt holes 22 are respectively provided on the boss structure 15 at positions corresponding to the first pair of locking bolt holes 14 and the second pair of locking bolt holes 20. By locking the first pair of locking bolt holes 14, the third pair of locking bolt holes 16, the second pair of locking bolt holes 20, and the fourth pair of locking bolt holes 22 with bolts, the rotational clearance of the landing gear outer cylinder 7 can be eliminated. The first pair of locking bolt holes 14, the third pair of locking bolt holes 16, the second pair of locking bolt holes 20, and the fourth pair of locking bolt holes 22 constitute a rotational clearance elimination mechanism.

[0084] In addition, an air hole 21 is provided in the center of the boss structure 15, and an air nozzle (not shown) is installed in the air hole 21 to play a role in buffering and shock absorption.

[0085] As described above, the body support 6 is formed in a roughly triangular shape, such as... Figure 2 As shown, the system includes a triangular frame 3a and a cylinder 6b extending through the center of the triangular frame 3a. The upper edge of the cylinder 6b is flush with the upper surface of the upper frame of the triangular frame 3a. The landing gear outer cylinder 7 is fitted inside the cylinder 6b of the fuselage support 6, with the upper edges of both being flush. Furthermore, the landing gear outer cylinder 7 is configured to rotate freely about its axial direction within the cylinder 6b of the fuselage support 6.

[0086] Next, refer to Figure 4 The structure of the main landing gear body is described.

[0087] The landing gear body includes an upper landing gear support 8, a landing gear torque arm 9, a landing gear inner and outer cylinder connecting end cap 10, a landing gear lower support 12, and a landing gear wheel W. In this embodiment, as a landing gear damping mechanism, an inner and outer cylinder structure is adopted. The inner cylinder 11 is sleeved inside the landing gear outer cylinder 7 by a piston and spring, playing a damping and buffering role. The landing gear torque arm 9 is used to restrict the rotation of the inner cylinder 11 around the axial direction within the landing gear outer cylinder 7, so that it can only move axially, that is, it can only extend or compress vertically, but cannot twist. The upper landing gear support 8 is used to connect the landing gear outer cylinder 7 and the landing gear torque arm 9. The landing gear inner and outer cylinder connecting end cap 10 is used to connect the inner cylinder 11 and the landing gear outer cylinder 7 and restrict the axial translation of the landing gear outer cylinder 7. The lower landing gear support 12 is used to connect the inner cylinder 11, the landing gear torque arm 9, and the landing gear wheel W.

[0088] The landing gear, based on the aforementioned structure, mainly includes a servo motor 1, a servo motor bracket 2, a fuselage bracket 6, a parallel-axis steering mechanism, and the landing gear body. The parallel-axis steering mechanism connects the servo motor and the landing gear body and is structurally matched to both. This mechanism ensures that there is no backlash, including steering and translational backlash, during the transmission of motion from the servo motor to the landing gear body. Furthermore, it keeps the transmission arm constant, ensuring that the force transmitted from the servo motor to the landing gear body and the force fed back from the landing gear body to the servo motor remain constant, thus preventing the amplification of the servo motor's torque resistance requirements. Additionally, the landing gear body is designed with an outer and inner cylinder. The inner cylinder is fitted inside the outer cylinder, and a piston is located at the top of the inner cylinder. Oil is injected into the outer cylinder, and the inner cylinder passes through a spring within the outer cylinder, thus achieving shock absorption.

[0089] As an anti-shielding device, it includes a parallel shaft steering mechanism and an inner cylinder 11 and an outer cylinder 7 of the landing gear as a landing gear damping mechanism.

[0090] The anti-shielding device and landing gear based on the above structure have the following technical effects:

[0091] (1) The design of servo motor plus parallel shaft steering mechanism realizes the miniaturization and weight reduction of the structure.

[0092] (2) By specifically designing the possible rotational clearance and translational clearance of the landing gear on the parallel shaft steering mechanism, one of the causes of landing gear shimmy - clearance - is eliminated.

[0093] (3) By keeping the drive arm unchanged on the parallel axis steering mechanism, the feedback force transmitted from the landing gear body to the servo motor is not amplified, thus avoiding the second cause of landing gear shimmy - insufficient support stiffness (servo motor resistance).

[0094] (4) The landing gear body is designed to have an outer cylinder and an inner cylinder. The inner cylinder is fitted inside the outer cylinder of the landing gear. A piston is set at the top of the inner cylinder, and oil is injected into the outer cylinder of the landing gear. The inner cylinder passes through a spring and is fitted inside the outer cylinder of the landing gear, thereby further realizing the shock absorption function.

[0095] The embodiments and variations of the present invention have been described above. However, it should be understood that this disclosure is not limited to the above embodiments and structures. This disclosure also includes various variations and modifications within the equivalent scope. In addition, various combinations and methods, and further combinations and methods that include only one element or more or less thereof, also fall within the scope and spirit of this disclosure.

[0096] For example, in the above embodiment, the front steering dial 5 has a groove 18 in the center, and a boss structure 15 is provided at the top of the landing gear outer cylinder 7. The front steering dial 5 and the landing gear body are connected by the engagement of the boss structure 15 and the groove 18. However, the present invention is not limited to this. For example, the opposite can also be used, with a boss structure in the center of the front steering dial 5 and a groove at the top of the landing gear outer cylinder 7. Furthermore, the connection method between the front steering dial 5 and the landing gear body is not limited to the engagement method of the groove and the boss structure; any connection method can be applied.

[0097] Furthermore, in the above embodiment, a top bolt hole and a nut pre-embedded position are provided in the groove 18, and a nut pre-embedded position is provided in the boss structure 15, thus forming a translational clearance elimination mechanism. However, the translational clearance elimination mechanism is not limited to this; it can limit the axial translational clearance of the landing gear body. For example, a direct bolt fastening method can also be used.

[0098] Furthermore, examples of the backlash elimination mechanism include the first pair of locking bolt holes 14, the third pair of locking bolt holes 16, the second pair of locking bolt holes 20, and the fourth pair of locking bolt holes 22. However, the backlash elimination mechanism is not limited to these, as long as it can limit the backlash of the landing gear body around its axis.

Claims

1. An anti-sway device, characterized in that, Including parallel shaft steering mechanism, The parallel axis steering mechanism includes a servo steering rudder (3), a parallel rotating arm (4), and a front steering turntable (5). The servo steering rudder is connected to the rotation shaft (1a) of the servo servo (1), the front steering dial is connected to the landing gear outer cylinder (7) of the landing gear body, and the parallel swing arm is connected between the servo steering rudder and the front steering dial. The servo steering dial, the parallel swing arm, and the front steering dial form a parallelogram mechanism. The anti-shielding device also includes a landing gear damping mechanism. The landing gear damping mechanism includes an outer cylinder (7) and an inner cylinder (11). The inner cylinder is fitted inside the outer cylinder of the landing gear. A piston is installed at the top of the inner cylinder. Oil is injected into the outer cylinder of the landing gear. The inner cylinder passes through a spring and is fitted inside the outer cylinder of the landing gear. A through hole (31) is formed in the center of the servo steering rudder, which is used for the insertion of the rotating shaft of the servo servo. A plurality of first mounting holes (32) are formed around the through hole, which are used for the passage of a pin, so as to directly connect the pin to the fixing member (1b) provided on the rotating shaft of the servo servo. The front steering dial includes a base portion (5a) and a protrusion portion (5b), the protrusion portion being provided such that it protrudes from the base portion toward the outer cylinder of the landing gear. A groove (18) is provided in the center of the front landing gear steering disc, and a boss structure (15) is formed in such a way that it protrudes from the top of the landing gear outer cylinder. The front landing gear steering disc is connected to the landing gear outer cylinder by the engagement of the boss structure with the groove. The parallel shaft steering mechanism includes a translational backlash elimination mechanism. The translational clearance elimination mechanism consists of a first top bolt hole (13), a second top bolt hole (23), a first nut pre-embedded position (19), and a second nut pre-embedded position (17). The first top bolt hole is formed on the first and second opposite surfaces of the groove, and the second top bolt hole is formed on the boss structure at the position corresponding to the first top bolt hole. The first and second top bolt holes form a hole for bolt insertion. The lower part of the first top bolt hole on the first and second opposite surfaces of the groove is formed with a first nut embedding position (19). The second nut embedding position (17) is formed on the boss structure at the position corresponding to the first nut embedding position. The first and second nut embedding positions form a space for nut embedding.

2. The anti-vibration device as described in claim 1, characterized in that, The parallel shaft steering mechanism includes a backlash elimination mechanism. The rotation clearance elimination mechanism is composed of a first pair of locking bolt holes (14), a third pair of locking bolt holes (16), a second pair of locking bolt holes (20), and a fourth pair of locking bolt holes (22). The first pair of locking bolt holes and the second pair of locking bolt holes are respectively provided on both sides of the front steering wheel. The third pair of locking bolt holes and the fourth pair of locking bolt holes are respectively provided at the positions corresponding to the first pair of locking bolt holes and the second pair of locking bolt holes on the boss structure.

3. The anti-vibration device as described in claim 1, characterized in that, At least one second mounting hole (33) is provided at each end of the long side of the servo steering disk. At least one third mounting hole (51) is provided at each end of the long side of the front steering turntable. The distance between the third mounting holes of the front steering turntable is the same as the distance between the second mounting holes of the servo steering rudder.

4. The anti-vibration device as described in claim 3, characterized in that, The parallel swing arm is formed in the shape of a long strip plate, and at least one fixing hole is formed at each end of the long side of the parallel swing arm. The parallel swing arm and the servo steering disk are fixed by passing a pin through the fixing hole and the second mounting hole of the servo steering disk. The parallel swing arm and the front steering disk are fixed by passing a pin through the fixing hole and the third mounting hole of the front steering disk.

5. The anti-vibration device as described in claim 1, characterized in that, An air hole (21) is provided in the center of the boss structure, and an air nozzle is installed in the air hole.

6. A landing gear, characterized in that, include: Servo motor (1); Servo bracket (2), the servo bracket is used to fix the servo servo; The anti-sway device according to any one of claims 1 to 5; Airframe bracket (6), which secures the servo bracket and the anti-vibration device to the aircraft airframe; and Landing gear main body.

7. The landing gear as claimed in claim 6, characterized in that, The fuselage support includes a triangular frame (3a) and a cylinder (6b) arranged through the center of the triangular frame, the landing gear outer cylinder being configured to rotate freely about the axial direction within the cylinder of the fuselage support.

Images