Retractable aircraft landing gear

Abstract

The present invention discloses a retractable aircraft landing gear, comprising a drive assembly, a buffer and a wheel assembly, wherein the wheel assembly comprises a connecting rocker arm and a telescopic rod, wherein the connecting rocker arm is connected to the wheel, and the connecting rocker arm is connected to a torque arm to ensure the normal operation of the device; the telescopic rod is hinged to the connecting rocker arm, so that the drive assembly can use a transmission mechanism to drive the telescopic rod to move, so that the connecting rocker arm can rotate relative to the buffer, and the angle between the connecting rocker arm and the buffer is changed to adjust the overall length of the retractable aircraft landing gear. When the aircraft takes off and lands, the landing gear is lowered and its length increases, so that the ground clearance of the aircraft meets the flight requirements. When the landing gear is retracted, the driving assembly retracts the landing gear and shortens the overall length of the landing gear at the same time, and the transmission mechanism is arranged in the buffer, and one end of the telescopic rod connected to the transmission mechanism also extends into the buffer. When the landing gear is retracted, the storage space requirements of the aircraft are met.

Description

Technical Field

[0001] The present invention relates to the technical field of aircraft and parts thereof, in particular to a retractable aircraft landing gear. Background Art

[0002] To meet the growing demand for air transportation, high capacity and low fuel consumption are the goals of modern passenger aircraft development. To reduce R&D costs, many aircraft manufacturers have developed derivative models based on their proven products. Increasing the bypass ratio and lengthening the fuselage are common methods for improving transport capacity and reducing operating costs, but these methods can pose a series of safety risks. For example, increasing engine size can result in insufficient ground clearance for the engine casing, while lengthening the fuselage limits the aircraft's takeoff pitch angle (the tail of the fuselage scrapes the ground). This problem can be addressed by lengthening the landing gear to increase ground clearance, but due to the aircraft's inherent structural limitations and storage space, most aircraft cannot accommodate the increased landing gear. Consequently, the engine installation height is increased, which changes the aircraft's aerodynamic characteristics and poses a safety risk. Summary of the Invention

[0003] The object of the present invention is to provide a retractable aircraft landing gear to solve the problems existing in the above-mentioned prior art, so that the size of the aircraft landing gear can be increased to ensure smooth take-off and landing of the aircraft, while at the same time making the aircraft landing gear meet the storage space requirements.

[0004] To achieve the above-mentioned object, the present invention provides the following solution: The present invention provides a retractable aircraft landing gear, comprising:

[0005] Drive components;

[0006] A buffer, the buffer comprising a main support outer tube and a main support piston rod, the main support piston rod being connected to the main support outer tube via a sliding pair, and the main support outer tube being further transmission-connected to the drive assembly;

[0007] The wheel assembly includes a connecting rocker arm and a telescopic rod, the connecting rocker arm can be connected to the wheel, one end of the telescopic rod extends from the main pillar piston rod and is hinged to the connecting rocker arm, the other end of the telescopic rod is connected to the drive assembly by a transmission mechanism, the transmission mechanism is arranged in the buffer, the connecting rocker arm is also rotatably connected to the main pillar outer tube by a torsion arm, and the drive assembly can use the transmission mechanism to drive the telescopic rod to move so that the connecting rocker arm rotates relative to the buffer.

[0008] Preferably, the wheel assembly also includes a transmission cylinder arranged in the main pillar piston rod, the transmission cylinder includes a transmission sleeve and a transmission piston, the transmission sleeve and the transmission piston are connected through a sliding pair, one end of the transmission piston is hinged to the telescopic rod, and the other end of the transmission piston extends into the transmission sleeve and is connected to the transmission mechanism, and the piston chamber of the transmission cylinder is connected to the piston chamber of the buffer.

[0009] Preferably, the transmission mechanism includes an upper connecting rod, an intermediate sleeve and a lower connecting rod connected in sequence, and the upper connecting rod and the lower connecting rod are both slidably connected to the intermediate sleeve. The end of the upper connecting rod away from the intermediate sleeve is connected to the drive assembly, and the end of the lower connecting rod away from the intermediate sleeve is connected to the transmission piston.

[0010] Preferably, the torque arm includes an upper torque arm and a lower torque arm, one end of the upper torque arm is hinged to the outer tube of the main pillar, the other end of the upper torque arm is hinged to the lower torque arm, and the end of the lower torque arm away from the upper torque arm is hinged to the connecting rocker arm.

[0011] Preferably, when the retractable aircraft landing gear is in a retracted state, the wheel assembly is in a retracted state, and the connecting rocker arm abuts against the main strut piston rod.

[0012] Preferably, the drive assembly includes an actuator and a first connecting rod, the length of the actuator can be adjusted, the movable end of the actuator is hinged to the outer tube of the main pillar, the fixed end of the actuator is hinged to the first connecting rod, and the first connecting rod is also hinged to the outer tube of the main pillar.

[0013] Preferably, the drive assembly also includes a second connecting rod, a third connecting rod, a first rocker arm and a second rocker arm, one end of the second connecting rod is hinged to the first connecting rod, the other end of the second connecting rod is hinged to one end of the first rocker arm, and the hinge surfaces of the two are spherical surfaces, the other end of the first rocker arm is hinged to one end of the third connecting rod, the other end of the third connecting rod is hinged to one end of the second rocker arm, and the other end of the second rocker arm is connected to the transmission mechanism.

[0014] Preferably, the second rocker arm is connected to a cam, the cam is located in the outer tube of the main pillar, the transmission mechanism is rotatably connected to the cam, and the second rocker arm can drive the cam to rotate, so that the cam drives the telescopic rod to move using the transmission mechanism.

[0015] Preferably, the cam has a guide groove, the transmission mechanism has a guide block adapted to the guide groove, and the guide block is slidably disposed in the guide groove.

[0016] The present invention also provides an aircraft comprising the above-mentioned retractable aircraft landing gear.

[0017] Compared with the prior art, the present invention has achieved the following technical effects: the retractable aircraft landing gear of the present invention includes a drive assembly, a buffer and a wheel assembly, wherein the buffer includes a main strut outer tube and a main strut piston rod, the main strut piston rod is connected to the main strut outer tube by a sliding pair, and the main strut outer tube is also transmission-connected to the drive assembly; the wheel assembly includes a connecting rocker arm and a telescopic rod, the connecting rocker arm can be connected to the wheel, one end of the telescopic rod extends from the main strut piston rod and is hinged to the connecting rocker arm, and the other end of the telescopic rod is transmission-connected to the drive assembly by a transmission mechanism, the transmission mechanism is arranged in the buffer, and the connecting rocker arm is also rotatably connected to the main strut outer tube by a torsion arm, and the drive assembly can use the transmission mechanism to drive the telescopic rod to move so that the connecting rocker arm rotates relative to the buffer.

[0018] The present invention also provides an aircraft, comprising the above-mentioned retractable aircraft landing gear, which improves the ground clearance of the aircraft and ensures the flight performance of the aircraft.

[0019] In the retractable aircraft landing gear of the present invention, the piston rod of the main strut of the buffer can slide relative to the outer tube of the main strut to absorb vibrations and impact loads during the aircraft's taxiing and landing. The drive assembly is transmission-connected to the buffer to ensure normal retraction and extension of the device. In the wheel assembly of the present invention, a connecting rocker arm is connected to the wheel, and the connecting rocker arm is connected to a torque arm to ensure normal operation of the device. At the same time, the telescopic rod is hingedly connected to the connecting rocker arm, allowing the drive assembly to use a transmission mechanism to drive the telescopic rod to move, so that the connecting rocker arm can rotate relative to the buffer, changing the angle between the connecting rocker arm and the buffer to adjust the overall length of the retractable aircraft landing gear. During takeoff and landing, the landing gear is lowered and its length increases, so that the aircraft's ground clearance meets flight requirements. When the landing gear is retracted, the drive assembly simultaneously retracts the landing gear and shortens its overall length. The transmission mechanism is disposed within the buffer, and the end of the telescopic rod connected to the transmission mechanism also extends into the buffer. When the landing gear is retracted, the storage space requirements of the aircraft are met. BRIEF DESCRIPTION OF THE DRAWINGS

[0020] In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the following briefly introduces the drawings required for use in the embodiments. Obviously, the drawings described below are only some embodiments of the present invention. For ordinary technicians in this field, other drawings can be obtained based on these drawings without paying any creative work.

[0021] Figure 1 is an axonometric schematic diagram of the retractable aircraft landing gear disclosed in an embodiment of the present invention;

[0022] Figure 2 is a schematic front view of a retractable aircraft landing gear disclosed in an embodiment of the present invention;

[0023] Figure 3 is a side view schematic diagram of the retractable aircraft landing gear disclosed in an embodiment of the present invention;

[0024] Figure 4 is a schematic top view of the retractable aircraft landing gear disclosed in an embodiment of the present invention;

[0025] Figure 5 It is an enlarged schematic diagram of a partial structure of a retractable aircraft landing gear disclosed in an embodiment of the present invention;

[0026] Figure 6 Schematic diagram of the internal structure of the retractable aircraft landing gear disclosed in an embodiment of the present invention;

[0027] Figure 7 Schematic diagram of a portion of the structure of the retractable aircraft landing gear disclosed in an embodiment of the present invention when retracted;

[0028] Figure 8 Schematic diagram of a portion of the structure of the retractable aircraft landing gear disclosed in an embodiment of the present invention when lowered;

[0029] Figure 9 Schematic diagram showing the internal structure of the retractable aircraft landing gear disclosed in an embodiment of the present invention when retracted or extended.

[0030] Among them, 100 is the drive assembly, 200 is the buffer, and 300 is the wheel assembly;

[0031] 1 is the main support outer tube, 2 is the main support piston rod, 3 is the connecting rocker arm, 4 is the telescopic rod, 5 is the transmission mechanism, 6 is the transmission sleeve, 7 is the transmission piston, 8 is the upper connecting rod, 9 is the middle sleeve, 10 is the lower connecting rod, 11 is the upper torque arm, 12 is the lower torque arm, 13 is the actuator, 14 is the first connecting rod, 15 is the second connecting rod, 16 is the third connecting rod, 17 is the first rocker arm, 18 is the second rocker arm, 19 is the cam, 20 is the guide groove, 21 is the guide block, and 22 is the oil limit needle rod. DETAILED DESCRIPTION

[0032] The following will clearly and completely describe the technical solutions in the embodiments of the present invention in conjunction with the accompanying drawings. Obviously, the described embodiments are only part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without making creative efforts are within the scope of protection of the present invention.

[0033] The object of the present invention is to provide a retractable aircraft landing gear to solve the problems existing in the above-mentioned prior art, so that the size of the aircraft landing gear can be increased to ensure smooth take-off and landing of the aircraft, while at the same time making the aircraft landing gear meet the storage space requirements.

[0034] In order to make the above-mentioned objects, features and advantages of the present invention more obvious and easy to understand, the present invention is further described in detail below with reference to the accompanying drawings and specific embodiments.

[0035] The present invention provides a retractable aircraft landing gear, including a drive assembly 100, a buffer 200 and a wheel assembly 300, wherein the buffer 200 includes a main strut outer tube 1 and a main strut piston rod 2, the main strut piston rod 2 is connected to the main strut outer tube 1 via a sliding pair, and the main strut outer tube 1 is also transmission-connected to the drive assembly 100; the wheel assembly 300 includes a connecting rocker arm 3 and a telescopic rod 4, the connecting rocker arm 3 can be connected to the wheel, one end of the telescopic rod 4 extends from the main strut piston rod 2 and is hinged to the connecting rocker arm 3, and the other end of the telescopic rod 4 is transmission-connected to the drive assembly 100 via a transmission mechanism 5, the transmission mechanism 5 is arranged in the buffer 200, the connecting rocker arm 3 is also rotatably connected to the main strut outer tube 1 via a torsion arm, and the drive assembly 100 can use the transmission mechanism 5 to drive the telescopic rod 4 to move, so that the connecting rocker arm 3 rotates relative to the buffer 200.

[0036] In the retractable aircraft landing gear of the present invention, the main strut piston rod 2 of the buffer 200 can slide relative to the main strut outer tube 1 to absorb the vibration and impact load during the taxiing and landing of the aircraft. The drive assembly 100 is connected to the buffer 200 in a transmission manner to ensure the normal retraction and extension of the device; in the wheel assembly 300 of the present invention, the connecting rocker arm 3 is connected to the wheel, and the connecting rocker arm 3 is connected to the torque arm to ensure the normal operation of the device; at the same time, the telescopic rod 4 is hinged to the connecting rocker arm 3, so that the drive assembly 100 can use the transmission mechanism 5 to drive the telescopic rod 4 to move, so that the connecting rocker The arm 3 can rotate relative to the buffer 200, changing the angle connecting the rocker arm 3 and the buffer 200 to adjust the overall length of the retractable aircraft landing gear. When the aircraft takes off and lands, the landing gear is lowered and the length increases, and the ground clearance of the aircraft meets the flight requirements. When the landing gear is retracted, the driving assembly 200 retracts the landing gear while shortening the overall length of the landing gear. The transmission mechanism 5 is arranged in the buffer 200, and the end of the telescopic rod 4 connected to the transmission mechanism 5 also extends into the buffer 200. When the landing gear is retracted, the storage space requirements of the aircraft are met. The driving assembly 200 is responsible for the retraction and extension of the landing gear as a whole, and can also drive the wheel assembly 300 to extend and retract, reducing the overall space occupied by the device and helping to reduce energy consumption.

[0037] It should also be noted that the wheel assembly 300 also includes a transmission cylinder disposed within the main support piston rod 2. The transmission cylinder includes a transmission sleeve 6 and a transmission piston 7. The transmission sleeve 6 and the transmission piston 7 are connected by a sliding pair (the sliding connection between the two forms a sliding pair). One end of the transmission piston 7 is hinged to the telescopic rod 4, and the other end of the transmission piston 7 extends into the transmission sleeve 6 and is connected to the transmission mechanism 5. The piston chamber of the transmission cylinder is connected to the piston chamber of the buffer 200. The telescopic rod 4 is connected to the transmission mechanism 5 via the transmission cylinder. Specifically, the transmission mechanism 5 uses the transmission piston 7 to drive the telescopic rod 4 to move, adjusting the length of the telescopic rod 4 extending from the main support piston rod 2. The transmission piston 7 cooperates with the transmission sleeve 6 to limit the extreme position of the telescopic rod 4, preventing the telescopic rod 4 from extending too long and improving the operating reliability of the device.

[0038] In this embodiment, the transmission mechanism 5 includes an upper connecting rod 8, an intermediate sleeve 9, and a lower connecting rod 10, which are sequentially connected. The upper connecting rod 8 and the lower connecting rod 10 are both slidably connected to the intermediate sleeve 9. The end of the upper connecting rod 8 away from the intermediate sleeve 9 is connected to the drive assembly 100, and the end of the lower connecting rod 10 away from the intermediate sleeve 9 is connected to the transmission piston 7. The upper connecting rod 8 and the lower connecting rod 10 both have a retaining block that fits into the sliding hole at the end of the intermediate sleeve 9 to prevent the upper connecting rod 8 and the lower connecting rod 10 from slipping out of the intermediate sleeve 9. This allows the drive assembly 100 to drive the telescopic rod 4 by pulling the transmission mechanism 5, while also preventing the buffer 200 from pushing the transmission mechanism 5 during the buffering process and affecting the normal operation of the telescopic rod 4. This improves the operational reliability of the transmission mechanism 5 and the telescopic rod 4 while ensuring the normal operation of the buffer 200. In this embodiment, the intermediate sleeve 9 passes through the main strut piston rod 2 and is connected to the drive assembly 100. This prevents the transmission mechanism 5 from affecting the operation of the buffer 200, saves space on the entire device, and ensures that the device can be stowed in an aircraft. It should also be noted here that a limiting convex ring is provided on the inner wall of the main support outer tube 1, which can limit the extreme position of the main support piston rod 2 and improve the working safety factor of the buffer 200.

[0039] Among them, the torque arm includes an upper torque arm 11 and a lower torque arm 12. One end of the upper torque arm 11 is hinged to the outer tube 1 of the main pillar, and the other end of the upper torque arm 11 is hinged to the lower torque arm 12. The end of the lower torque arm 12 away from the upper torque arm 11 is hinged to the connecting rocker arm 3. The torque arm can ensure the normal steering of the wheel. It should be noted that the hinge point of the connecting rocker arm 3 and the telescopic rod 4 is located between the connection point of the connecting rocker arm 3 and the wheel and the hinge point of the connecting rocker arm 3 and the lower torque arm 12, ensuring that the telescopic rod 4 can drive the connecting rocker arm 3 to rotate, thereby adjusting the overall height of the device.

[0040] Furthermore, when the retractable aircraft landing gear of the present invention is retracted, the wheel assembly 300 is retracted. At this point, the connecting rocker arm 3 abuts against the main strut piston rod 2, and the length of the connecting rocker arm 3 is perpendicular to the axis of the buffer 100, reducing the overall length of the landing gear. When the landing gear is lowered, the wheel assembly 300 is extended. At this point, the connecting rocker arm 3 rotates, and the end of the connecting rocker arm 3 connected to the wheel flips downward, increasing the overall length of the landing gear and meeting the aircraft's ground clearance requirements. Specifically, during takeoff and lift, lift gradually increases. When lift increases to a certain level, the gas space in the piston chamber of the buffer 200 increases, allowing oil to enter the piston chamber of the transmission cylinder, and using the transmission piston 7 to push the telescopic rod 4, which in turn pushes the connecting rocker arm 3 to rotate, increasing the overall length of the device. Since the transmission cylinder is disposed within the main strut piston rod 2, the cross-sectional area of ​​the piston cavity of the buffer 200 is greater than the cross-sectional area of ​​the transmission piston 7 cavity. The telescopic rod 4 extends a longer distance from the main strut piston rod 2, thereby ensuring that the aircraft's ground clearance meets the requirements and preventing the tail of the aircraft from scraping the ground. When the aircraft lands, a damping hole is provided above the main strut outer tube 1. The piston cavity of the buffer 200 is connected to the damping hole via the oil-limiting needle rod 22. When the telescopic rod 4 bears part of the load, it slowly retracts the main strut piston rod 2, connecting the rocker arm 3 to the main strut outer tube 1. The buffer 200 bears the main load, providing effective protection for the telescopic rod 4 and preventing it from failing due to excessive load. In addition, the provision of the damping hole and the oil-limiting needle rod 22 in the buffer 200 is common knowledge to those skilled in the art and will not be elaborated here.

[0041] Specifically, the drive assembly 100 includes an actuator 13 and a first connecting rod 14. The length of the actuator 13 is adjustable. The movable end of the actuator 13 is hinged to the main support outer tube 1, and the fixed end of the actuator 13 is hinged to the first connecting rod 14. The first connecting rod 14 is also hinged to the main support outer tube 1. The hinge point between the actuator 13 and the main support outer tube 1 does not coincide with the hinge point between the first connecting rod 14 and the main support outer tube 1. The change in the length of the actuator 13 can use the first connecting rod 14 to drive the main support outer tube 1 to rotate, smoothly achieving the retraction and extension of the entire device. In actual application, the actuator 13 can be selected from a cylinder or a telescopic rod 4 structure, which can be selected according to the actual working conditions to meet different working requirements and improve the flexibility and adaptability of the device.

[0042] To enable the drive assembly 100 to simultaneously drive the telescopic rod 4 and simplify the overall structure of the device, the drive assembly 100 also includes a second connecting rod 15, a third connecting rod 16, a first rocker arm 17, and a second rocker arm 18. One end of the second connecting rod 15 is hinged to the first connecting rod 14, and the other end of the second connecting rod 15 is hinged to one end of the first rocker arm 17, with the hinge surface of the two being a spherical surface. The other end of the first rocker arm 17 is hinged to one end of the third connecting rod 16, and the other end of the third connecting rod 16 is hinged to one end of the second rocker arm 18. The other end of the second rocker arm 18 is connected to the transmission mechanism 5. When the actuator 13 drives the first connecting rod 14 to rotate, the first connecting rod 14, through the second connecting rod 15, the first rocker arm 17, and the third connecting rod 16, drives the second rocker arm 18 to rotate. The second rocker arm 18, through the transmission mechanism 5, drives the transmission piston 7 to move, thereby achieving the purpose of driving the telescopic rod 4. In this embodiment, the second rocker lever utilizes the upper connecting rod 8 to drive the transmission piston 7, while the first connecting rod 14 utilizes the second connecting rod 15, the first rocker arm 17, and the third connecting rod 16 to drive the second rocker arm 18. This simple linkage mechanism provides reliable transmission, smoothly driving the telescopic rod 4 while minimizing the overall space occupied by the device, ensuring that the device can be easily stored. In practical applications, the second connecting rod 15 can be hinged to one end of the first rocker arm 17 using a fisheye ball joint.

[0043] More specifically, the second rocker arm 18 is connected to a cam 19, which is located within the main support outer tube 1. The upper connecting rod 8 of the transmission mechanism 5 is rotatably connected to the cam 19. The second rocker arm 18 can drive the cam 19 to rotate, so that the cam 19, via the transmission mechanism 5, drives the telescopic rod 4. The structure and dimensions of the cam 19 are appropriately designed so that when the cam 19 rotates, it can drive the transmission mechanism 5 through the upper connecting rod 8, and in turn, drive the transmission piston 7 and telescopic rod 4 connected to the transmission mechanism 5. In actual use, the second connecting rod 15 can be connected to the cam 19 via a connecting rod that passes through the outer wall of the main support outer tube 1 to achieve smooth power transmission.

[0044] In order to further ensure the working reliability of the device, the cam 19 has a guide groove 20, and the transmission mechanism 5 has a guide block 21 adapted to the guide groove 20. The guide block 21 is slidably arranged in the guide groove 20. When the cam 19 rotates, the guide block 21 slides along the guide groove 20, thereby pulling the transmission mechanism 5 to move.

[0045] Furthermore, the present invention also provides an aircraft, comprising the above-mentioned retractable aircraft landing gear, which improves the ground clearance of the aircraft and ensures the flight performance of the aircraft.

[0046] The retractable aircraft landing gear of the present invention, during the working process of the device, the actuator 13 drives the telescopic rod 4 from the lowered state (such as Figure 1As shown in the figure, the telescopic rod 4 is slowly retracted, and at the same time, the first connecting rod 14 is rotated relative to the outer tube 1 of the main support, thereby pushing the second connecting rod 15 downward. The second connecting rod 15 drives the third connecting rod 16 upward through the first rocker arm 17. The third connecting rod 16 drives the second rocker arm 18 to rotate, thereby driving the cam 19 inside the buffer 200 to rotate. The cam 19 drives the transmission mechanism 5 through the guide groove 20 to lift the transmission piston 7, causing the telescopic rod 4 to retract into the buffer 200. Figure 6 Similarly, when the device is put down, the cam 19 inside the buffer 200 will produce an opposite angle of rotation, and under the action of the air cavity pressure of the piston cavity 200 of the buffer, the transmission piston 7 moves downward and the telescopic rod 4 pops out.

[0047] During the aircraft takeoff and landing process, when the aircraft lands, the telescopic rod 4 will first bear the load. When the telescopic rod 4 is fully retracted into the main strut piston rod 2, the connecting rocker arm 3 contacts the main strut piston rod 2, so that the telescopic rod 4 no longer bears a larger load, thereby preventing the telescopic rod 4 from deformation and damage. When the aircraft takes off, the aircraft gradually rises and the lift gradually increases. When the lift increases to a certain value, the telescopic rod 4 pops out to prevent the tail of the aircraft from scraping the ground.

[0048] Compared with the landing gear in the prior art, the retractable aircraft landing gear of the present invention can automatically extend when the device is lowered, and pop out during the aircraft takeoff to prevent the tail of the aircraft from scraping the ground; the device can automatically retract when it is retracted to meet the storage space requirements; at the same time, the telescopic rod 4 can also be used as a primary buffer, and as a primary buffer during the landing phase, after the connecting rocker arm 3 contacts the main strut piston rod 2, the buffer 200 still assumes the main buffering role.

[0049] The present invention uses specific examples to illustrate the principles and implementation methods of the present invention. The above examples are only intended to help understand the method and core concept of the present invention. At the same time, those skilled in the art will find that the specific implementation methods and application scopes may vary based on the concept of the present invention. In summary, the contents of this specification should not be construed as limiting the present invention.

Claims

1. A retractable aircraft landing gear, characterized in that: include: Drive components; A buffer, the buffer comprising a main support outer tube and a main support piston rod, the main support piston rod being connected to the main support outer tube via a sliding pair, and the main support outer tube being further transmission-connected to the drive assembly; a wheel assembly, the wheel assembly comprising a connecting rocker arm and a telescopic rod, the connecting rocker arm being capable of being connected to the wheel, one end of the telescopic rod extending from the piston rod of the main strut and hingedly connected to the connecting rocker arm, the other end of the telescopic rod being transmission-connected to the drive assembly via a transmission mechanism, the transmission mechanism being disposed within the buffer, the connecting rocker arm being further rotatably connected to the outer cylinder of the main strut via a torsion arm, the drive assembly being capable of utilizing the transmission mechanism to drive the telescopic rod to move, thereby causing the connecting rocker arm to rotate relative to the buffer; The wheel assembly also includes a transmission cylinder arranged in the main pillar piston rod, the transmission cylinder includes a transmission sleeve and a transmission piston, the transmission sleeve and the transmission piston are connected by a sliding pair, one end of the transmission piston is hinged to the telescopic rod, and the other end of the transmission piston extends into the transmission sleeve and is connected to the transmission mechanism, and the piston chamber of the transmission cylinder is connected to the piston chamber of the buffer.

2. The retractable aircraft landing gear according to claim 1, characterized in that: The transmission mechanism includes an upper connecting rod, an intermediate sleeve and a lower connecting rod connected in sequence. The upper connecting rod and the lower connecting rod are both slidably connected to the intermediate sleeve. The end of the upper connecting rod away from the intermediate sleeve is connected to the drive assembly, and the end of the lower connecting rod away from the intermediate sleeve is connected to the transmission piston.

3. The retractable aircraft landing gear according to claim 1, characterized in that: The torque arm includes an upper torque arm and a lower torque arm, one end of the upper torque arm is hinged to the outer tube of the main pillar, the other end of the upper torque arm is hinged to the lower torque arm, and the end of the lower torque arm away from the upper torque arm is hinged to the connecting rocker arm.

4. The retractable aircraft landing gear according to claim 1, wherein: When the retractable aircraft landing gear is in a retracted state, the wheel assembly is in a retracted state, and the connecting rocker arm abuts against the main strut piston rod.

5. The retractable aircraft landing gear according to any one of claims 1 to 4, characterized in that: The drive assembly includes an actuator and a first connecting rod. The length of the actuator can be adjusted. The movable end of the actuator is hinged to the outer tube of the main pillar. The fixed end of the actuator is hinged to the first connecting rod. The first connecting rod is also hinged to the outer tube of the main pillar.

6. The retractable aircraft landing gear according to claim 5, characterized in that: The drive assembly also includes a second connecting rod, a third connecting rod, a first rocker arm and a second rocker arm, one end of the second connecting rod is hinged to the first connecting rod, the other end of the second connecting rod is hinged to one end of the first rocker arm, and the hinge surfaces of the two are spherical surfaces, the other end of the first rocker arm is hinged to one end of the third connecting rod, the other end of the third connecting rod is hinged to one end of the second rocker arm, and the other end of the second rocker arm is connected to the transmission mechanism.

7. The retractable aircraft landing gear according to claim 6, characterized in that: The second rocker arm is connected to a cam, which is located in the outer tube of the main pillar. The transmission mechanism is rotationally connected to the cam, and the second rocker arm can drive the cam to rotate, so that the cam drives the telescopic rod to move using the transmission mechanism.

8. The retractable aircraft landing gear according to claim 7, characterized in that: The cam has a guide groove, and the transmission mechanism has a guide block adapted to the guide groove. The guide block is slidably arranged in the guide groove.

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