Buffer of aircraft landing gear

Abstract

According to the technical scheme, the buffer is characterized in that the buffer comprises an outer ring, and the outer ring is used for being connected with a wheel axle frame; the inner ring is coaxially arranged in the outer ring and is used for being connected with a machine body; the elastic body is arranged between the inner ring and the outer ring in a vulcanization mode so that the axle frame can be compressed to rotate during landing, and the inner ring and the outer ring are driven to rotate relatively so as to compress the elastic body for buffering and vibration isolation. The buffer of the aircraft landing gear has the advantages that the structure is simple, and the effect of full buffering and damping can be achieved when the buffer is applied to a small aircraft.

Description

Technical Field

[0001] The present invention relates to the technical field of aircraft landing gear, and more particularly to a buffer of an aircraft landing gear. Background Art

[0002] The landing gear is an accessory device at the bottom of the aircraft used to support the aircraft during takeoff, landing or ground taxiing and to move on the ground. For helicopters, the landing gear is the only part that supports the entire aircraft, so it is an indispensable part of the aircraft. For helicopter landing gear, it is used to provide support during takeoff and landing, so that the aircraft can take off and land normally. The cushioning of the landing gear is an important part that determines the impact force of the aircraft during landing to protect the electronic components inside the body.

[0003] The existing Chinese patent with announcement number: CN205837180U discloses a buffer landing gear, including a rotating shaft, a bracket hinged to the rotating shaft, a buffer structure connected between the bracket and the rotating shaft, including a first sleeve piece hinged to the rotating shaft at one end, a second sleeve piece hinged to the bracket at one end, the first sleeve piece and the second sleeve piece are sleeved, a connecting ring is sleeved on the outside of the first sleeve piece and the second sleeve piece, a first buffer spring is provided between the connecting ring and the hinged end of the first sleeve piece, a second buffer spring is provided between the connecting ring and the hinged end of the second sleeve piece, and the first buffer spring and the second buffer spring have different limit loads. Due to the different limit loads of the first buffer spring and the second buffer spring, when subjected to external force, one spring is first actuated and compressed, and the other spring starts to act and be compressed, so as to adapt to various complex landing environments.

[0004] Although the prior art provides a buffer landing gear with a buffer function, the overall structure of the buffer landing gear is relatively complex, so that the cost is too high when applied to a small aircraft. Therefore, a simple and practical landing gear buffer is urgently needed. Summary of the invention

[0005] In view of the shortcomings of the prior art, the object of the present invention is to provide a buffer for an aircraft landing gear, which has a simple structure and can fully buffer and reduce shock when applied to small aircraft.

[0006] To achieve the above object, the present invention provides the following technical solutions: A buffer for an aircraft landing gear, comprising: An outer ring, the outer ring being used to be connected to the axle frame; An inner ring, the inner ring is coaxially arranged inside the outer ring and is used to connect with the fuselage; The elastomer is vulcanized and arranged between the inner ring and the outer ring, so that the axle frame is compressed and rotated during landing, driving the inner ring and the outer ring to rotate relative to compress the elastomer to buffer and isolate vibration.

[0007] As a further improvement of the present invention, a tenon is provided in the circumferential direction of the outer diameter of the inner ring, and the elastic member is sleeved outside the tenon and matched with the tenon.

[0008] As a further improvement of the present invention, a keyway is provided on the circumference of the outer wall of the outer ring, a connecting key is installed in the keyway, and the connecting key is used to transfer the torsional load of the axle frame.

[0009] As a further improvement of the present invention, the end of the outer ring is connected to an end cover via a thread, and the end cover is used to connect and position the inner ring and the outer ring.

[0010] As a further improvement of the present invention, a flexible support belt is provided between the inner ring and the end cover, and the flexible support belt is used to transfer radial load between the inner ring and the end cover.

[0011] As a further improvement of the present invention, a thrust washer is further provided between the inner ring and the end cover, and the thrust washer is used to transfer the axial load of the inner ring to the end cover.

[0012] As a further improvement of the present invention, O-rings are further provided on both sides of the flexible support belt, and the O-rings are used to prevent the grease from evaporating and leaking.

[0013] Beneficial effects of the present invention: When the aircraft is landing, the fuselage continues to press down after the wheels touch the ground, and the wheel position no longer changes in the vertical direction. As the fuselage continues to sink, the axle frame deflects counterclockwise with the joint axis as the fulcrum. The outer ring of the buffer at the joint axis is fixedly connected to the axle frame, and the inner ring of the buffer is fixedly connected to the fuselage. Therefore, relative rotation occurs between the inner and outer rings of the buffer, and the vulcanized elastomer between the inner and outer rings is squeezed or stretched. The buffer begins to absorb the landing impact of the aircraft. When the tenon of the inner ring gradually approaches the outer ring, the elastic members on both sides of the tenon approach the compression limit on one side and the tensile limit on the other side, and the stiffness and support are gradually improved. When the vertical height position of the aircraft tends to be stable, the downward force exerted by the fuselage on the landing gear also tends to be stable, and the reaction force of the elastic member arranged in the buffer to restore its own shape is balanced. When the aircraft stops, the elastic member remains in its original state, completing the release of the damping force. BRIEF DESCRIPTION OF THE DRAWINGS

[0014] Figure 1 A schematic diagram showing the three-dimensional structure of the buffer; Figure 2 A cross-sectional diagram showing a tenon.

[0015] Figure numerals: 1. connecting key; 2. outer ring; 3. end cover; 4. inner ring; 5. O-ring; 6. flexible support belt; 7. thrust washer; 8. elastic member; 9. tenon. DETAILED DESCRIPTION

[0016] The present invention is further described in detail below in conjunction with the accompanying drawings and embodiments. The same parts are represented by the same reference numerals. It should be noted that the words "front", "rear", "left", "right", "upper" and "lower" used in the following description refer to directions in the accompanying drawings, and the words "bottom surface" and "top surface", "inner" and "outer" refer to directions toward or away from the geometric center of a specific component, respectively.

[0017] refer to Figure 1 and Figure 2 As shown, a specific embodiment of a buffer of an aircraft landing gear of the present invention includes a buffer for connecting a fuselage and a wheel axle frame, the buffer includes an outer ring 2, an inner ring 4 and an elastic body, the outer wall circumference of the outer ring 2 is provided with a keyway, the keyway is used to install a connecting key 1, and the connecting key 1 is connected to the wheel axle frame and used to transmit the torsional load, the outer ring 2 is fixedly connected to the wheel axle frame to transmit the radial load and axial load between the wheel axle frame and the connecting key 1, the inner ring 4 is coaxially arranged inside the outer ring 2, and is fixedly connected to the fuselage interface, so that the radial force is transmitted through the inner wall of the inner ring 4 and the interface of the fuselage, The end of the outer ring 2 is connected to the end cover 3 by a thread to connect and position the inner ring 4 and the outer ring 2 so that radial load and axial load can be transmitted between the inner ring 4 and the outer ring 2. The elastomer is arranged between the outer ring 2 and the inner ring 4 by vulcanization and is used to transmit torsional load. Because the elastomer material is a flexible material, it absorbs the torsional impact transmitted by the axle frame when subjected to tensile and compressive deformation to form a buffering and damping effect. A tenon 9 is arranged in the circumferential direction of the outer diameter of the inner ring 4, and the elastic member 8 is sleeved on the tenon 9. The tenon 9 improves the support for the elastic member 8 and improves the buffering effect during buffering.

[0018] A flexible support belt 6 is provided between the inner ring 4 and the end cover 3. The flexible support belt 6 is used to transfer radial loads between the inner ring 4 and the end cover 3 to reduce the wear between the inner ring 4 and the end cover 3. A thrust washer 7 is also provided between the inner ring 4 and the end cover 3. The thrust washer 7 is used to transfer the axial load of the inner ring 4 to the end cover 3, further assisting in reducing the wear between the inner ring 4 and the end cover 3. O-rings 5 ​​are also provided on both sides of the flexible support belt 6. The O-rings 5 ​​are used to prevent grease evaporation and leakage to extend the maintenance period of the buffer.

[0019] Working principle and effect: During the landing of the aircraft, the fuselage continues to be pressed down after the wheels touch the ground, and the position of the wheels no longer changes in the vertical direction. As the fuselage continues to sink, the axle frame deflects counterclockwise with the joint axis as the fulcrum. The outer ring 2 of the buffer at the joint axis is fixedly connected to the axle frame, and the inner ring 4 of the buffer is fixedly connected to the fuselage. Therefore, relative rotation occurs between the inner and outer rings 2 of the buffer, and the vulcanized elastomer between the inner and outer rings 2 is squeezed or stretched, and the buffer begins to absorb the landing impact of the aircraft. When the tenon 9 of the inner ring 4 gradually approaches the outer ring 2, the elastic members 8 on both sides of the tenon 9 approach the compression limit on one side and the tensile limit on the other side, and the stiffness and support are gradually improved. When the vertical height position of the aircraft tends to be stable, the downward force applied by the fuselage to the landing gear also tends to be stable, and the reaction force of the elastic member 8 set in the buffer to restore its own shape is balanced. When the aircraft stops, the elastic member 8 remains in its original state, completing the release of the damping force.

[0020] The above is only a preferred embodiment of the present invention, and the protection scope of the present invention is not limited to the above embodiments. All technical solutions under the concept of the present invention belong to the protection scope of the present invention. It should be pointed out that for ordinary technicians in this technical field, some improvements and modifications without departing from the principle of the present invention should also be regarded as the protection scope of the present invention.

Claims

1. A buffer for an aircraft landing gear, characterized in that: include: An outer ring (2), the outer ring (2) being used for connecting with the axle frame; An inner ring (4), the inner ring (4) is coaxially arranged inside the outer ring (2) and is used to connect with the fuselage; An elastomer is vulcanized and arranged between the inner ring (4) and the outer ring (2), so that when landing, the axle frame is compressed and rotated, driving the inner ring (4) and the outer ring (2) to rotate relative to each other to compress the elastomer for vibration isolation.

2. The buffer of an aircraft landing gear according to claim 1, characterized in that: The inner ring (4) is provided with a tenon (9) in the circumferential direction of the outer diameter, and the elastic member (8) is sleeved outside the tenon (9) and matched with the tenon (9).

3. The buffer of an aircraft landing gear according to claim 2, characterized in that: The outer wall circumference of the outer ring (2) is provided with a keyway, in which a connecting key (1) is installed, and the connecting key (1) is used to transmit the torsional load of the axle frame.

4. The buffer of an aircraft landing gear according to claim 3, characterized in that: The end of the outer ring (2) is connected to an end cover (3) via a thread, and the end cover (3) is used to connect and position the inner ring (4) and the outer ring (2).

5. The buffer of an aircraft landing gear according to claim 4, characterized in that: A flexible support belt (6) is provided between the inner ring (4) and the end cover (3), and the flexible support belt (6) is used to transfer radial loads between the inner ring (4) and the end cover (3).

6. The buffer of an aircraft landing gear according to claim 5, characterized in that: A thrust washer (7) is also provided between the inner ring (4) and the end cover (3), and the thrust washer (7) is used to transfer the axial load of the inner ring (4) to the end cover (3).

7. The buffer of an aircraft landing gear according to claim 6, characterized in that: O-rings (5) are also provided on both sides of the flexible support belt (6), and the O-rings (5) are used to prevent grease from evaporating and leaking.

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