Damping structure for undercarriage of model airplane unmanned aerial vehicle

Abstract

The damping structure comprises a first supporting rod and a second supporting rod, a connecting shell is arranged between the first supporting rod and the second supporting rod, a transmission gear is rotationally arranged in the connecting shell, the second supporting rod is connected with the transmission gear, and the second supporting rod is connected with the transmission gear. A movable block is movably arranged in the connecting shell, a rack meshed with the transmission gear is fixedly connected to the surface of the movable block, a connecting pipe is arranged on the side wall of the connecting shell in a penetrating mode, and a piston movably connected with the connecting pipe is fixedly connected to the surface of the movable block. The first supporting rod and the second supporting rod jointly form an undercarriage, relative rotation of the second supporting rod relative to the first supporting rod is converted into movement of the movable block, the movable block drives the piston to move in the connecting pipe, the sealing plug overcomes the elastic element to move, the piston cannot reset under the action of the sealing plug, and the buffering effect is achieved.

Description

Technical Field

[0001] The utility model relates to the technical field of model drones, in particular to a shock-absorbing structure for the landing gear of a model drone. Background Technique

[0002] A model drone is a small aircraft that a pilot manipulates to fly in the air through a remote control. It mainly includes components such as a remote control handle, a fuselage, wings, propellers, a landing gear, and a camera. Some enthusiasts and technicians can use the model drone for taking pictures and so on.

[0003] At present, the common landing gear of model drones is generally fixed. When the model drone lands on the ground, there will be a certain impact force, which will be directly transmitted to the fuselage through the landing gear. Over time, it is easy to cause the loosening of the internal components of the fuselage, which is not conducive to the use of the drone. If the landing gear is made of elastic material, when the model lands, although the landing gear will deform to play a buffering role, the landing gear will quickly rebound, easily causing the drone to bounce, making the landing process of the drone difficult to operate. Therefore, a shock-absorbing structure for the landing gear of a model drone is proposed. Content of the Utility Model

[0004] The purpose of the utility model is to provide a shock-absorbing structure for the landing gear of a model drone to solve the problems raised in the above background technique.

[0005] To solve the above technical problems, the utility model provides the following technical solution: A shock-absorbing structure for the landing gear of a model drone, including a first support rod and a second support rod. A connection shell is provided between the first support rod and the second support rod. The first support rod is fixedly connected to the outer surface of the connection shell, and the second support rod is rotatably connected to the connection shell. A transmission gear is rotatably provided inside the connection shell, and the second support rod is connected to the transmission gear. An activity block is movably arranged inside the connection shell. A rack meshing with the transmission gear is fixedly connected to the surface of the activity block. A connection pipe penetrates through the side wall of the connection shell. A piston movably connected to the connection pipe is fixedly connected to the surface of the activity block. A sealing plug is connected to the inside of the connection pipe through an elastic element.

[0006] According to the above technical solution, a limiting ring is fixedly connected to the inner peripheral surface of the connection pipe. A limiting pipe is arranged at one end of the connection pipe far from the activity block. An activity rod is movably arranged on the inner surface of the limiting pipe. The sealing plug is fixedly connected to the activity rod. The elastic element is sleeved on the outer wall of the activity rod, and both ends of the elastic element are respectively connected to the sealing plug and the limiting pipe.

[0007] According to the above technical solution, the limiting pipe is coaxially arranged with the connection pipe, and the limiting pipe is movably connected to the connection pipe.

[0008] According to the above technical solution, an external thread is provided on the outer peripheral surface of the limit tube. One end of the limit tube corresponding to the outside of the connection shell is rotatably provided with an adjustment knob, and an adjustment block screwed to the limit tube is fixedly connected to the surface of the adjustment knob.

[0009] According to the above technical solution, a plurality of chutes extending in the same direction are fixedly connected to the outer peripheral surface of the limit tube, and a limit plate is fixedly connected to the inner surface of the connection shell. The limit plates are respectively slidably disposed inside the chutes.

[0010] According to the above technical solution, a transmission block is fixedly connected to the movable rod passing through the adjustment knob.

[0011] Compared with the prior art, the beneficial effects achieved by the present utility model are as follows: In the present utility model, by providing a first support rod and a second support rod, the first support rod and the second support rod together form a landing gear. A connection shell is provided between the first support rod and the second support rod. A gear, a rack and a movable block are provided inside the connection shell. The relative rotation of the second support rod relative to the first support rod is converted into the movement of the movable block. The movable block drives the piston to move inside the connection tube, so that the sealing plug overcomes the elastic element to move, and the piston cannot return to its original position under the action of the sealing plug, so that the landing gear will not rebound, playing a buffering role and avoiding the jumping of the drone at the same time, making it easier to operate. Description of the Drawings

[0012] The drawings are used to provide a further understanding of the present utility model and constitute a part of the specification. Together with the embodiments of the present utility model, they are used to explain the present utility model and do not constitute a limitation to the present utility model. In the drawings:

[0013] Figure 1 is the front view sectional structure schematic diagram of the present utility model;

[0014] Figure 2 is the internal structure schematic diagram of the connection shell of the present utility model;

[0015] Figure 3 is the structure schematic diagram of the limit tube of the present utility model;

[0016] Figure 4 is the front view sectional structure schematic diagram of the connection tube of the present utility model;

[0017] In the figure: 1 - first support rod, 2 - second support rod, 3 - connection shell, 4 - transmission gear, 5 - movable block, 6 - rack, 7 - connection tube, 8 - piston, 9 - sealing plug, 10 - limit ring, 11 - limit tube, 12 - movable rod, 13 - adjustment knob, 14 - adjustment block, 15 - chute, 16 - limit plate, 17 - transmission block. Detailed Embodiments

[0018] Next, the technical solutions in the embodiments of the present invention will be clearly and completely described in conjunction with the accompanying drawings in the embodiments of the present invention. Obviously, the described embodiments are only a part of the embodiments of the present invention, rather than all the embodiments. All other embodiments obtained by those of ordinary skill in the art based on the embodiments of the present invention without creative efforts shall fall within the protection scope of the present invention.

[0019] Please refer to Figures 1-4 , the present invention provides a technical solution: a shock-absorbing structure for the landing gear of a model UAV, including a first support rod 1 and a second support rod 2. As Figure 1 shown, a connection shell 3 is provided between the first support rod 1 and the second support rod 2. The first support rod 1 and the second support rod 2 are arranged in parallel to form the landing gear. The first support rod 1 is fixedly connected to the outer surface of the connection shell 3, and the second support rod 2 is rotatably connected to the connection shell 3. The second support rod 2 rotates relative to the connection shell 3, which can play a buffering function. As Figure 1 shown, a transmission gear 4 is rotatably provided inside the connection shell 3. The second support rod 2 is connected to the transmission gear 4. An activity block 5 is movably arranged inside the connection shell 3, and the activity block 5 can slide horizontally inside the connection shell 3. As Figure 2 shown, a strip-shaped through groove is provided through the end surface of the activity block 5. A positioning rod that is slidably connected to the strip-shaped through groove is fixedly connected to the inner surface of the connection shell 3, so that the activity block 5 can stably slide inside the connection shell 3. A through groove for the second support rod 2 to pass through and rotate is provided through the side wall of the connection shell 3. A rack 6 that meshes with the transmission gear 4 is fixedly connected to the surface of the activity block 5. A connection pipe 7 is provided through the side wall of the connection shell 3. A piston 8 that is movably connected to the connection pipe 7 is fixedly connected to the surface of the activity block 5. A sealing plug 9 is connected to the inside of the connection pipe 7 through an elastic element. The sealing plug 9 seals the connection pipe 7 under the action of the elastic element. When the second support rod 2 rotates relative to the first support rod 1, the transmission gear 4 is driven to rotate by the second support rod 2. The transmission gear 4 drives the activity block 5 to slide through the rack 6. The activity block 5 drives the piston 8 to slide inside the connection pipe 7, so that the sealing plug 9 moves against the elastic element and the gas is discharged. This process can provide buffering and reduce the vibration generated by the UAV. However, the piston 8 cannot reset, so the second support rod 2 will not reset and the landing gear will not rebound;

[0020] Specifically, as Figure 4As shown, a limiting ring 10 is fixedly connected to the inner peripheral surface of the connecting pipe 7. One end of the connecting pipe 7 away from the movable block 5 is provided with a limiting pipe 11. An activity rod 12 is movably arranged on the inner surface of the limiting pipe 11. The activity rod 12 extends along the axial direction of the connecting pipe 7. The sealing plug 9 is fixedly connected to the activity rod 12. The elastic element is sleeved on the outer wall of the activity rod 12, and both ends of the elastic element are respectively connected to the sealing plug 9 and the limiting pipe 11. Under the action of the elastic element, the sealing plug 9 is closely attached to the limiting ring 10 to form a seal. The outer diameter of the sealing plug 9 is smaller than the inner diameter of the connecting pipe 7 to ensure that gas can flow inside the connecting pipe 7. A closed cavity is formed between the sealing plug 9 and the piston 8. When the piston 8 moves towards the sealing plug 9, the sealing plug 9 will move under pressure to overcome the elastic element, so that the internal gas is discharged, and the piston 8 cannot move in the reverse direction;

[0021] Specifically, the limiting pipe 11 is coaxially arranged with the connecting pipe 7, and the limiting pipe 11 is movably connected to the connecting pipe 7. By adjusting the position of the limiting pipe 11, the pre-tightening force of the elastic element is controlled, and thus the force required for the second support rod 2 to rotate can be adjusted, so as to flexibly adjust the damping of the landing gear according to the weight of the drone and the landing environment;

[0022] Specifically, an external thread is provided on the outer peripheral surface of the limiting pipe 11. An adjusting knob 13 is rotatably arranged at one end of the limiting pipe 11 corresponding to the outside of the connecting shell 3. An adjusting block 14 screwed to the limiting pipe 11 is fixedly connected to the surface of the adjusting knob 13. By rotating the adjusting knob 13, the position of the limiting pipe 11 can be adjusted under the action of thread fit;

[0023] Specifically, in order to prevent the limiting pipe 11 from rotating together with the adjusting block 14, a plurality of chutes 15 extending in the same direction are fixedly connected to the outer peripheral surface of the limiting pipe 11. A limiting plate 16 is fixedly connected to the inner surface of the connecting shell 3. The limiting plates 16 are respectively slidably arranged inside the chutes 15. When adjusting the position of the limiting pipe 11, the limiting plate 16 slides relative to the chute 15 to limit the degree of freedom of the limiting pipe 11 and prevent it from rotating;

[0024] Specifically, a transmission block 17 is fixedly connected to the activity rod 12 passing through the adjusting knob 13. After landing is completed, the movement of the sealing plug 9 can be controlled through the transmission block 17 to allow external gas to enter the closed cavity, so that the second support rod 2 is reset for the next landing;

[0025] When the present utility model is in use, when the drone lands, the second support rod 2 rotates relative to the first support rod 1 under the action of impact force. During this process, the rack 6 is driven by the transmission gear 4 to move. The rack 6 causes the movable block 5 to slide inside the connecting shell 3. The movable block 5 drives the piston 8 to slide inside the limiting pipe 11. The sealing plug 9 is separated from the limiting ring 10 under pressure, and the gas is discharged to achieve buffering.

[0026] It should be noted that in this text, relational terms such as first and second are only used to distinguish one entity or operation from another entity or operation, and do not necessarily require or imply any actual relationship or order between these entities or operations. Moreover, the term "comprising", "including" or any other variant thereof is intended to cover non-exclusive inclusion, so that a process, method, article or device comprising a series of elements not only includes those elements, but also includes other elements not expressly listed, or further includes elements inherent to such process, method, article or device.

[0027] Finally, it should be noted that the above are only preferred embodiments of the present utility model and are not used to limit the present utility model. Although the present utility model has been described in detail with reference to the foregoing embodiments, those skilled in the art can still modify the technical solutions described in the foregoing embodiments, or perform equivalent replacements for some of the technical features. Any modifications, equivalent replacements, improvements, etc. made within the spirit and principle of the present utility model shall be included within the protection scope of the present utility model.

Claims

1. A shock absorption structure for the landing gear of a model UAV, comprising a first support rod (1) and a second support rod (2), characterized in that: A connection shell (3) is provided between the first support rod (1) and the second support rod (2). The first support rod (1) is fixedly connected to the outer surface of the connection shell (3), and the second support rod (2) is rotatably connected to the connection shell (3). A transmission gear (4) is rotatably provided inside the connection shell (3), and the second support rod (2) is connected to the transmission gear (4). A movable block (5) is movably arranged inside the connection shell (3). A rack (6) meshing with the transmission gear (4) is fixedly connected to the surface of the movable block (5). A connection pipe (7) penetrates through the side wall of the connection shell (3). A piston (8) movably connected to the connection pipe (7) is fixedly connected to the surface of the movable block (5). A sealing plug (9) is connected inside the connection pipe (7) through an elastic element.

2. The shock absorption structure for the landing gear of a model aircraft drone according to claim 1, characterized in that: A limiting ring (10) is fixedly connected to the inner peripheral surface of the connection pipe (7). A limiting pipe (11) is arranged at one end of the connection pipe (7) far from the movable block (5). A movable rod (12) is movably arranged on the inner surface of the limiting pipe (11). The sealing plug (9) is fixedly connected to the movable rod (12). The elastic element is sleeved on the outer wall of the movable rod (12), and two ends of the elastic element are respectively connected to the sealing plug (9) and the limiting pipe (11).

3. The shock-absorbing structure for the landing gear of a model aircraft drone according to claim 2, characterized in that: The limiting pipe (11) is coaxially arranged with the connection pipe (7), and the limiting pipe (11) is movably connected to the connection pipe (7).

4. A shock-absorbing structure for the landing gear of a model UAV according to claim 3, characterized in that: External threads are provided on the outer peripheral surface of the limiting pipe (11). An adjusting knob (13) is rotatably provided at one end of the limiting pipe (11) corresponding to the outside of the connection shell (3). An adjusting block (14) screwed to the limiting pipe (11) is fixedly connected to the surface of the adjusting knob (13).

5. A shock-absorbing structure for the landing gear of a model UAV according to claim 4, characterized in that: A plurality of chutes (15) extending in the same direction are fixedly connected to the outer peripheral surface of the limiting pipe (11). A limiting plate (16) is fixedly connected to the inner surface of the connection shell (3), and the limiting plates (16) are respectively slidably arranged inside the chutes (15).

6. The shock-absorbing structure for the landing gear of a model UAV according to claim 5, wherein: The movable rod (12) penetrates through the adjusting knob (13) and is fixedly connected to a transmission block (17).

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