Unmanned aerial vehicle buffering mechanism

Abstract

The utility model provides an unmanned aerial vehicle buffer mechanism, which relates to the technical field of unmanned aerial vehicles, and comprises a shell, a buffer mechanism is arranged on the shell, and the buffer mechanism comprises an elastic component A fixed on the inner top wall of the shell. According to the unmanned aerial vehicle buffering mechanism, vibration generated during take-off and landing is buffered through the air cushion, when the air cushion is impacted, air in the air cushion is compressed, impact energy is absorbed, when the unmanned aerial vehicle suddenly falls, the impact brought by the unmanned aerial vehicle is large, at the moment, an L-shaped pipe will drive a sliding block to abut against a check block, and when the sliding block abuts against the check block, the air cushion is pressed against the check block. The L-shaped rod also abuts against the top of an elastic component C, so that a limiting column enters a reserved hole in the top of the elastic component C, under the pulling force effect of an elastic component B and cooperation of a mounting block and a limiting block, a lengthening rod moves to the outside of the L-shaped pipe, and the contact area between the unmanned aerial vehicle and the ground is enlarged; and the risk of rollover or inclination of the unmanned aerial vehicle during landing is effectively reduced.

Description

Technical Field

[0001] The utility model relates to a buffer mechanism, in particular to a buffer mechanism for an unmanned aerial vehicle (UAV), and belongs to the technical field of UAVs. Background Art

[0002] Drones, also known as unmanned aerial vehicles, are aircraft that do not require human pilots. They can be remotely operated by a ground control station or perform missions through autonomous flight programs.

[0003] In Chinese patent publication CN220332981U, a buffer mechanism for drones is disclosed, which adopts the design of a buffer and shock-absorbing component. Specifically, the sliding support block is forced to slide and open on the sliding rod, thereby driving the sliding support rod to slide out from the inner side of one end of the fixed rod to perform initial movement buffering, and the first spring is stretched under force to provide a reaction force to perform secondary buffering of the vibration force, effectively improving the buffer and shock-absorbing performance of the structure and avoiding easy damage to the drone body and camera.

[0004] The buffer mechanism described in the aforementioned patent primarily uses springs to cushion impacts. However, in actual applications, it has been found that the spring's energy absorption relies primarily on elastic deformation, making it difficult to effectively dissipate energy. After an impact, the spring may release some of its energy as vibration, causing additional vibration. Furthermore, when a drone plummets, the speed of its fall is rapid, and the spring alone is insufficient to provide adequate cushioning protection, making the drone prone to tumbling. Therefore, a buffer mechanism for drones is proposed. Utility Model Content

[0005] The utility model proposes a UAV buffer mechanism that can effectively absorb and dissipate impact energy, reduce the risk of damage to the UAV during takeoff and landing and sudden falls, and at the same time can provide good buffering and protection when the UAV falls suddenly, effectively reducing the risk of the UAV rolling.

[0006] The utility model is achieved through the following technical solutions: A buffer mechanism of a drone comprises a shell, on which a buffer mechanism is provided.

[0007] The buffer mechanism includes an elastic component A fixed to the top wall of the shell, a slider that slides in contact with the inner wall of the shell is fixed to the lower end of the elastic component A, an L-shaped tube that passes through the shell is fixed to the bottom surface of the slider, a sliding groove is provided in the longitudinal direction of the L-shaped tube, and an L-shaped rod that extends into the interior of the L-shaped tube through the sliding groove is fixed to the bottom surface of the shell.

[0008] The L-shaped tube is provided with a first channel and a second channel in communication in the transverse direction, an extension rod is slidably connected in the first channel, a mounting block is fixed to the left end of the extension rod, an elastic component B sleeved on the extension rod is fixed between the mounting block and the second channel, a limit block in sliding contact with the second channel is fixed to the left end of the extension rod, an elastic component C is fixed in the reserved hole at the top of the limit block, a limit column in contact with the L-shaped tube is fixed to the upper end of the elastic component C, and an air cushion is fixed in the transverse direction of the L-shaped tube.

[0009] Specifically, a fixing plate is fixed on the shell, a mounting hole is opened on the fixing plate, and the shell is mounted on the drone through the fixing plate.

[0010] Specifically, a vent hole is provided on the top of the shell, and the interior of the shell is communicated with the external air pressure through the vent hole.

[0011] Furthermore, a stopper is fixed to the inner top wall of the shell, the distance between the bottom of the stopper and the top of the slider is equal to the distance between the bottom of the L-shaped rod and the top of the elastic component C, and the outer contour of the stopper is cylindrical.

[0012] Specifically, the outer contour of the mounting block is annular, and the mounting block is in sliding contact with the second channel.

[0013] Furthermore, the elastic component A and the elastic component C are both compression springs.

[0014] Specifically, the elastic component B is a tension spring, and the elastic component B is in a stretched state.

[0015] The utility model provides a buffer mechanism for a drone, which has the following beneficial effects:

[0016] 1. The vibration generated by the drone's buffer mechanism during takeoff and landing will be buffered by the air cushion. When the air cushion is impacted, the gas in the air cushion is compressed to absorb the impact energy. When the drone falls sharply, the impact caused by the drone is relatively large. At this time, the L-shaped tube will drive the slider to press against the block. At the same time as the slider presses against the block, the L-shaped rod will also press against the top of the elastic component C, so that the limit column enters the reserved hole at the top of the elastic component C. Under the pulling force of the elastic component B and the cooperation of the mounting block and the limit block, the extension rod will move to the outside of the L-shaped tube, expanding the contact area between the drone and the ground, effectively reducing the risk of the drone rolling over or tilting when landing. BRIEF DESCRIPTION OF THE DRAWINGS

[0017] Figure 1 This is a schematic diagram of the assembly of the utility model;

[0018] Figure 2 It is a schematic diagram of the three-dimensional structure of the utility model;

[0019] Figure 3 This is a cross-sectional view of the internal structure of the shell and L-shaped tube of the present invention;

[0020] Figure 4 This is a schematic diagram of the shell and L-shaped tube structure of the utility model;

[0021] Figure 5 This is a schematic diagram of the L-shaped tube and limit block structure of the utility model;

[0022] Figure 6 For the utility model Figure 3 A magnified schematic diagram of the structure in the middle.

[0023] Description of Reference Numerals

[0024] 1. Shell;

[0025] 2. Buffer mechanism; 201. Elastic component A; 202. Slider; 203. L-shaped tube; 2031. First channel; 2032. Second channel; 204. L-shaped rod; 205. Slide; 206. Extension rod;

[0026] 207, mounting block; 208, elastic component B; 209, limiting block; 210, elastic component C; 211, limiting column; 212, air cushion;

[0027] 3. Fixing plate; 4. Ventilation hole; 5. Drone; 6. Stop block. DETAILED DESCRIPTION

[0028] The following will be combined with the accompanying drawings in the embodiments of this application to clearly and completely describe the technical solutions in the embodiments of this application. Obviously, the embodiments described are only part of the embodiments of this application, not all of the embodiments. Based on the embodiments of this application, all other embodiments obtained by ordinary technicians in this field without making creative efforts are within the scope of protection of this application.

[0029] See also Figures 1 to 6 The embodiment of the utility model provides a buffer mechanism for a drone, including a shell 1, a fixing plate 3 is fixed on the shell 1, and a mounting hole is opened on the fixing plate 3. The fixing plate 3 is provided to facilitate the installation of the device. The shell 1 is installed on the drone 5 through the fixing plate 3. An air vent 4 is opened on the top of the shell 1. The interior of the shell 1 is connected to the external air pressure through the air vent 4 to avoid the slider 202 squeezing the air to generate resistance when moving inside the shell 1, which is not conducive to the movement of the slider 202 inside the shell 1.

[0030] Please refer to Figure 2 、 Figure 3 and Figure 4A buffer mechanism 2 is provided on the shell 1, and the buffer mechanism 2 includes an elastic component A201 fixed to the inner top wall of the shell 1, and a slider 202 is fixed to the lower end of the elastic component A201, which is in sliding contact with the inner wall of the shell 1, and the slider 202 can slide inside the shell 1. The bottom surface of the slider 202 is fixed with an L-shaped tube 203 that passes through the shell 1, and a sliding groove 205 is provided in the longitudinal direction of the L-shaped tube 203. An L-shaped rod 204 is fixed to the bottom surface of the shell 1 and extends to the inside of the L-shaped tube 203 through the sliding groove 205. When the longitudinal part of the L-shaped tube 203 drives the slider 202 to slide inside the shell 1, since the L-shaped rod 204 is fixed to the bottom of the shell 1 and the L-shaped rod 204 extends into the L-shaped tube 203, the limiting column 211 inside the L-shaped tube 203 will gradually approach the lower end of the L-shaped rod 204.

[0031] Please refer to Figure 5 and Figure 6 A first channel 2031 and a second channel 2032 are connected in the horizontal direction of the L-shaped tube 203. An extension rod 206 is slidably connected in the first channel 2031. Preferably, a rubber column can be fixed at the end of the extension rod 206 away from the limit block 209 to prevent the vibration from being directly transmitted to the drone 5 through the L-shaped tube 203, the slider 202, the shell 1, and the fixing plate 3 when the end of the extension rod 206 away from the elastic component C210 contacts the ground, thereby causing damage to the drone 5.

[0032] A mounting block 207 is fixed to the left end of the extension rod 206. The outer contour of the mounting block 207 is annular. The mounting block 207 is in sliding contact with the second channel 2032. An elastic component B208 is fixed between the mounting block 207 and the second channel 2032 and is sleeved on the extension rod 206. The elastic component B208 is a tension spring and is in a stretched state. A limit block 209 is fixed to the left end of the extension rod 206 and is in sliding contact with the second channel 2032. An elastic component C210 is fixed in the reserved hole at the top of the limit block 209.

[0033] Both the elastic component A201 and the elastic component C210 are compression springs. A stopper 6 is fixed to the inner top wall of the shell 1. The distance between the bottom of the stopper 6 and the top of the slider 202 is equal to the distance between the bottom of the L-shaped rod 204 and the top of the elastic component C210, that is, when the slider 202 is against the stopper 6, the lower end of the L-shaped rod 204 just against the top of the elastic component C210. At this time, the limiting column 211 and the L-shaped rod 204 are pushed into the reserved hole at the top of the elastic component C210. The outer contour of the stopper 6 is cylindrical. The upper end of the elastic component C210 is fixed with a limiting column 211 in contact with the L-shaped tube 203. The L-shaped tube 203 is fixed with an air cushion 212 in the horizontal direction. The air cushion 212 can absorb impact energy.

[0034] Working principle: When the drone is taking off and landing normally, the vibration generated by the drone 5 will be buffered by the air cushion 212. When the air cushion 212 is impacted, the gas in the air cushion 212 is compressed to absorb the impact energy. When the drone 5 fails during operation and falls sharply, the impact caused by the drone 5 is relatively large due to its high falling speed. At this time, after the air cushion 212 is buffered, the L-shaped tube 203 will drive the slider 202 to move inside the shell 1 until the slider 202 hits the stopper 6. When the slider 202 hits the stopper 6, Since the L-shaped rod 204 is fixed to the bottom of the shell 1, the L-shaped rod 204 will also press against the top of the elastic component C210, so that the limiting column 211 enters the reserved hole on the top of the elastic component C210. At this time, the limiting block 209 is no longer limited by the limiting column 211. Under the pulling force of the elastic component B208 and the cooperation of the mounting block 207 and the limiting block 209, the extension rod 206 will move to the outside of the L-shaped tube 203, thereby expanding the contact area between the drone 5 and the ground, and effectively reducing the risk of the drone 5 rolling over or tilting when landing.

[0035] The above shows and describes the basic principles, main features and advantages of the present invention. Those skilled in the art should understand that the present invention is not limited to the above embodiments. The above embodiments and descriptions are merely illustrative of the principles of the present invention. Various changes and improvements may be made to the present invention without departing from the spirit and scope of the present invention. Such changes and improvements are intended to fall within the scope of the present invention. The scope of protection claimed in this invention is defined by the appended claims and their equivalents.

Claims

1. A buffer mechanism for an unmanned aerial vehicle, comprising a housing (1), characterized in that: The housing (1) is provided with a buffer mechanism (2); The buffer mechanism (2) comprises an elastic component A (201) fixed to the inner top wall of the housing (1); a slider (202) is fixed to the lower end of the elastic component A (201) and is in sliding contact with the inner wall of the housing (1); an L-shaped tube (203) penetrating the housing (1) is fixed to the bottom surface of the slider (202); a sliding groove (205) is provided in the longitudinal direction of the L-shaped tube (203); and an L-shaped rod (204) is fixed to the bottom surface of the housing (1) and extends through the sliding groove (205) to the inside of the L-shaped tube (203); The L-shaped tube (203) is provided with a first channel (2031) and a second channel (2032) in communication in the transverse direction. An extension rod (206) is slidably connected in the first channel (2031). A mounting block (207) is fixed to the left end of the extension rod (206). An elastic component B (208) sleeved on the extension rod (206) is fixed between the mounting block (207) and the second channel (2032). A limit block (209) in sliding contact with the second channel (2032) is fixed to the left end of the extension rod (206). An elastic component C (210) is fixed in a reserved hole at the top of the limit block (209). A limit column (211) in contact with the L-shaped tube (203) is fixed to the upper end of the elastic component C (210). An air cushion (212) is fixed to the transverse direction of the L-shaped tube (203).

2. The UAV buffer mechanism according to claim 1, characterized in that: A fixing plate (3) is fixed on the housing (1), a mounting hole is provided on the fixing plate (3), and the housing (1) is mounted on the drone (5) via the fixing plate (3).

3. The UAV buffer mechanism according to claim 1, characterized in that: A vent hole (4) is provided on the top of the shell (1), and the interior of the shell (1) is connected to the external air pressure through the vent hole (4).

4. The UAV buffer mechanism according to claim 1, characterized in that: A stopper (6) is fixed to the inner top wall of the housing (1), the distance between the bottom of the stopper (6) and the top of the slider (202) is equal to the distance between the bottom of the L-shaped rod (204) and the top of the elastic component C (210), and the outer contour of the stopper (6) is cylindrical.

5. The UAV buffer mechanism according to claim 1, characterized in that: The outer contour of the mounting block (207) is annular, and the mounting block (207) is in sliding contact with the second channel (2032).

6. The UAV buffer mechanism according to claim 1, characterized in that: The elastic component A (201) and the elastic component C (210) are both compression springs.

7. The UAV buffer mechanism according to claim 1, characterized in that: The elastic component B (208) is a tension spring, and the elastic component B (208) is in a stretched state.

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