Undercarriage buffer device of unmanned aerial vehicle

Abstract

The utility model discloses an unmanned aerial vehicle undercarriage buffer device, belongs to the technical field of unmanned aerial vehicle undercarriages, and aims to solve the problem that the unmanned aerial vehicle is secondarily damaged due to the lack of a corresponding damping support structure and the damage of the buffer device, the unmanned aerial vehicle undercarriage buffer device comprises an unmanned aerial vehicle body, and an undercarriage is arranged at the bottom of the unmanned aerial vehicle body. A fixing ring is fixedly connected to the undercarriage, a connecting rod is fixedly installed on the upper portion of the fixing ring, the undercarriage is connected with the unmanned aerial vehicle body through the fixing ring and the connecting rod, a stabilizing mechanism is arranged on the undercarriage, and a buffering mechanism is arranged at the bottom of the fixing ring; by means of the arranged buffering mechanism, when impact kinetic energy is large in the landing process of the unmanned aerial vehicle body, buffering protection of the undercarriage cannot be achieved through the stabilizing mechanism, the buffering mechanism is matched, the impact kinetic energy can be absorbed, damage to the undercarriage is avoided, and meanwhile secondary damage to the unmanned aerial vehicle body is avoided; the practicability of the device is improved.

Description

Technical Field

[0001] The utility model belongs to the technical field of unmanned aerial vehicle landing gears, and particularly relates to a buffer device for an unmanned aerial vehicle landing gear. Background Technique

[0002] An unmanned aerial vehicle includes a fuselage and landing gears installed at the bottom of the fuselage. The landing gears are used to support the unmanned aerial vehicle during landing. Generally, the landing gears of unmanned aerial vehicles are mostly skid-type structures, and wheeled landing gears are used for unmanned aerial vehicles with relatively large weights.

[0003] During the landing process of an unmanned aerial vehicle, if the landing speed is too fast, when the unmanned aerial vehicle lands and hits the ground, it will be subjected to a large force, which may cause the fuselage or its components of the unmanned aerial vehicle to be damaged due to the impact, resulting in unnecessary losses. In the prior art, there is a buffer device for an unmanned aerial vehicle landing gear with the patent publication number of CN117566146A. In the above patent, by adopting the method of energy absorption and hierarchical destruction, the problem of energy absorption during the crash of the unmanned aerial vehicle during landing is solved. The landing gear buffer device proposed in this patent can greatly reduce the impact peak overload and effectively reduce the transmission of impact kinetic energy to the fuselage through the way of gradually controlled plastic deformation or destruction and energy absorption of the buffer stage. Therefore, it can increase the structural safety and improve the crash survivability of the unmanned aerial vehicle. At the same time, the buffer device of this unmanned aerial vehicle landing gear has a simple structure, low cost, and high buffer energy absorption efficiency. It can reduce the requirements for energy absorption of the fuselage during a crash, which has a positive significance for reducing the structural weight of the fuselage. However, there are the following two problems in this patent:

[0004] 1. During the landing process of the unmanned aerial vehicle, it does not get out of control or fall, resulting in the impact kinetic energy during the landing process of the unmanned aerial vehicle being insufficient to enable the buffer device to play its due buffer effect. Due to the lack of a corresponding shock absorption and support structure, the unmanned aerial vehicle cannot land smoothly.

[0005] 2. When the impact kinetic energy is large during the landing process of the unmanned aerial vehicle, it will cause the buffer device to be damaged to absorb its kinetic energy. The broken structure will scatter due to the large impact kinetic energy. At this time, the propeller blades of the unmanned aerial vehicle have not completely stopped rotating, which may cause the broken structure to hit the propeller blades, resulting in secondary damage to the unmanned aerial vehicle, thereby increasing the maintenance cost.

[0006] In view of the above shortcomings, it is necessary to design a buffer device for an unmanned aerial vehicle landing gear to overcome the above problems. Content of the Utility Model

[0007] The purpose of the utility model is to provide a buffer device for an unmanned aerial vehicle landing gear to solve the problems raised in the above background technique.

[0008] To achieve the above object, the present utility model provides the following technical solution: An unmanned aerial vehicle landing gear buffer device, including an unmanned aerial vehicle body, a landing gear is arranged at the bottom of the unmanned aerial vehicle body, a fixed ring is fixedly connected to the landing gear, a connecting rod is fixedly installed above the fixed ring, the landing gear is connected to the unmanned aerial vehicle body through the fixed ring and the connecting rod, a stabilizing mechanism is arranged on the landing gear, and a buffer mechanism is arranged at the bottom of the fixed ring.

[0009] The stabilizing mechanism includes a rotating ring, the rotating ring is rotatably sleeved on the landing gear, a support rod is fixedly connected to the outer surface of the rotating ring, a stop rod is fixedly connected to the bottom end of the support rod, and a torsion spring is sleeved on the outside of the landing gear on one side of the rotating ring.

[0010] It should be noted in the solution that there are four fixed rings, and the four fixed rings are arranged in two groups of two and are symmetrically arranged front and back on the landing gear, and the fixed rings are arranged close to one side of the landing gear.

[0011] Furthermore, it is worth noting that there are six rotating rings, and the six rotating rings are arranged in two groups of three. The two groups of rotating rings are symmetrically arranged front and back on the landing gear. In one group, the three rotating rings are arranged on the landing gear, and the two at the left and right ends are arranged outside the fixed ring.

[0012] Even further, it should be noted that there are four torsion springs, and the four torsion springs are arranged in two groups of two. Each group of torsion springs is matched with a group of rotating rings. The torsion springs are connected to the middle rotating ring and the other end is connected to the landing gear.

[0013] As a preferred embodiment, the buffer mechanism includes a connecting cylinder, the connecting cylinder is fixedly connected to the bottom of the fixed ring, a sliding seat is slidably arranged at the bottom end of the connecting cylinder, a resisting rod is fixedly connected to the inner top of the sliding seat, a piston block is fixedly connected to the top end of the resisting rod, a matching buffer groove is arranged in the connecting cylinder above the piston block, an air storage chamber is communicated in the connecting cylinder above the buffer groove, a through hole is opened on the connecting cylinder and is communicated with the air storage chamber, an air outlet head is fixedly connected to the outer surface of the connecting cylinder outside the through hole, and a rubber sealing piece is arranged in the air outlet head.

[0014] As a preferred embodiment, the piston block is made of rubber material and is closely slidably arranged in the connecting cylinder. The piston block is arranged in a conical shape, and the buffer groove is arranged in a conical shape to match the piston block.

[0015] As a preferred embodiment, the rubber sealing piece is arranged as a spliced rubber block.

[0016] Compared with the prior art, the unmanned aerial vehicle landing gear buffer device provided by the present utility model has at least the following beneficial effects:

[0017] (1) Through the provided stabilizing mechanism, during the landing process of the UAV body, it can stably support the UAV body and at the same time provide a certain degree of buffering protection for the landing gear, ensuring the stable landing of the UAV body.

[0018] (2) Through the provided buffering mechanism, when the impact kinetic energy is relatively large during the landing process of the UAV body and the buffering protection of the landing gear cannot be achieved by the stabilizing mechanism, the buffering mechanism can cooperate to absorb the impact kinetic energy, avoid damage to the landing gear, and at the same time avoid causing secondary damage to the UAV body, improving the practicality of the device. Description of the Drawings

[0019] Figure 1 is the structural schematic diagram of the first perspective of the present utility model;

[0020] Figure 2 is the structural schematic diagram of the second perspective of the present utility model;

[0021] Figure 3 is the split structural schematic diagram of the stabilizing mechanism of the present utility model;

[0022] Figure 4 is the sectional structural schematic diagram of the buffering mechanism of the present utility model.

[0023] In the figure: 1, UAV body; 2, landing gear; 201, fixing ring; 202, connecting rod; 3, stabilizing mechanism; 301, rotating ring; 302, support rod; 303, stop rod; 304, torsion spring; 4, buffering mechanism; 401, connecting cylinder; 402, sliding seat; 403, abutting rod; 404, piston block; 405, buffering groove; 406, air storage chamber; 407, through port; 408, air outlet head; 409, rubber sealing piece. Detailed Embodiment

[0024] The following further describes the present utility model in conjunction with embodiments.

[0025] Please refer to Figures 1-4 , the present utility model provides a buffering device for the landing gear of a UAV, including a UAV body 1. A landing gear 2 is provided at the bottom of the UAV body 1. A fixing ring 201 is fixedly connected to the landing gear 2. An upper part of the fixing ring 201 is fixedly installed with a connecting rod 202. The landing gear 2 is connected to the UAV body 1 through the fixing ring 201 and the connecting rod 202. A stabilizing mechanism 3 is provided on the landing gear 2, and a buffering mechanism 4 is provided at the bottom of the fixing ring 201.

[0026] The stabilizing mechanism 3 includes a rotating ring 301 which is rotatably sleeved on the landing gear 2. A support rod 302 is fixedly connected to the outer surface of the rotating ring 301, and a stop rod 303 is fixedly connected to the bottom end of the support rod 302. A torsion spring 304 is sleeved on the outside of the landing gear 2 on one side of the rotating ring 301; There are four fixing rings 201, and the four fixing rings 201 are arranged in two groups of two and symmetrically arranged front and back on the landing gear 2. The fixing rings 201 are arranged close to the landing gear 2. There are six rotating rings 301, and the six rotating rings 301 are arranged in two groups of three. The two groups of rotating rings 301 are symmetrically arranged front and back on the landing gear 2. The three rotating rings 301 in one group are arranged on the landing gear 2, and the two at the left and right ends are arranged outside the fixing ring 201. There are four torsion springs 304, and the four torsion springs 304 are arranged in two groups of two. Each group of torsion springs 304 is arranged to match a group of rotating rings 301. The torsion spring 304 is connected to the middle rotating ring 301 and the other end is connected to the landing gear 2.

[0027] In the case where the impact kinetic energy is small during the landing process, the drone body 1 is supported by the stop rod 303. At this time, the rotating ring 301 rotates on the landing gear 2 through the support rod 302 by the stop rod 303. Since the torsion spring 304 is connected to the rotating ring 301 and the landing gear 2, during the rotation of the rotating ring 301, the torsion spring 304 will be driven to rotate. The buffer support effect on the drone body 1 can be realized through the torsion spring 304, thereby improving the stability of the drone body 1 during the landing process and ensuring the normal landing of the drone body 1.

[0028] According to the above working process, it can be seen that through the provided stabilizing mechanism 3, during the landing of the drone body 1, it can stably support it, and at the same time, it can provide a certain buffer protection for the landing gear 2 to ensure the stable landing of the drone body 1.

[0029] Further as Figure 2 、 Figure 3 and Figure 4 shown, specifically, the buffer mechanism 4 includes a connecting cylinder 401 which is fixedly connected to the bottom of the fixing ring 201. A sliding seat 402 is slidably arranged at the bottom end of the connecting cylinder 401. A resisting rod 403 is fixedly connected to the inner top of the sliding seat 402. A piston block 404 is fixedly connected to the top end of the resisting rod 403. A matching buffer groove 405 is arranged in the connecting cylinder 401 above the piston block 404. An air storage chamber 406 is communicated with the connecting cylinder 401 above the buffer groove 405. A through port 407 is opened on the connecting cylinder 401 and is communicated with the air storage chamber 406. A matching air outlet head 408 is fixedly connected to the outer surface of the connecting cylinder 401 outside the through port 407. A rubber sealing piece 409 is arranged in the air outlet head 408.

[0030] When the impact kinetic energy is relatively large during the landing process of the UAV body 1, at this time, the stable mechanism 3 alone cannot buffer and protect the UAV body 1, which is likely to cause damage to the landing gear 2. At this time, the sliding seat 402 receives the impact kinetic energy during the landing process to support the UAV body 1, causing the sliding seat 402 to slide at the bottom end of the connecting cylinder 401, so that the piston block 404 slides upward inside the connecting cylinder 401, thereby squeezing the air pressure in the air storage chamber 406, and slowly releasing the air pressure in the air storage chamber 406 by opening the rubber sealing piece 409, so as to absorb the impact kinetic energy and improve the protection of the landing gear 2.

[0031] Further, as Figure 4 shown, it is specifically noted that the piston block 404 is made of rubber and is tightly slidably arranged inside the connecting cylinder 401. The piston block 404 is conically arranged, and the buffer groove 405 is matched with the piston block 404 to be conical, and the rubber sealing piece 409 is arranged as a spliced rubber block.

[0032] By squeezing the gas in the air storage chamber 406 with the piston block 404, when the impact kinetic energy reaches a certain threshold, the air pressure in the air storage chamber 406 will impact the rubber sealing piece 409, causing the rubber sealing piece 409 to be in an open state, and the gas can be discharged adaptively according to the size of the impact kinetic energy, thereby causing the sliding seat 402 to receive a certain buffer and protecting the landing gear 2.

[0033] This solution has the following working process: When this device is in use, during the landing process of the UAV body 1, if the impact kinetic energy is small, the UAV body 1 is supported by the stop rod 303. At this time, the rotating ring 301 rotates on the landing gear 2 through the support rod 302 due to the stop rod 303. Since the torsion spring 304 is connected to the rotating ring 301 and the landing gear 2, during the rotation of the rotating ring 301, the torsion spring 304 will be driven to rotate. The buffer support effect on the UAV body 1 can be achieved through the torsion spring 304, thereby improving the stability of the UAV body 1 during the landing process and ensuring the normal landing of the UAV body 1. When the impact kinetic energy is large during the landing process of the UAV body 1, at this time, only through the stabilizing mechanism 3, it is impossible to provide buffer protection for the UAV body 1, which is likely to cause damage to the landing gear 2. At this time, the sliding seat 402 is supported by the impact kinetic energy during the landing process to support the UAV body 1, causing the sliding seat 402 to slide at the bottom end of the connecting cylinder 401, so that the piston block 404 slides upward into the connecting cylinder 401, thereby squeezing the air pressure in the air storage chamber 406. When the impact kinetic energy reaches a certain threshold, the air pressure in the air storage chamber 406 will impact the rubber sealing piece 409, causing the rubber sealing piece 409 to open and slowly release the air pressure in the air storage chamber 406, so as to play a role in absorbing the impact kinetic energy, thereby improving the protection of the landing gear 2, and the energy absorption operation can be adaptively performed according to the size of the impact kinetic energy, thereby improving the practicality of the device.

[0034] In summary: Through the set stabilizing mechanism 3, during the landing process of the UAV body 1, it can stably support it, and at the same time provide a certain buffer protection for the landing gear 2 to ensure the stable landing of the UAV body 1; through the set buffer mechanism 4, when the impact kinetic energy is large during the landing process of the UAV body 1 and the buffer protection of the landing gear 2 cannot be achieved through the stabilizing mechanism 3, in cooperation with the buffer mechanism 4, it can absorb the impact kinetic energy, avoid damage to the landing gear 2, and at the same time avoid secondary damage to the UAV body 1, improving the practicality of the device.

Claims

1. A landing gear buffer device for an unmanned aerial vehicle, comprising an unmanned aerial vehicle body (1), characterized in that: A landing gear (2) is arranged at the bottom of the drone body (1); a fixing ring (201) is fixedly connected to the landing gear (2); a connecting rod (202) is fixedly installed on the upper part of the fixing ring (201); the landing gear (2) is connected to the drone body (1) via the fixing ring (201) and the connecting rod (202); a stabilizing mechanism (3) is arranged on the landing gear (2); and a buffer mechanism (4) is arranged at the bottom of the fixing ring (201); The stabilizing mechanism (3) comprises a rotating ring (301), the rotating ring (301) being rotatably sleeved on the landing gear (2), a support rod (302) being fixedly connected to the outer surface of the rotating ring (301), a blocking rod (303) being fixedly connected to the bottom end of the support rod (302), and a torsion spring (304) being sleeved on one side of the rotating ring (301) on the outer side of the landing gear (2).

2. The UAV landing gear buffer device according to claim 1, characterized in that: Four fixing rings (201) are provided, and the four fixing rings (201) are provided in two groups, and are symmetrically arranged on the landing gear (2) in front and back. The fixing rings (201) are provided close to one side of the landing gear (2).

3. The UAV landing gear buffer device according to claim 1, characterized in that: Six rotating rings (301) are provided, and the six rotating rings (301) are provided in two groups of three. The two groups of rotating rings (301) are symmetrically arranged on the landing gear (2) in the front and rear. Three rotating rings (301) in one group are arranged in an arranged manner on the landing gear (2), and two rotating rings at the left and right ends are arranged outside the fixed ring (201).

4. The UAV landing gear buffer device according to claim 1, characterized in that: Four torsion springs (304) are provided, and the four torsion springs (304) are arranged in a group of two. Each group of torsion springs (304) is matched with a group of rotating rings (301). The torsion springs (304) are connected to the middle rotating ring (301) and the other end is connected to the landing gear (2).

5. The UAV landing gear buffer device according to claim 1, characterized in that: The buffer mechanism (4) comprises a connecting tube (401), wherein the connecting tube (401) is fixedly connected to the bottom of the fixing ring (201), a sliding seat (402) is slidably arranged at the bottom of the connecting tube (401), a push rod (403) is fixedly connected to the top of the sliding seat (402), a piston block (404) is fixedly connected to the top of the push rod (403), a matching buffer groove (405) is arranged on the upper part of the piston block (404) in the connecting tube (401), an air storage chamber (406) is arranged in communication with the upper part of the buffer groove (405) in the connecting tube (401), a through hole (407) is opened on the connecting tube (401) and is in communication with the air storage chamber (406), a matching air outlet head (408) is fixedly connected to the outer surface of the connecting tube (401) on the outer side of the through hole (407), and a rubber sealing sheet (409) is arranged in the air outlet head (408).

6. The UAV landing gear buffer device according to claim 5, characterized in that: The piston block (404) is made of rubber material and is tightly slidably arranged in the connecting cylinder (401). The piston block (404) is arranged in a conical shape, and the buffer groove (405) is arranged in a conical shape to match the piston block (404).

7. The UAV landing gear buffer device according to claim 5, characterized in that: The adhesive sealing sheet (409) is a spliced ​​adhesive block arrangement.

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