Buffer device for landing of unmanned aerial vehicle

Abstract

The application relates to the technical field of unmanned planes, and discloses a buffer device for landing of an unmanned plane, which is arranged on the main body of the unmanned plane, four fixing cylinders are arranged in a ring shape at the lower end of the main body of the unmanned plane, the upper part of the fixing cylinder is a sealing section, the lower part is an avoiding section, the diameter of the sealing section is smaller than that of the avoiding section; a supporting frame is arranged in each fixing cylinder and can ascend and descend, the supporting frame sequentially comprises a sealing seat, a supporting rod and a base from top to bottom, the diameter of the supporting rod is smaller than that of the sealing seat, the sealing seat can ascend and descend in the fixing cylinder and is in sliding sealing with the sealing section, the supporting rod penetrates through the lower end of the fixing cylinder, the base is in contact with the land surface, and the base is in contact with the land surface after the sealing seat descends in the avoiding section; an air pump is arranged on the main body of the unmanned plane, the air outlet end of the air pump is communicated with the four sealing sections, and the gas in the sealing section is discharged from the air inlet end of the air pump after the sealing seat slides upwards in the sealing section. Through the technical scheme, the problem that the impact force is still large at the moment of landing and touching the ground in the prior art is solved.

Description

Technical Field

[0001] This invention relates to the field of unmanned aerial vehicle (UAV) technology, and more particularly to a buffer device for UAV landing. Background Technology

[0002] Due to their significant weight or the expensive equipment they carry, medium to large-sized drones require landing cushioning structures to reduce impact and protect their structure and equipment. Existing cushioning methods typically rely on elastic shock absorption and airbag protection. However, these structures must provide sufficient support for medium to large-sized drones. The cushioning structure itself cannot be too flexible under normal conditions; its elastic support must be substantial and consistently maintained. When the drone lands, the lower part of the cushioning structure contacts the ground at a high relative speed, making a slow descent difficult and still resulting in a significant impact.

[0003] The problem that the impact force is still relatively large at the moment of landing needs to be solved with existing technology. Summary of the Invention

[0004] The technical problem to be solved by the present invention is to provide a buffer device for drone landing, which addresses the above-mentioned technical deficiencies and solves the problem that the impact force is still relatively large at the moment of landing and touching the ground in the prior art.

[0005] The technical solution adopted in this invention is: to provide a buffer device for drone landing, which is installed on the main body of the drone, characterized in that it includes: The fixed cylinder has four sections, which are arranged in a ring at the lower end of the UAV body. The upper part of the interior of each fixed cylinder is a sealing section, and the lower part is a clearance section. The diameter of the sealing section is smaller than the diameter of the clearance section. The support frame has four components, and each of the fixed cylinders has one support frame that is raised and lowered. The support frame consists of a sealing seat, a support rod, and a base from top to bottom. The diameter of the support rod is smaller than the diameter of the sealing seat. The sealing seat is raised and lowered within the fixed cylinder and slides to seal with the sealing section. The support rod passes through the lower end of the fixed cylinder. The base is used to abut against the land surface. After the sealing seat is lowered within the clearance section, the base abuts against the land surface. An air pump is installed on the main body of the drone. The air outlet of the air pump is connected to the four sealing sections. When the sealing seat slides upward within the sealing section, the gas in the sealing section is discharged from the air inlet of the air pump.

[0006] To further optimize this technical solution, a transition section is provided between the sealing section and the clearance section inside the fixed cylinder, and the diameter of the transition section gradually increases from top to bottom.

[0007] To further optimize this technical solution, the base and the support rod are detachably connected.

[0008] To further optimize this technical solution, the lower end of the drone body has two legs, and each leg is provided with two fixed cylinders spaced apart.

[0009] Further optimization of this technical solution also includes: The system has four connecting pipes, with the air outlet of the air pump connected to each of the four connecting pipes, and each of the four connecting pipes connected to the upper end of one of the four fixed cylinders.

[0010] To further optimize this technical solution, the sealing seat is made of rubber.

[0011] To further optimize this technical solution, the support rod has an elastic section in the middle.

[0012] To further optimize this technical solution, the lower end of the base has an elastic pad.

[0013] To further optimize this technical solution, the lower end of the fixed cylinder has a guide tube, and there is a gap between the support rod and the inner wall of the guide tube.

[0014] The beneficial effects of this invention are as follows: 1. During landing, the support frame descends from the fixed cylinder, the sealing seat is in the avoidance section, and the base touches the ground, reducing the impact transmission to the main body of the drone upon contact with the ground. After contact with the ground, gas is injected into the fixed cylinder, and the main body of the drone gradually descends. The sealing seat enters the sealing section for sealing and sliding. The air pump is turned off, and the gas in the sealing section is discharged with resistance from the air pump's inlet. The sliding resistance of the sealing seat and the exhaust resistance achieve landing buffering. When the support frame of the main body of the drone touches the ground or the support frame abuts against the fixed cylinder in the vertical direction to complete the landing, the speed of the main body of the drone can be very low, and the impact force is relatively small.

[0015] 2. By allowing for a relatively free fall, the support frame first establishes a connection with the ground, without causing a high-speed impact on the drone body. The drag reduces speed while also providing support for the drone body, allowing it to descend slowly without crashing or falling at high speed. Attached Figure Description

[0016] Figure 1 This is a schematic diagram of the front structure of the present invention; Figure 2 This is a schematic diagram of the internal structure of the fixed cylinder of the present invention; Figure 3 This is a schematic diagram of the left-side structure of the present invention; Figure 4 This is a schematic diagram of the fixed cylinder and support frame structure of the present invention; Figure 5 This is a schematic diagram of the support frame structure after it has been lowered according to the present invention; Figure 6 This is a schematic diagram of the support frame structure of the present invention; The markings in the diagram are as follows: 1. Main body of the drone; 101. Legs; 1011. Crossbar; 2. Fixing cylinder; 201. Sealing section; 202. Transition section; 203. Clearance section; 204. Guide tube; 3. Support frame; 301. Sealing seat; 302. Support rod; 3021. Elastic section; 303. Base; 3031. Elastic pad; 4. Air pump; 401. Connecting pipe. Detailed Implementation

[0017] The present invention will now be described in further detail with reference to the accompanying drawings and specific embodiments.

[0018] To keep the drawings concise, each figure only schematically shows the parts relevant to the invention, and these do not represent the actual structure of the product. Furthermore, for ease of understanding, in some figures, only one of the components with the same structure or function is schematically shown, or only one is labeled. In this document, "one" not only means "only one," but can also mean "more than one," and "several" includes "two" and "more than two."

[0019] In this document, it should be noted that, unless otherwise explicitly specified and limited, the terms "installation," "connection," and "linking" should be interpreted broadly. For example, they can refer to fixed connections, detachable connections, or integral connections; they can refer to mechanical connections or electrical connections; they can refer to direct connections or indirect connections through an intermediate medium; and they can refer to the internal connection between two components. Those skilled in the art can understand the specific meaning of the above terms in this invention according to the specific circumstances.

[0020] Furthermore, in the description of this application, the terms "first," "second," etc., are used only to distinguish descriptions and should not be construed as indicating or implying relative importance.

[0021] like Figure 1-6 As shown, a landing buffer device for a drone is installed on the main body 1 of the drone and includes: There are four fixed cylinders 2, which are distributed in a ring at the lower end of the UAV body 1. The upper part of the inside of the fixed cylinder 2 is a sealing section 201 and the lower part is a clearance section 203. The diameter of the sealing section 201 is smaller than the diameter of the clearance section 203. The support frame 3 has four components, with one support frame 3 being raised and lowered inside each of the fixed cylinders 2. The support frame 3 consists of a sealing seat 301, a support rod 302, and a base 303 from top to bottom. The diameter of the support rod 302 is smaller than the diameter of the sealing seat 301. The sealing seat 301 is raised and lowered inside the fixed cylinder 2 and slides to seal with the sealing section 201. The support rod 302 passes through the lower end of the fixed cylinder 2. The base 303 is used to abut against the land surface. After the sealing seat 301 is lowered inside the clearance section 203, the base 303 abuts against the land surface. An air pump 4 is installed on the main body 1 of the drone. The air outlet of the air pump 4 is connected to the four sealing sections 201. When the sealing seat 301 slides upward in the sealing section 201, the gas in the sealing section 201 is discharged from the air inlet of the air pump 4.

[0022] When in use, the sealing seat 301 is located inside the sealing section 201 while the drone is in flight. The support frame 3 is positioned by friction. When landing is required, the drone body 1 descends close to the ground, at a certain distance from the ground. Then, the air pump 4 is activated to inject gas into the sealing section 201 inside the four fixed cylinders 2 to increase the pressure. Under the action of air pressure, the sealing seat 301 is pushed downward until it enters the clearance section 203, and the gas leaks out. At the same time, the sealing seat 301 falls downward in the clearance section 203 until the base 303 touches the ground. The sealing seat 301 stays in the clearance section 203 without contacting the inner wall of the clearance section 203. The support rod 302 passes through the lower end of the fixed cylinder 2, and the contact resistance between it and the fixed cylinder 2 is small. The impact caused by the support frame 3 falling to the ground from a certain height will not have a significant impact on the drone body 1. After the base 303 touches the ground, the drone body 1 begins to descend further closer to the ground. As the drone body 1 descends, the sealing seat 301 rises relative to the fixed cylinder 2 and gradually enters the sealing section 201. The sealing seat 301 and the inner wall of the sealing section 201 slide and seal, generating significant resistance and providing vertical support for the drone body 1. At this time, the drone body 1 is still not in contact with the ground. Then, the drone continues to reduce its rotation speed to decrease lift and gradually descends. At the same time, under the frictional resistance between the sealing seat 301 and the sealing section 201, it is equivalent to the drone body 1 slowly sliding down along the support frame 3. Due to the resistance, it will not directly stall and fall. The speed of the drone body 1 relative to the ground at the moment of contact can be very low.

[0023] The coefficient of friction can be changed through surface treatment. The sliding friction between the sealing section 201 and the sealing seat 301 can be gradually increased from bottom to top, reducing the resistance when the sealing seat 301 and the lower part of the sealing section 201 begin to contact, thereby reducing the impact force.

[0024] During descent, as the sealing seat 301 moves upward relative to the sealing section 201, gas can be injected into the sealing section 201 using the air pump 4 to increase the air pressure within the sealing section 201, thereby increasing the resistance to the relative upward movement of the sealing seat 301. When the air pump 4 is turned off, the sealing seat 301 moves upward, the gas space within the sealing section 201 shrinks, and the air pressure increases. The gas can then be discharged from the air pump 4's inlet. Although the air pump 4 does not have a one-way valve, the air path influences the resistance encountered when the gas is discharged from its inlet. Alternatively, the air pump 4 can be intermittently turned on to alter the pressure resistance, increasing the resistance encountered by the sealing seat 301 during its relative upward movement. This changes the support capacity for the UAV body 1. When the UAV's rotational lift is reduced or lost, the resistance can approach gravity, reducing the descent acceleration. The addition of pressure resistance facilitates resistance adjustment to adapt to gravity. An air pressure monitoring module can be installed at the upper end of the fixed cylinder 2, and a distance monitoring module can also be added to monitor the distance the sealing seat 301 can rise, determining the remaining altitude difference for descent.

[0025] The ring-shaped distribution of the fixed cylinder 2 can be a circular ring with intervals at angles, or it can be distributed in the form of four right-angle positions of a rectangle, etc., and is relatively evenly distributed on the west side of the UAV body 1.

[0026] Furthermore, within the fixed cylinder 2, there is a transition section 202 between the sealing section 201 and the clearance section 203, and the diameter of the transition section 202 gradually increases from top to bottom.

[0027] During use, the transition section 202 guides the sealing seat 301 and reduces the impact force when the sealing seat 301 and the sealing section 201 come into instantaneous contact. The transition section 202 is conical with a large opening at the lower end and the same diameter as the sealing section 201 at the upper end, ensuring that the sealing seat 301 can enter the sealing section 201 and avoid jamming.

[0028] Furthermore, the base 303 and the support rod 302 are detachably connected.

[0029] The lower end of the base 303 has an elastic pad 3031.

[0030] During use, the base 303 is detachably mounted on the lower end of the support rod 302. Different bases 303 can be replaced, and the detachable connection can be achieved through threaded connection, plug-in connection, or pin connection. The base 303 can be a flat plate, or it can have a serrated structure or other features at its lower end to enhance the stability of the connection with the ground. A conventional elastic pad 3031 can also be installed at the lower end of the base 303, which acts as a buffer when the base 303 contacts the ground during landing on hard surfaces. The drone should land on a flat surface.

[0031] Furthermore, the lower end of the drone body 1 has two legs 101, and each leg 101 is provided with two fixed cylinders 2 at intervals.

[0032] In use, a support leg 101 is installed on each of the left and right sides of the lower end of the drone body 1. Each support leg 101 has a horizontally fixed crossbar 1011 in the middle. Two fixing cylinders 2 are fixedly installed on each crossbar 1011, so that the four fixing cylinders 2 are arranged in two rows and two columns, and are symmetrically arranged from left to right, so that the support distribution is more even. The fixing cylinders 2 can be located between two support legs 101 or on the outside of two support legs 101.

[0033] When the drone lands, the lower ends of the outriggers 101 can be used for support, and the base 303 can be flush with the lower ends of the outriggers 101. Alternatively, the support frame 3 can be fixed relative to the fixing cylinder 2 to support the main body of the drone 1.

[0034] Furthermore, it also includes: There are four connecting pipes 401. The air outlet of the air pump 4 is connected to the four connecting pipes 401. The four connecting pipes 401 are respectively connected to the upper ends of the four fixed cylinders 2.

[0035] When in use, the outlet of the air pump 4 is connected to the upper end of the four fixed cylinders 2 through four connecting pipes 401 respectively, so that the gas delivery can be relatively uniform, the gas can be evenly distributed, and the gas pressure change in the four fixed cylinders 2 can be roughly synchronized.

[0036] Furthermore, the sealing seat 301 is made of rubber.

[0037] During use, the sealing seat 301 is made of rubber and slides in a sealing fit with the sealing section 201, providing good sealing performance and high frictional resistance. Simultaneously, the impact force is relatively small when the sealing seat 301 and the sealing section 201 come into instantaneous contact.

[0038] The upper part of the sealing seat 301 can reduce its diameter through a chamfered structure to facilitate entry into the sealing section 201. At the same time, the upper part of the sealing seat 301 can use a softer cushioning material or structure to reduce the generation and transmission of contact impact force.

[0039] Furthermore, the support rod 302 has an elastic segment 3021 in the middle.

[0040] In use, the elastic section 3021 in the middle of the support rod 302 can be a rubber column or a damping shock absorber rod, which has a certain compressive elasticity. It can play a buffering role at the moment when the base 303 touches the ground and at the moment when the sealing seat 301 contacts the sealing section 201, reducing the generation and transmission of contact impact force.

[0041] Furthermore, the lower end of the fixed cylinder 2 has a guide tube 204, and there is a gap between the support rod 302 and the inner wall of the guide tube 204.

[0042] In use, the support rod 302 passes through the guide tube 204 in the middle of the lower end of the fixed cylinder 2. The guide tube 204 acts as a limit, so that the support rod 302 can remain relatively vertical. During the process of rising relative to the fixed cylinder 2, the sealing seat 301 can smoothly enter the sealing section 201 and reduce the deviation, so that the guide positioning of the four fixed cylinders 2 is roughly parallel and the deviation is reduced.

[0043] The guide tube 204 and the support rod 302 are in clearance fit, which can reduce the force transmitted to the fixed cylinder 2 when the support frame 3 falls freely to the ground.

[0044] It is understood that the present invention has been described through some embodiments, and those skilled in the art will recognize that various changes or equivalent substitutions can be made to these features and embodiments without departing from the spirit and scope of the invention. Furthermore, under the teachings of the present invention, these features and embodiments can be modified to adapt to specific situations and materials without departing from the spirit and scope of the invention. Therefore, the present invention is not limited to the specific embodiments disclosed herein, and all embodiments falling within the scope of the claims of this application are within the protection scope of the present invention.

Claims

1. A landing buffer device for a drone, mounted on the main body (1) of the drone, characterized in that, include: The fixed cylinder (2) has four of them, which are distributed in a ring at the lower end of the UAV body (1). The upper part of the fixed cylinder (2) is a sealing section (201) and the lower part is a clearance section (203). The diameter of the sealing section (201) is smaller than the diameter of the clearance section (203). The support frame (3) has four components, and each of the fixed cylinders (2) has one support frame (3) that is raised and lowered. The support frame (3) consists of a sealing seat (301), a support rod (302), and a base (303) from top to bottom. The diameter of the support rod (302) is smaller than the diameter of the sealing seat (301). The sealing seat (301) is raised and lowered in the fixed cylinder (2) and slides and seals with the sealing section (201). The support rod (302) passes through the lower end of the fixed cylinder (2). The base (303) is used to abut against the land surface. After the sealing seat (301) is lowered in the clearance section (203), the base (303) abuts against the land surface. An air pump (4) is installed on the main body (1) of the UAV. The air outlet of the air pump (4) is connected to the four sealing sections (201). When the sealing seat (301) slides upward in the sealing section (201), the gas in the sealing section (201) is discharged from the air inlet of the air pump (4).

2. The buffer device for unmanned aerial vehicle landing according to claim 1, characterized in that, Inside the fixed cylinder (2), there is a transition section (202) between the sealing section (201) and the clearance section (203), and the diameter of the transition section (202) gradually increases from top to bottom.

3. A buffer device for drone landing according to claim 1, characterized in that, The base (303) and the support rod (302) are detachably connected.

4. A buffer device for drone landing according to claim 1, characterized in that, The lower end of the drone body (1) has two legs (101), and each leg (101) is provided with two fixed cylinders (2) spaced apart.

5. A buffer device for drone landing according to claim 1, characterized in that, Also includes: There are four connecting pipes (401), and the air outlet of the air pump (4) is connected to the four connecting pipes (401). The four connecting pipes (401) are respectively connected to the upper ends of the four fixed cylinders (2).

6. A buffer device for unmanned aerial vehicle landing according to claim 1, characterized in that, The sealing seat (301) is made of rubber.

7. A buffer device for unmanned aerial vehicle landing according to claim 1, characterized in that, The support rod (302) has an elastic section (3021) in the middle.

8. A buffer device for drone landing according to claim 1, characterized in that, The lower end of the base (303) has an elastic pad (3031).

9. A buffer device for unmanned aerial vehicle landing according to claim 1, characterized in that, The lower end of the fixed cylinder (2) has a guide tube (204), and there is a gap between the support rod (302) and the inner wall of the guide tube (204).

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