Undercarriage structure of unmanned aerial vehicle

Abstract

The utility model relates to the technical field of unmanned aerial vehicle accessories, in particular to an unmanned aerial vehicle undercarriage structure which comprises a mounting plate used for being connected with the bottom of an external unmanned aerial vehicle and four supporting cylinders, cylindrical mounting protrusions are arranged at the four corners of the mounting plate, and magnetic attraction blocks are mounted at the tops of the interiors of the mounting protrusions. The upper end of the supporting cylinder is inserted into the mounting bulge and is provided with an adsorption sheet with magnetic attraction; according to the unmanned aerial vehicle damping device, the defect that the unmanned aerial vehicle cannot be quickly static due to springback of a spring after damping is overcome, so that the phenomenon that the unmanned aerial vehicle shakes and even falls down due to springback of the spring is avoided, the air pressure in the buffer cavity can be automatically and correspondingly adjusted according to potential energy generated when the unmanned aerial vehicle descends through the arrangement of the adjusting plug, and the safety of the unmanned aerial vehicle is improved. And meanwhile, through the arrangement of magnetic attraction blocks, all parts used for supporting can be conveniently detached from the mounting plate, namely the unmanned aerial vehicle, and therefore the unmanned aerial vehicle and the undercarriage can be conveniently stored.

Description

Technical Field

[0001] The utility model relates to the technical field of unmanned aerial vehicle accessories, in particular to a landing gear structure of a unmanned aerial vehicle. Background Art

[0002] A drone is an unmanned aircraft controlled by a radio remote control device and a self-contained program control device, or operated completely or intermittently autonomously by an onboard computer. Compared with manned aircraft, drones are often more suitable for missions that are too "dull, dirty or dangerous". When a drone lands, it contacts the ground through the landing gear at the bottom. In order to avoid damage to the drone caused by the impact force generated during landing, its landing gear is usually required to have a certain degree of shock absorption effect.

[0003] The existing Chinese patent with application number: 202123077236.X discloses a UAV landing gear, including a fixing plate detachably connected to the bottom of the UAV body, a fixing rod fixedly connected to the bottom of the UAV body and with a vertical axis, and four supporting mechanisms arranged on the fixing plate, the four supporting mechanisms are respectively arranged near the four corners of the fixing plate, the supporting mechanism includes a supporting rod with a vertical axis and a shock-absorbing rod arranged at the bottom of the supporting rod; a receiving hole with a vertical axis is provided at the bottom of the support rod, the shock-absorbing rod is a round rod, the shock-absorbing rod and the receiving hole are coaxial and have the same diameter, the top of the shock-absorbing rod is inserted into the receiving hole, the top of the shock-absorbing rod is fixedly connected to a spring located in the receiving hole, and the top of the spring is fixedly connected to the hole wall at the top of the receiving hole.

[0004] When the above technology is in use, the support rods used to support the drone at four places need to be disassembled after the screws are unscrewed before they can be removed from the fixing plate, and the shock-absorbing rods located inside the support rods are supported by springs, so that when personnel store the drone, the protruding support rods and shock-absorbing rods will seriously affect the convenience of storing the drone. At the same time, since there is no energy-absorbing component for spring rebound, the spring will rebound multiple times after absorbing the kinetic energy of the drone during landing, so that the drone cannot quickly maintain stability after landing; therefore, in order to solve the defect that the drone landing gear proposed by the above technology cannot quickly stop the drone after landing when it is used, we propose a drone landing gear structure. Utility Model Content

[0005] The utility model aims to solve the shortcomings in the prior art and proposes a landing gear structure for a drone.

[0006] In order to achieve the above purpose, the utility model adopts the following technical solutions:

[0007] A landing gear structure for an unmanned aerial vehicle comprises a mounting plate for connecting to the bottom of an external unmanned aerial vehicle and four supporting tubes, wherein the four corners of the mounting plate are provided with cylindrical mounting protrusions, a magnetic block is installed at the top inside the mounting protrusions, the upper end of the supporting tube is inserted into the mounting protrusions and is provided with a magnetic adsorption sheet, a buffer cavity is provided inside the supporting tube, a lifting rod is slidably provided inside the buffer cavity, the lower end of the lifting rod extends to the bottom of the supporting tube, a pressure relief groove is provided at the upper end of the buffer cavity, an adjusting plug is slidably provided inside the upper end of the supporting tube corresponding to the pressure relief groove, and the lower end of the adjusting plug is inserted into the pressure relief groove.

[0008] Preferably, a mounting groove is provided at the lower end of the lifting rod, and a ball is installed in the mounting groove.

[0009] Preferably, a mounting cavity is provided inside the upper end of the support tube, the adjusting plug is slidably arranged at the lower end inside the mounting cavity, and a top spring is provided at the upper end inside the mounting cavity.

[0010] Preferably, a mounting block is installed on the outer wall of the support tube corresponding to the pressure relief groove, and a plurality of filter holes are provided on the plate body of the mounting block.

[0011] Preferably, a cavity is provided inside the mounting block, and dust filter cotton is installed in the cavity.

[0012] Preferably, an annular breathable cotton pad is provided at the lower end of the buffer cavity, and the breathable cotton pad is sleeved on the outer ring surface of the lifting rod.

[0013] Preferably, the outer annular surface of the lifting rod and the inner wall of the buffer cavity are smooth surfaces, and a weight-reducing cavity is provided inside the rod body of the lifting rod.

[0014] The utility model provides a landing gear structure for a drone, which has the following beneficial effects:

[0015] 1: In the utility model, the pneumatic shock absorption effect is achieved through the cooperation between the lifting rod and the buffer chamber, and compared with the traditional solution, the defect that the drone cannot be quickly stationary due to the rebound of the spring after shock absorption is solved, thereby avoiding the phenomenon that the drone shakes or even falls due to the rebound of the spring. The setting of the adjusting plug can automatically adjust the air flow rate in the pressure relief groove according to the potential energy of the drone when it descends, so that the air pressure inside the buffer chamber can be better maintained within the corresponding range. At the same time, through the setting of the magnetic suction block, the various supporting components can be more conveniently removed from the mounting plate, that is, the drone, thereby facilitating the storage of the drone and the landing gear.

[0016] 2: The setting of the top spring in the utility model prevents the adjusting plug from moving upward easily, so that the gas in the buffer chamber cannot escape quickly; the setting of the mounting block prevents external dust from entering the pressure relief groove, thereby avoiding the smoothness between the lifting rod and the buffer chamber caused by dust; the setting of the dust filter cotton further improves the protection effect of the pressure relief groove; the setting of the breathable cotton pad further improves the protection effect of the inside of the buffer chamber, and avoids a large pulling resistance to the lifting rod when it moves; the setting of the weight-reducing cavity effectively reduces the weight of the lifting rod, thereby avoiding a large burden on the drone. BRIEF DESCRIPTION OF THE DRAWINGS

[0017] Figure 1 This is a schematic diagram of the landing gear structure of a UAV proposed in the utility model;

[0018] Figure 2 A landing gear structure of a drone proposed in the utility model Figure 1 A cross-sectional schematic diagram of

[0019] Figure 3 A landing gear structure of a drone proposed in the utility model Figure 2 A is an enlarged schematic diagram;

[0020] Figure 4 This is a schematic diagram of the coordination of the support tube UI lifting rod of the landing gear structure of a UAV proposed in the utility model;

[0021] Figure 5 A landing gear structure of a drone proposed in the utility model Figure 4 The enlarged schematic diagram of point B in FIG.

[0022] Figure 6 A landing gear structure of a drone proposed in the utility model Figure 4 The enlarged schematic diagram of point C in FIG.

[0023] In the figure: 1. Mounting plate; 2. Mounting protrusion; 3. Magnetic block; 4. Support tube; 5. Adsorption sheet; 6. Buffer chamber; 7. Lifting rod; 8. Pressure relief groove; 9. Adjusting plug; 10. Ball; 11. Top spring; 12. Mounting block; 13. Dust filter cotton; 14. Breathable cotton pad; 15. Weight reduction chamber. DETAILED DESCRIPTION

[0024] The technical solutions in the embodiments of the present invention will be described clearly and completely below in conjunction with the drawings in the embodiments of the present invention. Obviously, the described embodiments are only part of the embodiments of the present invention, rather than all of the embodiments.

[0025] Example 1

[0026] Reference Figure 1-6 A landing gear structure of a drone comprises a mounting plate 1 for connecting with the bottom of an external drone and four supporting tubes 4. The mounting plate 1 is provided with cylindrical mounting protrusions 2 at four corners. A magnetic block 3 is installed at the top of the mounting protrusion 2. The upper end of the supporting tube 4 is inserted into the mounting protrusion 2 and is provided with a magnetic adsorption sheet 5. A buffer cavity 6 is provided inside the supporting tube 4. A lifting rod 7 is slidably provided inside the buffer cavity 6. The lower end of the lifting rod 7 extends to the bottom of the supporting tube 4. A pressure relief groove 8 is provided at the upper end of the buffer cavity 6. An adjusting plug 9 is slidably provided inside the upper end of the supporting tube 4 corresponding to the pressure relief groove 8. The lower end of the adjusting plug 9 is inserted into the pressure relief groove 8.

[0027] Example 2

[0028] Reference Figure 1-6 , when other parts are the same as those in Example 1, the difference between this embodiment and Example 1 is that:

[0029] A mounting groove is provided at the lower end of the lifting rod 7, and a ball 10 is installed in the mounting groove. The setting of the ball 10 ensures that when the drone lands through the landing gear provided by the present solution, there is rolling friction between the lower end of the landing gear and the ground, thereby avoiding the phenomenon that the landing gear cannot slide on the ground and causes the drone to tilt and somersault when landing; a mounting cavity is provided inside the upper end of the support tube 4, and the adjusting plug 9 is slidably arranged at the lower end of the mounting cavity, and a top spring 11 is provided at the upper end of the mounting cavity. The setting of the top spring 11 prevents the adjusting plug 9 from moving upward easily, so that the gas in the buffer cavity 6 cannot escape quickly; a mounting block 12 is installed on the outer wall of the support tube 4 corresponding to the pressure relief groove 8, and a plurality of filter holes are provided on the plate body of the mounting block 12. The setting of the mounting block 12 is convenient for preventing external dust from entering the pressure relief groove 8, thereby avoiding the smoothness between the lifting rod 7 and the buffer cavity 6 caused by dust.

[0030] A cavity is provided inside the mounting block 12, and dust filter cotton 13 is installed in the cavity. The setting of the dust filter cotton 13 further enhances the protection effect of the pressure relief groove 8; an annular breathable cotton pad 14 is provided at the lower end of the buffer cavity 6, and the dust filter cotton 13 and the breathable cotton pad 14 are both made of breathable sponge, non-woven fabric and other materials, and the breathable cotton pad 14 is sleeved on the outer ring surface of the lifting rod 7. The setting of the breathable cotton pad 14 further enhances the protection effect of the inside of the buffer cavity 6 and avoids the lifting rod 7 from causing a large pulling resistance when it moves; the outer ring surface of the lifting rod 7 and the inner wall of the buffer cavity 6 are smooth surfaces, and a weight reduction cavity 15 is provided inside the rod body of the lifting rod 7. The setting of the weight reduction cavity 15 effectively reduces the weight of the lifting rod 7, thereby avoiding a large burden on the drone.

[0031] Principle and advantages of use: During use of the utility model, the mounting plate 1 is installed to the bottom of the drone by means of screws or adhesives. Then, when the drone is stored, the personnel directly apply force to hold the support tube 4 until the force is greater than the suction force of the magnetic block 3, so that the support tube 4 is pulled out from the mounting protrusion 2. At this time, the disassembly of each support leg is completed, making the drone more convenient to store. When the drone needs to be used, the personnel directly insert each support leg into each mounting protrusion 2 through the suction sheet 5 at the upper end of the support tube 4.

[0032] Furthermore, in the above process, after the UAV takes off, under the action of gravity, the lifting rod 7 automatically slides down until the upper end of the lifting rod 7 abuts against the bottom of the buffer chamber 6. At this time, the lifting rod 7 moves to the maximum stroke. In this process, as the lifting rod 7 descends, suction is generated inside the buffer chamber 6 and the outside air is sucked in through the pressure relief groove 8. That is, after the outside air enters the pressure relief groove 8, it can enter the buffer chamber 6 through the small gap between the end of the regulating plug 9 and the pressure relief groove 8. When the UAV lands, the UAV drives the support under the action of gravity and potential energy. The cylinder 4 falls rapidly toward the ground until the lower end of the lifting rod 7 contacts the ground, and then the lifting rod 7 cannot move further downward, that is, the upper end of the lifting rod 7 pushes toward the inside of the buffer chamber 6, that is, the gas at the upper end of the buffer chamber 6 flows out to the outside through the pressure relief groove 8. However, due to the excessive descent speed of the UAV, the gas inside the buffer chamber 6 cannot flow out quickly enough. At this time, the gas inside the buffer chamber 6 is pressurized, thereby absorbing the potential energy of the UAV, that is, quickly reducing the falling speed of the UAV. When the upper end of the lifting rod 7 abuts against the upper end of the buffer chamber 6, the UAV has completed the landing operation.

[0033] At the same time, in the above process, since the adjusting plug 9 can move up and down, that is, the discharge speed of the gas inside the buffer chamber 6 is adjusted by the automatic movement of the adjusting plug 9, thereby avoiding the phenomenon that the gas cannot be discharged smoothly, resulting in excessive pressure inside the buffer chamber 6, and ultimately unable to achieve the corresponding shock-absorbing effect. At the same time, it also avoids the phenomenon that the gas inside the buffer chamber 6 is discharged too smoothly, resulting in low air pressure inside the buffer chamber 6, and then unable to achieve the corresponding buffering and shock-absorbing effect.

[0034] In summary, when the drone landing gear structure proposed in this scheme is in use, a pneumatic shock absorption effect is achieved through the cooperation between the lifting rod 7 and the buffer chamber 6. Compared with the traditional scheme, it solves the defect that the drone cannot be quickly stationary due to the rebound of the spring after shock absorption, thereby avoiding the phenomenon of the drone shaking or even falling due to the spring rebound. Through the setting of the adjusting plug 9, the air flow rate in the pressure relief groove 8 can be automatically adjusted according to the potential energy of the drone when it descends, so that the air pressure inside the buffer chamber 6 can be better maintained within the corresponding range. At the same time, through the setting of the magnetic suction block 3, the various supporting components can be more conveniently removed from the mounting plate 1, that is, the drone, thereby facilitating the storage of the drone and the landing gear.

[0035] It should be further explained that the setting of the ball 10 ensures that when the drone lands through the landing gear provided by the present solution, there is rolling friction between the lower end of the landing gear and the ground, thereby avoiding the phenomenon that the landing gear cannot slide on the ground and causes the drone to tilt and somersault when landing; the setting of the top spring 11 prevents the adjusting plug 9 from moving upward easily, so that the gas in the buffer chamber 6 cannot escape quickly; the setting of the mounting block 12 facilitates the prevention of external dust from entering the pressure relief groove 8, thereby preventing the dust from affecting the smoothness between the lifting rod 7 and the buffer chamber 6; the setting of the dust filter cotton 13 further enhances the protective effect of the pressure relief groove 8; the setting of the breathable cotton pad 14 further enhances the protective effect of the inside of the buffer chamber 6, and avoids the lifting rod 7 from causing a large pulling resistance to it when it moves; the setting of the weight reduction chamber 15 effectively reduces the weight of the lifting rod 7, thereby avoiding a large burden on the drone.

[0036] The above description is only a preferred specific implementation manner of the present invention, but the protection scope of the present invention is not limited thereto. Any technician familiar with the technical field can make equivalent replacements or changes within the technical scope disclosed by the present invention according to the technical scheme and the utility model concept of the present invention, which should be covered by the protection scope of the present invention.

Claims

1. A landing gear structure of an unmanned aerial vehicle, comprising a mounting plate (1) for connecting to the bottom of an external unmanned aerial vehicle and four supporting tubes (4), characterized in that: The four corners of the mounting plate (1) are each provided with a cylindrical mounting protrusion (2), a magnetic attraction block (3) is installed at the top of the mounting protrusion (2), the upper end of the support cylinder (4) is inserted into the mounting protrusion (2) and is provided with a magnetic attraction sheet (5), a buffer chamber (6) is provided inside the support cylinder (4), a lifting rod (7) is slidably provided inside the buffer chamber (6), the lower end of the lifting rod (7) extends to the bottom of the support cylinder (4), a pressure relief groove (8) is provided at the upper end of the buffer chamber (6), an adjusting plug (9) is slidably provided inside the upper end of the support cylinder (4) corresponding to the pressure relief groove (8), and the lower end of the adjusting plug (9) is inserted into the pressure relief groove (8).

2. The landing gear structure of a drone according to claim 1, characterized in that: The lower end of the lifting rod (7) is provided with a mounting groove, in which a ball (10) is installed.

3. The landing gear structure of a drone according to claim 1, characterized in that: An installation cavity is provided inside the upper end of the support tube (4), an adjusting plug (9) is slidably arranged at the lower end inside the installation cavity, and a top spring (11) is provided at the upper end inside the installation cavity.

4. The landing gear structure of a drone according to claim 1, characterized in that: A mounting block (12) is mounted on the outer wall of the support tube (4) corresponding to the pressure relief groove (8), and a plurality of filtering holes are arranged on the plate body of the mounting block (12).

5. The landing gear structure of a UAV according to claim 4, characterized in that: The installation block (12) is provided with a cavity inside, and dust filter cotton (13) is installed in the cavity.

6. The landing gear structure of a drone according to claim 1, characterized in that: An annular breathable cotton pad (14) is provided at the lower end of the buffer chamber (6), and the breathable cotton pad (14) is sleeved on the outer ring surface of the lifting rod (7).

7. The landing gear structure of a drone according to claim 1, characterized in that: The outer annular surface of the lifting rod (7) and the inner wall of the buffer cavity (6) are smooth surfaces, and a weight-reducing cavity (15) is provided inside the rod body of the lifting rod (7).

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